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source: palm/trunk/SOURCE/wind_turbine_model_mod.f90 @ 2309

Last change on this file since 2309 was 2257, checked in by witha, 7 years ago
Bugfix in PALM-WTM, modifications for lceddy
Property svn:keywords set to `Id`
File size: 109.0 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 2257 2017-06-07 14:07:05Z gronemeier $
28	! Bugfix: turb_cl_tab and turb_cd_tab were set to zero before being allocated
29	!
30	! 2233 2017-05-30 18:08:54Z suehring
31	!
32	! 2232 2017-05-30 17:47:52Z suehring
33	! Adjustments to new topography concept
34	!
35	! 2152 2017-02-17 13:27:24Z lvollmer
36	! Bugfix in subroutine wtm_read_blade_tables
37	! Addition of a tip loss model
38	!
39	! 2015 2016-09-28 08:45:18Z lvollmer
40	! Bugfix of pitch control
41	!
42	! 2000 2016-08-20 18:09:15Z knoop
43	! Forced header and separation lines into 80 columns
44	!
45	! 1929 2016-06-09 16:25:25Z suehring
46	! Bugfix: added preprocessor directives for parallel and serial mode
47	!
48	! 1914 2016-05-26 14:44:07Z witha
49	! Initial revision
50	!
51	!
52	! Description:
53	! ------------
54	!> This module calculates the effect of wind turbines on the flow fields. The
55	!> initial version contains only the advanced actuator disk with rotation method
56	!> (ADM-R).
57	!> The wind turbines include the tower effect, can be yawed and tilted.
58	!> The wind turbine model includes controllers for rotational speed, pitch and
59	!> yaw.
60	!> Currently some specifications of the NREL 5 MW reference turbine
61	!> are hardcoded whereas most input data comes from separate files (currently
62	!> external, planned to be included as namelist which will be read in
63	!> automatically).
64	!>
65	!> @todo Revise code according to PALM Coding Standard
66	!> @todo Implement ADM and ALM turbine models
67	!> @todo Generate header information
68	!> @todo Implement further parameter checks and error messages
69	!> @todo Revise and add code documentation
70	!> @todo Output turbine parameters as timeseries
71	!> @todo Include additional output variables
72	!> @todo Revise smearing the forces for turbines in yaw
73	!> @todo Revise nacelle and tower parameterization
74	!> @todo Allow different turbine types in one simulation
75	!
76	!------------------------------------------------------------------------------!
77	MODULE wind_turbine_model_mod
78
79	USE arrays_3d, &
80	ONLY: dd2zu, tend, u, v, w, zu, zw
81
82	USE constants
83
84	USE control_parameters, &
85	ONLY: dt_3d, dz, message_string, simulated_time
86
87	USE cpulog, &
88	ONLY: cpu_log, log_point_s
89
90	USE grid_variables, &
91	ONLY: ddx, dx, ddy, dy
92
93	USE indices, &
94	ONLY: nbgp, nx, nxl, nxlg, nxr, nxrg, ny, nyn, nyng, nys, nysg, nz, &
95	nzb, nzt, wall_flags_0
96
97	USE kinds
98
99	USE pegrid
100
101
102	IMPLICIT NONE
103
104	PRIVATE
105
106	LOGICAL :: wind_turbine=.FALSE. !< switch for use of wind turbine model
107
108	!
109	!-- Variables specified in the namelist wind_turbine_par
110
111	INTEGER(iwp) :: nairfoils = 8 !< number of airfoils of the used turbine model (for ADM-R and ALM)
112	INTEGER(iwp) :: nturbines = 1 !< number of turbines
113
114	LOGICAL :: pitch_control = .FALSE. !< switch for use of pitch controller
115	LOGICAL :: speed_control = .FALSE. !< switch for use of speed controller
116	LOGICAL :: yaw_control = .FALSE. !< switch for use of yaw controller
117	LOGICAL :: tl_cor = .FALSE. !< switch for use of tip loss correct.
118
119	REAL(wp) :: segment_length = 1.0_wp !< length of the segments, the rotor area is divided into
120	!< (in tangential direction, as factor of MIN(dx,dy,dz))
121	REAL(wp) :: segment_width = 0.5_wp !< width of the segments, the rotor area is divided into
122	!< (in radial direction, as factor of MIN(dx,dy,dz))
123	REAL(wp) :: time_turbine_on = 0.0_wp !< time at which turbines are started
124	REAL(wp) :: tilt = 0.0_wp !< vertical tilt of the rotor [degree] ( positive = backwards )
125
126	REAL(wp), DIMENSION(1:100) :: dtow = 0.0_wp !< tower diameter [m]
127	REAL(wp), DIMENSION(1:100) :: omega_rot = 0.0_wp !< inital or constant rotor speed [rad/s]
128	REAL(wp), DIMENSION(1:100) :: phi_yaw = 0.0_wp !< yaw angle [degree] ( clockwise, 0 = facing west )
129	REAL(wp), DIMENSION(1:100) :: pitch_add = 0.0_wp !< constant pitch angle
130	REAL(wp), DIMENSION(1:100) :: rcx = 9999999.9_wp !< position of hub in x-direction
131	REAL(wp), DIMENSION(1:100) :: rcy = 9999999.9_wp !< position of hub in y-direction
132	REAL(wp), DIMENSION(1:100) :: rcz = 9999999.9_wp !< position of hub in z-direction
133	REAL(wp), DIMENSION(1:100) :: rnac = 0.0_wp !< nacelle diameter [m]
134	REAL(wp), DIMENSION(1:100) :: rr = 63.0_wp !< rotor radius [m]
135	REAL(wp), DIMENSION(1:100) :: turb_cd_nacelle = 0.85_wp !< drag coefficient for nacelle
136	REAL(wp), DIMENSION(1:100) :: turb_cd_tower = 1.2_wp !< drag coefficient for tower
137
138	!
139	!-- Variables specified in the namelist for speed controller
140	!-- Default values are from the NREL 5MW research turbine (Jonkman, 2008)
141
142	REAL(wp) :: rated_power = 5296610.0_wp !< rated turbine power [W]
143	REAL(wp) :: gear_ratio = 97.0_wp !< Gear ratio from rotor to generator
144	REAL(wp) :: inertia_rot = 34784179.0_wp !< Inertia of the rotor [kg/m2]
145	REAL(wp) :: inertia_gen = 534.116_wp !< Inertia of the generator [kg/m2]
146	REAL(wp) :: gen_eff = 0.944_wp !< Electric efficiency of the generator
147	REAL(wp) :: gear_eff = 1.0_wp !< Loss between rotor and generator
148	REAL(wp) :: air_dens = 1.225_wp !< Air density to convert to W [kg/m3]
149	REAL(wp) :: rated_genspeed = 121.6805_wp !< Rated generator speed [rad/s]
150	REAL(wp) :: max_torque_gen = 47402.91_wp !< Maximum of the generator torque [Nm]
151	REAL(wp) :: slope2 = 2.332287_wp !< Slope constant for region 2
152	REAL(wp) :: min_reg2 = 91.21091_wp !< Lower generator speed boundary of region 2 [rad/s]
153	REAL(wp) :: min_reg15 = 70.16224_wp !< Lower generator speed boundary of region 1.5 [rad/s]
154	REAL(wp) :: max_trq_rate = 15000.0_wp !< Max generator torque increase [Nm/s]
155	REAL(wp) :: pitch_rate = 8.0_wp !< Max pitch rate [degree/s]
156
157
158	!
159	!-- Variables specified in the namelist for yaw control
160
161	REAL(wp) :: yaw_speed = 0.005236_wp !< speed of the yaw actuator [rad/s]
162	REAL(wp) :: max_miss = 0.08726_wp !< maximum tolerated yaw missalignment [rad]
163	REAL(wp) :: min_miss = 0.008726_wp !< minimum yaw missalignment for which the actuator stops [rad]
164
165	!
166	!-- Set flag for output files TURBINE_PARAMETERS
167	TYPE file_status
168	LOGICAL :: opened, opened_before
169	END TYPE file_status
170
171	TYPE(file_status), DIMENSION(500) :: openfile_turb_mod = &
172	file_status(.FALSE.,.FALSE.)
173
174	!
175	!-- Variables for initialization of the turbine model
176
177	INTEGER(iwp) :: inot !< turbine loop index (turbine id)
178	INTEGER(iwp) :: nsegs_max !< maximum number of segments (all turbines, required for allocation of arrays)
179	INTEGER(iwp) :: nrings_max !< maximum number of rings (all turbines, required for allocation of arrays)
180	INTEGER(iwp) :: ring !< ring loop index (ring number)
181	INTEGER(iwp) :: rr_int !<
182	INTEGER(iwp) :: upper_end !<
183
184	INTEGER(iwp), DIMENSION(1) :: lct !<
185
186	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: i_hub !< index belonging to x-position of the turbine
187	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: i_smear !< index defining the area for the smearing of the forces (x-direction)
188	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: j_hub !< index belonging to y-position of the turbine
189	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: j_smear !< index defining the area for the smearing of the forces (y-direction)
190	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: k_hub !< index belonging to hub height
191	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: k_smear !< index defining the area for the smearing of the forces (z-direction)
192	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: nrings !< number of rings per turbine
193	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: nsegs_total !< total number of segments per turbine
194
195	INTEGER(iwp), DIMENSION(:,:), ALLOCATABLE :: nsegs !< number of segments per ring and turbine
196
197	!
198	!- parameters for the smearing from the rotor to the cartesian grid
199	REAL(wp) :: pol_a !< parameter for the polynomial smearing fct
200	REAL(wp) :: pol_b !< parameter for the polynomial smearing fct
201	REAL(wp) :: delta_t_factor !<
202	REAL(wp) :: eps_factor !<
203	REAL(wp) :: eps_min !<
204	REAL(wp) :: eps_min2 !<
205	REAL(wp) :: sqrt_arg !<
206
207	!
208	!-- Variables for the calculation of lift and drag coefficients
209	REAL(wp), DIMENSION(:), ALLOCATABLE :: ard !<
210	REAL(wp), DIMENSION(:), ALLOCATABLE :: crd !<
211	REAL(wp), DIMENSION(:), ALLOCATABLE :: delta_r !< radial segment length
212	REAL(wp), DIMENSION(:), ALLOCATABLE :: lrd !<
213
214	REAL(wp) :: accu_cl_cd_tab = 0.1_wp !< Accuracy of the interpolation of
215	!< the lift and drag coeff [deg]
216
217	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: turb_cd_tab !< table of the blade drag coefficient
218	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: turb_cl_tab !< table of the blade lift coefficient
219
220	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: nac_cd_surf !< 3d field of the tower drag coefficient
221	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: tow_cd_surf !< 3d field of the nacelle drag coefficient
222
223	!
224	!-- Variables for the calculation of the forces
225
226	REAL(wp) :: cur_r !<
227	REAL(wp) :: delta_t !< tangential segment length
228	REAL(wp) :: phi_rotor !<
229	REAL(wp) :: pre_factor !<
230	REAL(wp) :: torque_seg !<
231	REAL(wp) :: u_int_l !<
232	REAL(wp) :: u_int_u !<
233	REAL(wp) :: u_rot !<
234	REAL(wp) :: v_int_l !<
235	REAL(wp) :: v_int_u !<
236	REAL(wp) :: w_int_l !<
237	REAL(wp) :: w_int_u !<
238	!
239	!- Tendencies from the nacelle and tower thrust
240	REAL(wp) :: tend_nac_x = 0.0_wp !<
241	REAL(wp) :: tend_tow_x = 0.0_wp !<
242	REAL(wp) :: tend_nac_y = 0.0_wp !<
243	REAL(wp) :: tend_tow_y = 0.0_wp !<
244
245	REAL(wp), DIMENSION(:), ALLOCATABLE :: alpha_attack !<
246	REAL(wp), DIMENSION(:), ALLOCATABLE :: chord !<
247	REAL(wp), DIMENSION(:), ALLOCATABLE :: omega_gen !< curr. generator speed
248	REAL(wp), DIMENSION(:), ALLOCATABLE :: phi_rel !<
249	REAL(wp), DIMENSION(:), ALLOCATABLE :: pitch_add_old!<
250	REAL(wp), DIMENSION(:), ALLOCATABLE :: torque_total !<
251	REAL(wp), DIMENSION(:), ALLOCATABLE :: thrust_rotor !<
252	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cl !<
253	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cd !<
254	REAL(wp), DIMENSION(:), ALLOCATABLE :: vrel !<
255	REAL(wp), DIMENSION(:), ALLOCATABLE :: vtheta !<
256
257	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: rbx, rby, rbz !< coordinates of the blade elements
258	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: rotx, roty, rotz !< normal vectors to the rotor coordinates
259
260	!
261	!- Fields for the interpolation of velocities on the rotor grid
262	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: u_int !<
263	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: u_int_1_l !<
264	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: v_int !<
265	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: v_int_1_l !<
266	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: w_int !<
267	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: w_int_1_l !<
268
269	!
270	!- rotor tendencies on the segments
271	REAL(wp), DIMENSION(:), ALLOCATABLE :: thrust_seg !<
272	REAL(wp), DIMENSION(:), ALLOCATABLE :: torque_seg_y !<
273	REAL(wp), DIMENSION(:), ALLOCATABLE :: torque_seg_z !<
274
275	!
276	!- rotor tendencies on the rings
277	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: thrust_ring !<
278	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: torque_ring_y !<
279	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: torque_ring_z !<
280
281	!
282	!- rotor tendencies on rotor grids for all turbines
283	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: thrust !<
284	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: torque_y !<
285	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: torque_z !<
286
287	!
288	!- rotor tendencies on coordinate grid
289	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: rot_tend_x !<
290	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: rot_tend_y !<
291	REAL(wp), DIMENSION(:,:,:), ALLOCATABLE :: rot_tend_z !<
292	!
