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source: palm/trunk/SOURCE/wind_turbine_model_mod.f90 @ 2322

Last change on this file since 2322 was 2322, checked in by Giersch, 7 years ago
Bugfix of error message and assign error numbers
Property svn:keywords set to `Id`
File size: 109.1 KB

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1	!> @file wind_turbine_model_mod.f90
2	!------------------------------------------------------------------------------!
3	! This file is part of PALM.
4	!
5	! PALM is free software: you can redistribute it and/or modify it under the
6	! terms of the GNU General Public License as published by the Free Software
7	! Foundation, either version 3 of the License, or (at your option) any later
8	! version.
9	!
10	! PALM is distributed in the hope that it will be useful, but WITHOUT ANY
11	! WARRANTY; without even the implied warranty of MERCHANTABILITY or FITNESS FOR
12	! A PARTICULAR PURPOSE. See the GNU General Public License for more details.
13	!
14	! You should have received a copy of the GNU General Public License along with
15	! PALM. If not, see <http://www.gnu.org/licenses/>.
16	!
17	! Copyright 2009-2017 Carl von Ossietzky Universitaet Oldenburg
18	! Copyright 1997-2017 Leibniz Universitaet Hannover
19	!------------------------------------------------------------------------------!
20	!
21	! Current revisions:
22	! -----------------
23	!
24	!
25	! Former revisions:
26	! -----------------
27	! $Id: wind_turbine_model_mod.f90 2322 2017-07-26 08:30:28Z Giersch $
28	! Bugfix of error message and assign error numbers
29	!
30	! 2257 2017-06-07 14:07:05Z witha
31	! Bugfix: turb_cl_tab and turb_cd_tab were set to zero before being allocated
32	!
33	! 2233 2017-05-30 18:08:54Z suehring
34	!
35	! 2232 2017-05-30 17:47:52Z suehring
36	! Adjustments to new topography concept
37	!
38	! 2152 2017-02-17 13:27:24Z lvollmer
39	! Bugfix in subroutine wtm_read_blade_tables
40	! Addition of a tip loss model
41	!
42	! 2015 2016-09-28 08:45:18Z lvollmer
43	! Bugfix of pitch control
44	!
45	! 2000 2016-08-20 18:09:15Z knoop
46	! Forced header and separation lines into 80 columns
47	!
48	! 1929 2016-06-09 16:25:25Z suehring
49	! Bugfix: added preprocessor directives for parallel and serial mode
50	!
51	! 1914 2016-05-26 14:44:07Z witha
52	! Initial revision
53	!
54	!
55	! Description:
56	! ------------
57	!> This module calculates the effect of wind turbines on the flow fields. The
58	!> initial version contains only the advanced actuator disk with rotation method
59	!> (ADM-R).
60	!> The wind turbines include the tower effect, can be yawed and tilted.
61	!> The wind turbine model includes controllers for rotational speed, pitch and
62	!> yaw.
63	!> Currently some specifications of the NREL 5 MW reference turbine
64	!> are hardcoded whereas most input data comes from separate files (currently
65	!> external, planned to be included as namelist which will be read in
66	!> automatically).
67	!>
68	!> @todo Revise code according to PALM Coding Standard
69	!> @todo Implement ADM and ALM turbine models
70	!> @todo Generate header information
71	!> @todo Implement further parameter checks and error messages
72	!> @todo Revise and add code documentation
73	!> @todo Output turbine parameters as timeseries
74	!> @todo Include additional output variables
75	!> @todo Revise smearing the forces for turbines in yaw
76	!> @todo Revise nacelle and tower parameterization
77	!> @todo Allow different turbine types in one simulation
78	!
79	!------------------------------------------------------------------------------!
80	MODULE wind_turbine_model_mod
81
82	USE arrays_3d, &
83	ONLY: dd2zu, tend, u, v, w, zu, zw
84
85	USE constants
86
87	USE control_parameters, &
88	ONLY: dt_3d, dz, message_string, simulated_time
89
90	USE cpulog, &
91	ONLY: cpu_log, log_point_s
92
93	USE grid_variables, &
94	ONLY: ddx, dx, ddy, dy
95
96	USE indices, &
97	ONLY: nbgp, nx, nxl, nxlg, nxr, nxrg, ny, nyn, nyng, nys, nysg, nz, &
98	nzb, nzt, wall_flags_0
99
100	USE kinds
101
102	USE pegrid
103
104
105	IMPLICIT NONE
106
107	PRIVATE
108
109	LOGICAL :: wind_turbine=.FALSE. !< switch for use of wind turbine model
110
111	!
112	!-- Variables specified in the namelist wind_turbine_par
113
114	INTEGER(iwp) :: nairfoils = 8 !< number of airfoils of the used turbine model (for ADM-R and ALM)
115	INTEGER(iwp) :: nturbines = 1 !< number of turbines
116
117	LOGICAL :: pitch_control = .FALSE. !< switch for use of pitch controller
118	LOGICAL :: speed_control = .FALSE. !< switch for use of speed controller
119	LOGICAL :: yaw_control = .FALSE. !< switch for use of yaw controller
120	LOGICAL :: tl_cor = .FALSE. !< switch for use of tip loss correct.
121
122	REAL(wp) :: segment_length = 1.0_wp !< length of the segments, the rotor area is divided into
123	!< (in tangential direction, as factor of MIN(dx,dy,dz))
124	REAL(wp) :: segment_width = 0.5_wp !< width of the segments, the rotor area is divided into
125	!< (in radial direction, as factor of MIN(dx,dy,dz))
126	REAL(wp) :: time_turbine_on = 0.0_wp !< time at which turbines are started
127	REAL(wp) :: tilt = 0.0_wp !< vertical tilt of the rotor [degree] ( positive = backwards )
128
129	REAL(wp), DIMENSION(1:100) :: dtow = 0.0_wp !< tower diameter [m]
130	REAL(wp), DIMENSION(1:100) :: omega_rot = 0.0_wp !< inital or constant rotor speed [rad/s]
131	REAL(wp), DIMENSION(1:100) :: phi_yaw = 0.0_wp !< yaw angle [degree] ( clockwise, 0 = facing west )
132	REAL(wp), DIMENSION(1:100) :: pitch_add = 0.0_wp !< constant pitch angle
133	REAL(wp), DIMENSION(1:100) :: rcx = 9999999.9_wp !< position of hub in x-direction
134	REAL(wp), DIMENSION(1:100) :: rcy = 9999999.9_wp !< position of hub in y-direction
135	REAL(wp), DIMENSION(1:100) :: rcz = 9999999.9_wp !< position of hub in z-direction
136	REAL(wp), DIMENSION(1:100) :: rnac = 0.0_wp !< nacelle diameter [m]
137	REAL(wp), DIMENSION(1:100) :: rr = 63.0_wp !< rotor radius [m]
138	REAL(wp), DIMENSION(1:100) :: turb_cd_nacelle = 0.85_wp !< drag coefficient for nacelle
139	REAL(wp), DIMENSION(1:100) :: turb_cd_tower = 1.2_wp !< drag coefficient for tower
140
141	!
142	!-- Variables specified in the namelist for speed controller
143	!-- Default values are from the NREL 5MW research turbine (Jonkman, 2008)
144
145	REAL(wp) :: rated_power = 5296610.0_wp !< rated turbine power [W]
146	REAL(wp) :: gear_ratio = 97.0_wp !< Gear ratio from rotor to generator
147	REAL(wp) :: inertia_rot = 34784179.0_wp !< Inertia of the rotor [kg/m2]
148	REAL(wp) :: inertia_gen = 534.116_wp !< Inertia of the generator [kg/m2]
149	REAL(wp) :: gen_eff = 0.944_wp !< Electric efficiency of the generator
150	REAL(wp) :: gear_eff = 1.0_wp !< Loss between rotor and generator
151	REAL(wp) :: air_dens = 1.225_wp !< Air density to convert to W [kg/m3]
152	REAL(wp) :: rated_genspeed = 121.6805_wp !< Rated generator speed [rad/s]
153	REAL(wp) :: max_torque_gen = 47402.91_wp !< Maximum of the generator torque [Nm]
154	REAL(wp) :: slope2 = 2.332287_wp !< Slope constant for region 2
155	REAL(wp) :: min_reg2 = 91.21091_wp !< Lower generator speed boundary of region 2 [rad/s]
156	REAL(wp) :: min_reg15 = 70.16224_wp !< Lower generator speed boundary of region 1.5 [rad/s]
157	REAL(wp) :: max_trq_rate = 15000.0_wp !< Max generator torque increase [Nm/s]
158	REAL(wp) :: pitch_rate = 8.0_wp !< Max pitch rate [degree/s]
159
160
161	!
162	!-- Variables specified in the namelist for yaw control
163
164	REAL(wp) :: yaw_speed = 0.005236_wp !< speed of the yaw actuator [rad/s]
165	REAL(wp) :: max_miss = 0.08726_wp !< maximum tolerated yaw missalignment [rad]
166	REAL(wp) :: min_miss = 0.008726_wp !< minimum yaw missalignment for which the actuator stops [rad]
167
168	!
169	!-- Set flag for output files TURBINE_PARAMETERS
170	TYPE file_status
171	LOGICAL :: opened, opened_before
172	END TYPE file_status
173
174	TYPE(file_status), DIMENSION(500) :: openfile_turb_mod = &
175	file_status(.FALSE.,.FALSE.)
176
177	!
178	!-- Variables for initialization of the turbine model
179
180	INTEGER(iwp) :: inot !< turbine loop index (turbine id)
181	INTEGER(iwp) :: nsegs_max !< maximum number of segments (all turbines, required for allocation of arrays)
182	INTEGER(iwp) :: nrings_max !< maximum number of rings (all turbines, required for allocation of arrays)
183	INTEGER(iwp) :: ring !< ring loop index (ring number)
184	INTEGER(iwp) :: rr_int !<
185	INTEGER(iwp) :: upper_end !<
186
187	INTEGER(iwp), DIMENSION(1) :: lct !<
188
189	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: i_hub !< index belonging to x-position of the turbine
190	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: i_smear !< index defining the area for the smearing of the forces (x-direction)
191	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: j_hub !< index belonging to y-position of the turbine
192	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: j_smear !< index defining the area for the smearing of the forces (y-direction)
193	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: k_hub !< index belonging to hub height
194	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: k_smear !< index defining the area for the smearing of the forces (z-direction)
195	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: nrings !< number of rings per turbine
196	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: nsegs_total !< total number of segments per turbine
197
198	INTEGER(iwp), DIMENSION(:,:), ALLOCATABLE :: nsegs !< number of segments per ring and turbine
199
200	!
201	!- parameters for the smearing from the rotor to the cartesian grid
202	REAL(wp) :: pol_a !< parameter for the polynomial smearing fct
203	REAL(wp) :: pol_b !< parameter for the polynomial smearing fct
204	REAL(wp) :: delta_t_factor !<
205	REAL(wp) :: eps_factor !<
206	REAL(wp) :: eps_min !<
207	REAL(wp) :: eps_min2 !<
208	REAL(wp) :: sqrt_arg !<
209
210	!
211	!-- Variables for the calculation of lift and drag coefficients
212	REAL(wp), DIMENSION(:), ALLOCATABLE :: ard !<
213	REAL(wp), DIMENSION(:), ALLOCATABLE :: crd !<
214	REAL(wp), DIMENSION(:), ALLOCATABLE :: delta_r !< radial segment length
215	REAL(wp), DIMENSION(:), ALLOCATABLE :: lrd !<
216
217	REAL(wp) :: accu_cl_cd_tab = 0.1_wp !< Accuracy of the interpolation of
218	!< the lift and drag coeff [deg]
219
220	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: turb_cd_tab !< table of the blade drag coefficient
221	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: turb_cl_tab !< table of the blade lift coefficient
222
223	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: nac_cd_surf !< 3d field of the tower drag coefficient
224	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: tow_cd_surf !< 3d field of the nacelle drag coefficient
225
226	!
227	!-- Variables for the calculation of the forces
228
229	REAL(wp) :: cur_r !<
230	REAL(wp) :: delta_t !< tangential segment length
231	REAL(wp) :: phi_rotor !<
232	REAL(wp) :: pre_factor !<
233	REAL(wp) :: torque_seg !<
234	REAL(wp) :: u_int_l !<
235	REAL(wp) :: u_int_u !<
236	REAL(wp) :: u_rot !<
237	REAL(wp) :: v_int_l !<
238	REAL(wp) :: v_int_u !<
239	REAL(wp) :: w_int_l !<
240	REAL(wp) :: w_int_u !<
241	!
242	!- Tendencies from the nacelle and tower thrust
243	REAL(wp) :: tend_nac_x = 0.0_wp !<
244	REAL(wp) :: tend_tow_x = 0.0_wp !<
245	REAL(wp) :: tend_nac_y = 0.0_wp !<
246	REAL(wp) :: tend_tow_y = 0.0_wp !<
247
248	REAL(wp), DIMENSION(:), ALLOCATABLE :: alpha_attack !<
249	REAL(wp), DIMENSION(:), ALLOCATABLE :: chord !<
250	REAL(wp), DIMENSION(:), ALLOCATABLE :: omega_gen !< curr. generator speed
251	REAL(wp), DIMENSION(:), ALLOCATABLE :: phi_rel !<
252	REAL(wp), DIMENSION(:), ALLOCATABLE :: pitch_add_old!<
253	REAL(wp), DIMENSION(:), ALLOCATABLE :: torque_total !<
254	REAL(wp), DIMENSION(:), ALLOCATABLE :: thrust_rotor !<
255	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cl !<
256	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cd !<
257	REAL(wp), DIMENSION(:), ALLOCATABLE :: vrel !<
258	REAL(wp), DIMENSION(:), ALLOCATABLE :: vtheta !<
259
260	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: rbx, rby, rbz !< coordinates of the blade elements
261	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: rotx, roty, rotz !< normal vectors to the rotor coordinates
262
263	!
264	!- Fields for the interpolation of velocities on the rotor grid
265	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: u_int !<
266	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: u_int_1_l !<
267	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: v_int !<
268	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: v_int_1_l !<
269	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: w_int !<
270	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: w_int_1_l !<
271
272	!
273	!- rotor tendencies on the segments
274	REAL(wp), DIMENSION(:), ALLOCATABLE :: thrust_seg !<
275	REAL(wp), DIMENSION(:), ALLOCATABLE :: torque_seg_y !<
276	REAL(wp), DIMENSION(:), ALLOCATABLE :: torque_seg_z !<
277
278	!
279	!- rotor tendencies on the rings
280	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: thrust_ring !<
281	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: torque_ring_y !<
282	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: torque_ring_z !<
283
284	!
285	!- rotor tendencies on rotor grids for all turbines
286	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: thrust !<
287	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: torque_y !<
288	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: torque_z !<
289
290	!