293	!- variables for the rotation of the rotor coordinates
294	REAL(wp), DIMENSION(1:100,1:3,1:3) :: rot_coord_trans !< matrix for rotation of rotor coordinates
295
296	REAL(wp), DIMENSION(1:3) :: rot_eigen_rad !<
297	REAL(wp), DIMENSION(1:3) :: rot_eigen_azi !<
298	REAL(wp), DIMENSION(1:3) :: rot_eigen_nor !<
299	REAL(wp), DIMENSION(1:3) :: re !<
300	REAL(wp), DIMENSION(1:3) :: rea !<
301	REAL(wp), DIMENSION(1:3) :: ren !<
302	REAL(wp), DIMENSION(1:3) :: rote !<
303	REAL(wp), DIMENSION(1:3) :: rota !<
304	REAL(wp), DIMENSION(1:3) :: rotn !<
305
306	!
307	!-- Fixed variables for the speed controller
308
309	LOGICAL :: start_up = .TRUE. !<
310
311	REAL(wp) :: Fcorner !< corner freq for the controller low pass filter
312	REAL(wp) :: min_reg25 !< min region 2.5
313	REAL(wp) :: om_rate !< rotor speed change
314	REAL(wp) :: slope15 !< slope in region 1.5
315	REAL(wp) :: slope25 !< slope in region 2.5
316	REAL(wp) :: trq_rate !< torque change
317	REAL(wp) :: vs_sysp !<
318	REAL(wp) :: lp_coeff !< coeff for the controller low pass filter
319
320	REAL(wp), DIMENSION(:), ALLOCATABLE :: omega_gen_old !< last gen. speed
321	REAL(wp), DIMENSION(:), ALLOCATABLE :: omega_gen_f !< filtered gen. sp
322	REAL(wp), DIMENSION(:), ALLOCATABLE :: omega_gen_f_old !< last filt. gen. sp
323	REAL(wp), DIMENSION(:), ALLOCATABLE :: torque_gen !< generator torque
324	REAL(wp), DIMENSION(:), ALLOCATABLE :: torque_gen_old !< last gen. torque
325
326	REAL(wp), DIMENSION(100) :: omega_rot_l = 0.0_wp !< local rot speed [rad/s]
327	!
328	!-- Fixed variables for the yaw controller
329
330	REAL(wp), DIMENSION(:) , ALLOCATABLE :: yawdir !< direction to yaw
331	REAL(wp), DIMENSION(:) , ALLOCATABLE :: phi_yaw_l !< local (cpu) yaw angle
332	REAL(wp), DIMENSION(:) , ALLOCATABLE :: wd30_l !< local (cpu) long running avg of the wd
333	REAL(wp), DIMENSION(:) , ALLOCATABLE :: wd2_l !< local (cpu) short running avg of the wd
334	REAL(wp), DIMENSION(:) , ALLOCATABLE :: wdir !< wind direction at hub
335	REAL(wp), DIMENSION(:) , ALLOCATABLE :: u_inflow !< wind speed at hub
336	REAL(wp), DIMENSION(:) , ALLOCATABLE :: wdir_l !<
337	REAL(wp), DIMENSION(:) , ALLOCATABLE :: u_inflow_l !<
338	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: wd30 !<
339	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: wd2 !<
340	LOGICAL, DIMENSION(1:100) :: doyaw = .FALSE. !<
341	INTEGER(iwp) :: WDLON !<
342	INTEGER(iwp) :: WDSHO !<
343
344
345	SAVE
346
347
348	INTERFACE wtm_parin
349	MODULE PROCEDURE wtm_parin
350	END INTERFACE wtm_parin
351
352	INTERFACE wtm_check_parameters
353	MODULE PROCEDURE wtm_check_parameters
354	END INTERFACE wtm_check_parameters
355
356	INTERFACE wtm_init_arrays
357	MODULE PROCEDURE wtm_init_arrays
358	END INTERFACE wtm_init_arrays
359
360	INTERFACE wtm_init
361	MODULE PROCEDURE wtm_init
362	END INTERFACE wtm_init
363
364	INTERFACE wtm_read_blade_tables
365	MODULE PROCEDURE wtm_read_blade_tables
366	END INTERFACE wtm_read_blade_tables
367
368	INTERFACE wtm_forces
369	MODULE PROCEDURE wtm_forces
370	MODULE PROCEDURE wtm_yawcontrol
371	END INTERFACE wtm_forces
372
373	INTERFACE wtm_rotate_rotor
374	MODULE PROCEDURE wtm_rotate_rotor
375	END INTERFACE wtm_rotate_rotor
376
377	INTERFACE wtm_speed_control
378	MODULE PROCEDURE wtm_init_speed_control
379	MODULE PROCEDURE wtm_speed_control
380	END INTERFACE wtm_speed_control
381
382	INTERFACE wtm_tendencies
383	MODULE PROCEDURE wtm_tendencies
384	MODULE PROCEDURE wtm_tendencies_ij
385	END INTERFACE wtm_tendencies
386
387
388	PUBLIC wtm_check_parameters, wtm_forces, wtm_init, wtm_init_arrays, &
389	wtm_parin, wtm_tendencies, wtm_tendencies_ij, wind_turbine
390
391	CONTAINS
392
393
394	!------------------------------------------------------------------------------!
395	! Description:
396	! ------------
397	!> Parin for &wind_turbine_par for wind turbine model
398	!------------------------------------------------------------------------------!
399	SUBROUTINE wtm_parin
400
401
402	IMPLICIT NONE
403
404	INTEGER(iwp) :: ierrn !<
405
406	CHARACTER (LEN=80) :: line !< dummy string that contains the current line of the parameter file
407
408	NAMELIST /wind_turbine_par/ air_dens, dtow, gear_eff, gear_ratio, &
409	gen_eff, inertia_gen, inertia_rot, max_miss, &
410	max_torque_gen, max_trq_rate, min_miss, &
411	min_reg15, min_reg2, nairfoils, nturbines, &
412	omega_rot, phi_yaw, pitch_add, pitch_control,&
413	rated_genspeed, rated_power, rcx, rcy, rcz, &
414	rnac, rr, segment_length, segment_width, &
415	slope2, speed_control, tilt, time_turbine_on,&
416	turb_cd_nacelle, turb_cd_tower, &
417	yaw_control, yaw_speed, tl_cor
418
419	!
420	!-- Try to find wind turbine model package
421	REWIND ( 11 )
422	line = ' '
423	DO WHILE ( INDEX( line, '&wind_turbine_par' ) == 0 )
424	READ ( 11, '(A)', END=10 ) line
425	ENDDO
426	BACKSPACE ( 11 )
427
428	!
429	!-- Read user-defined namelist
430	READ ( 11, wind_turbine_par, IOSTAT=ierrn )
431
432	IF ( ierrn < 0 ) THEN
433	message_string = 'errors in \$wind_turbine_par'
434	CALL message( 'wtm_parin', 'PA0???', 1, 2, 0, 6, 0 )
435	ENDIF
436
437	!
438	!-- Set flag that indicates that the wind turbine model is switched on
439	wind_turbine = .TRUE.
440
441	10 CONTINUE ! TBD Change from continue, mit ierrn machen
442
443
444	END SUBROUTINE wtm_parin
445
446	SUBROUTINE wtm_check_parameters
447
448
449	IMPLICIT NONE
450
451	IF ( ( .NOT.speed_control ) .AND. pitch_control ) THEN
452	message_string = 'pitch_control = .TRUE. requires '// &
453	'speed_control = .TRUE.'
454	CALL message( 'wtm_check_parameters', 'PA0???', 1, 2, 0, 6, 0 )
455	ENDIF
456
457	IF ( ANY( omega_rot(1:nturbines) <= 0.0 ) ) THEN
458	message_string = 'omega_rot <= 0.0, Please set omega_rot to ' // &
459	'a value larger than zero'
460	CALL message( 'wtm_check_parameters', 'PA0???', 1, 2, 0, 6, 0 )
461	ENDIF
462
463
464	IF ( ANY( rcx(1:nturbines) == 9999999.9_wp ) .OR. &
465	ANY( rcy(1:nturbines) == 9999999.9_wp ) .OR. &
466	ANY( rcz(1:nturbines) == 9999999.9_wp ) ) THEN
467
468	message_string = 'rcx, rcy, rcz ' // &
469	'have to be given for each turbine.'
470	CALL message( 'wtm_check_parameters', 'PA0???', 1, 2, 0, 6, 0 )
471
472	ENDIF
473
474
475	END SUBROUTINE wtm_check_parameters
476
477
478	!------------------------------------------------------------------------------!
479	! Description:
480	! ------------
481	!> Allocate wind turbine model arrays
482	!------------------------------------------------------------------------------!
483	SUBROUTINE wtm_init_arrays
484
485
486	IMPLICIT NONE
487
488	REAL(wp) :: delta_r_factor !<
489	REAL(wp) :: delta_r_init !<
490
491	!
492	!-- To be able to allocate arrays with dimension of rotor rings and segments,
493	!-- the maximum possible numbers of rings and segments have to be calculated:
494
495	ALLOCATE( nrings(1:nturbines) )
496	ALLOCATE( delta_r(1:nturbines) )
497
498	nrings(:) = 0
499	delta_r(:) = 0.0_wp
500
501	!
502	!-- Thickness (radial) of each ring and length (tangential) of each segment:
503	delta_r_factor = segment_width
504	delta_t_factor = segment_length
505	delta_r_init = delta_r_factor * MIN( dx, dy, dz)
506	delta_t = delta_t_factor * MIN( dx, dy, dz)
507
508	DO inot = 1, nturbines
509	!
510	!-- Determine number of rings:
511	nrings(inot) = NINT( rr(inot) / delta_r_init )
512
513	delta_r(inot) = rr(inot) / nrings(inot)
514
515	ENDDO
516
517	nrings_max = MAXVAL(nrings)
518
519	ALLOCATE( nsegs(1:nrings_max,1:nturbines) )
520	ALLOCATE( nsegs_total(1:nturbines) )
521
522	nsegs(:,:) = 0
523	nsegs_total(:) = 0
524
525
526	DO inot = 1, nturbines
527	DO ring = 1, nrings(inot)
528	!
529	!-- Determine number of segments for each ring:
530	nsegs(ring,inot) = MAX( 8, CEILING( delta_r_factor * pi * &
531	( 2.0_wp * ring - 1.0_wp ) / &
532	delta_t_factor ) )
533	ENDDO
534	!
535	!-- Total sum of all rotor segments:
536	nsegs_total(inot) = SUM( nsegs(:,inot) )
537
538	ENDDO
539
540	!
541	!-- Maximum number of segments per ring:
542	nsegs_max = MAXVAL(nsegs)
543
544	!!
545	!!-- TODO: Folgendes im Header ausgeben!
546	! IF ( myid == 0 ) THEN
547	! PRINT*, 'nrings(1) = ', nrings(1)
548	! PRINT*, '--------------------------------------------------'
549	! PRINT*, 'nsegs(:,1) = ', nsegs(:,1)
550	! PRINT*, '--------------------------------------------------'
551	! PRINT*, 'nrings_max = ', nrings_max
552	! PRINT*, 'nsegs_max = ', nsegs_max
553	! PRINT*, 'nsegs_total(1) = ', nsegs_total(1)
554	! ENDIF
555
556
557	!
558	!-- Allocate 1D arrays (dimension = number of turbines)
559	ALLOCATE( i_hub(1:nturbines) )
560	ALLOCATE( i_smear(1:nturbines) )
561	ALLOCATE( j_hub(1:nturbines) )
562	ALLOCATE( j_smear(1:nturbines) )
563	ALLOCATE( k_hub(1:nturbines) )
564	ALLOCATE( k_smear(1:nturbines) )
565	ALLOCATE( torque_total(1:nturbines) )
566	ALLOCATE( thrust_rotor(1:nturbines) )
567
568	!
569	!-- Allocation of the 1D arrays for speed pitch_control
570	ALLOCATE( omega_gen(1:nturbines) )
571	ALLOCATE( omega_gen_old(1:nturbines) )
572	ALLOCATE( omega_gen_f(1:nturbines) )
573	ALLOCATE( omega_gen_f_old(1:nturbines) )
574	ALLOCATE( pitch_add_old(1:nturbines) )
575	ALLOCATE( torque_gen(1:nturbines) )
576	ALLOCATE( torque_gen_old(1:nturbines) )
577
578	!
579	!-- Allocation of the 1D arrays for yaw control
580	ALLOCATE( yawdir(1:nturbines) )
581	ALLOCATE( u_inflow(1:nturbines) )
582	ALLOCATE( wdir(1:nturbines) )
583	ALLOCATE( u_inflow_l(1:nturbines) )
584	ALLOCATE( wdir_l(1:nturbines) )
585	ALLOCATE( phi_yaw_l(1:nturbines) )
586
587	!
588	!-- Allocate 1D arrays (dimension = number of rotor segments)
589	ALLOCATE( alpha_attack(1:nsegs_max) )
590	ALLOCATE( chord(1:nsegs_max) )
591	ALLOCATE( phi_rel(1:nsegs_max) )
592	ALLOCATE( thrust_seg(1:nsegs_max) )
593	ALLOCATE( torque_seg_y(1:nsegs_max) )
594	ALLOCATE( torque_seg_z(1:nsegs_max) )
595	ALLOCATE( turb_cd(1:nsegs_max) )
596	ALLOCATE( turb_cl(1:nsegs_max) )
597	ALLOCATE( vrel(1:nsegs_max) )
598	ALLOCATE( vtheta(1:nsegs_max) )
599
600	!
601	!-- Allocate 2D arrays (dimension = number of rotor rings and segments)
602	ALLOCATE( rbx(1:nrings_max,1:nsegs_max) )
603	ALLOCATE( rby(1:nrings_max,1:nsegs_max) )
604	ALLOCATE( rbz(1:nrings_max,1:nsegs_max) )
605	ALLOCATE( thrust_ring(1:nrings_max,1:nsegs_max) )
606	ALLOCATE( torque_ring_y(1:nrings_max,1:nsegs_max) )
607	ALLOCATE( torque_ring_z(1:nrings_max,1:nsegs_max) )
608
609	!
610	!-- Allocate additional 2D arrays
611	ALLOCATE( rotx(1:nturbines,1:3) )
612	ALLOCATE( roty(1:nturbines,1:3) )
613	ALLOCATE( rotz(1:nturbines,1:3) )
614
615	!