291	!- rotor tendencies on coordinate grid
292	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: rot_tend_x !<
293	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: rot_tend_y !<
294	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: rot_tend_z !<
295	!
296	!- variables for the rotation of the rotor coordinates
297	REAL(wp), DIMENSION(1:100,1:3,1:3) :: rot_coord_trans !< matrix for rotation of rotor coordinates
298
299	REAL(wp), DIMENSION(1:3) :: rot_eigen_rad !<
300	REAL(wp), DIMENSION(1:3) :: rot_eigen_azi !<
301	REAL(wp), DIMENSION(1:3) :: rot_eigen_nor !<
302	REAL(wp), DIMENSION(1:3) :: re !<
303	REAL(wp), DIMENSION(1:3) :: rea !<
304	REAL(wp), DIMENSION(1:3) :: ren !<
305	REAL(wp), DIMENSION(1:3) :: rote !<
306	REAL(wp), DIMENSION(1:3) :: rota !<
307	REAL(wp), DIMENSION(1:3) :: rotn !<
308
309	!
310	!-- Fixed variables for the speed controller
311
312	LOGICAL :: start_up = .TRUE. !<
313
314	REAL(wp) :: Fcorner !< corner freq for the controller low pass filter
315	REAL(wp) :: min_reg25 !< min region 2.5
316	REAL(wp) :: om_rate !< rotor speed change
317	REAL(wp) :: slope15 !< slope in region 1.5
318	REAL(wp) :: slope25 !< slope in region 2.5
319	REAL(wp) :: trq_rate !< torque change
320	REAL(wp) :: vs_sysp !<
321	REAL(wp) :: lp_coeff !< coeff for the controller low pass filter
322
323	REAL(wp), DIMENSION(:), ALLOCATABLE :: omega_gen_old !< last gen. speed
324	REAL(wp), DIMENSION(:), ALLOCATABLE :: omega_gen_f !< filtered gen. sp
325	REAL(wp), DIMENSION(:), ALLOCATABLE :: omega_gen_f_old !< last filt. gen. sp
326	REAL(wp), DIMENSION(:), ALLOCATABLE :: torque_gen !< generator torque
327	REAL(wp), DIMENSION(:), ALLOCATABLE :: torque_gen_old !< last gen. torque
328
329	REAL(wp), DIMENSION(100) :: omega_rot_l = 0.0_wp !< local rot speed [rad/s]
330	!
331	!-- Fixed variables for the yaw controller
332
333	REAL(wp), DIMENSION(:) , ALLOCATABLE :: yawdir !< direction to yaw
334	REAL(wp), DIMENSION(:) , ALLOCATABLE :: phi_yaw_l !< local (cpu) yaw angle
335	REAL(wp), DIMENSION(:) , ALLOCATABLE :: wd30_l !< local (cpu) long running avg of the wd
336	REAL(wp), DIMENSION(:) , ALLOCATABLE :: wd2_l !< local (cpu) short running avg of the wd
337	REAL(wp), DIMENSION(:) , ALLOCATABLE :: wdir !< wind direction at hub
338	REAL(wp), DIMENSION(:) , ALLOCATABLE :: u_inflow !< wind speed at hub
339	REAL(wp), DIMENSION(:) , ALLOCATABLE :: wdir_l !<
340	REAL(wp), DIMENSION(:) , ALLOCATABLE :: u_inflow_l !<
341	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: wd30 !<
342	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: wd2 !<
343	LOGICAL, DIMENSION(1:100) :: doyaw = .FALSE. !<
344	INTEGER(iwp) :: WDLON !<
345	INTEGER(iwp) :: WDSHO !<
346
347
348	SAVE
349
350
351	INTERFACE wtm_parin
352	MODULE PROCEDURE wtm_parin
353	END INTERFACE wtm_parin
354
355	INTERFACE wtm_check_parameters
356	MODULE PROCEDURE wtm_check_parameters
357	END INTERFACE wtm_check_parameters
358
359	INTERFACE wtm_init_arrays
360	MODULE PROCEDURE wtm_init_arrays
361	END INTERFACE wtm_init_arrays
362
363	INTERFACE wtm_init
364	MODULE PROCEDURE wtm_init
365	END INTERFACE wtm_init
366
367	INTERFACE wtm_read_blade_tables
368	MODULE PROCEDURE wtm_read_blade_tables
369	END INTERFACE wtm_read_blade_tables
370
371	INTERFACE wtm_forces
372	MODULE PROCEDURE wtm_forces
373	MODULE PROCEDURE wtm_yawcontrol
374	END INTERFACE wtm_forces
375
376	INTERFACE wtm_rotate_rotor
377	MODULE PROCEDURE wtm_rotate_rotor
378	END INTERFACE wtm_rotate_rotor
379
380	INTERFACE wtm_speed_control
381	MODULE PROCEDURE wtm_init_speed_control
382	MODULE PROCEDURE wtm_speed_control
383	END INTERFACE wtm_speed_control
384
385	INTERFACE wtm_tendencies
386	MODULE PROCEDURE wtm_tendencies
387	MODULE PROCEDURE wtm_tendencies_ij
388	END INTERFACE wtm_tendencies
389
390
391	PUBLIC wtm_check_parameters, wtm_forces, wtm_init, wtm_init_arrays, &
392	wtm_parin, wtm_tendencies, wtm_tendencies_ij, wind_turbine
393
394	CONTAINS
395
396
397	!------------------------------------------------------------------------------!
398	! Description:
399	! ------------
400	!> Parin for &wind_turbine_par for wind turbine model
401	!------------------------------------------------------------------------------!
402	SUBROUTINE wtm_parin
403
404
405	IMPLICIT NONE
406
407	INTEGER(iwp) :: ierrn !<
408
409	CHARACTER (LEN=80) :: line !< dummy string that contains the current line of the parameter file
410
411	NAMELIST /wind_turbine_par/ air_dens, dtow, gear_eff, gear_ratio, &
412	gen_eff, inertia_gen, inertia_rot, max_miss, &
413	max_torque_gen, max_trq_rate, min_miss, &
414	min_reg15, min_reg2, nairfoils, nturbines, &
415	omega_rot, phi_yaw, pitch_add, pitch_control,&
416	rated_genspeed, rated_power, rcx, rcy, rcz, &
417	rnac, rr, segment_length, segment_width, &
418	slope2, speed_control, tilt, time_turbine_on,&
419	turb_cd_nacelle, turb_cd_tower, &
420	yaw_control, yaw_speed, tl_cor
421
422	!
423	!-- Try to find wind turbine model package
424	REWIND ( 11 )
425	line = ' '
426	DO WHILE ( INDEX( line, '&wind_turbine_par' ) == 0 )
427	READ ( 11, '(A)', END=10 ) line
428	ENDDO
429	BACKSPACE ( 11 )
430
431	!
432	!-- Read user-defined namelist
433	READ ( 11, wind_turbine_par, IOSTAT=ierrn )
434
435	IF ( ierrn < 0 ) THEN
436	message_string = 'errors in \$wind_turbine_par'
437	CALL message( 'wtm_parin', 'PA0460', 1, 2, 0, 6, 0 )
438	ENDIF
439
440	!
441	!-- Set flag that indicates that the wind turbine model is switched on
442	wind_turbine = .TRUE.
443
444	10 CONTINUE ! TBD Change from continue, mit ierrn machen
445
446
447	END SUBROUTINE wtm_parin
448
449	SUBROUTINE wtm_check_parameters
450
451
452	IMPLICIT NONE
453
454	IF ( ( .NOT.speed_control ) .AND. pitch_control ) THEN
455	message_string = 'pitch_control = .TRUE. requires '// &
456	'speed_control = .TRUE.'
457	CALL message( 'wtm_check_parameters', 'PA0461', 1, 2, 0, 6, 0 )
458	ENDIF
459
460	IF ( ANY( omega_rot(1:nturbines) < 0.0 ) ) THEN
461	message_string = 'omega_rot < 0.0, Please set omega_rot to ' // &
462	'a value larger than zero'
463	CALL message( 'wtm_check_parameters', 'PA0462', 1, 2, 0, 6, 0 )
464	ENDIF
465
466
467	IF ( ANY( rcx(1:nturbines) == 9999999.9_wp ) .OR. &
468	ANY( rcy(1:nturbines) == 9999999.9_wp ) .OR. &
469	ANY( rcz(1:nturbines) == 9999999.9_wp ) ) THEN
470
471	message_string = 'rcx, rcy, rcz ' // &
472	'have to be given for each turbine.'
473	CALL message( 'wtm_check_parameters', 'PA0463', 1, 2, 0, 6, 0 )
474
475	ENDIF
476
477
478	END SUBROUTINE wtm_check_parameters
479
480
481	!------------------------------------------------------------------------------!
482	! Description:
483	! ------------
484	!> Allocate wind turbine model arrays
485	!------------------------------------------------------------------------------!
486	SUBROUTINE wtm_init_arrays
487
488
489	IMPLICIT NONE
490
491	REAL(wp) :: delta_r_factor !<
492	REAL(wp) :: delta_r_init !<
493
494	!
495	!-- To be able to allocate arrays with dimension of rotor rings and segments,
496	!-- the maximum possible numbers of rings and segments have to be calculated:
497
498	ALLOCATE( nrings(1:nturbines) )
499	ALLOCATE( delta_r(1:nturbines) )
500
501	nrings(:) = 0
502	delta_r(:) = 0.0_wp
503
504	!
505	!-- Thickness (radial) of each ring and length (tangential) of each segment:
506	delta_r_factor = segment_width
507	delta_t_factor = segment_length
508	delta_r_init = delta_r_factor * MIN( dx, dy, dz)
509	delta_t = delta_t_factor * MIN( dx, dy, dz)
510
511	DO inot = 1, nturbines
512	!
513	!-- Determine number of rings:
514	nrings(inot) = NINT( rr(inot) / delta_r_init )
515
516	delta_r(inot) = rr(inot) / nrings(inot)
517
518	ENDDO
519
520	nrings_max = MAXVAL(nrings)
521
522	ALLOCATE( nsegs(1:nrings_max,1:nturbines) )
523	ALLOCATE( nsegs_total(1:nturbines) )
524
525	nsegs(:,:) = 0
526	nsegs_total(:) = 0
527
528
529	DO inot = 1, nturbines
530	DO ring = 1, nrings(inot)
531	!
532	!-- Determine number of segments for each ring:
533	nsegs(ring,inot) = MAX( 8, CEILING( delta_r_factor * pi * &
534	( 2.0_wp * ring - 1.0_wp ) / &
535	delta_t_factor ) )
536	ENDDO
537	!
538	!-- Total sum of all rotor segments:
539	nsegs_total(inot) = SUM( nsegs(:,inot) )
540
541	ENDDO
542
543	!
544	!-- Maximum number of segments per ring:
545	nsegs_max = MAXVAL(nsegs)
546
547	!!
548	!!-- TODO: Folgendes im Header ausgeben!
549	! IF ( myid == 0 ) THEN
550	! PRINT*, 'nrings(1) = ', nrings(1)
551	! PRINT*, '--------------------------------------------------'
552	! PRINT*, 'nsegs(:,1) = ', nsegs(:,1)
553	! PRINT*, '--------------------------------------------------'
554	! PRINT*, 'nrings_max = ', nrings_max
555	! PRINT*, 'nsegs_max = ', nsegs_max
556	! PRINT*, 'nsegs_total(1) = ', nsegs_total(1)
557	! ENDIF
558
559
560	!
561	!-- Allocate 1D arrays (dimension = number of turbines)
562	ALLOCATE( i_hub(1:nturbines) )
563	ALLOCATE( i_smear(1:nturbines) )
564	ALLOCATE( j_hub(1:nturbines) )
565	ALLOCATE( j_smear(1:nturbines) )
566	ALLOCATE( k_hub(1:nturbines) )
567	ALLOCATE( k_smear(1:nturbines) )
568	ALLOCATE( torque_total(1:nturbines) )
569	ALLOCATE( thrust_rotor(1:nturbines) )
570
571	!
572	!-- Allocation of the 1D arrays for speed pitch_control
573	ALLOCATE( omega_gen(1:nturbines) )
574	ALLOCATE( omega_gen_old(1:nturbines) )
575	ALLOCATE( omega_gen_f(1:nturbines) )
576	ALLOCATE( omega_gen_f_old(1:nturbines) )
577	ALLOCATE( pitch_add_old(1:nturbines) )
578	ALLOCATE( torque_gen(1:nturbines) )
579	ALLOCATE( torque_gen_old(1:nturbines) )
580
581	!
582	!-- Allocation of the 1D arrays for yaw control
583	ALLOCATE( yawdir(1:nturbines) )
584	ALLOCATE( u_inflow(1:nturbines) )
585	ALLOCATE( wdir(1:nturbines) )
586	ALLOCATE( u_inflow_l(1:nturbines) )
587	ALLOCATE( wdir_l(1:nturbines) )
588	ALLOCATE( phi_yaw_l(1:nturbines) )
589
590	!
591	!-- Allocate 1D arrays (dimension = number of rotor segments)
592	ALLOCATE( alpha_attack(1:nsegs_max) )
593	ALLOCATE( chord(1:nsegs_max) )
594	ALLOCATE( phi_rel(1:nsegs_max) )
595	ALLOCATE( thrust_seg(1:nsegs_max) )
596	ALLOCATE( torque_seg_y(1:nsegs_max) )
597	ALLOCATE( torque_seg_z(1:nsegs_max) )
598	ALLOCATE( turb_cd(1:nsegs_max) )
599	ALLOCATE( turb_cl(1:nsegs_max) )
600	ALLOCATE( vrel(1:nsegs_max) )
601	ALLOCATE( vtheta(1:nsegs_max) )
602
603	!
604	!-- Allocate 2D arrays (dimension = number of rotor rings and segments)
605	ALLOCATE( rbx(1:nrings_max,1:nsegs_max) )
606	ALLOCATE( rby(1:nrings_max,1:nsegs_max) )
607	ALLOCATE( rbz(1:nrings_max,1:nsegs_max) )
608	ALLOCATE( thrust_ring(1:nrings_max,1:nsegs_max) )
609	ALLOCATE( torque_ring_y(1:nrings_max,1:nsegs_max) )
610	ALLOCATE( torque_ring_z(1:nrings_max,1:nsegs_max) )
611
612	!
613	!-- Allocate additional 2D arrays
614	ALLOCATE( rotx(1:nturbines,1:3) )
615	ALLOCATE( roty(1:nturbines,1:3) )
616	ALLOCATE( rotz(1:nturbines,1:3) )
617
618	!
619	!-- Allocate 3D arrays (dimension = number of grid points)
620	ALLOCATE( nac_cd_surf(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
621	ALLOCATE( rot_tend_x(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
622	ALLOCATE( rot_tend_y(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
623	ALLOCATE( rot_tend_z(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
624	ALLOCATE( thrust(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
625	ALLOCATE( torque_y(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
626	ALLOCATE( torque_z(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
627	ALLOCATE( tow_cd_surf(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
628
629	!
630	!-- Allocate additional 3D arrays
631	ALLOCATE( u_int(1:nturbines,1:nrings_max,1:nsegs_max) )
632	ALLOCATE( u_int_1_l(1:nturbines,1:nrings_max,1:nsegs_max) )
633	ALLOCATE( v_int(1:nturbines,1:nrings_max,1:nsegs_max) )
634	ALLOCATE( v_int_1_l(1:nturbines,1:nrings_max,1:nsegs_max) )
635	ALLOCATE( w_int(1:nturbines,1:nrings_max,1:nsegs_max) )
636	ALLOCATE( w_int_1_l(1:nturbines,1:nrings_max,1:nsegs_max) )
637
638	!
639	!-- All of the arrays are initialized with a value of zero:
640	i_hub(:) = 0
641	i_smear(:) = 0
642	j_hub(:) = 0
643	j_smear(:) = 0
644	k_hub(:) = 0
645	k_smear(:) = 0
646
647	torque_total(:) = 0.0_wp
648	thrust_rotor(:) = 0.0_wp
649
650	omega_gen(:) = 0.0_wp
651	omega_gen_old(:) = 0.0_wp
652	omega_gen_f(:) = 0.0_wp
653	omega_gen_f_old(:) = 0.0_wp
654	pitch_add_old(:) = 0.0_wp
655	torque_gen(:) = 0.0_wp
656	torque_gen_old(:) = 0.0_wp
657
658	yawdir(:) = 0.0_wp
659	wdir(:) = 0.0_wp
660	u_inflow(:) = 0.0_wp
661
662	!
663	!-- Allocate 1D arrays (dimension = number of rotor segments)
664	alpha_attack(:) = 0.0_wp
665	chord(:) = 0.0_wp
666	phi_rel(:) = 0.0_wp
667	thrust_seg(:) = 0.0_wp
668	torque_seg_y(:) = 0.0_wp
669	torque_seg_z(:) = 0.0_wp
670	turb_cd(:) = 0.0_wp
671	turb_cl(:) = 0.0_wp
672	vrel(:) = 0.0_wp
673	vtheta(:) = 0.0_wp
674
675	rbx(:,:) = 0.0_wp
676	rby(:,:) = 0.0_wp
677	rbz(:,:) = 0.0_wp
678	thrust_ring(:,:) = 0.0_wp
679	torque_ring_y(:,:) = 0.0_wp
680	torque_ring_z(:,:) = 0.0_wp
681
682	rotx(:,:) = 0.0_wp
683	roty(:,:) = 0.0_wp
684	rotz(:,:) = 0.0_wp
685
686	nac_cd_surf(:,:,:) = 0.0_wp
687	rot_tend_x(:,:,:) = 0.0_wp
688	rot_tend_y(:,:,:) = 0.0_wp
689	rot_tend_z(:,:,:) = 0.0_wp
690	thrust(:,:,:) = 0.0_wp
691	torque_y(:,:,:) = 0.0_wp
692	torque_z(:,:,:) = 0.0_wp
693	tow_cd_surf(:,:,:) = 0.0_wp
694
695	u_int(:,:,:) = 0.0_wp
696	u_int_1_l(:,:,:) = 0.0_wp
697	v_int(:,:,:) = 0.0_wp
698	v_int_1_l(:,:,:) = 0.0_wp
699	w_int(:,:,:) = 0.0_wp
700	w_int_1_l(:,:,:) = 0.0_wp
701
702
703	END SUBROUTINE wtm_init_arrays
704
705
706	!------------------------------------------------------------------------------!
707	! Description:
708	! ------------
709	!> Initialization of the wind turbine model
710	!------------------------------------------------------------------------------!
711	SUBROUTINE wtm_init
712
713
714	IMPLICIT NONE
715
716	INTEGER(iwp) :: i !< running index
717	INTEGER(iwp) :: j !< running index
718	INTEGER(iwp) :: k !< running index
719
720	!
721	!-- Help variables for the smearing function
722	REAL(wp) :: eps_kernel !<
723
724	!
725	!-- Help variables for calculation of the tower drag
726	INTEGER(iwp) :: tower_n !<
727	INTEGER(iwp) :: tower_s !<
728	!
729	!-- Help variables for the calulaction of the nacelle drag
730	INTEGER(iwp) :: i_ip !<
731	INTEGER(iwp) :: i_ipg !<
732
733	REAL(wp) :: yvalue
734	REAL(wp) :: dy_int !<
735	REAL(wp) :: dz_int !<
736
737	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: circle_points !<
738
739	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: index_nacb !<
740	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: index_nacl !<
741	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: index_nacr !<
742	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: index_nact !<
743
744	ALLOCATE( index_nacb(1:nturbines) )
745	ALLOCATE( index_nacl(1:nturbines) )
746	ALLOCATE( index_nacr(1:nturbines) )
747	ALLOCATE( index_nact(1:nturbines) )
748
749
750	IF ( speed_control) THEN
751
752	CALL wtm_speed_control
753
754	ENDIF
755
756	!
757	!------------------------------------------------------------------------------!
758	!-- Calculation of parameters for the regularization kernel
759	!-- (smearing of the forces)
760	!------------------------------------------------------------------------------!
761	!
762	!-- In the following, some of the required parameters for the smearing will
763	!-- be calculated:
764
765	!-- The kernel is set equal to twice the grid spacing which has turned out to
766	!-- be a reasonable value (see e.g. Troldborg et al. (2013), Wind Energy,
767	!-- DOI: 10.1002/we.1608):
768	eps_kernel = 2.0_wp * dx
769	!
770	!-- The zero point (eps_min) of the polynomial function must be the following
771	!-- if the integral of the polynomial function (for values < eps_min) shall
772	!-- be equal to the integral of the Gaussian function used before:
773	eps_min = ( 105.0_wp / 32.0_wp )*( 1.0_wp / 3.0_wp ) &
774	pi*( 1.0_wp / 6.0_wp ) eps_kernel
775	!
776	!-- Square of eps_min:
777	eps_min2 = eps_min**2
778	!
779	!-- Parameters in the polynomial function:
780	pol_a = 1.0_wp / eps_min**4
781	pol_b = 2.0_wp / eps_min**2
782	!
783	!-- Normalization factor which is the inverse of the integral of the smearing
784	!-- function:
785	eps_factor = 105.0_wp / ( 32.0_wp * pi * eps_min**3 )
786
787	!-- Change tilt angle to rad:
788	tilt = tilt * pi / 180.0_wp
789
790	!
791	!-- Change yaw angle to rad:
792	phi_yaw(:) = phi_yaw(:) * pi / 180.0_wp
793
794
795	DO inot = 1, nturbines
796	!
797	!-- Rotate the rotor coordinates in case yaw and tilt are defined
798	CALL wtm_rotate_rotor( inot )
799
800	!
801	!-- Determine the indices of the hub height
802	i_hub(inot) = INT( rcx(inot) / dx )
803	j_hub(inot) = INT( ( rcy(inot) + 0.5_wp * dy ) / dy )
804	k_hub(inot) = INT( ( rcz(inot) + 0.5_wp * dz ) / dz )
805
806	!
807	!-- Determining the area to which the smearing of the forces is applied.
808	!-- As smearing now is effectively applied only for distances smaller than
809	!-- eps_min, the smearing area can be further limited and regarded as a
810	!-- function of eps_min:
811	i_smear(inot) = CEILING( ( rr(inot) + eps_min ) / dx )
812	j_smear(inot) = CEILING( ( rr(inot) + eps_min ) / dy )
813	k_smear(inot) = CEILING( ( rr(inot) + eps_min ) / dz )
814
815	ENDDO
816
817	!
818	!------------------------------------------------------------------------------!
819	!-- Determine the area within each grid cell that overlaps with the area
820	!-- of the nacelle and the tower (needed for calculation of the forces)
821	!------------------------------------------------------------------------------!
822	!
823	!-- Note: so far this is only a 2D version, in that the mean flow is
824	!-- perpendicular to the rotor area.
825
826	!
827	!-- Allocation of the array containing information on the intersection points
828	!-- between rotor disk and the numerical grid:
829	upper_end = ( ny + 1 ) * 10000
830
831	ALLOCATE( circle_points(1:2,1:upper_end) )
832
833	circle_points(:,:) = 0.0_wp
834
835
836	DO inot = 1, nturbines ! loop over number of turbines
837	!
838	!-- Determine the grid index (u-grid) that corresponds to the location of
839	!-- the rotor center (reduces the amount of calculations in the case that
840	!-- the mean flow is perpendicular to the rotor area):
841	i = i_hub(inot)
842
843	!
844	!-- Determine the left and the right edge of the nacelle (corresponding
845	!-- grid point indices):
846	index_nacl(inot) = INT( ( rcy(inot) - rnac(inot) + 0.5_wp * dy ) / dy )
847	index_nacr(inot) = INT( ( rcy(inot) + rnac(inot) + 0.5_wp * dy ) / dy )
848	!
849	!-- Determine the bottom and the top edge of the nacelle (corresponding
850	!-- grid point indices).The grid point index has to be increased by 1, as
851	!-- the first level for the u-component (index 0) is situated below the
852	!-- surface. All points between z=0 and z=dz/s would already be contained
853	!-- in grid box 1.
854	index_nacb(inot) = INT( ( rcz(inot) - rnac(inot) ) / dz ) + 1
855	index_nact(inot) = INT( ( rcz(inot) + rnac(inot) ) / dz ) + 1
856
857	!
858	!-- Determine the indices of the grid boxes containing the left and
859	!-- the right boundaries of the tower:
860	tower_n = ( rcy(inot) + 0.5_wp * dtow(inot) - 0.5_wp * dy ) / dy
861	tower_s = ( rcy(inot) - 0.5_wp * dtow(inot) - 0.5_wp * dy ) / dy
862
863	!
864	!-- Determine the fraction of the grid box area overlapping with the tower
865	!-- area and multiply it with the drag of the tower:
866	IF ( ( nxlg <= i ) .AND. ( nxrg >= i ) ) THEN
867
868	DO j = nys, nyn
869	!
870	!-- Loop from south to north boundary of tower
871	IF ( ( j >= tower_s ) .AND. ( j <= tower_n ) ) THEN
872
873	DO k = nzb, nzt
874
875	IF ( k == k_hub(inot) ) THEN
876	IF ( tower_n - tower_s >= 1 ) THEN
877	!
878	!-- leftmost and rightmost grid box:
879	IF ( j == tower_s ) THEN
880	tow_cd_surf(k,j,i) = ( rcz(inot) - &
881	( k_hub(inot) * dz - 0.5_wp * dz ) ) * & ! extension in z-direction
882	( ( tower_s + 1.0_wp + 0.5_wp ) * dy - &
883	( rcy(inot) - 0.5_wp * dtow(inot) ) ) * & ! extension in y-direction
884	turb_cd_tower(inot)
885	ELSEIF ( j == tower_n ) THEN
886	tow_cd_surf(k,j,i) = ( rcz(inot) - &
887	( k_hub(inot) * dz - 0.5_wp * dz ) ) * & ! extension in z-direction
888	( ( rcy(inot) + 0.5_wp * dtow(inot) ) - &
889	( tower_n + 0.5_wp ) * dy ) * & ! extension in y-direction
890	turb_cd_tower(inot)
891	!
892	!-- grid boxes inbetween
893	!-- (where tow_cd_surf = grid box area):
894	ELSE
895	tow_cd_surf(k,j,i) = ( rcz(inot) - &
896	( k_hub(inot) * dz - 0.5_wp * dz ) ) * &
897	dy * turb_cd_tower(inot)
898	ENDIF
899	!
900	!-- tower lies completely within one grid box:
901	ELSE
902	tow_cd_surf(k,j,i) = ( rcz(inot) - &
903	( k_hub(inot) * dz - 0.5_wp * dz ) ) * &
904	dtow(inot) * turb_cd_tower(inot)
905	ENDIF
906	!
907	!-- In case that k is smaller than k_hub the following actions
908	!-- are carried out:
909	ELSEIF ( k < k_hub(inot) ) THEN
910
911	IF ( ( tower_n - tower_s ) >= 1 ) THEN
912	!
913	!-- leftmost and rightmost grid box:
914	IF ( j == tower_s ) THEN
915	tow_cd_surf(k,j,i) = dz * ( &
916	( tower_s + 1 + 0.5_wp ) * dy - &
917	( rcy(inot) - 0.5_wp * dtow(inot) ) &
918	) * turb_cd_tower(inot)
919	ELSEIF ( j == tower_n ) THEN
920	tow_cd_surf(k,j,i) = dz * ( &
921	( rcy(inot) + 0.5_wp * dtow(inot) ) - &
922	( tower_n + 0.5_wp ) * dy &
923	) * turb_cd_tower(inot)
924	!
925	!-- grid boxes inbetween
926	!-- (where tow_cd_surf = grid box area):
927	ELSE
928	tow_cd_surf(k,j,i) = dz * dy * turb_cd_tower(inot)
929	ENDIF
930	!
931	!-- tower lies completely within one grid box:
932	ELSE
933	tow_cd_surf(k,j,i) = dz * dtow(inot) * &
934	turb_cd_tower(inot)
935	ENDIF ! end if larger than grid box
936
937	ENDIF ! end if k == k_hub
938
939	ENDDO ! end loop over k
940
941	ENDIF ! end if inside north and south boundary of tower
942
943	ENDDO ! end loop over j
944
945	ENDIF ! end if hub inside domain + ghostpoints
946
947
948	CALL exchange_horiz( tow_cd_surf, nbgp )
949
950	!
951	!-- Calculation of the nacelle area
952	!-- CAUTION: Currently disabled due to segmentation faults on the FLOW HPC
953	!-- cluster (Oldenburg)
954	!!
955	!!-- Tabulate the points on the circle that are required in the following for
956	!!-- the calculation of the Riemann integral (node points; they are called
957	!!-- circle_points in the following):
958	!
959	! dy_int = dy / 10000.0_wp
960	!
961	! DO i_ip = 1, upper_end
962	! yvalue = dy_int * ( i_ip - 0.5_wp ) + 0.5_wp * dy !<--- segmentation fault
963	! sqrt_arg = rnac(inot)2 - ( yvalue - rcy(inot) )2 !<--- segmentation fault
964	! IF ( sqrt_arg >= 0.0_wp ) THEN
965	!!
966	!!-- bottom intersection point
967	! circle_points(1,i_ip) = rcz(inot) - SQRT( sqrt_arg )
968	!!
969	!!-- top intersection point
970	! circle_points(2,i_ip) = rcz(inot) + SQRT( sqrt_arg ) !<--- segmentation fault
971	! ELSE
972	! circle_points(:,i_ip) = -111111 !<--- segmentation fault
973	! ENDIF
974	! ENDDO
975	!
976	!
977	! DO j = nys, nyn
978	!!