616	!-- Allocate 3D arrays (dimension = number of grid points)
617	ALLOCATE( nac_cd_surf(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
618	ALLOCATE( rot_tend_x(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
619	ALLOCATE( rot_tend_y(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
620	ALLOCATE( rot_tend_z(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
621	ALLOCATE( thrust(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
622	ALLOCATE( torque_y(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
623	ALLOCATE( torque_z(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
624	ALLOCATE( tow_cd_surf(nzb:nzt+1,nysg:nyng,nxlg:nxrg) )
625
626	!
627	!-- Allocate additional 3D arrays
628	ALLOCATE( u_int(1:nturbines,1:nrings_max,1:nsegs_max) )
629	ALLOCATE( u_int_1_l(1:nturbines,1:nrings_max,1:nsegs_max) )
630	ALLOCATE( v_int(1:nturbines,1:nrings_max,1:nsegs_max) )
631	ALLOCATE( v_int_1_l(1:nturbines,1:nrings_max,1:nsegs_max) )
632	ALLOCATE( w_int(1:nturbines,1:nrings_max,1:nsegs_max) )
633	ALLOCATE( w_int_1_l(1:nturbines,1:nrings_max,1:nsegs_max) )
634
635	!
636	!-- All of the arrays are initialized with a value of zero:
637	i_hub(:) = 0
638	i_smear(:) = 0
639	j_hub(:) = 0
640	j_smear(:) = 0
641	k_hub(:) = 0
642	k_smear(:) = 0
643
644	torque_total(:) = 0.0_wp
645	thrust_rotor(:) = 0.0_wp
646
647	omega_gen(:) = 0.0_wp
648	omega_gen_old(:) = 0.0_wp
649	omega_gen_f(:) = 0.0_wp
650	omega_gen_f_old(:) = 0.0_wp
651	pitch_add_old(:) = 0.0_wp
652	torque_gen(:) = 0.0_wp
653	torque_gen_old(:) = 0.0_wp
654
655	yawdir(:) = 0.0_wp
656	wdir(:) = 0.0_wp
657	u_inflow(:) = 0.0_wp
658
659	!
660	!-- Allocate 1D arrays (dimension = number of rotor segments)
661	alpha_attack(:) = 0.0_wp
662	chord(:) = 0.0_wp
663	phi_rel(:) = 0.0_wp
664	thrust_seg(:) = 0.0_wp
665	torque_seg_y(:) = 0.0_wp
666	torque_seg_z(:) = 0.0_wp
667	turb_cd(:) = 0.0_wp
668	turb_cl(:) = 0.0_wp
669	vrel(:) = 0.0_wp
670	vtheta(:) = 0.0_wp
671
672	rbx(:,:) = 0.0_wp
673	rby(:,:) = 0.0_wp
674	rbz(:,:) = 0.0_wp
675	thrust_ring(:,:) = 0.0_wp
676	torque_ring_y(:,:) = 0.0_wp
677	torque_ring_z(:,:) = 0.0_wp
678
679	rotx(:,:) = 0.0_wp
680	roty(:,:) = 0.0_wp
681	rotz(:,:) = 0.0_wp
682
683	nac_cd_surf(:,:,:) = 0.0_wp
684	rot_tend_x(:,:,:) = 0.0_wp
685	rot_tend_y(:,:,:) = 0.0_wp
686	rot_tend_z(:,:,:) = 0.0_wp
687	thrust(:,:,:) = 0.0_wp
688	torque_y(:,:,:) = 0.0_wp
689	torque_z(:,:,:) = 0.0_wp
690	tow_cd_surf(:,:,:) = 0.0_wp
691
692	u_int(:,:,:) = 0.0_wp
693	u_int_1_l(:,:,:) = 0.0_wp
694	v_int(:,:,:) = 0.0_wp
695	v_int_1_l(:,:,:) = 0.0_wp
696	w_int(:,:,:) = 0.0_wp
697	w_int_1_l(:,:,:) = 0.0_wp
698
699
700	END SUBROUTINE wtm_init_arrays
701
702
703	!------------------------------------------------------------------------------!
704	! Description:
705	! ------------
706	!> Initialization of the wind turbine model
707	!------------------------------------------------------------------------------!
708	SUBROUTINE wtm_init
709
710
711	IMPLICIT NONE
712
713	INTEGER(iwp) :: i !< running index
714	INTEGER(iwp) :: j !< running index
715	INTEGER(iwp) :: k !< running index
716
717	!
718	!-- Help variables for the smearing function
719	REAL(wp) :: eps_kernel !<
720
721	!
722	!-- Help variables for calculation of the tower drag
723	INTEGER(iwp) :: tower_n !<
724	INTEGER(iwp) :: tower_s !<
725	!
726	!-- Help variables for the calulaction of the nacelle drag
727	INTEGER(iwp) :: i_ip !<
728	INTEGER(iwp) :: i_ipg !<
729
730	REAL(wp) :: yvalue
731	REAL(wp) :: dy_int !<
732	REAL(wp) :: dz_int !<
733
734	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: circle_points !<
735
736	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: index_nacb !<
737	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: index_nacl !<
738	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: index_nacr !<
739	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: index_nact !<
740
741	ALLOCATE( index_nacb(1:nturbines) )
742	ALLOCATE( index_nacl(1:nturbines) )
743	ALLOCATE( index_nacr(1:nturbines) )
744	ALLOCATE( index_nact(1:nturbines) )
745
746
747	IF ( speed_control) THEN
748
749	CALL wtm_speed_control
750
751	ENDIF
752
753	!
754	!------------------------------------------------------------------------------!
755	!-- Calculation of parameters for the regularization kernel
756	!-- (smearing of the forces)
757	!------------------------------------------------------------------------------!
758	!
759	!-- In the following, some of the required parameters for the smearing will
760	!-- be calculated:
761
762	!-- The kernel is set equal to twice the grid spacing which has turned out to
763	!-- be a reasonable value (see e.g. Troldborg et al. (2013), Wind Energy,
764	!-- DOI: 10.1002/we.1608):
765	eps_kernel = 2.0_wp * dx
766	!
767	!-- The zero point (eps_min) of the polynomial function must be the following
768	!-- if the integral of the polynomial function (for values < eps_min) shall
769	!-- be equal to the integral of the Gaussian function used before:
770	eps_min = ( 105.0_wp / 32.0_wp )*( 1.0_wp / 3.0_wp ) &
771	pi*( 1.0_wp / 6.0_wp ) eps_kernel
772	!
773	!-- Square of eps_min:
774	eps_min2 = eps_min**2
775	!
776	!-- Parameters in the polynomial function:
777	pol_a = 1.0_wp / eps_min**4
778	pol_b = 2.0_wp / eps_min**2
779	!
780	!-- Normalization factor which is the inverse of the integral of the smearing
781	!-- function:
782	eps_factor = 105.0_wp / ( 32.0_wp * pi * eps_min**3 )
783
784	!-- Change tilt angle to rad:
785	tilt = tilt * pi / 180.0_wp
786
787	!
788	!-- Change yaw angle to rad:
789	phi_yaw(:) = phi_yaw(:) * pi / 180.0_wp
790
791
792	DO inot = 1, nturbines
793	!
794	!-- Rotate the rotor coordinates in case yaw and tilt are defined
795	CALL wtm_rotate_rotor( inot )
796
797	!
798	!-- Determine the indices of the hub height
799	i_hub(inot) = INT( rcx(inot) / dx )
800	j_hub(inot) = INT( ( rcy(inot) + 0.5_wp * dy ) / dy )
801	k_hub(inot) = INT( ( rcz(inot) + 0.5_wp * dz ) / dz )
802
803	!
804	!-- Determining the area to which the smearing of the forces is applied.
805	!-- As smearing now is effectively applied only for distances smaller than
806	!-- eps_min, the smearing area can be further limited and regarded as a
807	!-- function of eps_min:
808	i_smear(inot) = CEILING( ( rr(inot) + eps_min ) / dx )
809	j_smear(inot) = CEILING( ( rr(inot) + eps_min ) / dy )
810	k_smear(inot) = CEILING( ( rr(inot) + eps_min ) / dz )
811
812	ENDDO
813
814	!
815	!------------------------------------------------------------------------------!
816	!-- Determine the area within each grid cell that overlaps with the area
817	!-- of the nacelle and the tower (needed for calculation of the forces)
818	!------------------------------------------------------------------------------!
819	!
820	!-- Note: so far this is only a 2D version, in that the mean flow is
821	!-- perpendicular to the rotor area.
822
823	!
824	!-- Allocation of the array containing information on the intersection points
825	!-- between rotor disk and the numerical grid:
826	upper_end = ( ny + 1 ) * 10000
827
828	ALLOCATE( circle_points(1:2,1:upper_end) )
829
830	circle_points(:,:) = 0.0_wp
831
832
833	DO inot = 1, nturbines ! loop over number of turbines
834	!
835	!-- Determine the grid index (u-grid) that corresponds to the location of
836	!-- the rotor center (reduces the amount of calculations in the case that
837	!-- the mean flow is perpendicular to the rotor area):
838	i = i_hub(inot)
839
840	!
841	!-- Determine the left and the right edge of the nacelle (corresponding
842	!-- grid point indices):
843	index_nacl(inot) = INT( ( rcy(inot) - rnac(inot) + 0.5_wp * dy ) / dy )
844	index_nacr(inot) = INT( ( rcy(inot) + rnac(inot) + 0.5_wp * dy ) / dy )
845	!
846	!-- Determine the bottom and the top edge of the nacelle (corresponding
847	!-- grid point indices).The grid point index has to be increased by 1, as
848	!-- the first level for the u-component (index 0) is situated below the
849	!-- surface. All points between z=0 and z=dz/s would already be contained
850	!-- in grid box 1.
851	index_nacb(inot) = INT( ( rcz(inot) - rnac(inot) ) / dz ) + 1
852	index_nact(inot) = INT( ( rcz(inot) + rnac(inot) ) / dz ) + 1
853
854	!
855	!-- Determine the indices of the grid boxes containing the left and
856	!-- the right boundaries of the tower:
857	tower_n = ( rcy(inot) + 0.5_wp * dtow(inot) - 0.5_wp * dy ) / dy
858	tower_s = ( rcy(inot) - 0.5_wp * dtow(inot) - 0.5_wp * dy ) / dy
859
860	!
861	!-- Determine the fraction of the grid box area overlapping with the tower
862	!-- area and multiply it with the drag of the tower:
863	IF ( ( nxlg <= i ) .AND. ( nxrg >= i ) ) THEN
864
865	DO j = nys, nyn
866	!
867	!-- Loop from south to north boundary of tower
868	IF ( ( j >= tower_s ) .AND. ( j <= tower_n ) ) THEN
869
870	DO k = nzb, nzt
871
872	IF ( k == k_hub(inot) ) THEN
873	IF ( tower_n - tower_s >= 1 ) THEN
874	!
875	!-- leftmost and rightmost grid box:
876	IF ( j == tower_s ) THEN
877	tow_cd_surf(k,j,i) = ( rcz(inot) - &
878	( k_hub(inot) * dz - 0.5_wp * dz ) ) * & ! extension in z-direction
879	( ( tower_s + 1.0_wp + 0.5_wp ) * dy - &
880	( rcy(inot) - 0.5_wp * dtow(inot) ) ) * & ! extension in y-direction
881	turb_cd_tower(inot)
882	ELSEIF ( j == tower_n ) THEN
883	tow_cd_surf(k,j,i) = ( rcz(inot) - &
884	( k_hub(inot) * dz - 0.5_wp * dz ) ) * & ! extension in z-direction
885	( ( rcy(inot) + 0.5_wp * dtow(inot) ) - &
886	( tower_n + 0.5_wp ) * dy ) * & ! extension in y-direction
887	turb_cd_tower(inot)
888	!
889	!-- grid boxes inbetween
890	!-- (where tow_cd_surf = grid box area):
891	ELSE
892	tow_cd_surf(k,j,i) = ( rcz(inot) - &
893	( k_hub(inot) * dz - 0.5_wp * dz ) ) * &
894	dy * turb_cd_tower(inot)
895	ENDIF
896	!
897	!-- tower lies completely within one grid box:
898	ELSE
899	tow_cd_surf(k,j,i) = ( rcz(inot) - &
900	( k_hub(inot) * dz - 0.5_wp * dz ) ) * &
901	dtow(inot) * turb_cd_tower(inot)
902	ENDIF
903	!
904	!-- In case that k is smaller than k_hub the following actions
905	!-- are carried out:
906	ELSEIF ( k < k_hub(inot) ) THEN
907
908	IF ( ( tower_n - tower_s ) >= 1 ) THEN
909	!
910	!-- leftmost and rightmost grid box:
911	IF ( j == tower_s ) THEN
912	tow_cd_surf(k,j,i) = dz * ( &
913	( tower_s + 1 + 0.5_wp ) * dy - &
914	( rcy(inot) - 0.5_wp * dtow(inot) ) &
915	) * turb_cd_tower(inot)
916	ELSEIF ( j == tower_n ) THEN
917	tow_cd_surf(k,j,i) = dz * ( &
918	( rcy(inot) + 0.5_wp * dtow(inot) ) - &
919	( tower_n + 0.5_wp ) * dy &
920	) * turb_cd_tower(inot)
921	!
922	!-- grid boxes inbetween
923	!-- (where tow_cd_surf = grid box area):
924	ELSE
925	tow_cd_surf(k,j,i) = dz * dy * turb_cd_tower(inot)
926	ENDIF
927	!
928	!-- tower lies completely within one grid box:
929	ELSE
930	tow_cd_surf(k,j,i) = dz * dtow(inot) * &
931	turb_cd_tower(inot)
932	ENDIF ! end if larger than grid box
933
934	ENDIF ! end if k == k_hub
935
936	ENDDO ! end loop over k
937
938	ENDIF ! end if inside north and south boundary of tower
939
940	ENDDO ! end loop over j
941
942	ENDIF ! end if hub inside domain + ghostpoints
943
944
945	CALL exchange_horiz( tow_cd_surf, nbgp )
946
947	!
948	!-- Calculation of the nacelle area
949	!-- CAUTION: Currently disabled due to segmentation faults on the FLOW HPC
950	!-- cluster (Oldenburg)
951	!!