979	!!-- In case that the grid box is located completely outside the nacelle
980	!!-- (y) it can automatically be stated that there is no overlap between
981	!!-- the grid box and the nacelle and consequently we can set
982	!!-- nac_cd_surf(:,j,i) = 0.0:
983	! IF ( ( j >= index_nacl(inot) ) .AND. ( j <= index_nacr(inot) ) ) THEN
984	! DO k = nzb+1, nzt
985	!!
986	!!-- In case that the grid box is located completely outside the
987	!!-- nacelle (z) it can automatically be stated that there is no
988	!!-- overlap between the grid box and the nacelle and consequently
989	!!-- we can set nac_cd_surf(k,j,i) = 0.0:
990	! IF ( ( k >= index_nacb(inot) ) .OR. &
991	! ( k <= index_nact(inot) ) ) THEN
992	!!
993	!!-- For all other cases Riemann integrals are calculated.
994	!!-- Here, the points on the circle that have been determined
995	!!-- above are used in order to calculate the overlap between the
996	!!-- gridbox and the nacelle area (area approached by 10000
997	!!-- rectangulars dz_int * dy_int):
998	! DO i_ipg = 1, 10000
999	! dz_int = dz
1000	! i_ip = j * 10000 + i_ipg
1001	!!
1002	!!-- Determine the vertical extension dz_int of the circle
1003	!!-- within the current grid box:
1004	! IF ( ( circle_points(2,i_ip) < zw(k) ) .AND. & !<--- segmentation fault
1005	! ( circle_points(2,i_ip) >= zw(k-1) ) ) THEN
1006	! dz_int = dz_int - & !<--- segmentation fault
1007	! ( zw(k) - circle_points(2,i_ip) )
1008	! ENDIF
1009	! IF ( ( circle_points(1,i_ip) <= zw(k) ) .AND. & !<--- segmentation fault
1010	! ( circle_points(1,i_ip) > zw(k-1) ) ) THEN
1011	! dz_int = dz_int - &
1012	! ( circle_points(1,i_ip) - zw(k-1) )
1013	! ENDIF
1014	! IF ( zw(k-1) > circle_points(2,i_ip) ) THEN
1015	! dz_int = 0.0_wp
1016	! ENDIF
1017	! IF ( zw(k) < circle_points(1,i_ip) ) THEN
1018	! dz_int = 0.0_wp
1019	! ENDIF
1020	! IF ( ( nxlg <= i ) .AND. ( nxrg >= i ) ) THEN
1021	! nac_cd_surf(k,j,i) = nac_cd_surf(k,j,i) + & !<--- segmentation fault
1022	! dy_int * dz_int * turb_cd_nacelle(inot)
1023	! ENDIF
1024	! ENDDO
1025	! ENDIF
1026	! ENDDO
1027	! ENDIF
1028	!
1029	! ENDDO
1030	!
1031	! CALL exchange_horiz( nac_cd_surf, nbgp ) !<--- segmentation fault
1032
1033	ENDDO ! end of loop over turbines
1034
1035	tow_cd_surf = tow_cd_surf / ( dx * dy * dz ) ! Normalize tower drag
1036	nac_cd_surf = nac_cd_surf / ( dx * dy * dz ) ! Normalize nacelle drag
1037
1038	CALL wtm_read_blade_tables
1039
1040	END SUBROUTINE wtm_init
1041
1042
1043	!------------------------------------------------------------------------------!
1044	! Description:
1045	! ------------
1046	!> Read in layout of the rotor blade , the lift and drag tables
1047	!> and the distribution of lift and drag tables along the blade
1048	!------------------------------------------------------------------------------!
1049	!
1050	SUBROUTINE wtm_read_blade_tables
1051
1052
1053	IMPLICIT NONE
1054
1055	INTEGER(iwp) :: ii !< running index
1056	INTEGER(iwp) :: jj !< running index
1057
1058	INTEGER(iwp) :: ierrn !<
1059
1060	CHARACTER(200) :: chmess !< Read in string
1061
1062	INTEGER(iwp) :: dlen !< no. rows of local table
1063	INTEGER(iwp) :: dlenbl !< no. rows of cd, cl table
1064	INTEGER(iwp) :: ialpha !< table position of current alpha value
1065	INTEGER(iwp) :: iialpha !<
1066	INTEGER(iwp) :: iir !<
1067	INTEGER(iwp) :: radres !< radial resolution
1068	INTEGER(iwp) :: t1 !< no. of airfoil
1069	INTEGER(iwp) :: t2 !< no. of airfoil
1070	INTEGER(iwp) :: trow !<
1071	INTEGER(iwp) :: dlenbl_int !< no. rows of interpolated cd, cl tables
1072
1073	REAL(wp) :: alpha_attack_i !<
1074	REAL(wp) :: weight_a !<
1075	REAL(wp) :: weight_b !<
1076
1077	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: ttoint1 !<
1078	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: ttoint2 !<
1079
1080	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cd_sel1 !<
1081	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cd_sel2 !<
1082	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cl_sel1 !<
1083	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cl_sel2 !<
1084	REAL(wp), DIMENSION(:), ALLOCATABLE :: read_cl_cd !< read in var array
1085
1086	REAL(wp), DIMENSION(:), ALLOCATABLE :: alpha_attack_tab !<
1087	REAL(wp), DIMENSION(:), ALLOCATABLE :: trad1 !<
1088	REAL(wp), DIMENSION(:), ALLOCATABLE :: trad2 !<
1089	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: turb_cd_table !<
1090	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: turb_cl_table !<
1091
1092	ALLOCATE ( read_cl_cd(1:2*nairfoils+1) )
1093
1094	!
1095	!-- Read in the distribution of lift and drag tables along the blade, the
1096	!-- layout of the rotor blade and the lift and drag tables:
1097
1098	OPEN ( 201, FILE='WTM_DATA', STATUS='OLD', FORM='FORMATTED', IOSTAT=ierrn )
1099
1100	IF ( ierrn /= 0 ) THEN
1101	message_string = 'file WTM_DATA does not exist'
1102	CALL message( 'wtm_init', 'PA0464', 1, 2, 0, 6, 0 )
1103	ENDIF
1104	!
1105	!-- Read distribution table:
1106
1107	dlen = 0
1108
1109	READ ( 201, '(3/)' )
1110
1111	rloop3: DO
1112	READ ( 201, *, IOSTAT=ierrn ) chmess
1113	IF ( ierrn < 0 .OR. chmess == '#' .OR. chmess == '') EXIT rloop3
1114	dlen = dlen + 1
1115	ENDDO rloop3
1116
1117	ALLOCATE( trad1(1:dlen), trad2(1:dlen), ttoint1(1:dlen), ttoint2(1:dlen))
1118
1119	DO jj = 1,dlen+1
1120	BACKSPACE ( 201, IOSTAT=ierrn )
1121	ENDDO
1122
1123	DO jj = 1,dlen
1124	READ ( 201, * ) trad1(jj), trad2(jj), ttoint1(jj), ttoint2(jj)
1125	ENDDO
1126
1127	!
1128	!-- Read layout table:
1129
1130	dlen = 0
1131
1132	READ ( 201, '(3/)')
1133
1134	rloop1: DO
1135	READ ( 201, *, IOSTAT=ierrn ) chmess
1136	IF ( ierrn < 0 .OR. chmess == '#' .OR. chmess == '') EXIT rloop1
1137	dlen = dlen + 1
1138	ENDDO rloop1
1139
1140	ALLOCATE( lrd(1:dlen), ard(1:dlen), crd(1:dlen) )
1141	DO jj = 1, dlen+1
1142	BACKSPACE ( 201, IOSTAT=ierrn )
1143	ENDDO
1144	DO jj = 1, dlen
1145	READ ( 201, * ) lrd(jj), ard(jj), crd(jj)
1146	ENDDO
1147
1148	!
1149	!-- Read tables (turb_cl(alpha),turb_cd(alpha) for the different profiles:
1150
1151	dlen = 0
1152
1153	READ ( 201, '(3/)' )
1154
1155	rloop2: DO
1156	READ ( 201, *, IOSTAT=ierrn ) chmess
1157	IF ( ierrn < 0 .OR. chmess == '#' .OR. chmess == '') EXIT rloop2
1158	dlen = dlen + 1
1159	ENDDO rloop2
1160
1161	ALLOCATE( alpha_attack_tab(1:dlen), turb_cl_table(1:dlen,1:nairfoils), &
1162	turb_cd_table(1:dlen,1:nairfoils) )
1163
1164	DO jj = 1,dlen+1
1165	BACKSPACE ( 201, IOSTAT=ierrn )
1166	ENDDO
1167
1168	DO jj = 1,dlen
1169	READ ( 201, * ) read_cl_cd
1170	alpha_attack_tab(jj) = read_cl_cd(1)
1171	DO ii= 1, nairfoils
1172	turb_cl_table(jj,ii) = read_cl_cd(ii*2)
1173	turb_cd_table(jj,ii) = read_cl_cd(ii*2+1)
1174	ENDDO
1175
1176	ENDDO
1177
1178	dlenbl = dlen
1179
1180	CLOSE ( 201 )
1181
1182	!
1183	!-- For each possible radial position (resolution: 0.1 m --> 630 values) and
1184	!-- each possible angle of attack (resolution: 0.01 degrees --> 36000 values!)
1185	!-- determine the lift and drag coefficient by interpolating between the
1186	!-- tabulated values of each table (interpolate to current angle of attack)
1187	!-- and between the tables (interpolate to current radial position):
1188
1189	ALLOCATE( turb_cl_sel1(0:dlenbl) )
1190	ALLOCATE( turb_cl_sel2(0:dlenbl) )
1191	ALLOCATE( turb_cd_sel1(0:dlenbl) )
1192	ALLOCATE( turb_cd_sel2(0:dlenbl) )
1193
1194	radres = INT( rr(1) * 10.0_wp ) + 1_iwp
1195	dlenbl_int = INT( 360.0_wp / accu_cl_cd_tab ) + 1_iwp
1196
1197
1198	ALLOCATE( turb_cl_tab(0:dlenbl_int,1:radres) )
1199	ALLOCATE( turb_cd_tab(0:dlenbl_int,1:radres) )
1200
1201
1202	DO iir = 1, radres ! loop over radius
1203
1204	DO iialpha = 1, dlenbl_int ! loop over angles
1205
1206	cur_r = ( iir - 1_iwp ) * 0.1_wp
1207	alpha_attack_i = -180.0_wp + REAL( iialpha-1 ) * accu_cl_cd_tab
1208	ialpha = 1
1209
1210	DO WHILE ( ( alpha_attack_i > alpha_attack_tab(ialpha) ) .AND. (ialpha <= dlen ) )
1211	ialpha = ialpha + 1
1212	ENDDO
1213	!
1214	!-- Find position in table
1215	lct = MINLOC( ABS( trad1 - cur_r ) )
1216	! lct(1) = lct(1)
1217
1218	IF ( ( trad1(lct(1)) - cur_r ) .GT. 0.0 ) THEN
1219	lct(1) = lct(1) - 1
1220	ENDIF
1221
1222	trow = lct(1)
1223	!
1224	!-- Calculate weights for interpolation
1225	weight_a = ( trad2(trow) - cur_r ) / ( trad2(trow) - trad1(trow) )
1226	weight_b = ( cur_r - trad1(trow) ) / ( trad2(trow) - trad1(trow) )
1227	t1 = ttoint1(trow)
1228	t2 = ttoint2(trow)
1229
1230	IF ( t1 .EQ. t2 ) THEN ! if both are the same, the weights are NaN
1231	weight_a = 0.5_wp ! then do interpolate in between same twice
1232	weight_b = 0.5_wp ! using 0.5 as weight
1233	ENDIF
1234
1235	IF ( t1 == 0 .AND. t2 == 0 ) THEN
1236	turb_cd_sel1 = 0.0_wp
1237	turb_cd_sel2 = 0.0_wp
1238	turb_cl_sel1 = 0.0_wp
1239	turb_cl_sel2 = 0.0_wp
1240	ELSE
1241	turb_cd_sel1 = turb_cd_table(:,t1)
1242	turb_cd_sel2 = turb_cd_table(:,t2)
1243	turb_cl_sel1 = turb_cl_table(:,t1)
1244	turb_cl_sel2 = turb_cl_table(:,t2)
1245	ENDIF
1246
1247	!
1248	!-- Interpolation of lift and drag coefficiencts on fine grid of radius
1249	!-- segments and angles of attack
1250
1251	turb_cl_tab(iialpha,iir) = ( alpha_attack_tab(ialpha) - &
1252	alpha_attack_i ) / &
1253	( alpha_attack_tab(ialpha) - &
1254	alpha_attack_tab(ialpha-1) ) * &
1255	( weight_a * turb_cl_sel1(ialpha-1) + &
1256	weight_b * turb_cl_sel2(ialpha-1) ) +&
1257	( alpha_attack_i - &
1258	alpha_attack_tab(ialpha-1) ) / &
1259	( alpha_attack_tab(ialpha) - &
1260	alpha_attack_tab(ialpha-1) ) * &
1261	( weight_a * turb_cl_sel1(ialpha) + &
1262	weight_b * turb_cl_sel2(ialpha) )
1263	turb_cd_tab(iialpha,iir) = ( alpha_attack_tab(ialpha) - &
1264	alpha_attack_i ) / &
1265	( alpha_attack_tab(ialpha) - &
1266	alpha_attack_tab(ialpha-1) ) * &
1267	( weight_a * turb_cd_sel1(ialpha-1) + &
1268	weight_b * turb_cd_sel2(ialpha-1) ) +&
1269	( alpha_attack_i - &
1270	alpha_attack_tab(ialpha-1) ) / &
1271	( alpha_attack_tab(ialpha) - &
1272	alpha_attack_tab(ialpha-1) ) * &
1273	( weight_a * turb_cd_sel1(ialpha) + &
1274	weight_b * turb_cd_sel2(ialpha) )
1275
1276	ENDDO ! end loop over angles of attack
1277
1278	ENDDO ! end loop over radius
1279
1280	END SUBROUTINE wtm_read_blade_tables
1281
1282
1283	!------------------------------------------------------------------------------!
1284	! Description:
1285	! ------------
1286	!> The projection matrix for the coordinate system of therotor disc in respect
1287	!> to the yaw and tilt angle of the rotor is calculated
1288	!------------------------------------------------------------------------------!
1289	SUBROUTINE wtm_rotate_rotor( inot )
1290
1291
1292	IMPLICIT NONE
1293
1294	INTEGER(iwp) :: inot
1295	!
1296	!-- Calculation of the rotation matrix for the application of the tilt to
1297	!-- the rotors
1298	rot_eigen_rad(1) = SIN( phi_yaw(inot) ) ! x-component of the radial eigenvector
1299	rot_eigen_rad(2) = COS( phi_yaw(inot) ) ! y-component of the radial eigenvector
1300	rot_eigen_rad(3) = 0.0_wp ! z-component of the radial eigenvector
1301
1302	rot_eigen_azi(1) = 0.0_wp ! x-component of the azimuth eigenvector
1303	rot_eigen_azi(2) = 0.0_wp ! y-component of the azimuth eigenvector
1304	rot_eigen_azi(3) = 1.0_wp ! z-component of the azimuth eigenvector
1305
1306	rot_eigen_nor(1) = COS( phi_yaw(inot) ) ! x-component of the normal eigenvector
1307	rot_eigen_nor(2) = -SIN( phi_yaw(inot) ) ! y-component of the normal eigenvector
1308	rot_eigen_nor(3) = 0.0_wp ! z-component of the normal eigenvector
1309
1310	!
1311	!-- Calculation of the coordinate transformation matrix to apply a tilt to
1312	!-- the rotor. If tilt = 0, rot_coord_trans is a unit matrix.
1313
1314	rot_coord_trans(inot,1,1) = rot_eigen_rad(1)*2 &
1315	( 1.0_wp - COS( tilt ) ) + COS( tilt )
1316	rot_coord_trans(inot,1,2) = rot_eigen_rad(1) * rot_eigen_rad(2) * &
1317	( 1.0_wp - COS( tilt ) ) - &
1318	rot_eigen_rad(3) * SIN( tilt )
1319	rot_coord_trans(inot,1,3) = rot_eigen_rad(1) * rot_eigen_rad(3) * &
1320	( 1.0_wp - COS( tilt ) ) + &
1321	rot_eigen_rad(2) * SIN( tilt )
1322	rot_coord_trans(inot,2,1) = rot_eigen_rad(2) * rot_eigen_rad(1) * &
1323	( 1.0_wp - COS( tilt ) ) + &
1324	rot_eigen_rad(3) * SIN( tilt )
1325	rot_coord_trans(inot,2,2) = rot_eigen_rad(2)*2 &
1326	( 1.0_wp - COS( tilt ) ) + COS( tilt )
1327	rot_coord_trans(inot,2,3) = rot_eigen_rad(2) * rot_eigen_rad(3) * &
1328	( 1.0_wp - COS( tilt ) ) - &
1329	rot_eigen_rad(1) * SIN( tilt )
1330	rot_coord_trans(inot,3,1) = rot_eigen_rad(3) * rot_eigen_rad(1) * &
1331	( 1.0_wp - COS( tilt ) ) - &
1332	rot_eigen_rad(2) * SIN( tilt )
1333	rot_coord_trans(inot,3,2) = rot_eigen_rad(3) * rot_eigen_rad(2) * &
1334	( 1.0_wp - COS( tilt ) ) + &
1335	rot_eigen_rad(1) * SIN( tilt )
1336	rot_coord_trans(inot,3,3) = rot_eigen_rad(3)*2 &
1337	( 1.0_wp - COS( tilt ) ) + COS( tilt )
1338
1339	!
1340	!-- Vectors for the Transformation of forces from the rotor's spheric
1341	!-- coordinate system to the cartesian coordinate system
1342	rotx(inot,:) = MATMUL( rot_coord_trans(inot,:,:), rot_eigen_nor )
1343	roty(inot,:) = MATMUL( rot_coord_trans(inot,:,:), rot_eigen_rad )
1344	rotz(inot,:) = MATMUL( rot_coord_trans(inot,:,:), rot_eigen_azi )
1345
1346	END SUBROUTINE wtm_rotate_rotor
1347
1348
1349	!------------------------------------------------------------------------------!
1350	! Description:
1351	! ------------
1352	!> Calculation of the forces generated by the wind turbine
1353	!------------------------------------------------------------------------------!
1354	SUBROUTINE wtm_forces
1355
1356
1357	IMPLICIT NONE
1358
1359	CHARACTER (LEN=2) :: turbine_id
1360
1361	INTEGER(iwp) :: i, j, k !< loop indices
1362	INTEGER(iwp) :: inot !< turbine loop index (turbine id)
1363	INTEGER(iwp) :: iialpha, iir !<
1364	INTEGER(iwp) :: rseg, rseg_int !<
1365	INTEGER(iwp) :: ring, ring_int !<
1366	INTEGER(iwp) :: ii, jj, kk !<
1367
1368	REAL(wp) :: flag !< flag to mask topography grid points
1369	REAL(wp) :: sin_rot, cos_rot !<
1370	REAL(wp) :: sin_yaw, cos_yaw !<
1371
1372	REAL(wp) :: aa, bb, cc, dd !< interpolation distances
1373	REAL(wp) :: gg !< interpolation volume var
1374
1375	REAL(wp) :: dist_u_3d, dist_v_3d, dist_w_3d !< smearing distances
1376
1377
1378	!
1379	! Variables for pitch control
1380	REAL(wp) :: torque_max=0.0_wp
1381	LOGICAL :: pitch_sw=.FALSE.
1382
1383	INTEGER(iwp), DIMENSION(1) :: lct=0
1384	REAL(wp), DIMENSION(1) :: rad_d=0.0_wp
1385
1386	REAL(wp) :: tl_factor !< factor for tip loss correction
1387
1388
1389	CALL cpu_log( log_point_s(61), 'wtm_forces', 'start' )
1390
1391
1392	IF ( simulated_time >= time_turbine_on ) THEN
1393
1394	!
1395	!-- Set forces to zero for each new time step:
1396	thrust(:,:,:) = 0.0_wp
1397	torque_y(:,:,:) = 0.0_wp
1398	torque_z(:,:,:) = 0.0_wp
1399	torque_total(:) = 0.0_wp
1400	rot_tend_x(:,:,:) = 0.0_wp
1401	rot_tend_y(:,:,:) = 0.0_wp
1402	rot_tend_z(:,:,:) = 0.0_wp
1403	thrust_rotor(:) = 0.0_wp
1404	!
1405	!-- Loop over number of turbines:
1406	DO inot = 1, nturbines
1407
1408	cos_yaw = COS(phi_yaw(inot))
1409	sin_yaw = SIN(phi_yaw(inot))
1410	!
1411	!-- Loop over rings of each turbine:
1412	DO ring = 1, nrings(inot)
1413
1414	thrust_seg(:) = 0.0_wp
1415	torque_seg_y(:) = 0.0_wp
1416	torque_seg_z(:) = 0.0_wp
1417	!
1418	!-- Determine distance between each ring (center) and the hub:
1419	cur_r = (ring - 0.5_wp) * delta_r(inot)
1420
1421	!
1422	!-- Loop over segments of each ring of each turbine:
1423	DO rseg = 1, nsegs(ring,inot)
1424	!
1425	!-- !-----------------------------------------------------------!
1426	!-- !-- Determine coordinates of the ring segments --!
1427	!-- !-----------------------------------------------------------!
1428	!
1429	!-- Determine angle of ring segment towards zero degree angle of
1430	!-- rotor system (at zero degree rotor direction vectors aligned
1431	!-- with y-axis):
1432	phi_rotor = rseg * 2.0_wp * pi / nsegs(ring,inot)
1433	cos_rot = COS( phi_rotor )
1434	sin_rot = SIN( phi_rotor )
1435
1436	!-- Now the direction vectors can be determined with respect to
1437	!-- the yaw and tilt angle:
1438	re(1) = cos_rot * sin_yaw
1439	re(2) = cos_rot * cos_yaw
1440	re(3) = sin_rot
1441
1442	rote = MATMUL( rot_coord_trans(inot,:,:), re )
1443	!
1444	!-- Coordinates of the single segments (center points):
1445	rbx(ring,rseg) = rcx(inot) + cur_r * rote(1)
1446	rby(ring,rseg) = rcy(inot) + cur_r * rote(2)
1447	rbz(ring,rseg) = rcz(inot) + cur_r * rote(3)
1448
1449	!-- !-----------------------------------------------------------!
1450	!-- !-- Interpolation of the velocity components from the --!
1451	!-- !-- cartesian grid point to the coordinates of each ring --!
1452	!-- !-- segment (follows a method used in the particle model) --!
1453	!-- !-----------------------------------------------------------!
1454
1455	u_int(inot,ring,rseg) = 0.0_wp
1456	u_int_1_l(inot,ring,rseg) = 0.0_wp
1457
1458	v_int(inot,ring,rseg) = 0.0_wp
1459	v_int_1_l(inot,ring,rseg) = 0.0_wp
1460
1461	w_int(inot,ring,rseg) = 0.0_wp
1462	w_int_1_l(inot,ring,rseg) = 0.0_wp
1463
1464	!
1465	!-- Interpolation of the u-component:
1466
1467	ii = rbx(ring,rseg) * ddx
1468	jj = ( rby(ring,rseg) - 0.5_wp * dy ) * ddy
1469	kk = ( rbz(ring,rseg) - 0.5_wp * dz ) / dz
1470	!
1471	!-- Interpolate only if all required information is available on
1472	!-- the current PE:
1473	IF ( ( ii >= nxl ) .AND. ( ii <= nxr ) ) THEN
1474	IF ( ( jj >= nys ) .AND. ( jj <= nyn ) ) THEN
1475
1476	aa = ( ( ii + 1 ) * dx - rbx(ring,rseg) ) * &
1477	( ( jj + 1 + 0.5_wp ) * dy - rby(ring,rseg) )
1478	bb = ( rbx(ring,rseg) - ii * dx ) * &
1479	( ( jj + 1 + 0.5_wp ) * dy - rby(ring,rseg) )
1480	cc = ( ( ii+1 ) * dx - rbx(ring,rseg) ) * &
1481	( rby(ring,rseg) - ( jj + 0.5_wp ) * dy )
1482	dd = ( rbx(ring,rseg) - ii * dx ) * &
1483	( rby(ring,rseg) - ( jj + 0.5_wp ) * dy )
1484	gg = dx * dy
1485
1486	u_int_l = ( aa * u(kk,jj,ii) + &
1487	bb * u(kk,jj,ii+1) + &
1488	cc * u(kk,jj+1,ii) + &
1489	dd * u(kk,jj+1,ii+1) &
1490	) / gg
1491
1492	u_int_u = ( aa * u(kk+1,jj,ii) + &
1493	bb * u(kk+1,jj,ii+1) + &
1494	cc * u(kk+1,jj+1,ii) + &
1495	dd * u(kk+1,jj+1,ii+1) &
1496	) / gg
1497
1498	u_int_1_l(inot,ring,rseg) = u_int_l + &
1499	( rbz(ring,rseg) - zu(kk) ) / dz * &
1500	( u_int_u - u_int_l )
1501
1502	ELSE
1503	u_int_1_l(inot,ring,rseg) = 0.0_wp
1504	ENDIF
1505	ELSE
1506	u_int_1_l(inot,ring,rseg) = 0.0_wp
1507	ENDIF
1508
1509
1510	!
1511	!-- Interpolation of the v-component:
1512	ii = ( rbx(ring,rseg) - 0.5_wp * dx ) * ddx
1513	jj = rby(ring,rseg) * ddy
1514	kk = ( rbz(ring,rseg) + 0.5_wp * dz ) / dz
1515	!
1516	!-- Interpolate only if all required information is available on
1517	!-- the current PE:
1518	IF ( ( ii >= nxl ) .AND. ( ii <= nxr ) ) THEN
1519	IF ( ( jj >= nys ) .AND. ( jj <= nyn ) ) THEN
1520
1521	aa = ( ( ii + 1 + 0.5_wp ) * dx - rbx(ring,rseg) ) * &
1522	( ( jj + 1 ) * dy - rby(ring,rseg) )
1523	bb = ( rbx(ring,rseg) - ( ii + 0.5_wp ) * dx ) * &
1524	( ( jj + 1 ) * dy - rby(ring,rseg) )
1525	cc = ( ( ii + 1 + 0.5_wp ) * dx - rbx(ring,rseg) ) * &
1526	( rby(ring,rseg) - jj * dy )
1527	dd = ( rbx(ring,rseg) - ( ii + 0.5_wp ) * dx ) * &
1528	( rby(ring,rseg) - jj * dy )
1529	gg = dx * dy
1530
1531	v_int_l = ( aa * v(kk,jj,ii) + &
1532	bb * v(kk,jj,ii+1) + &
1533	cc * v(kk,jj+1,ii) + &
1534	dd * v(kk,jj+1,ii+1) &
1535	) / gg
1536
1537	v_int_u = ( aa * v(kk+1,jj,ii) + &
1538	bb * v(kk+1,jj,ii+1) + &
1539	cc * v(kk+1,jj+1,ii) + &
1540	dd * v(kk+1,jj+1,ii+1) &
1541	) / gg
1542
1543	v_int_1_l(inot,ring,rseg) = v_int_l + &
1544	( rbz(ring,rseg) - zu(kk) ) / dz * &
1545	( v_int_u - v_int_l )
1546
1547	ELSE
1548	v_int_1_l(inot,ring,rseg) = 0.0_wp
1549	ENDIF
1550	ELSE
1551	v_int_1_l(inot,ring,rseg) = 0.0_wp
1552	ENDIF
1553
1554
1555	!
1556	!-- Interpolation of the w-component:
1557	ii = ( rbx(ring,rseg) - 0.5_wp * dx ) * ddx
1558	jj = ( rby(ring,rseg) - 0.5_wp * dy ) * ddy
1559	kk = rbz(ring,rseg) / dz
1560	!
1561	!-- Interpolate only if all required information is available on
1562	!-- the current PE:
1563	IF ( ( ii >= nxl ) .AND. ( ii <= nxr ) ) THEN
1564	IF ( ( jj >= nys ) .AND. ( jj <= nyn ) ) THEN
1565
1566	aa = ( ( ii + 1 + 0.5_wp ) * dx - rbx(ring,rseg) ) * &
1567	( ( jj + 1 + 0.5_wp ) * dy - rby(ring,rseg) )
1568	bb = ( rbx(ring,rseg) - ( ii + 0.5_wp ) * dx ) * &
1569	( ( jj + 1 + 0.5_wp ) * dy - rby(ring,rseg) )
1570	cc = ( ( ii + 1 + 0.5_wp ) * dx - rbx(ring,rseg) ) * &
1571	( rby(ring,rseg) - ( jj + 0.5_wp ) * dy )
1572	dd = ( rbx(ring,rseg) - ( ii + 0.5_wp ) * dx ) * &
1573	( rby(ring,rseg) - ( jj + 0.5_wp ) * dy )
1574	gg = dx * dy
1575
1576	w_int_l = ( aa * w(kk,jj,ii) + &
1577	bb * w(kk,jj,ii+1) + &
1578	cc * w(kk,jj+1,ii) + &
1579	dd * w(kk,jj+1,ii+1) &
1580	) / gg
1581
1582	w_int_u = ( aa * w(kk+1,jj,ii) + &
1583	bb * w(kk+1,jj,ii+1) + &
1584	cc * w(kk+1,jj+1,ii) + &
1585	dd * w(kk+1,jj+1,ii+1) &
1586	) / gg
1587
1588	w_int_1_l(inot,ring,rseg) = w_int_l + &
1589	( rbz(ring,rseg) - zw(kk) ) / dz * &
1590	( w_int_u - w_int_l )
1591	ELSE
1592	w_int_1_l(inot,ring,rseg) = 0.0_wp
1593	ENDIF
1594	ELSE
1595	w_int_1_l(inot,ring,rseg) = 0.0_wp
1596	ENDIF
1597
1598	ENDDO
1599	ENDDO
1600
1601	ENDDO
1602
1603	!