952	!!-- Tabulate the points on the circle that are required in the following for
953	!!-- the calculation of the Riemann integral (node points; they are called
954	!!-- circle_points in the following):
955	!
956	! dy_int = dy / 10000.0_wp
957	!
958	! DO i_ip = 1, upper_end
959	! yvalue = dy_int * ( i_ip - 0.5_wp ) + 0.5_wp * dy !<--- segmentation fault
960	! sqrt_arg = rnac(inot)2 - ( yvalue - rcy(inot) )2 !<--- segmentation fault
961	! IF ( sqrt_arg >= 0.0_wp ) THEN
962	!!
963	!!-- bottom intersection point
964	! circle_points(1,i_ip) = rcz(inot) - SQRT( sqrt_arg )
965	!!
966	!!-- top intersection point
967	! circle_points(2,i_ip) = rcz(inot) + SQRT( sqrt_arg ) !<--- segmentation fault
968	! ELSE
969	! circle_points(:,i_ip) = -111111 !<--- segmentation fault
970	! ENDIF
971	! ENDDO
972	!
973	!
974	! DO j = nys, nyn
975	!!
976	!!-- In case that the grid box is located completely outside the nacelle
977	!!-- (y) it can automatically be stated that there is no overlap between
978	!!-- the grid box and the nacelle and consequently we can set
979	!!-- nac_cd_surf(:,j,i) = 0.0:
980	! IF ( ( j >= index_nacl(inot) ) .AND. ( j <= index_nacr(inot) ) ) THEN
981	! DO k = nzb+1, nzt
982	!!
983	!!-- In case that the grid box is located completely outside the
984	!!-- nacelle (z) it can automatically be stated that there is no
985	!!-- overlap between the grid box and the nacelle and consequently
986	!!-- we can set nac_cd_surf(k,j,i) = 0.0:
987	! IF ( ( k >= index_nacb(inot) ) .OR. &
988	! ( k <= index_nact(inot) ) ) THEN
989	!!
990	!!-- For all other cases Riemann integrals are calculated.
991	!!-- Here, the points on the circle that have been determined
992	!!-- above are used in order to calculate the overlap between the
993	!!-- gridbox and the nacelle area (area approached by 10000
994	!!-- rectangulars dz_int * dy_int):
995	! DO i_ipg = 1, 10000
996	! dz_int = dz
997	! i_ip = j * 10000 + i_ipg
998	!!
999	!!-- Determine the vertical extension dz_int of the circle
1000	!!-- within the current grid box:
1001	! IF ( ( circle_points(2,i_ip) < zw(k) ) .AND. & !<--- segmentation fault
1002	! ( circle_points(2,i_ip) >= zw(k-1) ) ) THEN
1003	! dz_int = dz_int - & !<--- segmentation fault
1004	! ( zw(k) - circle_points(2,i_ip) )
1005	! ENDIF
1006	! IF ( ( circle_points(1,i_ip) <= zw(k) ) .AND. & !<--- segmentation fault
1007	! ( circle_points(1,i_ip) > zw(k-1) ) ) THEN
1008	! dz_int = dz_int - &
1009	! ( circle_points(1,i_ip) - zw(k-1) )
1010	! ENDIF
1011	! IF ( zw(k-1) > circle_points(2,i_ip) ) THEN
1012	! dz_int = 0.0_wp
1013	! ENDIF
1014	! IF ( zw(k) < circle_points(1,i_ip) ) THEN
1015	! dz_int = 0.0_wp
1016	! ENDIF
1017	! IF ( ( nxlg <= i ) .AND. ( nxrg >= i ) ) THEN
1018	! nac_cd_surf(k,j,i) = nac_cd_surf(k,j,i) + & !<--- segmentation fault
1019	! dy_int * dz_int * turb_cd_nacelle(inot)
1020	! ENDIF
1021	! ENDDO
1022	! ENDIF
1023	! ENDDO
1024	! ENDIF
1025	!
1026	! ENDDO
1027	!
1028	! CALL exchange_horiz( nac_cd_surf, nbgp ) !<--- segmentation fault
1029
1030	ENDDO ! end of loop over turbines
1031
1032	tow_cd_surf = tow_cd_surf / ( dx * dy * dz ) ! Normalize tower drag
1033	nac_cd_surf = nac_cd_surf / ( dx * dy * dz ) ! Normalize nacelle drag
1034
1035	CALL wtm_read_blade_tables
1036
1037	END SUBROUTINE wtm_init
1038
1039
1040	!------------------------------------------------------------------------------!
1041	! Description:
1042	! ------------
1043	!> Read in layout of the rotor blade , the lift and drag tables
1044	!> and the distribution of lift and drag tables along the blade
1045	!------------------------------------------------------------------------------!
1046	!
1047	SUBROUTINE wtm_read_blade_tables
1048
1049
1050	IMPLICIT NONE
1051
1052	INTEGER(iwp) :: ii !< running index
1053	INTEGER(iwp) :: jj !< running index
1054
1055	INTEGER(iwp) :: ierrn !<
1056
1057	CHARACTER(200) :: chmess !< Read in string
1058
1059	INTEGER(iwp) :: dlen !< no. rows of local table
1060	INTEGER(iwp) :: dlenbl !< no. rows of cd, cl table
1061	INTEGER(iwp) :: ialpha !< table position of current alpha value
1062	INTEGER(iwp) :: iialpha !<
1063	INTEGER(iwp) :: iir !<
1064	INTEGER(iwp) :: radres !< radial resolution
1065	INTEGER(iwp) :: t1 !< no. of airfoil
1066	INTEGER(iwp) :: t2 !< no. of airfoil
1067	INTEGER(iwp) :: trow !<
1068	INTEGER(iwp) :: dlenbl_int !< no. rows of interpolated cd, cl tables
1069
1070	REAL(wp) :: alpha_attack_i !<
1071	REAL(wp) :: weight_a !<
1072	REAL(wp) :: weight_b !<
1073
1074	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: ttoint1 !<
1075	INTEGER(iwp), DIMENSION(:), ALLOCATABLE :: ttoint2 !<
1076
1077	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cd_sel1 !<
1078	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cd_sel2 !<
1079	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cl_sel1 !<
1080	REAL(wp), DIMENSION(:), ALLOCATABLE :: turb_cl_sel2 !<
1081	REAL(wp), DIMENSION(:), ALLOCATABLE :: read_cl_cd !< read in var array
1082
1083	REAL(wp), DIMENSION(:), ALLOCATABLE :: alpha_attack_tab !<
1084	REAL(wp), DIMENSION(:), ALLOCATABLE :: trad1 !<
1085	REAL(wp), DIMENSION(:), ALLOCATABLE :: trad2 !<
1086	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: turb_cd_table !<
1087	REAL(wp), DIMENSION(:,:), ALLOCATABLE :: turb_cl_table !<
1088
1089	ALLOCATE ( read_cl_cd(1:2*nairfoils+1) )
1090
1091	!
1092	!-- Read in the distribution of lift and drag tables along the blade, the
1093	!-- layout of the rotor blade and the lift and drag tables:
1094
1095	OPEN ( 201, FILE='WTM_DATA', STATUS='OLD', FORM='FORMATTED', IOSTAT=ierrn )
1096
1097	IF ( ierrn /= 0 ) THEN
1098	message_string = 'file WTM_DATA does not exist'
1099	CALL message( 'wtm_init', 'PA0???', 1, 2, 0, 6, 0 )
1100	ENDIF
1101	!
1102	!-- Read distribution table:
1103
1104	dlen = 0
1105
1106	READ ( 201, '(3/)' )
1107
1108	rloop3: DO
1109	READ ( 201, *, IOSTAT=ierrn ) chmess
1110	IF ( ierrn < 0 .OR. chmess == '#' .OR. chmess == '') EXIT rloop3
1111	dlen = dlen + 1
1112	ENDDO rloop3
1113
1114	ALLOCATE( trad1(1:dlen), trad2(1:dlen), ttoint1(1:dlen), ttoint2(1:dlen))
1115
1116	DO jj = 1,dlen+1
1117	BACKSPACE ( 201, IOSTAT=ierrn )
1118	ENDDO
1119
1120	DO jj = 1,dlen
1121	READ ( 201, * ) trad1(jj), trad2(jj), ttoint1(jj), ttoint2(jj)
1122	ENDDO
1123
1124	!
1125	!-- Read layout table:
1126
1127	dlen = 0
1128
1129	READ ( 201, '(3/)')
1130
1131	rloop1: DO
1132	READ ( 201, *, IOSTAT=ierrn ) chmess
1133	IF ( ierrn < 0 .OR. chmess == '#' .OR. chmess == '') EXIT rloop1
1134	dlen = dlen + 1
1135	ENDDO rloop1
1136
1137	ALLOCATE( lrd(1:dlen), ard(1:dlen), crd(1:dlen) )
1138	DO jj = 1, dlen+1
1139	BACKSPACE ( 201, IOSTAT=ierrn )
1140	ENDDO
1141	DO jj = 1, dlen
1142	READ ( 201, * ) lrd(jj), ard(jj), crd(jj)
1143	ENDDO
1144
1145	!
1146	!-- Read tables (turb_cl(alpha),turb_cd(alpha) for the different profiles:
1147
1148	dlen = 0
1149
1150	READ ( 201, '(3/)' )
1151
1152	rloop2: DO
1153	READ ( 201, *, IOSTAT=ierrn ) chmess
1154	IF ( ierrn < 0 .OR. chmess == '#' .OR. chmess == '') EXIT rloop2
1155	dlen = dlen + 1
1156	ENDDO rloop2
1157
1158	ALLOCATE( alpha_attack_tab(1:dlen), turb_cl_table(1:dlen,1:nairfoils), &
1159	turb_cd_table(1:dlen,1:nairfoils) )
1160
1161	DO jj = 1,dlen+1
1162	BACKSPACE ( 201, IOSTAT=ierrn )
1163	ENDDO
1164
1165	DO jj = 1,dlen
1166	READ ( 201, * ) read_cl_cd
1167	alpha_attack_tab(jj) = read_cl_cd(1)
1168	DO ii= 1, nairfoils
1169	turb_cl_table(jj,ii) = read_cl_cd(ii*2)
1170	turb_cd_table(jj,ii) = read_cl_cd(ii*2+1)
1171	ENDDO
1172
1173	ENDDO
1174
1175	dlenbl = dlen
1176
1177	CLOSE ( 201 )
1178
1179	!
1180	!-- For each possible radial position (resolution: 0.1 m --> 630 values) and
1181	!-- each possible angle of attack (resolution: 0.01 degrees --> 36000 values!)
1182	!-- determine the lift and drag coefficient by interpolating between the
1183	!-- tabulated values of each table (interpolate to current angle of attack)
1184	!-- and between the tables (interpolate to current radial position):
1185
1186	ALLOCATE( turb_cl_sel1(0:dlenbl) )
1187	ALLOCATE( turb_cl_sel2(0:dlenbl) )
1188	ALLOCATE( turb_cd_sel1(0:dlenbl) )
1189	ALLOCATE( turb_cd_sel2(0:dlenbl) )
1190
1191	radres = INT( rr(1) * 10.0_wp ) + 1_iwp
1192	dlenbl_int = INT( 360.0_wp / accu_cl_cd_tab ) + 1_iwp
1193
1194
1195	ALLOCATE( turb_cl_tab(0:dlenbl_int,1:radres) )
1196	ALLOCATE( turb_cd_tab(0:dlenbl_int,1:radres) )
1197
1198
1199	DO iir = 1, radres ! loop over radius
1200
1201	DO iialpha = 1, dlenbl_int ! loop over angles
1202
1203	cur_r = ( iir - 1_iwp ) * 0.1_wp
1204	alpha_attack_i = -180.0_wp + REAL( iialpha-1 ) * accu_cl_cd_tab
1205	ialpha = 1
1206
1207	DO WHILE ( ( alpha_attack_i > alpha_attack_tab(ialpha) ) .AND. (ialpha <= dlen ) )
1208	ialpha = ialpha + 1
1209	ENDDO
1210	!
1211	!-- Find position in table
1212	lct = MINLOC( ABS( trad1 - cur_r ) )
1213	! lct(1) = lct(1)
1214
1215	IF ( ( trad1(lct(1)) - cur_r ) .GT. 0.0 ) THEN
1216	lct(1) = lct(1) - 1
1217	ENDIF
1218
1219	trow = lct(1)
1220	!
1221	!-- Calculate weights for interpolation
1222	weight_a = ( trad2(trow) - cur_r ) / ( trad2(trow) - trad1(trow) )
1223	weight_b = ( cur_r - trad1(trow) ) / ( trad2(trow) - trad1(trow) )
1224	t1 = ttoint1(trow)
1225	t2 = ttoint2(trow)
1226
1227	IF ( t1 .EQ. t2 ) THEN ! if both are the same, the weights are NaN
1228	weight_a = 0.5_wp ! then do interpolate in between same twice
1229	weight_b = 0.5_wp ! using 0.5 as weight
1230	ENDIF
1231
1232	IF ( t1 == 0 .AND. t2 == 0 ) THEN
1233	turb_cd_sel1 = 0.0_wp
1234	turb_cd_sel2 = 0.0_wp
1235	turb_cl_sel1 = 0.0_wp
1236	turb_cl_sel2 = 0.0_wp
1237	ELSE
1238	turb_cd_sel1 = turb_cd_table(:,t1)
1239	turb_cd_sel2 = turb_cd_table(:,t2)
1240	turb_cl_sel1 = turb_cl_table(:,t1)
1241	turb_cl_sel2 = turb_cl_table(:,t2)
1242	ENDIF
1243
1244	!