1604	!-- Exchange between PEs (information required on each PE):
1605	#if defined( __parallel )
1606	CALL MPI_ALLREDUCE( u_int_1_l, u_int, nturbines * MAXVAL(nrings) * &
1607	MAXVAL(nsegs), MPI_REAL, MPI_SUM, comm2d, ierr )
1608	CALL MPI_ALLREDUCE( v_int_1_l, v_int, nturbines * MAXVAL(nrings) * &
1609	MAXVAL(nsegs), MPI_REAL, MPI_SUM, comm2d, ierr )
1610	CALL MPI_ALLREDUCE( w_int_1_l, w_int, nturbines * MAXVAL(nrings) * &
1611	MAXVAL(nsegs), MPI_REAL, MPI_SUM, comm2d, ierr )
1612	#else
1613	u_int = u_int_1_l
1614	v_int = v_int_1_l
1615	w_int = w_int_1_l
1616	#endif
1617
1618
1619	!
1620	!-- Loop over number of turbines:
1621
1622	DO inot = 1, nturbines
1623	pit_loop: DO
1624
1625	IF ( pitch_sw ) THEN
1626	torque_total(inot) = 0.0_wp
1627	thrust_rotor(inot) = 0.0_wp
1628	pitch_add(inot) = pitch_add(inot) + 0.25_wp
1629	! IF ( myid == 0 ) PRINT*, 'Pitch', inot, pitch_add(inot)
1630	ELSE
1631	cos_yaw = COS(phi_yaw(inot))
1632	sin_yaw = SIN(phi_yaw(inot))
1633	IF ( pitch_control ) THEN
1634	pitch_add(inot) = MAX(pitch_add_old(inot) - pitch_rate * &
1635	dt_3d , 0.0_wp )
1636	ENDIF
1637	ENDIF
1638
1639	!
1640	!-- Loop over rings of each turbine:
1641	DO ring = 1, nrings(inot)
1642	!
1643	!-- Determine distance between each ring (center) and the hub:
1644	cur_r = (ring - 0.5_wp) * delta_r(inot)
1645	!
1646	!-- Loop over segments of each ring of each turbine:
1647	DO rseg = 1, nsegs(ring,inot)
1648	!
1649	!-- Determine angle of ring segment towards zero degree angle of
1650	!-- rotor system (at zero degree rotor direction vectors aligned
1651	!-- with y-axis):
1652	phi_rotor = rseg * 2.0_wp * pi / nsegs(ring,inot)
1653	cos_rot = COS(phi_rotor)
1654	sin_rot = SIN(phi_rotor)
1655	!
1656	!-- Now the direction vectors can be determined with respect to
1657	!-- the yaw and tilt angle:
1658	re(1) = cos_rot * sin_yaw
1659	re(2) = cos_rot * cos_yaw
1660	re(3) = sin_rot
1661
1662	! The current unit vector in azimuthal direction:
1663	rea(1) = - sin_rot * sin_yaw
1664	rea(2) = - sin_rot * cos_yaw
1665	rea(3) = cos_rot
1666
1667	!
1668	!-- To respect the yawing angle for the calculations of
1669	!-- velocities and forces the unit vectors perpendicular to the
1670	!-- rotor area in direction of the positive yaw angle are defined:
1671	ren(1) = cos_yaw
1672	ren(2) = - sin_yaw
1673	ren(3) = 0.0_wp
1674	!
1675	!-- Multiplication with the coordinate transformation matrix
1676	!-- gives the final unit vector with consideration of the rotor
1677	!-- tilt:
1678	rote = MATMUL( rot_coord_trans(inot,:,:), re )
1679	rota = MATMUL( rot_coord_trans(inot,:,:), rea )
1680	rotn = MATMUL( rot_coord_trans(inot,:,:), ren )
1681	!
1682	!-- Coordinates of the single segments (center points):
1683	rbx(ring,rseg) = rcx(inot) + cur_r * rote(1)
1684
1685	rby(ring,rseg) = rcy(inot) + cur_r * rote(2)
1686
1687	rbz(ring,rseg) = rcz(inot) + cur_r * rote(3)
1688
1689	!
1690	!-- !-----------------------------------------------------------!
1691	!-- !-- Calculation of various angles and relative velocities --!
1692	!-- !-----------------------------------------------------------!
1693	!
1694	!-- In the following the 3D-velocity field is projected its
1695	!-- components perpedicular and parallel to the rotor area
1696	!-- The calculation of forces will be done in the rotor-
1697	!-- coordinates y' and z.
1698	!-- The yaw angle will be reintroduced when the force is applied
1699	!-- on the hydrodynamic equations
1700	!
1701	!-- Projection of the xy-velocities relative to the rotor area
1702	!
1703	!-- Velocity perpendicular to the rotor area:
1704	u_rot = u_int(inot,ring,rseg)*rotn(1) + &
1705	v_int(inot,ring,rseg)*rotn(2) + &
1706	w_int(inot,ring,rseg)*rotn(3)
1707	!
1708	!-- Projection of the 3D-velocity vector in the azimuthal
1709	!-- direction:
1710	vtheta(rseg) = rota(1) * u_int(inot,ring,rseg) + &
1711	rota(2) * v_int(inot,ring,rseg) + &
1712	rota(3) * w_int(inot,ring,rseg)
1713	!
1714	!-- Determination of the angle phi_rel between the rotor plane
1715	!-- and the direction of the flow relative to the rotor:
1716
1717	phi_rel(rseg) = ATAN( u_rot / &
1718	( omega_rot(inot) * cur_r - &
1719	vtheta(rseg) ) )
1720
1721	!
1722	!-- Interpolation of the local pitch angle from tabulated values
1723	!-- to the current radial position:
1724
1725	lct=minloc(ABS(cur_r-lrd))
1726	rad_d=cur_r-lrd(lct)
1727
1728	IF (cur_r == 0.0_wp) THEN
1729	alpha_attack(rseg) = 0.0_wp
1730	ELSE IF (cur_r >= lrd(size(ard))) THEN
1731	alpha_attack(rseg) = ( ard(size(ard)) + &
1732	ard(size(ard)-1) ) / 2.0_wp
1733	ELSE
1734	alpha_attack(rseg) = ( ard(lct(1)) * &
1735	( ( lrd(lct(1)+1) - cur_r ) / &
1736	( lrd(lct(1)+1) - lrd(lct(1)) ) &
1737	) ) + ( ard(lct(1)+1) * &
1738	( ( cur_r - lrd(lct(1)) ) / &
1739	( lrd(lct(1)+1) - lrd(lct(1)) ) ) )
1740	ENDIF
1741
1742	!
1743	!-- In Fortran radian instead of degree is used as unit for all
1744	!-- angles. Therefore, a transformation from angles given in
1745	!-- degree to angles given in radian is necessary here:
1746	alpha_attack(rseg) = alpha_attack(rseg) * &
1747	( (2.0_wp*pi) / 360.0_wp )
1748	!
1749	!-- Substraction of the local pitch angle to obtain the local
1750	!-- angle of attack:
1751	alpha_attack(rseg) = phi_rel(rseg) - alpha_attack(rseg)
1752	!
1753	!-- Preliminary transformation back from angles given in radian
1754	!-- to angles given in degree:
1755	alpha_attack(rseg) = alpha_attack(rseg) * &
1756	( 360.0_wp / (2.0_wp*pi) )
1757	!
1758	!-- Correct with collective pitch angle:
1759	alpha_attack = alpha_attack - pitch_add(inot)
1760
1761	!
1762	!-- Determination of the magnitude of the flow velocity relative
1763	!-- to the rotor:
1764	vrel(rseg) = SQRT( u_rot**2 + &
1765	( omega_rot(inot) * cur_r - &
1766	vtheta(rseg) )**2 )
1767
1768	!
1769	!-- !-----------------------------------------------------------!
1770	!-- !-- Interpolation of chord as well as lift and drag --!
1771	!-- !-- coefficients from tabulated values --!
1772	!-- !-----------------------------------------------------------!
1773
1774	!
1775	!-- Interpolation of the chord_length from tabulated values to
1776	!-- the current radial position:
1777
1778	IF (cur_r == 0.0_wp) THEN
1779	chord(rseg) = 0.0_wp
1780	ELSE IF (cur_r >= lrd(size(crd))) THEN
1781	chord(rseg) = (crd(size(crd)) + ard(size(crd)-1)) / 2.0_wp
1782	ELSE
1783	chord(rseg) = ( crd(lct(1)) * &
1784	( ( lrd(lct(1)+1) - cur_r ) / &
1785	( lrd(lct(1)+1) - lrd(lct(1)) ) ) ) + &
1786	( crd(lct(1)+1) * &
1787	( ( cur_r-lrd(lct(1)) ) / &
1788	( lrd(lct(1)+1) - lrd(lct(1)) ) ) )
1789	ENDIF
1790
1791	!
1792	!-- Determine index of current angle of attack, needed for
1793	!-- finding the appropriate interpolated values of the lift and
1794	!-- drag coefficients (-180.0 degrees = 0, +180.0 degrees = 36000,
1795	!-- so one index every 0.01 degrees):
1796	iialpha = CEILING( ( alpha_attack(rseg) + 180.0_wp ) &
1797	* ( 1.0_wp / accu_cl_cd_tab ) )
1798	!
1799	!-- Determine index of current radial position, needed for
1800	!-- finding the appropriate interpolated values of the lift and
1801	!-- drag coefficients (one index every 0.1 m):
1802	iir = CEILING( cur_r * 10.0_wp )
1803	!
1804	!-- Read in interpolated values of the lift and drag coefficients
1805	!-- for the current radial position and angle of attack:
1806	turb_cl(rseg) = turb_cl_tab(iialpha,iir)
1807	turb_cd(rseg) = turb_cd_tab(iialpha,iir)
1808
1809	!
1810	!-- Final transformation back from angles given in degree to
1811	!-- angles given in radian:
1812	alpha_attack(rseg) = alpha_attack(rseg) * &
1813	( (2.0_wp*pi) / 360.0_wp )
1814
1815	IF ( tl_cor ) THEN
1816
1817	!-- Tip loss correction following Schito
1818	!-- Schito applies the tip loss correction only to the lift force
1819	!-- Therefore, the tip loss correction is only applied to the lift
1820	!-- coefficient and not to the drag coefficient in our case
1821	!--
1822	tl_factor = ( 2.0 / pi ) * &
1823	ACOS( EXP( -1.0 * ( 3.0 * ( rr(inot) - cur_r ) / &
1824	( 2.0 * cur_r * abs( sin( phi_rel(rseg) ) ) ) ) ) )
1825
1826	turb_cl(rseg) = tl_factor * turb_cl(rseg)
1827
1828	END IF
1829	!
1830	!-- !-----------------------------------------------------!
1831	!-- !-- Calculation of the forces --!
1832	!-- !-----------------------------------------------------!
1833
1834	!
1835	!-- Calculate the pre_factor for the thrust and torque forces:
1836
1837	pre_factor = 0.5_wp * (vrel(rseg)*2) 3.0_wp * &
1838	chord(rseg) * delta_r(inot) / nsegs(ring,inot)
1839
1840	!
1841	!-- Calculate the thrust force (x-component of the total force)
1842	!-- for each ring segment:
1843	thrust_seg(rseg) = pre_factor * &
1844	( turb_cl(rseg) * COS(phi_rel(rseg)) + &
1845	turb_cd(rseg) * SIN(phi_rel(rseg)) )
1846
1847	!
1848	!-- Determination of the second of the additional forces acting
1849	!-- on the flow in the azimuthal direction: force vector as basis
1850	!-- for torque (torque itself would be the vector product of the
1851	!-- radius vector and the force vector):
1852	torque_seg = pre_factor * &
1853	( turb_cl(rseg) * SIN(phi_rel(rseg)) - &
1854	turb_cd(rseg) * COS(phi_rel(rseg)) )
1855	!
1856	!-- Decomposition of the force vector into two parts:
1857	!-- One acting along the y-direction and one acting along the
1858	!-- z-direction of the rotor coordinate system:
1859
1860	torque_seg_y(rseg) = -torque_seg * sin_rot
1861	torque_seg_z(rseg) = torque_seg * cos_rot
1862
1863	!
1864	!-- Add the segment thrust to the thrust of the whole rotor
1865	thrust_rotor(inot) = thrust_rotor(inot) + &
1866	thrust_seg(rseg)
1867
1868
1869	torque_total(inot) = torque_total(inot) + (torque_seg * cur_r)
1870
1871	ENDDO !-- end of loop over ring segments
1872
1873	!
1874	!-- Restore the forces into arrays containing all the segments of
1875	!-- each ring:
1876	thrust_ring(ring,:) = thrust_seg(:)
1877	torque_ring_y(ring,:) = torque_seg_y(:)
1878	torque_ring_z(ring,:) = torque_seg_z(:)
1879
1880
1881	ENDDO !-- end of loop over rings
1882
1883
1884	CALL cpu_log( log_point_s(62), 'wtm_controller', 'start' )
1885
1886
1887	IF ( speed_control ) THEN
1888	!
1889	!-- Calculation of the current generator speed for rotor speed control
1890
1891	!
1892	!-- The acceleration of the rotor speed is calculated from
1893	!-- the force balance of the accelerating torque
1894	!-- and the torque of the rotating rotor and generator
1895	om_rate = ( torque_total(inot) * air_dens * gear_eff - &
1896	gear_ratio * torque_gen_old(inot) ) / &
1897	( inertia_rot + &
1898	gear_ratio * gear_ratio * inertia_gen ) * dt_3d
1899
1900	!
1901	!-- The generator speed is given by the product of gear gear_ratio
1902	!-- and rotor speed
1903	omega_gen(inot) = gear_ratio * ( omega_rot(inot) + om_rate )
1904
1905	ENDIF
1906
1907	IF ( pitch_control ) THEN
1908
1909	!
1910	!-- If the current generator speed is above rated, the pitch is not
1911	!-- saturated and the change from the last time step is within the
1912	!-- maximum pitch rate, then the pitch loop is repeated with a pitch
1913	!-- gain
1914	IF ( ( omega_gen(inot) > rated_genspeed ) .AND. &
1915	( pitch_add(inot) < 25.0_wp ) .AND. &
1916	( pitch_add(inot) < pitch_add_old(inot) + &
1917	pitch_rate * dt_3d ) ) THEN
1918	pitch_sw = .TRUE.