1245	!-- Interpolation of lift and drag coefficiencts on fine grid of radius
1246	!-- segments and angles of attack
1247
1248	turb_cl_tab(iialpha,iir) = ( alpha_attack_tab(ialpha) - &
1249	alpha_attack_i ) / &
1250	( alpha_attack_tab(ialpha) - &
1251	alpha_attack_tab(ialpha-1) ) * &
1252	( weight_a * turb_cl_sel1(ialpha-1) + &
1253	weight_b * turb_cl_sel2(ialpha-1) ) +&
1254	( alpha_attack_i - &
1255	alpha_attack_tab(ialpha-1) ) / &
1256	( alpha_attack_tab(ialpha) - &
1257	alpha_attack_tab(ialpha-1) ) * &
1258	( weight_a * turb_cl_sel1(ialpha) + &
1259	weight_b * turb_cl_sel2(ialpha) )
1260	turb_cd_tab(iialpha,iir) = ( alpha_attack_tab(ialpha) - &
1261	alpha_attack_i ) / &
1262	( alpha_attack_tab(ialpha) - &
1263	alpha_attack_tab(ialpha-1) ) * &
1264	( weight_a * turb_cd_sel1(ialpha-1) + &
1265	weight_b * turb_cd_sel2(ialpha-1) ) +&
1266	( alpha_attack_i - &
1267	alpha_attack_tab(ialpha-1) ) / &
1268	( alpha_attack_tab(ialpha) - &
1269	alpha_attack_tab(ialpha-1) ) * &
1270	( weight_a * turb_cd_sel1(ialpha) + &
1271	weight_b * turb_cd_sel2(ialpha) )
1272
1273	ENDDO ! end loop over angles of attack
1274
1275	ENDDO ! end loop over radius
1276
1277	END SUBROUTINE wtm_read_blade_tables
1278
1279
1280	!------------------------------------------------------------------------------!
1281	! Description:
1282	! ------------
1283	!> The projection matrix for the coordinate system of therotor disc in respect
1284	!> to the yaw and tilt angle of the rotor is calculated
1285	!------------------------------------------------------------------------------!
1286	SUBROUTINE wtm_rotate_rotor( inot )
1287
1288
1289	IMPLICIT NONE
1290
1291	INTEGER(iwp) :: inot
1292	!
1293	!-- Calculation of the rotation matrix for the application of the tilt to
1294	!-- the rotors
1295	rot_eigen_rad(1) = SIN( phi_yaw(inot) ) ! x-component of the radial eigenvector
1296	rot_eigen_rad(2) = COS( phi_yaw(inot) ) ! y-component of the radial eigenvector
1297	rot_eigen_rad(3) = 0.0_wp ! z-component of the radial eigenvector
1298
1299	rot_eigen_azi(1) = 0.0_wp ! x-component of the azimuth eigenvector
1300	rot_eigen_azi(2) = 0.0_wp ! y-component of the azimuth eigenvector
1301	rot_eigen_azi(3) = 1.0_wp ! z-component of the azimuth eigenvector
1302
1303	rot_eigen_nor(1) = COS( phi_yaw(inot) ) ! x-component of the normal eigenvector
1304	rot_eigen_nor(2) = -SIN( phi_yaw(inot) ) ! y-component of the normal eigenvector
1305	rot_eigen_nor(3) = 0.0_wp ! z-component of the normal eigenvector
1306
1307	!
1308	!-- Calculation of the coordinate transformation matrix to apply a tilt to
1309	!-- the rotor. If tilt = 0, rot_coord_trans is a unit matrix.
1310
1311	rot_coord_trans(inot,1,1) = rot_eigen_rad(1)*2 &
1312	( 1.0_wp - COS( tilt ) ) + COS( tilt )
1313	rot_coord_trans(inot,1,2) = rot_eigen_rad(1) * rot_eigen_rad(2) * &
1314	( 1.0_wp - COS( tilt ) ) - &
1315	rot_eigen_rad(3) * SIN( tilt )
1316	rot_coord_trans(inot,1,3) = rot_eigen_rad(1) * rot_eigen_rad(3) * &
1317	( 1.0_wp - COS( tilt ) ) + &
1318	rot_eigen_rad(2) * SIN( tilt )
1319	rot_coord_trans(inot,2,1) = rot_eigen_rad(2) * rot_eigen_rad(1) * &
1320	( 1.0_wp - COS( tilt ) ) + &
1321	rot_eigen_rad(3) * SIN( tilt )
1322	rot_coord_trans(inot,2,2) = rot_eigen_rad(2)*2 &
1323	( 1.0_wp - COS( tilt ) ) + COS( tilt )
1324	rot_coord_trans(inot,2,3) = rot_eigen_rad(2) * rot_eigen_rad(3) * &
1325	( 1.0_wp - COS( tilt ) ) - &
1326	rot_eigen_rad(1) * SIN( tilt )
1327	rot_coord_trans(inot,3,1) = rot_eigen_rad(3) * rot_eigen_rad(1) * &
1328	( 1.0_wp - COS( tilt ) ) - &
1329	rot_eigen_rad(2) * SIN( tilt )
1330	rot_coord_trans(inot,3,2) = rot_eigen_rad(3) * rot_eigen_rad(2) * &
1331	( 1.0_wp - COS( tilt ) ) + &
1332	rot_eigen_rad(1) * SIN( tilt )
1333	rot_coord_trans(inot,3,3) = rot_eigen_rad(3)*2 &
1334	( 1.0_wp - COS( tilt ) ) + COS( tilt )
1335
1336	!
1337	!-- Vectors for the Transformation of forces from the rotor's spheric
1338	!-- coordinate system to the cartesian coordinate system
1339	rotx(inot,:) = MATMUL( rot_coord_trans(inot,:,:), rot_eigen_nor )
1340	roty(inot,:) = MATMUL( rot_coord_trans(inot,:,:), rot_eigen_rad )
1341	rotz(inot,:) = MATMUL( rot_coord_trans(inot,:,:), rot_eigen_azi )
1342
1343	END SUBROUTINE wtm_rotate_rotor
1344
1345
1346	!------------------------------------------------------------------------------!
1347	! Description:
1348	! ------------
1349	!> Calculation of the forces generated by the wind turbine
1350	!------------------------------------------------------------------------------!
1351	SUBROUTINE wtm_forces
1352
1353
1354	IMPLICIT NONE
1355
1356	CHARACTER (LEN=2) :: turbine_id
1357
1358	INTEGER(iwp) :: i, j, k !< loop indices
1359	INTEGER(iwp) :: inot !< turbine loop index (turbine id)
1360	INTEGER(iwp) :: iialpha, iir !<
1361	INTEGER(iwp) :: rseg, rseg_int !<
1362	INTEGER(iwp) :: ring, ring_int !<
1363	INTEGER(iwp) :: ii, jj, kk !<
1364
1365	REAL(wp) :: flag !< flag to mask topography grid points
1366	REAL(wp) :: sin_rot, cos_rot !<
1367	REAL(wp) :: sin_yaw, cos_yaw !<
1368
1369	REAL(wp) :: aa, bb, cc, dd !< interpolation distances
1370	REAL(wp) :: gg !< interpolation volume var
1371
1372	REAL(wp) :: dist_u_3d, dist_v_3d, dist_w_3d !< smearing distances
1373
1374
1375	!
1376	! Variables for pitch control
1377	REAL(wp) :: torque_max=0.0_wp
1378	LOGICAL :: pitch_sw=.FALSE.
1379
1380	INTEGER(iwp), DIMENSION(1) :: lct=0
1381	REAL(wp), DIMENSION(1) :: rad_d=0.0_wp
1382
1383	REAL(wp) :: tl_factor !< factor for tip loss correction
1384
1385
1386	CALL cpu_log( log_point_s(61), 'wtm_forces', 'start' )
1387
1388
1389	IF ( simulated_time >= time_turbine_on ) THEN
1390
1391	!
1392	!-- Set forces to zero for each new time step:
1393	thrust(:,:,:) = 0.0_wp
1394	torque_y(:,:,:) = 0.0_wp
1395	torque_z(:,:,:) = 0.0_wp
1396	torque_total(:) = 0.0_wp
1397	rot_tend_x(:,:,:) = 0.0_wp
1398	rot_tend_y(:,:,:) = 0.0_wp
1399	rot_tend_z(:,:,:) = 0.0_wp
1400	thrust_rotor(:) = 0.0_wp
1401	!
1402	!-- Loop over number of turbines:
1403	DO inot = 1, nturbines
1404
1405	cos_yaw = COS(phi_yaw(inot))
1406	sin_yaw = SIN(phi_yaw(inot))
1407	!
1408	!-- Loop over rings of each turbine:
1409	DO ring = 1, nrings(inot)
1410
1411	thrust_seg(:) = 0.0_wp
1412	torque_seg_y(:) = 0.0_wp
1413	torque_seg_z(:) = 0.0_wp
1414	!
1415	!-- Determine distance between each ring (center) and the hub:
1416	cur_r = (ring - 0.5_wp) * delta_r(inot)
1417
1418	!
1419	!-- Loop over segments of each ring of each turbine:
1420	DO rseg = 1, nsegs(ring,inot)
1421	!
1422	!-- !-----------------------------------------------------------!
1423	!-- !-- Determine coordinates of the ring segments --!
1424	!-- !-----------------------------------------------------------!
1425	!
1426	!-- Determine angle of ring segment towards zero degree angle of
1427	!-- rotor system (at zero degree rotor direction vectors aligned
1428	!-- with y-axis):
1429	phi_rotor = rseg * 2.0_wp * pi / nsegs(ring,inot)
1430	cos_rot = COS( phi_rotor )
1431	sin_rot = SIN( phi_rotor )
1432
1433	!-- Now the direction vectors can be determined with respect to
1434	!-- the yaw and tilt angle:
1435	re(1) = cos_rot * sin_yaw
1436	re(2) = cos_rot * cos_yaw
1437	re(3) = sin_rot
1438
1439	rote = MATMUL( rot_coord_trans(inot,:,:), re )
1440	!
1441	!-- Coordinates of the single segments (center points):
1442	rbx(ring,rseg) = rcx(inot) + cur_r * rote(1)
1443	rby(ring,rseg) = rcy(inot) + cur_r * rote(2)
1444	rbz(ring,rseg) = rcz(inot) + cur_r * rote(3)
1445
1446	!-- !-----------------------------------------------------------!
1447	!-- !-- Interpolation of the velocity components from the --!
1448	!-- !-- cartesian grid point to the coordinates of each ring --!
1449	!-- !-- segment (follows a method used in the particle model) --!
1450	!-- !-----------------------------------------------------------!
1451
1452	u_int(inot,ring,rseg) = 0.0_wp
1453	u_int_1_l(inot,ring,rseg) = 0.0_wp
1454
1455	v_int(inot,ring,rseg) = 0.0_wp
1456	v_int_1_l(inot,ring,rseg) = 0.0_wp
1457
1458	w_int(inot,ring,rseg) = 0.0_wp
1459	w_int_1_l(inot,ring,rseg) = 0.0_wp
1460
1461	!
1462	!-- Interpolation of the u-component:
1463
1464	ii = rbx(ring,rseg) * ddx
1465	jj = ( rby(ring,rseg) - 0.5_wp * dy ) * ddy
1466	kk = ( rbz(ring,rseg) - 0.5_wp * dz ) / dz
1467	!
1468	!-- Interpolate only if all required information is available on
1469	!-- the current PE:
1470	IF ( ( ii >= nxl ) .AND. ( ii <= nxr ) ) THEN
1471	IF ( ( jj >= nys ) .AND. ( jj <= nyn ) ) THEN
1472
1473	aa = ( ( ii + 1 ) * dx - rbx(ring,rseg) ) * &
1474	( ( jj + 1 + 0.5_wp ) * dy - rby(ring,rseg) )
1475	bb = ( rbx(ring,rseg) - ii * dx ) * &
1476	( ( jj + 1 + 0.5_wp ) * dy - rby(ring,rseg) )
1477	cc = ( ( ii+1 ) * dx - rbx(ring,rseg) ) * &
1478	( rby(ring,rseg) - ( jj + 0.5_wp ) * dy )
1479	dd = ( rbx(ring,rseg) - ii * dx ) * &
1480	( rby(ring,rseg) - ( jj + 0.5_wp ) * dy )
1481	gg = dx * dy
1482
1483	u_int_l = ( aa * u(kk,jj,ii) + &
1484	bb * u(kk,jj,ii+1) + &
1485	cc * u(kk,jj+1,ii) + &
1486	dd * u(kk,jj+1,ii+1) &
1487	) / gg
1488
1489	u_int_u = ( aa * u(kk+1,jj,ii) + &
1490	bb * u(kk+1,jj,ii+1) + &
1491	cc * u(kk+1,jj+1,ii) + &
1492	dd * u(kk+1,jj+1,ii+1) &
1493	) / gg
1494
1495	u_int_1_l(inot,ring,rseg) = u_int_l + &
1496	( rbz(ring,rseg) - zu(kk) ) / dz * &
1497	( u_int_u - u_int_l )
1498
1499	ELSE
1500	u_int_1_l(inot,ring,rseg) = 0.0_wp
1501	ENDIF
1502	ELSE
1503	u_int_1_l(inot,ring,rseg) = 0.0_wp
1504	ENDIF
1505
1506
1507	!
1508	!-- Interpolation of the v-component:
1509	ii = ( rbx(ring,rseg) - 0.5_wp * dx ) * ddx
1510	jj = rby(ring,rseg) * ddy
1511	kk = ( rbz(ring,rseg) + 0.5_wp * dz ) / dz
1512	!
1513	!-- Interpolate only if all required information is available on
1514	!-- the current PE:
1515	IF ( ( ii >= nxl ) .AND. ( ii <= nxr ) ) THEN
1516	IF ( ( jj >= nys ) .AND. ( jj <= nyn ) ) THEN
1517
1518	aa = ( ( ii + 1 + 0.5_wp ) * dx - rbx(ring,rseg) ) * &
1519	( ( jj + 1 ) * dy - rby(ring,rseg) )
1520	bb = ( rbx(ring,rseg) - ( ii + 0.5_wp ) * dx ) * &
1521	( ( jj + 1 ) * dy - rby(ring,rseg) )
1522	cc = ( ( ii + 1 + 0.5_wp ) * dx - rbx(ring,rseg) ) * &
1523	( rby(ring,rseg) - jj * dy )
1524	dd = ( rbx(ring,rseg) - ( ii + 0.5_wp ) * dx ) * &
1525	( rby(ring,rseg) - jj * dy )
1526	gg = dx * dy
1527
1528	v_int_l = ( aa * v(kk,jj,ii) + &
1529	bb * v(kk,jj,ii+1) + &
1530	cc * v(kk,jj+1,ii) + &
1531	dd * v(kk,jj+1,ii+1) &
1532	) / gg
1533
1534	v_int_u = ( aa * v(kk+1,jj,ii) + &
1535	bb * v(kk+1,jj,ii+1) + &
1536	cc * v(kk+1,jj+1,ii) + &
1537	dd * v(kk+1,jj+1,ii+1) &
1538	) / gg
1539
1540	v_int_1_l(inot,ring,rseg) = v_int_l + &
1541	( rbz(ring,rseg) - zu(kk) ) / dz * &
1542	( v_int_u - v_int_l )
1543
1544	ELSE
1545	v_int_1_l(inot,ring,rseg) = 0.0_wp
1546	ENDIF
1547	ELSE
1548	v_int_1_l(inot,ring,rseg) = 0.0_wp
1549	ENDIF
1550
1551
1552	!
1553	!-- Interpolation of the w-component:
1554	ii = ( rbx(ring,rseg) - 0.5_wp * dx ) * ddx
1555	jj = ( rby(ring,rseg) - 0.5_wp * dy ) * ddy
1556	kk = rbz(ring,rseg) / dz
1557	!
1558	!-- Interpolate only if all required information is available on
1559	!-- the current PE:
1560	IF ( ( ii >= nxl ) .AND. ( ii <= nxr ) ) THEN
1561	IF ( ( jj >= nys ) .AND. ( jj <= nyn ) ) THEN
1562
1563	aa = ( ( ii + 1 + 0.5_wp ) * dx - rbx(ring,rseg) ) * &
1564	( ( jj + 1 + 0.5_wp ) * dy - rby(ring,rseg) )
1565	bb = ( rbx(ring,rseg) - ( ii + 0.5_wp ) * dx ) * &
1566	( ( jj + 1 + 0.5_wp ) * dy - rby(ring,rseg) )
1567	cc = ( ( ii + 1 + 0.5_wp ) * dx - rbx(ring,rseg) ) * &
1568	( rby(ring,rseg) - ( jj + 0.5_wp ) * dy )
1569	dd = ( rbx(ring,rseg) - ( ii + 0.5_wp ) * dx ) * &
1570	( rby(ring,rseg) - ( jj + 0.5_wp ) * dy )
1571	gg = dx * dy
1572
1573	w_int_l = ( aa * w(kk,jj,ii) + &
1574	bb * w(kk,jj,ii+1) + &
1575	cc * w(kk,jj+1,ii) + &
1576	dd * w(kk,jj+1,ii+1) &
1577	) / gg
1578
1579	w_int_u = ( aa * w(kk+1,jj,ii) + &
1580	bb * w(kk+1,jj,ii+1) + &
1581	cc * w(kk+1,jj+1,ii) + &
1582	dd * w(kk+1,jj+1,ii+1) &
1583	) / gg
1584
1585	w_int_1_l(inot,ring,rseg) = w_int_l + &
1586	( rbz(ring,rseg) - zw(kk) ) / dz * &
1587	( w_int_u - w_int_l )
1588	ELSE
1589	w_int_1_l(inot,ring,rseg) = 0.0_wp
1590	ENDIF
1591	ELSE
1592	w_int_1_l(inot,ring,rseg) = 0.0_wp
1593	ENDIF
1594
1595	ENDDO
1596	ENDDO
1597
1598	ENDDO
1599
1600	!
1601	!-- Exchange between PEs (information required on each PE):
1602	#if defined( __parallel )
1603	CALL MPI_ALLREDUCE( u_int_1_l, u_int, nturbines * MAXVAL(nrings) * &
1604	MAXVAL(nsegs), MPI_REAL, MPI_SUM, comm2d, ierr )
1605	CALL MPI_ALLREDUCE( v_int_1_l, v_int, nturbines * MAXVAL(nrings) * &
1606	MAXVAL(nsegs), MPI_REAL, MPI_SUM, comm2d, ierr )
1607	CALL MPI_ALLREDUCE( w_int_1_l, w_int, nturbines * MAXVAL(nrings) * &
1608	MAXVAL(nsegs), MPI_REAL, MPI_SUM, comm2d, ierr )
1609	#else
1610	u_int = u_int_1_l
1611	v_int = v_int_1_l
1612	w_int = w_int_1_l
1613	#endif
1614
1615
1616	!
1617	!-- Loop over number of turbines:
1618
1619	DO inot = 1, nturbines
1620	pit_loop: DO
1621
1622	IF ( pitch_sw ) THEN
1623	torque_total(inot) = 0.0_wp
1624	thrust_rotor(inot) = 0.0_wp
1625	pitch_add(inot) = pitch_add(inot) + 0.25_wp
1626	! IF ( myid == 0 ) PRINT*, 'Pitch', inot, pitch_add(inot)
1627	ELSE
1628	cos_yaw = COS(phi_yaw(inot))
1629	sin_yaw = SIN(phi_yaw(inot))
1630	IF ( pitch_control ) THEN
1631	pitch_add(inot) = MAX(pitch_add_old(inot) - pitch_rate * &
1632	dt_3d , 0.0_wp )
1633	ENDIF
1634	ENDIF
1635
1636	!
1637	!-- Loop over rings of each turbine:
1638	DO ring = 1, nrings(inot)
1639	!
1640	!-- Determine distance between each ring (center) and the hub:
1641	cur_r = (ring - 0.5_wp) * delta_r(inot)
1642	!
1643	!-- Loop over segments of each ring of each turbine:
1644	DO rseg = 1, nsegs(ring,inot)
1645	!
1646	!-- Determine angle of ring segment towards zero degree angle of
1647	!-- rotor system (at zero degree rotor direction vectors aligned
1648	!-- with y-axis):
1649	phi_rotor = rseg * 2.0_wp * pi / nsegs(ring,inot)
1650	cos_rot = COS(phi_rotor)
1651	sin_rot = SIN(phi_rotor)
1652	!
1653	!-- Now the direction vectors can be determined with respect to
1654	!-- the yaw and tilt angle:
1655	re(1) = cos_rot * sin_yaw
1656	re(2) = cos_rot * cos_yaw
1657	re(3) = sin_rot
1658
1659	! The current unit vector in azimuthal direction:
1660	rea(1) = - sin_rot * sin_yaw
1661	rea(2) = - sin_rot * cos_yaw
1662	rea(3) = cos_rot
1663
1664	!
1665	!-- To respect the yawing angle for the calculations of
1666	!-- velocities and forces the unit vectors perpendicular to the
1667	!-- rotor area in direction of the positive yaw angle are defined:
1668	ren(1) = cos_yaw
1669	ren(2) = - sin_yaw
1670	ren(3) = 0.0_wp
1671	!
1672	!-- Multiplication with the coordinate transformation matrix
1673	!-- gives the final unit vector with consideration of the rotor
1674	!-- tilt:
1675	rote = MATMUL( rot_coord_trans(inot,:,:), re )
1676	rota = MATMUL( rot_coord_trans(inot,:,:), rea )
1677	rotn = MATMUL( rot_coord_trans(inot,:,:), ren )
1678	!
1679	!-- Coordinates of the single segments (center points):
1680	rbx(ring,rseg) = rcx(inot) + cur_r * rote(1)
1681
1682	rby(ring,rseg) = rcy(inot) + cur_r * rote(2)
1683
1684	rbz(ring,rseg) = rcz(inot) + cur_r * rote(3)
1685
1686	!
1687	!-- !-----------------------------------------------------------!
1688	!-- !-- Calculation of various angles and relative velocities --!
1689	!-- !-----------------------------------------------------------!
1690	!
1691	!-- In the following the 3D-velocity field is projected its
1692	!-- components perpedicular and parallel to the rotor area
1693	!-- The calculation of forces will be done in the rotor-
1694	!-- coordinates y' and z.
1695	!-- The yaw angle will be reintroduced when the force is applied
1696	!-- on the hydrodynamic equations
1697	!
1698	!-- Projection of the xy-velocities relative to the rotor area
1699	!
1700	!-- Velocity perpendicular to the rotor area:
1701	u_rot = u_int(inot,ring,rseg)*rotn(1) + &
1702	v_int(inot,ring,rseg)*rotn(2) + &
1703	w_int(inot,ring,rseg)*rotn(3)
1704	!
1705	!-- Projection of the 3D-velocity vector in the azimuthal
1706	!-- direction:
1707	vtheta(rseg) = rota(1) * u_int(inot,ring,rseg) + &
1708	rota(2) * v_int(inot,ring,rseg) + &
1709	rota(3) * w_int(inot,ring,rseg)
1710	!
1711	!-- Determination of the angle phi_rel between the rotor plane
1712	!-- and the direction of the flow relative to the rotor:
1713
1714	phi_rel(rseg) = ATAN( u_rot / &
1715	( omega_rot(inot) * cur_r - &
1716	vtheta(rseg) ) )
1717
1718	!
1719	!-- Interpolation of the local pitch angle from tabulated values
1720	!-- to the current radial position:
1721
1722	lct=minloc(ABS(cur_r-lrd))
1723	rad_d=cur_r-lrd(lct)
1724
1725	IF (cur_r == 0.0_wp) THEN
1726	alpha_attack(rseg) = 0.0_wp
1727	ELSE IF (cur_r >= lrd(size(ard))) THEN
1728	alpha_attack(rseg) = ( ard(size(ard)) + &
1729	ard(size(ard)-1) ) / 2.0_wp
1730	ELSE
1731	alpha_attack(rseg) = ( ard(lct(1)) * &
1732	( ( lrd(lct(1)+1) - cur_r ) / &
1733	( lrd(lct(1)+1) - lrd(lct(1)) ) &
1734	) ) + ( ard(lct(1)+1) * &
1735	( ( cur_r - lrd(lct(1)) ) / &
1736	( lrd(lct(1)+1) - lrd(lct(1)) ) ) )
1737	ENDIF
1738
1739	!
1740	!-- In Fortran radian instead of degree is used as unit for all
1741	!-- angles. Therefore, a transformation from angles given in
1742	!-- degree to angles given in radian is necessary here:
1743	alpha_attack(rseg) = alpha_attack(rseg) * &
1744	( (2.0_wp*pi) / 360.0_wp )
1745	!
1746	!-- Substraction of the local pitch angle to obtain the local
1747	!-- angle of attack:
1748	alpha_attack(rseg) = phi_rel(rseg) - alpha_attack(rseg)
1749	!
1750	!-- Preliminary transformation back from angles given in radian
1751	!-- to angles given in degree:
1752	alpha_attack(rseg) = alpha_attack(rseg) * &
1753	( 360.0_wp / (2.0_wp*pi) )
1754	!
1755	!-- Correct with collective pitch angle:
1756	alpha_attack = alpha_attack - pitch_add(inot)
1757
1758	!
1759	!-- Determination of the magnitude of the flow velocity relative
1760	!-- to the rotor:
1761	vrel(rseg) = SQRT( u_rot**2 + &
1762	( omega_rot(inot) * cur_r - &
1763	vtheta(rseg) )**2 )
1764
1765	!
1766	!-- !-----------------------------------------------------------!
1767	!-- !-- Interpolation of chord as well as lift and drag --!
1768	!-- !-- coefficients from tabulated values --!
1769	!-- !-----------------------------------------------------------!
1770
1771	!
1772	!-- Interpolation of the chord_length from tabulated values to
1773	!-- the current radial position:
1774
1775	IF (cur_r == 0.0_wp) THEN
1776	chord(rseg) = 0.0_wp
1777	ELSE IF (cur_r >= lrd(size(crd))) THEN
1778	chord(rseg) = (crd(size(crd)) + ard(size(crd)-1)) / 2.0_wp
1779	ELSE
1780	chord(rseg) = ( crd(lct(1)) * &
1781	( ( lrd(lct(1)+1) - cur_r ) / &
1782	( lrd(lct(1)+1) - lrd(lct(1)) ) ) ) + &
1783	( crd(lct(1)+1) * &
1784	( ( cur_r-lrd(lct(1)) ) / &
1785	( lrd(lct(1)+1) - lrd(lct(1)) ) ) )
1786	ENDIF
1787
1788	!
1789	!-- Determine index of current angle of attack, needed for
1790	!-- finding the appropriate interpolated values of the lift and
1791	!-- drag coefficients (-180.0 degrees = 0, +180.0 degrees = 36000,
1792	!-- so one index every 0.01 degrees):
1793	iialpha = CEILING( ( alpha_attack(rseg) + 180.0_wp ) &
1794	* ( 1.0_wp / accu_cl_cd_tab ) )
1795	!
1796	!-- Determine index of current radial position, needed for
1797	!-- finding the appropriate interpolated values of the lift and
1798	!-- drag coefficients (one index every 0.1 m):
1799	iir = CEILING( cur_r * 10.0_wp )
1800	!
1801	!-- Read in interpolated values of the lift and drag coefficients
1802	!-- for the current radial position and angle of attack:
1803	turb_cl(rseg) = turb_cl_tab(iialpha,iir)
1804	turb_cd(rseg) = turb_cd_tab(iialpha,iir)
1805
1806	!
1807	!-- Final transformation back from angles given in degree to
1808	!-- angles given in radian:
1809	alpha_attack(rseg) = alpha_attack(rseg) * &
1810	( (2.0_wp*pi) / 360.0_wp )
1811
1812	IF ( tl_cor ) THEN
1813
1814	!-- Tip loss correction following Schito
1815	!-- Schito applies the tip loss correction only to the lift force
1816	!-- Therefore, the tip loss correction is only applied to the lift
1817	!-- coefficient and not to the drag coefficient in our case
1818	!--
1819	tl_factor = ( 2.0 / pi ) * &
1820	ACOS( EXP( -1.0 * ( 3.0 * ( rr(inot) - cur_r ) / &
1821	( 2.0 * cur_r * abs( sin( phi_rel(rseg) ) ) ) ) ) )
1822
1823	turb_cl(rseg) = tl_factor * turb_cl(rseg)
1824
1825	END IF
1826	!
1827	!-- !-----------------------------------------------------!
1828	!-- !-- Calculation of the forces --!