1919	!
1920	!-- Go back to beginning of pit_loop
1921	CYCLE pit_loop
1922	ENDIF
1923
1924	!
1925	!-- The current pitch is saved for the next time step
1926	pitch_add_old(inot) = pitch_add(inot)
1927	pitch_sw = .FALSE.
1928	ENDIF
1929	EXIT pit_loop
1930	ENDDO pit_loop ! Recursive pitch control loop
1931
1932
1933	!
1934	!-- Call the rotor speed controller
1935
1936	IF ( speed_control ) THEN
1937	!
1938	!-- Find processor at i_hub, j_hub
1939	IF ( ( nxl <= i_hub(inot) ) .AND. ( nxr >= i_hub(inot) ) ) &
1940	THEN
1941	IF ( ( nys <= j_hub(inot) ) .AND. ( nyn >= j_hub(inot) ) )&
1942	THEN
1943	CALL wtm_speed_control( inot )
1944	ENDIF
1945	ENDIF
1946
1947	ENDIF
1948
1949
1950	CALL cpu_log( log_point_s(62), 'wtm_controller', 'stop' )
1951
1952	CALL cpu_log( log_point_s(63), 'wtm_smearing', 'start' )
1953
1954
1955	!-- !-----------------------------------------------------------------!
1956	!-- !-- Regularization kernel --!
1957	!-- !-- Smearing of the forces and interpolation to cartesian grid --!
1958	!-- !-----------------------------------------------------------------!
1959	!
1960	!-- The aerodynamic blade forces need to be distributed smoothly on
1961	!-- several mesh points in order to avoid singular behaviour
1962	!
1963	!-- Summation over sum of weighted forces. The weighting factor
1964	!-- (calculated in user_init) includes information on the distance
1965	!-- between the center of the grid cell and the rotor segment under
1966	!-- consideration
1967	!
1968	!-- To save computing time, apply smearing only for the relevant part
1969	!-- of the model domain:
1970	!
1971	!--
1972	!-- Calculation of the boundaries:
1973	i_smear(inot) = CEILING( ( rr(inot) * ABS( roty(inot,1) ) + &
1974	eps_min ) / dx )
1975	j_smear(inot) = CEILING( ( rr(inot) * ABS( roty(inot,2) ) + &
1976	eps_min ) / dy )
1977
1978	DO i = MAX( nxl, i_hub(inot) - i_smear(inot) ), &
1979	MIN( nxr, i_hub(inot) + i_smear(inot) )
1980	DO j = MAX( nys, j_hub(inot) - j_smear(inot) ), &
1981	MIN( nyn, j_hub(inot) + j_smear(inot) )
1982	! DO k = MAX( nzb_u_inner(j,i)+1, k_hub(inot) - k_smear(inot) ), &
1983	! k_hub(inot) + k_smear(inot)
1984	DO k = nzb+1, k_hub(inot) + k_smear(inot)
1985	DO ring = 1, nrings(inot)
1986	DO rseg = 1, nsegs(ring,inot)
1987	!
1988	!-- Predetermine flag to mask topography
1989	flag = MERGE( 1.0_wp, 0.0_wp, BTEST( wall_flags_0(k,j,i), 1 ) )
1990
1991	!
1992	!-- Determine the square of the distance between the
1993	!-- current grid point and each rotor area segment:
1994	dist_u_3d = ( i * dx - rbx(ring,rseg) )**2 + &
1995	( j * dy + 0.5_wp * dy - rby(ring,rseg) )**2 + &
1996	( k * dz - 0.5_wp * dz - rbz(ring,rseg) )**2
1997	dist_v_3d = ( i * dx + 0.5_wp * dx - rbx(ring,rseg) )**2 + &
1998	( j * dy - rby(ring,rseg) )**2 + &
1999	( k * dz - 0.5_wp * dz - rbz(ring,rseg) )**2
2000	dist_w_3d = ( i * dx + 0.5_wp * dx - rbx(ring,rseg) )**2 + &
2001	( j * dy + 0.5_wp * dy - rby(ring,rseg) )**2 + &
2002	( k * dz - rbz(ring,rseg) )**2
2003
2004	!
2005	!-- 3D-smearing of the forces with a polynomial function
2006	!-- (much faster than the old Gaussian function), using
2007	!-- some parameters that have been calculated in user_init.
2008	!-- The function is only similar to Gaussian function for
2009	!-- squared distances <= eps_min2:
2010	IF ( dist_u_3d <= eps_min2 ) THEN
2011	thrust(k,j,i) = thrust(k,j,i) + &
2012	thrust_ring(ring,rseg) * &
2013	( ( pol_a * dist_u_3d - pol_b ) * &
2014	dist_u_3d + 1.0_wp ) * eps_factor *&
2015	flag
2016	ENDIF
2017	IF ( dist_v_3d <= eps_min2 ) THEN
2018	torque_y(k,j,i) = torque_y(k,j,i) + &
2019	torque_ring_y(ring,rseg) * &
2020	( ( pol_a * dist_v_3d - pol_b ) * &
2021	dist_v_3d + 1.0_wp ) * eps_factor * &
2022	flag
2023	ENDIF
2024	IF ( dist_w_3d <= eps_min2 ) THEN
2025	torque_z(k,j,i) = torque_z(k,j,i) + &
2026	torque_ring_z(ring,rseg) * &
2027	( ( pol_a * dist_w_3d - pol_b ) * &
2028	dist_w_3d + 1.0_wp ) * eps_factor * &
2029	flag
2030	ENDIF
2031
2032	ENDDO ! End of loop over rseg
2033	ENDDO ! End of loop over ring
2034
2035	!
2036	!-- Rotation of force components:
2037	rot_tend_x(k,j,i) = rot_tend_x(k,j,i) + ( &
2038	thrust(k,j,i)*rotx(inot,1) + &
2039	torque_y(k,j,i)*roty(inot,1) + &
2040	torque_z(k,j,i)*rotz(inot,1) &
2041	) * flag
2042
2043	rot_tend_y(k,j,i) = rot_tend_y(k,j,i) + ( &
2044	thrust(k,j,i)*rotx(inot,2) + &
2045	torque_y(k,j,i)*roty(inot,2) + &
2046	torque_z(k,j,i)*rotz(inot,2) &
2047	) * flag
2048
2049	rot_tend_z(k,j,i) = rot_tend_z(k,j,i) + ( &
2050	thrust(k,j,i)*rotx(inot,3) + &
2051	torque_y(k,j,i)*roty(inot,3) + &
2052	torque_z(k,j,i)*rotz(inot,3) &
2053	) * flag
2054
2055	ENDDO ! End of loop over k
2056	ENDDO ! End of loop over j
2057	ENDDO ! End of loop over i
2058
2059	CALL cpu_log( log_point_s(63), 'wtm_smearing', 'stop' )
2060
2061	ENDDO !-- end of loop over turbines
2062
2063
2064	IF ( yaw_control ) THEN
2065	!
2066	!-- Allocate arrays for yaw control at first call
2067	!-- Can't be allocated before dt_3d is set
2068	IF ( start_up ) THEN
2069	WDLON = NINT( 30.0_wp / dt_3d ) ! 30s running mean array
2070	ALLOCATE( wd30(1:nturbines,1:WDLON) )
2071	wd30 = 999.0_wp ! Set to dummy value
2072	ALLOCATE( wd30_l(1:WDLON) )
2073
2074	WDSHO = NINT( 2.0_wp / dt_3d ) ! 2s running mean array
2075	ALLOCATE( wd2(1:nturbines,1:WDSHO) )
2076	wd2 = 999.0_wp ! Set to dummy value
2077	ALLOCATE( wd2_l(1:WDSHO) )
2078	start_up = .FALSE.
2079	ENDIF
2080
2081	!
2082	!-- Calculate the inflow wind speed
2083	!--
2084	!-- Loop over number of turbines:
2085	DO inot = 1, nturbines
2086	!
2087	!-- Find processor at i_hub, j_hub
2088	IF ( ( nxl <= i_hub(inot) ) .AND. ( nxr >= i_hub(inot) ) ) &
2089	THEN
2090	IF ( ( nys <= j_hub(inot) ) .AND. ( nyn >= j_hub(inot) ) )&
2091	THEN
2092
2093	u_inflow_l(inot) = u(k_hub(inot),j_hub(inot),i_hub(inot))
2094
2095	wdir_l(inot) = -1.0_wp * ATAN2( &
2096	0.5_wp * ( v(k_hub(inot),j_hub(inot),i_hub(inot)+1) + &
2097	v(k_hub(inot),j_hub(inot),i_hub(inot)) ) , &
2098	0.5_wp * ( u(k_hub(inot),j_hub(inot)+1,i_hub(inot)) + &
2099	u(k_hub(inot),j_hub(inot),i_hub(inot)) ) )
2100
2101	CALL wtm_yawcontrol( inot )
2102
2103	phi_yaw_l(inot) = phi_yaw(inot)
2104
2105	ENDIF
2106	ENDIF
2107
2108	ENDDO !-- end of loop over turbines
2109
2110	!
2111	!-- Transfer of information to the other cpus
2112	#if defined( __parallel )
2113	CALL MPI_ALLREDUCE( u_inflow_l, u_inflow, nturbines, MPI_REAL, &
2114	MPI_SUM, comm2d, ierr )
2115	CALL MPI_ALLREDUCE( wdir_l, wdir, nturbines, MPI_REAL, MPI_SUM, &
2116	comm2d, ierr )
2117	CALL MPI_ALLREDUCE( phi_yaw_l, phi_yaw, nturbines, MPI_REAL, &
2118	MPI_SUM, comm2d, ierr )
2119	#else
2120	u_inflow = u_inflow_l
2121	wdir = wdir_l
2122	phi_yaw = phi_yaw_l
2123
2124
2125	#endif
2126	DO inot = 1, nturbines
2127	!
2128	!-- Update rotor orientation
2129	CALL wtm_rotate_rotor( inot )
2130
2131	ENDDO ! End of loop over turbines
2132
2133	END IF ! end of yaw control
2134
2135	IF ( speed_control ) THEN
2136	!
2137	!-- Transfer of information to the other cpus
2138	! CALL MPI_ALLREDUCE( omega_gen, omega_gen_old, nturbines, &
2139	! MPI_REAL,MPI_SUM, comm2d, ierr )
2140	#if defined( __parallel )
2141	CALL MPI_ALLREDUCE( torque_gen, torque_gen_old, nturbines, &
2142	MPI_REAL, MPI_SUM, comm2d, ierr )
2143	CALL MPI_ALLREDUCE( omega_rot_l, omega_rot, nturbines, &
2144	MPI_REAL, MPI_SUM, comm2d, ierr )
2145	CALL MPI_ALLREDUCE( omega_gen_f, omega_gen_f_old, nturbines, &
2146	MPI_REAL, MPI_SUM, comm2d, ierr )
2147	#else
2148	torque_gen_old = torque_gen
2149	omega_rot = omega_rot_l
2150	omega_gen_f_old = omega_gen_f
2151	#endif
2152
2153	ENDIF
2154
2155	DO inot = 1, nturbines
2156
2157	IF ( myid == 0 ) THEN
2158	IF ( openfile_turb_mod(400+inot)%opened ) THEN
2159	WRITE ( 400+inot, 106 ) simulated_time, omega_rot(inot), &
2160	omega_gen(inot), torque_gen_old(inot), &
2161	torque_total(inot), pitch_add(inot), &
2162	torque_gen_old(inot)omega_gen(inot)gen_eff, &
2163	torque_total(inot)omega_rot(inot)air_dens, &
2164	thrust_rotor(inot), &
2165	wdir(inot)*180.0_wp/pi, &
2166	(phi_yaw(inot))*180.0_wp/pi
2167
2168	ELSE
2169
2170	WRITE ( turbine_id,'(I2.2)') inot
2171	OPEN ( 400+inot, FILE=( 'TURBINE_PARAMETERS'//turbine_id ), &
2172	FORM='FORMATTED' )
2173	WRITE ( 400+inot, 105 ) inot
2174	WRITE ( 400+inot, 106 ) simulated_time, omega_rot(inot), &
2175	omega_gen(inot), torque_gen_old(inot), &
2176	torque_total(inot), pitch_add(inot), &
2177	torque_gen_old(inot)omega_gen(inot)gen_eff, &
2178	torque_total(inot)omega_rot(inot)air_dens, &
2179	thrust_rotor(inot), &
2180	wdir(inot)*180.0_wp/pi, &
2181	(phi_yaw(inot))*180.0_wp/pi
2182	ENDIF
2183	ENDIF
2184
2185	!-- Set open flag
2186	openfile_turb_mod(400+inot)%opened = .TRUE.
2187	ENDDO !-- end of loop over turbines
2188
2189	ENDIF
2190
2191	CALL cpu_log( log_point_s(61), 'wtm_forces', 'stop' )
2192
2193	!
2194	!-- Formats
2195	105 FORMAT ('Turbine control data for turbine ',I2,1X,':'/ &
2196	&'----------------------------------------'/ &
2197	&' Time RSpeed GSpeed ', &
2198	'GenTorque AeroTorque Pitch Power(Gen) Power(Rot) ', &
2199	'RotThrust WDirection YawOrient')
2200
2201	106 FORMAT (F9.3,2X,F7.3,2X,F7.2,2X,F9.1,3X,F9.1,1X,F6.2,2X,F10.1,2X, &
2202	F10.1,1X,F9.1,2X,F7.2,1X,F7.2)
2203
2204
2205	END SUBROUTINE wtm_forces
2206
2207
2208	!------------------------------------------------------------------------------!
2209	! Description:
2210	! ------------
2211	!> Yaw controller for the wind turbine model
2212	!------------------------------------------------------------------------------!
2213	SUBROUTINE wtm_yawcontrol( inot )
2214
2215	USE constants
2216	USE kinds
2217
2218	IMPLICIT NONE
2219
2220	INTEGER(iwp) :: inot
2221	INTEGER(iwp) :: i_wd_30
2222	REAL(wp) :: missal
2223
2224	i_wd_30 = 0_iwp
2225
2226	!
2227	!-- The yaw controller computes a 30s running mean of the wind direction.
2228	!-- If the difference between turbine alignment and wind direction exceeds
2229	!-- 5Â°, the turbine is yawed. The mechanism stops as soon as the 2s-running
2230	!-- mean of the missalignment is smaller than 0.5Â°.
2231	!-- Attention: If the timestep during the simulation changes significantly
2232	!-- the lengths of the running means change and it does not correspond to
2233	!-- 30s/2s anymore.
2234	!-- ! Needs to be modified for these situations !
2235	!-- For wind from the east, the averaging of the wind direction could cause
2236	!-- problems and the yaw controller is probably flawed. -> Routine for
2237	!-- averaging needs to be improved!
2238	!