1829	!-- !-----------------------------------------------------!
1830
1831	!
1832	!-- Calculate the pre_factor for the thrust and torque forces:
1833
1834	pre_factor = 0.5_wp * (vrel(rseg)*2) 3.0_wp * &
1835	chord(rseg) * delta_r(inot) / nsegs(ring,inot)
1836
1837	!
1838	!-- Calculate the thrust force (x-component of the total force)
1839	!-- for each ring segment:
1840	thrust_seg(rseg) = pre_factor * &
1841	( turb_cl(rseg) * COS(phi_rel(rseg)) + &
1842	turb_cd(rseg) * SIN(phi_rel(rseg)) )
1843
1844	!
1845	!-- Determination of the second of the additional forces acting
1846	!-- on the flow in the azimuthal direction: force vector as basis
1847	!-- for torque (torque itself would be the vector product of the
1848	!-- radius vector and the force vector):
1849	torque_seg = pre_factor * &
1850	( turb_cl(rseg) * SIN(phi_rel(rseg)) - &
1851	turb_cd(rseg) * COS(phi_rel(rseg)) )
1852	!
1853	!-- Decomposition of the force vector into two parts:
1854	!-- One acting along the y-direction and one acting along the
1855	!-- z-direction of the rotor coordinate system:
1856
1857	torque_seg_y(rseg) = -torque_seg * sin_rot
1858	torque_seg_z(rseg) = torque_seg * cos_rot
1859
1860	!
1861	!-- Add the segment thrust to the thrust of the whole rotor
1862	thrust_rotor(inot) = thrust_rotor(inot) + &
1863	thrust_seg(rseg)
1864
1865
1866	torque_total(inot) = torque_total(inot) + (torque_seg * cur_r)
1867
1868	ENDDO !-- end of loop over ring segments
1869
1870	!
1871	!-- Restore the forces into arrays containing all the segments of
1872	!-- each ring:
1873	thrust_ring(ring,:) = thrust_seg(:)
1874	torque_ring_y(ring,:) = torque_seg_y(:)
1875	torque_ring_z(ring,:) = torque_seg_z(:)
1876
1877
1878	ENDDO !-- end of loop over rings
1879
1880
1881	CALL cpu_log( log_point_s(62), 'wtm_controller', 'start' )
1882
1883
1884	IF ( speed_control ) THEN
1885	!
1886	!-- Calculation of the current generator speed for rotor speed control
1887
1888	!
1889	!-- The acceleration of the rotor speed is calculated from
1890	!-- the force balance of the accelerating torque
1891	!-- and the torque of the rotating rotor and generator
1892	om_rate = ( torque_total(inot) * air_dens * gear_eff - &
1893	gear_ratio * torque_gen_old(inot) ) / &
1894	( inertia_rot + &
1895	gear_ratio * gear_ratio * inertia_gen ) * dt_3d
1896
1897	!
1898	!-- The generator speed is given by the product of gear gear_ratio
1899	!-- and rotor speed
1900	omega_gen(inot) = gear_ratio * ( omega_rot(inot) + om_rate )
1901
1902	ENDIF
1903
1904	IF ( pitch_control ) THEN
1905
1906	!
1907	!-- If the current generator speed is above rated, the pitch is not
1908	!-- saturated and the change from the last time step is within the
1909	!-- maximum pitch rate, then the pitch loop is repeated with a pitch
1910	!-- gain
1911	IF ( ( omega_gen(inot) > rated_genspeed ) .AND. &
1912	( pitch_add(inot) < 25.0_wp ) .AND. &
1913	( pitch_add(inot) < pitch_add_old(inot) + &
1914	pitch_rate * dt_3d ) ) THEN
1915	pitch_sw = .TRUE.
1916	!
1917	!-- Go back to beginning of pit_loop
1918	CYCLE pit_loop
1919	ENDIF
1920
1921	!
1922	!-- The current pitch is saved for the next time step
1923	pitch_add_old(inot) = pitch_add(inot)
1924	pitch_sw = .FALSE.
1925	ENDIF
1926	EXIT pit_loop
1927	ENDDO pit_loop ! Recursive pitch control loop
1928
1929
1930	!
1931	!-- Call the rotor speed controller
1932
1933	IF ( speed_control ) THEN
1934	!
1935	!-- Find processor at i_hub, j_hub
1936	IF ( ( nxl <= i_hub(inot) ) .AND. ( nxr >= i_hub(inot) ) ) &
1937	THEN
1938	IF ( ( nys <= j_hub(inot) ) .AND. ( nyn >= j_hub(inot) ) )&
1939	THEN
1940	CALL wtm_speed_control( inot )
1941	ENDIF
1942	ENDIF
1943
1944	ENDIF
1945
1946
1947	CALL cpu_log( log_point_s(62), 'wtm_controller', 'stop' )
1948
1949	CALL cpu_log( log_point_s(63), 'wtm_smearing', 'start' )
1950
1951
1952	!-- !-----------------------------------------------------------------!
1953	!-- !-- Regularization kernel --!
1954	!-- !-- Smearing of the forces and interpolation to cartesian grid --!
1955	!-- !-----------------------------------------------------------------!
1956	!
1957	!-- The aerodynamic blade forces need to be distributed smoothly on
1958	!-- several mesh points in order to avoid singular behaviour
1959	!
1960	!-- Summation over sum of weighted forces. The weighting factor
1961	!-- (calculated in user_init) includes information on the distance
1962	!-- between the center of the grid cell and the rotor segment under
1963	!-- consideration
1964	!
1965	!-- To save computing time, apply smearing only for the relevant part
1966	!-- of the model domain:
1967	!
1968	!--
1969	!-- Calculation of the boundaries:
1970	i_smear(inot) = CEILING( ( rr(inot) * ABS( roty(inot,1) ) + &
1971	eps_min ) / dx )
1972	j_smear(inot) = CEILING( ( rr(inot) * ABS( roty(inot,2) ) + &
1973	eps_min ) / dy )
1974
1975	DO i = MAX( nxl, i_hub(inot) - i_smear(inot) ), &
1976	MIN( nxr, i_hub(inot) + i_smear(inot) )
1977	DO j = MAX( nys, j_hub(inot) - j_smear(inot) ), &
1978	MIN( nyn, j_hub(inot) + j_smear(inot) )
1979	! DO k = MAX( nzb_u_inner(j,i)+1, k_hub(inot) - k_smear(inot) ), &
1980	! k_hub(inot) + k_smear(inot)
1981	DO k = nzb+1, k_hub(inot) + k_smear(inot)
1982	DO ring = 1, nrings(inot)
1983	DO rseg = 1, nsegs(ring,inot)
1984	!
1985	!-- Predetermine flag to mask topography
1986	flag = MERGE( 1.0_wp, 0.0_wp, BTEST( wall_flags_0(k,j,i), 1 ) )
1987
1988	!
1989	!-- Determine the square of the distance between the
1990	!-- current grid point and each rotor area segment:
1991	dist_u_3d = ( i * dx - rbx(ring,rseg) )**2 + &
1992	( j * dy + 0.5_wp * dy - rby(ring,rseg) )**2 + &
1993	( k * dz - 0.5_wp * dz - rbz(ring,rseg) )**2
1994	dist_v_3d = ( i * dx + 0.5_wp * dx - rbx(ring,rseg) )**2 + &
1995	( j * dy - rby(ring,rseg) )**2 + &
1996	( k * dz - 0.5_wp * dz - rbz(ring,rseg) )**2
1997	dist_w_3d = ( i * dx + 0.5_wp * dx - rbx(ring,rseg) )**2 + &
1998	( j * dy + 0.5_wp * dy - rby(ring,rseg) )**2 + &
1999	( k * dz - rbz(ring,rseg) )**2
2000
2001	!
2002	!-- 3D-smearing of the forces with a polynomial function
2003	!-- (much faster than the old Gaussian function), using
2004	!-- some parameters that have been calculated in user_init.
2005	!-- The function is only similar to Gaussian function for
2006	!-- squared distances <= eps_min2:
2007	IF ( dist_u_3d <= eps_min2 ) THEN
2008	thrust(k,j,i) = thrust(k,j,i) + &
2009	thrust_ring(ring,rseg) * &
2010	( ( pol_a * dist_u_3d - pol_b ) * &
2011	dist_u_3d + 1.0_wp ) * eps_factor *&
2012	flag
2013	ENDIF
2014	IF ( dist_v_3d <= eps_min2 ) THEN
2015	torque_y(k,j,i) = torque_y(k,j,i) + &
2016	torque_ring_y(ring,rseg) * &
2017	( ( pol_a * dist_v_3d - pol_b ) * &
2018	dist_v_3d + 1.0_wp ) * eps_factor * &
2019	flag
2020	ENDIF
2021	IF ( dist_w_3d <= eps_min2 ) THEN
2022	torque_z(k,j,i) = torque_z(k,j,i) + &
2023	torque_ring_z(ring,rseg) * &
2024	( ( pol_a * dist_w_3d - pol_b ) * &
2025	dist_w_3d + 1.0_wp ) * eps_factor * &
2026	flag
2027	ENDIF
2028
2029	ENDDO ! End of loop over rseg
2030	ENDDO ! End of loop over ring
2031
2032	!
2033	!-- Rotation of force components:
2034	rot_tend_x(k,j,i) = rot_tend_x(k,j,i) + ( &
2035	thrust(k,j,i)*rotx(inot,1) + &
2036	torque_y(k,j,i)*roty(inot,1) + &
2037	torque_z(k,j,i)*rotz(inot,1) &
2038	) * flag
2039
2040	rot_tend_y(k,j,i) = rot_tend_y(k,j,i) + ( &
2041	thrust(k,j,i)*rotx(inot,2) + &
2042	torque_y(k,j,i)*roty(inot,2) + &
2043	torque_z(k,j,i)*rotz(inot,2) &
2044	) * flag
2045
2046	rot_tend_z(k,j,i) = rot_tend_z(k,j,i) + ( &
2047	thrust(k,j,i)*rotx(inot,3) + &
2048	torque_y(k,j,i)*roty(inot,3) + &
2049	torque_z(k,j,i)*rotz(inot,3) &
2050	) * flag
2051
2052	ENDDO ! End of loop over k
2053	ENDDO ! End of loop over j
2054	ENDDO ! End of loop over i
2055
2056	CALL cpu_log( log_point_s(63), 'wtm_smearing', 'stop' )
2057
2058	ENDDO !-- end of loop over turbines
2059
2060
2061	IF ( yaw_control ) THEN
2062	!
2063	!-- Allocate arrays for yaw control at first call
2064	!-- Can't be allocated before dt_3d is set
2065	IF ( start_up ) THEN
2066	WDLON = NINT( 30.0_wp / dt_3d ) ! 30s running mean array
2067	ALLOCATE( wd30(1:nturbines,1:WDLON) )
2068	wd30 = 999.0_wp ! Set to dummy value
2069	ALLOCATE( wd30_l(1:WDLON) )
2070
2071	WDSHO = NINT( 2.0_wp / dt_3d ) ! 2s running mean array
2072	ALLOCATE( wd2(1:nturbines,1:WDSHO) )
2073	wd2 = 999.0_wp ! Set to dummy value
2074	ALLOCATE( wd2_l(1:WDSHO) )
2075	start_up = .FALSE.
2076	ENDIF
2077
2078	!
2079	!-- Calculate the inflow wind speed
2080	!--
2081	!-- Loop over number of turbines:
2082	DO inot = 1, nturbines
2083	!
2084	!-- Find processor at i_hub, j_hub
2085	IF ( ( nxl <= i_hub(inot) ) .AND. ( nxr >= i_hub(inot) ) ) &
2086	THEN
2087	IF ( ( nys <= j_hub(inot) ) .AND. ( nyn >= j_hub(inot) ) )&
2088	THEN
2089
2090	u_inflow_l(inot) = u(k_hub(inot),j_hub(inot),i_hub(inot))
2091
2092	wdir_l(inot) = -1.0_wp * ATAN2( &
2093	0.5_wp * ( v(k_hub(inot),j_hub(inot),i_hub(inot)+1) + &
2094	v(k_hub(inot),j_hub(inot),i_hub(inot)) ) , &
2095	0.5_wp * ( u(k_hub(inot),j_hub(inot)+1,i_hub(inot)) + &
2096	u(k_hub(inot),j_hub(inot),i_hub(inot)) ) )
2097
2098	CALL wtm_yawcontrol( inot )
2099
2100	phi_yaw_l(inot) = phi_yaw(inot)
2101
2102	ENDIF
2103	ENDIF
2104
2105	ENDDO !-- end of loop over turbines
2106
2107	!
2108	!-- Transfer of information to the other cpus
2109	#if defined( __parallel )
2110	CALL MPI_ALLREDUCE( u_inflow_l, u_inflow, nturbines, MPI_REAL, &
2111	MPI_SUM, comm2d, ierr )
2112	CALL MPI_ALLREDUCE( wdir_l, wdir, nturbines, MPI_REAL, MPI_SUM, &
2113	comm2d, ierr )
2114	CALL MPI_ALLREDUCE( phi_yaw_l, phi_yaw, nturbines, MPI_REAL, &
2115	MPI_SUM, comm2d, ierr )
2116	#else
2117	u_inflow = u_inflow_l
2118	wdir = wdir_l
2119	phi_yaw = phi_yaw_l
2120
2121
2122	#endif
2123	DO inot = 1, nturbines
2124	!
2125	!-- Update rotor orientation
2126	CALL wtm_rotate_rotor( inot )
2127
2128	ENDDO ! End of loop over turbines
2129
2130	END IF ! end of yaw control
2131
2132	IF ( speed_control ) THEN
2133	!