2239	!-- Check if turbine is not yawing
2240	IF ( .NOT. doyaw(inot) ) THEN
2241	!
2242	!-- Write current wind direction into array
2243	wd30_l = wd30(inot,:)
2244	wd30_l = CSHIFT( wd30_l, SHIFT=-1 )
2245	wd30_l(1) = wdir(inot)
2246	!
2247	!-- Check if array is full ( no more dummies )
2248	IF ( .NOT. ANY( wd30_l == 999.) ) THEN
2249
2250	missal = SUM( wd30_l ) / SIZE( wd30_l ) - phi_yaw(inot)
2251	!
2252	!-- Check if turbine is missaligned by more than max_miss
2253	IF ( ABS( missal ) > max_miss ) THEN
2254	!
2255	!-- Check in which direction to yaw
2256	yawdir(inot) = SIGN( 1.0_wp, missal )
2257	!
2258	!-- Start yawing of turbine
2259	phi_yaw(inot) = phi_yaw(inot) + yawdir(inot) * yaw_speed * dt_3d
2260	doyaw(inot) = .TRUE.
2261	wd30_l = 999. ! fill with dummies again
2262	ENDIF
2263	ENDIF
2264
2265	wd30(inot,:) = wd30_l
2266
2267	!
2268	!-- If turbine is already yawing:
2269	!-- Initialize 2 s running mean and yaw until the missalignment is smaller
2270	!-- than min_miss
2271
2272	ELSE
2273	!
2274	!-- Initialize 2 s running mean
2275	wd2_l = wd2(inot,:)
2276	wd2_l = CSHIFT( wd2_l, SHIFT = -1 )
2277	wd2_l(1) = wdir(inot)
2278	!
2279	!-- Check if array is full ( no more dummies )
2280	IF ( .NOT. ANY( wd2_l == 999.0_wp ) ) THEN
2281	!
2282	!-- Calculate missalignment of turbine
2283	missal = SUM( wd2_l - phi_yaw(inot) ) / SIZE( wd2_l )
2284	!
2285	!-- Check if missalignment is still larger than 0.5 degree and if the
2286	!-- yaw direction is still right
2287	IF ( ( ABS( missal ) > min_miss ) .AND. &
2288	( yawdir(inot) == SIGN( 1.0_wp, missal ) ) ) THEN
2289	!
2290	!-- Continue yawing
2291	phi_yaw(inot) = phi_yaw(inot) + yawdir(inot) * yaw_speed * dt_3d
2292	ELSE
2293	!
2294	!-- Stop yawing
2295	doyaw(inot) = .FALSE.
2296	wd2_l = 999.0_wp ! fill with dummies again
2297	ENDIF
2298	ELSE
2299	!
2300	!-- Continue yawing
2301	phi_yaw(inot) = phi_yaw(inot) + yawdir(inot) * yaw_speed * dt_3d
2302	ENDIF
2303
2304	wd2(inot,:) = wd2_l
2305
2306	ENDIF
2307
2308	END SUBROUTINE wtm_yawcontrol
2309
2310
2311	!------------------------------------------------------------------------------!
2312	! Description:
2313	! ------------
2314	!> Initialization of the speed control
2315	!------------------------------------------------------------------------------!
2316	SUBROUTINE wtm_init_speed_control
2317
2318
2319	IMPLICIT NONE
2320
2321	!
2322	!-- If speed control is set, remaining variables and control_parameters for
2323	!-- the control algorithm are calculated
2324	!
2325	!-- Calculate slope constant for region 15
2326	slope15 = ( slope2 * min_reg2 * min_reg2 ) / ( min_reg2 - min_reg15 )
2327	!
2328	!-- Calculate upper limit of slipage region
2329	vs_sysp = rated_genspeed / 1.1_wp
2330	!
2331	!-- Calculate slope of slipage region
2332	slope25 = ( rated_power / rated_genspeed ) / &
2333	( rated_genspeed - vs_sysp )
2334	!
2335	!-- Calculate lower limit of slipage region
2336	min_reg25 = ( slope25 - SQRT( slope25 * ( slope25 - 4.0_wp * &
2337	slope2 * vs_sysp ) ) ) / &
2338	( 2.0_wp * slope2 )
2339	!
2340	!-- Frequency for the simple low pass filter
2341	Fcorner = 0.25_wp
2342	!
2343	!-- At the first timestep the torque is set to its maximum to prevent
2344	!-- an overspeeding of the rotor
2345	torque_gen_old(:) = max_torque_gen
2346
2347	END SUBROUTINE wtm_init_speed_control
2348
2349
2350	!------------------------------------------------------------------------------!
2351	! Description:
2352	! ------------
2353	!> Simple controller for the regulation of the rotor speed
2354	!------------------------------------------------------------------------------!
2355	SUBROUTINE wtm_speed_control( inot )
2356
2357
2358	IMPLICIT NONE
2359
2360	INTEGER(iwp) :: inot
2361
2362
2363
2364	!
2365	!-- The controller is based on the fortran script from Jonkman
2366	!-- et al. 2009 "Definition of a 5 MW Reference Wind Turbine for
2367	!-- offshore system developement"
2368
2369	!
2370	!-- The generator speed is filtered by a low pass filter
2371	!-- for the control of the generator torque
2372	lp_coeff = EXP( -2.0_wp * 3.14_wp * dt_3d * Fcorner )
2373	omega_gen_f(inot) = ( 1.0_wp - lp_coeff ) * omega_gen(inot) + lp_coeff *&
2374	omega_gen_f_old(inot)
2375
2376	IF ( omega_gen_f(inot) <= min_reg15 ) THEN
2377	!
2378	!-- Region 1: Generator torque is set to zero to accelerate the rotor:
2379	torque_gen(inot) = 0
2380
2381	ELSEIF ( omega_gen_f(inot) <= min_reg2 ) THEN
2382	!
2383	!-- Region 1.5: Generator torque is increasing linearly with rotor speed:
2384	torque_gen(inot) = slope15 * ( omega_gen_f(inot) - min_reg15 )
2385
2386	ELSEIF ( omega_gen_f(inot) <= min_reg25 ) THEN
2387	!
2388	!-- Region 2: Generator torque is increased by the square of the generator
2389	!-- speed to keep the TSR optimal:
2390	torque_gen(inot) = slope2 * omega_gen_f(inot) * omega_gen_f(inot)
2391
2392	ELSEIF ( omega_gen_f(inot) < rated_genspeed ) THEN
2393	!
2394	!-- Region 2.5: Slipage region between 2 and 3:
2395	torque_gen(inot) = slope25 * ( omega_gen_f(inot) - vs_sysp )
2396
2397	ELSE
2398	!
2399	!-- Region 3: Generator torque is antiproportional to the rotor speed to
2400	!-- keep the power constant:
2401	torque_gen(inot) = rated_power / omega_gen_f(inot)
2402
2403	ENDIF
2404	!
2405	!-- Calculate torque rate and confine with a max
2406	trq_rate = ( torque_gen(inot) - torque_gen_old(inot) ) / dt_3d
2407	trq_rate = MIN( MAX( trq_rate, -1.0_wp * max_trq_rate ), max_trq_rate )
2408	!
2409	!-- Calculate new gen torque and confine with max torque
2410	torque_gen(inot) = torque_gen_old(inot) + trq_rate * dt_3d
2411	torque_gen(inot) = MIN( torque_gen(inot), max_torque_gen )
2412	!
2413	!-- Overwrite values for next timestep
2414	omega_rot_l(inot) = omega_gen(inot) / gear_ratio
2415
2416
2417	END SUBROUTINE wtm_speed_control
2418
2419
2420	!------------------------------------------------------------------------------!
2421	! Description:
2422	! ------------
2423	!> Application of the additional forces generated by the wind turbine on the
2424	!> flow components (tendency terms)
2425	!> Call for all grid points
2426	!------------------------------------------------------------------------------!
2427	SUBROUTINE wtm_tendencies( component )
2428
2429
2430	IMPLICIT NONE
2431
2432	INTEGER(iwp) :: component !< prognostic variable (u,v,w)
2433	INTEGER(iwp) :: i !< running index
2434	INTEGER(iwp) :: j !< running index
2435	INTEGER(iwp) :: k !< running index
2436
2437
2438	SELECT CASE ( component )
2439
2440	CASE ( 1 )
2441	!
2442	!-- Apply the x-component of the force to the u-component of the flow:
2443	IF ( simulated_time >= time_turbine_on ) THEN
2444	DO i = nxlg, nxrg
2445	DO j = nysg, nyng
2446	DO k = nzb+1, k_hub(1) + k_smear(1)
2447	!
2448	!-- Calculate the thrust generated by the nacelle and the tower
2449	tend_nac_x = 0.5_wp * nac_cd_surf(k,j,i) * &
2450	SIGN( u(k,j,i)**2 , u(k,j,i) )
2451	tend_tow_x = 0.5_wp * tow_cd_surf(k,j,i) * &
2452	SIGN( u(k,j,i)**2 , u(k,j,i) )
2453
2454	tend(k,j,i) = tend(k,j,i) + ( - rot_tend_x(k,j,i) &
2455	- tend_nac_x - tend_tow_x ) &
2456	* MERGE( 1.0_wp, 0.0_wp, &
2457	BTEST( wall_flags_0(k,j,i), 1 ) )
2458	ENDDO
2459	ENDDO
2460	ENDDO
2461	ENDIF
2462
2463	CASE ( 2 )
2464	!
2465	!-- Apply the y-component of the force to the v-component of the flow:
2466	IF ( simulated_time >= time_turbine_on ) THEN
2467	DO i = nxlg, nxrg
2468	DO j = nysg, nyng
2469	DO k = nzb+1, k_hub(1) + k_smear(1)
2470	tend_nac_y = 0.5_wp * nac_cd_surf(k,j,i) * &
2471	SIGN( v(k,j,i)**2 , v(k,j,i) )
2472	tend_tow_y = 0.5_wp * tow_cd_surf(k,j,i) * &
2473	SIGN( v(k,j,i)**2 , v(k,j,i) )
2474	tend(k,j,i) = tend(k,j,i) + ( - rot_tend_y(k,j,i) &
2475	- tend_nac_y - tend_tow_y ) &
2476	* MERGE( 1.0_wp, 0.0_wp, &
2477	BTEST( wall_flags_0(k,j,i), 2 ) )
2478	ENDDO
2479	ENDDO
2480	ENDDO
2481	ENDIF
2482
2483	CASE ( 3 )
2484	!
2485	!-- Apply the z-component of the force to the w-component of the flow:
2486	IF ( simulated_time >= time_turbine_on ) THEN
2487	DO i = nxlg, nxrg
2488	DO j = nysg, nyng
2489	DO k = nzb+1, k_hub(1) + k_smear(1)
2490	tend(k,j,i) = tend(k,j,i) - rot_tend_z(k,j,i) &
2491	* MERGE( 1.0_wp, 0.0_wp, &
2492	BTEST( wall_flags_0(k,j,i), 3 ) )
2493	ENDDO
2494	ENDDO
2495	ENDDO
2496	ENDIF
2497
2498
2499	CASE DEFAULT
2500
2501	WRITE( message_string, * ) 'unknown prognostic variable: ', component
2502	CALL message( 'wtm_tendencies', 'PA04??', 1, 2, 0, 6, 0 )
2503
2504	END SELECT
2505
2506
2507	END SUBROUTINE wtm_tendencies
2508
2509
2510	!------------------------------------------------------------------------------!
2511	! Description:
2512	! ------------
2513	!> Application of the additional forces generated by the wind turbine on the
2514	!> flow components (tendency terms)
2515	!> Call for grid point i,j
2516	!------------------------------------------------------------------------------!
2517	SUBROUTINE wtm_tendencies_ij( i, j, component )
2518
2519
2520	IMPLICIT NONE
2521
2522	INTEGER(iwp) :: component !< prognostic variable (u,v,w)
2523	INTEGER(iwp) :: i !< running index
2524	INTEGER(iwp) :: j !< running index
2525	INTEGER(iwp) :: k !< running index
2526
2527	SELECT CASE ( component )
2528
2529	CASE ( 1 )
2530	!
2531	!-- Apply the x-component of the force to the u-component of the flow:
2532	IF ( simulated_time >= time_turbine_on ) THEN
2533
2534	DO k = nzb+1, k_hub(1) + k_smear(1)
2535	!
2536	!-- Calculate the thrust generated by the nacelle and the tower
2537	tend_nac_x = 0.5_wp * nac_cd_surf(k,j,i) * &
2538	SIGN( u(k,j,i)**2 , u(k,j,i) )
2539	tend_tow_x = 0.5_wp * tow_cd_surf(k,j,i) * &
2540	SIGN( u(k,j,i)**2 , u(k,j,i) )
2541	tend(k,j,i) = tend(k,j,i) + ( - rot_tend_x(k,j,i) &
2542	- tend_nac_x - tend_tow_x ) &
2543	* MERGE( 1.0_wp, 0.0_wp, &
2544	BTEST( wall_flags_0(k,j,i), 1 ) )
2545	ENDDO
2546	ENDIF
2547
2548	CASE ( 2 )
2549	!
2550	!-- Apply the y-component of the force to the v-component of the flow:
2551	IF ( simulated_time >= time_turbine_on ) THEN
2552	DO k = nzb+1, k_hub(1) + k_smear(1)
2553	tend_nac_y = 0.5_wp * nac_cd_surf(k,j,i) * &
2554	SIGN( v(k,j,i)**2 , v(k,j,i) )
2555	tend_tow_y = 0.5_wp * tow_cd_surf(k,j,i) * &
2556	SIGN( v(k,j,i)**2 , v(k,j,i) )
2557	tend(k,j,i) = tend(k,j,i) + ( - rot_tend_y(k,j,i) &
2558	- tend_nac_y - tend_tow_y ) &
2559	* MERGE( 1.0_wp, 0.0_wp, &
2560	BTEST( wall_flags_0(k,j,i), 2 ) )
2561	ENDDO
2562	ENDIF
2563
2564	CASE ( 3 )
2565	!
2566	!-- Apply the z-component of the force to the w-component of the flow:
2567	IF ( simulated_time >= time_turbine_on ) THEN
2568	DO k = nzb+1, k_hub(1) + k_smear(1)
2569	tend(k,j,i) = tend(k,j,i) - rot_tend_z(k,j,i) &
2570	* MERGE( 1.0_wp, 0.0_wp, &
2571	BTEST( wall_flags_0(k,j,i), 3 ) )
2572	ENDDO
2573	ENDIF
2574
2575
2576	CASE DEFAULT
2577
2578	WRITE( message_string, * ) 'unknown prognostic variable: ', component
2579	CALL message( 'wtm_tendencies', 'PA04??', 1, 2, 0, 6, 0 )
2580
2581	END SELECT
2582
2583
2584	END SUBROUTINE wtm_tendencies_ij
2585
2586	END MODULE wind_turbine_model_mod

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