2134	!-- Transfer of information to the other cpus
2135	! CALL MPI_ALLREDUCE( omega_gen, omega_gen_old, nturbines, &
2136	! MPI_REAL,MPI_SUM, comm2d, ierr )
2137	#if defined( __parallel )
2138	CALL MPI_ALLREDUCE( torque_gen, torque_gen_old, nturbines, &
2139	MPI_REAL, MPI_SUM, comm2d, ierr )
2140	CALL MPI_ALLREDUCE( omega_rot_l, omega_rot, nturbines, &
2141	MPI_REAL, MPI_SUM, comm2d, ierr )
2142	CALL MPI_ALLREDUCE( omega_gen_f, omega_gen_f_old, nturbines, &
2143	MPI_REAL, MPI_SUM, comm2d, ierr )
2144	#else
2145	torque_gen_old = torque_gen
2146	omega_rot = omega_rot_l
2147	omega_gen_f_old = omega_gen_f
2148	#endif
2149
2150	ENDIF
2151
2152	DO inot = 1, nturbines
2153
2154	IF ( myid == 0 ) THEN
2155	IF ( openfile_turb_mod(400+inot)%opened ) THEN
2156	WRITE ( 400+inot, 106 ) simulated_time, omega_rot(inot), &
2157	omega_gen(inot), torque_gen_old(inot), &
2158	torque_total(inot), pitch_add(inot), &
2159	torque_gen_old(inot)omega_gen(inot)gen_eff, &
2160	torque_total(inot)omega_rot(inot)air_dens, &
2161	thrust_rotor(inot), &
2162	wdir(inot)*180.0_wp/pi, &
2163	(phi_yaw(inot))*180.0_wp/pi
2164
2165	ELSE
2166
2167	WRITE ( turbine_id,'(I2.2)') inot
2168	OPEN ( 400+inot, FILE=( 'TURBINE_PARAMETERS'//turbine_id ), &
2169	FORM='FORMATTED' )
2170	WRITE ( 400+inot, 105 ) inot
2171	WRITE ( 400+inot, 106 ) simulated_time, omega_rot(inot), &
2172	omega_gen(inot), torque_gen_old(inot), &
2173	torque_total(inot), pitch_add(inot), &
2174	torque_gen_old(inot)omega_gen(inot)gen_eff, &
2175	torque_total(inot)omega_rot(inot)air_dens, &
2176	thrust_rotor(inot), &
2177	wdir(inot)*180.0_wp/pi, &
2178	(phi_yaw(inot))*180.0_wp/pi
2179	ENDIF
2180	ENDIF
2181
2182	!-- Set open flag
2183	openfile_turb_mod(400+inot)%opened = .TRUE.
2184	ENDDO !-- end of loop over turbines
2185
2186	ENDIF
2187
2188	CALL cpu_log( log_point_s(61), 'wtm_forces', 'stop' )
2189
2190	!
2191	!-- Formats
2192	105 FORMAT ('Turbine control data for turbine ',I2,1X,':'/ &
2193	&'----------------------------------------'/ &
2194	&' Time RSpeed GSpeed ', &
2195	'GenTorque AeroTorque Pitch Power(Gen) Power(Rot) ', &
2196	'RotThrust WDirection YawOrient')
2197
2198	106 FORMAT (F9.3,2X,F7.3,2X,F7.2,2X,F9.1,3X,F9.1,1X,F6.2,2X,F10.1,2X, &
2199	F10.1,1X,F9.1,2X,F7.2,1X,F7.2)
2200
2201
2202	END SUBROUTINE wtm_forces
2203
2204
2205	!------------------------------------------------------------------------------!
2206	! Description:
2207	! ------------
2208	!> Yaw controller for the wind turbine model
2209	!------------------------------------------------------------------------------!
2210	SUBROUTINE wtm_yawcontrol( inot )
2211
2212	USE constants
2213	USE kinds
2214
2215	IMPLICIT NONE
2216
2217	INTEGER(iwp) :: inot
2218	INTEGER(iwp) :: i_wd_30
2219	REAL(wp) :: missal
2220
2221	i_wd_30 = 0_iwp
2222
2223	!
2224	!-- The yaw controller computes a 30s running mean of the wind direction.
2225	!-- If the difference between turbine alignment and wind direction exceeds
2226	!-- 5Â°, the turbine is yawed. The mechanism stops as soon as the 2s-running
2227	!-- mean of the missalignment is smaller than 0.5Â°.
2228	!-- Attention: If the timestep during the simulation changes significantly
2229	!-- the lengths of the running means change and it does not correspond to
2230	!-- 30s/2s anymore.
2231	!-- ! Needs to be modified for these situations !
2232	!-- For wind from the east, the averaging of the wind direction could cause
2233	!-- problems and the yaw controller is probably flawed. -> Routine for
2234	!-- averaging needs to be improved!
2235	!
2236	!-- Check if turbine is not yawing
2237	IF ( .NOT. doyaw(inot) ) THEN
2238	!
2239	!-- Write current wind direction into array
2240	wd30_l = wd30(inot,:)
2241	wd30_l = CSHIFT( wd30_l, SHIFT=-1 )
2242	wd30_l(1) = wdir(inot)
2243	!
2244	!-- Check if array is full ( no more dummies )
2245	IF ( .NOT. ANY( wd30_l == 999.) ) THEN
2246
2247	missal = SUM( wd30_l ) / SIZE( wd30_l ) - phi_yaw(inot)
2248	!
2249	!-- Check if turbine is missaligned by more than max_miss
2250	IF ( ABS( missal ) > max_miss ) THEN
2251	!
2252	!-- Check in which direction to yaw
2253	yawdir(inot) = SIGN( 1.0_wp, missal )
2254	!
2255	!-- Start yawing of turbine
2256	phi_yaw(inot) = phi_yaw(inot) + yawdir(inot) * yaw_speed * dt_3d
2257	doyaw(inot) = .TRUE.
2258	wd30_l = 999. ! fill with dummies again
2259	ENDIF
2260	ENDIF
2261
2262	wd30(inot,:) = wd30_l
2263
2264	!
2265	!-- If turbine is already yawing:
2266	!-- Initialize 2 s running mean and yaw until the missalignment is smaller
2267	!-- than min_miss
2268
2269	ELSE
2270	!
2271	!-- Initialize 2 s running mean
2272	wd2_l = wd2(inot,:)
2273	wd2_l = CSHIFT( wd2_l, SHIFT = -1 )
2274	wd2_l(1) = wdir(inot)
2275	!
2276	!-- Check if array is full ( no more dummies )
2277	IF ( .NOT. ANY( wd2_l == 999.0_wp ) ) THEN
2278	!
2279	!-- Calculate missalignment of turbine
2280	missal = SUM( wd2_l - phi_yaw(inot) ) / SIZE( wd2_l )
2281	!
2282	!-- Check if missalignment is still larger than 0.5 degree and if the
2283	!-- yaw direction is still right
2284	IF ( ( ABS( missal ) > min_miss ) .AND. &
2285	( yawdir(inot) == SIGN( 1.0_wp, missal ) ) ) THEN
2286	!
2287	!-- Continue yawing
2288	phi_yaw(inot) = phi_yaw(inot) + yawdir(inot) * yaw_speed * dt_3d
2289	ELSE
2290	!
2291	!-- Stop yawing
2292	doyaw(inot) = .FALSE.
2293	wd2_l = 999.0_wp ! fill with dummies again
2294	ENDIF
2295	ELSE
2296	!
2297	!-- Continue yawing
2298	phi_yaw(inot) = phi_yaw(inot) + yawdir(inot) * yaw_speed * dt_3d
2299	ENDIF
2300
2301	wd2(inot,:) = wd2_l
2302
2303	ENDIF
2304
2305	END SUBROUTINE wtm_yawcontrol
2306
2307
2308	!------------------------------------------------------------------------------!
2309	! Description:
2310	! ------------
2311	!> Initialization of the speed control
2312	!------------------------------------------------------------------------------!
2313	SUBROUTINE wtm_init_speed_control
2314
2315
2316	IMPLICIT NONE
2317
2318	!
2319	!-- If speed control is set, remaining variables and control_parameters for
2320	!-- the control algorithm are calculated
2321	!
2322	!-- Calculate slope constant for region 15
2323	slope15 = ( slope2 * min_reg2 * min_reg2 ) / ( min_reg2 - min_reg15 )
2324	!
2325	!-- Calculate upper limit of slipage region
2326	vs_sysp = rated_genspeed / 1.1_wp
2327	!
2328	!-- Calculate slope of slipage region
2329	slope25 = ( rated_power / rated_genspeed ) / &
2330	( rated_genspeed - vs_sysp )
2331	!
2332	!-- Calculate lower limit of slipage region
2333	min_reg25 = ( slope25 - SQRT( slope25 * ( slope25 - 4.0_wp * &
2334	slope2 * vs_sysp ) ) ) / &
2335	( 2.0_wp * slope2 )
2336	!
2337	!-- Frequency for the simple low pass filter
2338	Fcorner = 0.25_wp
2339	!
2340	!-- At the first timestep the torque is set to its maximum to prevent
2341	!-- an overspeeding of the rotor
2342	torque_gen_old(:) = max_torque_gen
2343
2344	END SUBROUTINE wtm_init_speed_control
2345
2346
2347	!------------------------------------------------------------------------------!
2348	! Description:
2349	! ------------
2350	!> Simple controller for the regulation of the rotor speed
2351	!------------------------------------------------------------------------------!
2352	SUBROUTINE wtm_speed_control( inot )
2353
2354
2355	IMPLICIT NONE
2356
2357	INTEGER(iwp) :: inot
2358
2359
2360
2361	!
2362	!-- The controller is based on the fortran script from Jonkman
2363	!-- et al. 2009 "Definition of a 5 MW Reference Wind Turbine for
2364	!-- offshore system developement"
2365
2366	!
2367	!-- The generator speed is filtered by a low pass filter
2368	!-- for the control of the generator torque
2369	lp_coeff = EXP( -2.0_wp * 3.14_wp * dt_3d * Fcorner )
2370	omega_gen_f(inot) = ( 1.0_wp - lp_coeff ) * omega_gen(inot) + lp_coeff *&
2371	omega_gen_f_old(inot)
2372
2373	IF ( omega_gen_f(inot) <= min_reg15 ) THEN
2374	!
2375	!-- Region 1: Generator torque is set to zero to accelerate the rotor:
2376	torque_gen(inot) = 0
2377
2378	ELSEIF ( omega_gen_f(inot) <= min_reg2 ) THEN
2379	!
2380	!-- Region 1.5: Generator torque is increasing linearly with rotor speed:
2381	torque_gen(inot) = slope15 * ( omega_gen_f(inot) - min_reg15 )
2382
2383	ELSEIF ( omega_gen_f(inot) <= min_reg25 ) THEN
2384	!
2385	!-- Region 2: Generator torque is increased by the square of the generator
2386	!-- speed to keep the TSR optimal:
2387	torque_gen(inot) = slope2 * omega_gen_f(inot) * omega_gen_f(inot)
2388
2389	ELSEIF ( omega_gen_f(inot) < rated_genspeed ) THEN
2390	!
2391	!-- Region 2.5: Slipage region between 2 and 3:
2392	torque_gen(inot) = slope25 * ( omega_gen_f(inot) - vs_sysp )
2393
2394	ELSE
2395	!
2396	!-- Region 3: Generator torque is antiproportional to the rotor speed to
2397	!-- keep the power constant:
2398	torque_gen(inot) = rated_power / omega_gen_f(inot)
2399
2400	ENDIF
2401	!
2402	!-- Calculate torque rate and confine with a max
2403	trq_rate = ( torque_gen(inot) - torque_gen_old(inot) ) / dt_3d
2404	trq_rate = MIN( MAX( trq_rate, -1.0_wp * max_trq_rate ), max_trq_rate )
2405	!
2406	!-- Calculate new gen torque and confine with max torque
2407	torque_gen(inot) = torque_gen_old(inot) + trq_rate * dt_3d
2408	torque_gen(inot) = MIN( torque_gen(inot), max_torque_gen )
2409	!
2410	!-- Overwrite values for next timestep
2411	omega_rot_l(inot) = omega_gen(inot) / gear_ratio
2412
2413
2414	END SUBROUTINE wtm_speed_control
2415
2416
2417	!------------------------------------------------------------------------------!
2418	! Description:
2419	! ------------
2420	!> Application of the additional forces generated by the wind turbine on the
2421	!> flow components (tendency terms)
2422	!> Call for all grid points
2423	!------------------------------------------------------------------------------!
2424	SUBROUTINE wtm_tendencies( component )
2425
2426
2427	IMPLICIT NONE
2428
2429	INTEGER(iwp) :: component !< prognostic variable (u,v,w)
2430	INTEGER(iwp) :: i !< running index
2431	INTEGER(iwp) :: j !< running index
2432	INTEGER(iwp) :: k !< running index
2433
2434
2435	SELECT CASE ( component )
2436
2437	CASE ( 1 )
2438	!
2439	!-- Apply the x-component of the force to the u-component of the flow:
2440	IF ( simulated_time >= time_turbine_on ) THEN
2441	DO i = nxlg, nxrg
2442	DO j = nysg, nyng
2443	DO k = nzb+1, k_hub(1) + k_smear(1)
2444	!
2445	!-- Calculate the thrust generated by the nacelle and the tower
2446	tend_nac_x = 0.5_wp * nac_cd_surf(k,j,i) * &
2447	SIGN( u(k,j,i)**2 , u(k,j,i) )
2448	tend_tow_x = 0.5_wp * tow_cd_surf(k,j,i) * &
2449	SIGN( u(k,j,i)**2 , u(k,j,i) )
2450
2451	tend(k,j,i) = tend(k,j,i) + ( - rot_tend_x(k,j,i) &
2452	- tend_nac_x - tend_tow_x ) &
2453	* MERGE( 1.0_wp, 0.0_wp, &
2454	BTEST( wall_flags_0(k,j,i), 1 ) )
2455	ENDDO
2456	ENDDO
2457	ENDDO
2458	ENDIF
2459
2460	CASE ( 2 )
2461	!
2462	!-- Apply the y-component of the force to the v-component of the flow:
2463	IF ( simulated_time >= time_turbine_on ) THEN
2464	DO i = nxlg, nxrg
2465	DO j = nysg, nyng
2466	DO k = nzb+1, k_hub(1) + k_smear(1)
2467	tend_nac_y = 0.5_wp * nac_cd_surf(k,j,i) * &
2468	SIGN( v(k,j,i)**2 , v(k,j,i) )
2469	tend_tow_y = 0.5_wp * tow_cd_surf(k,j,i) * &
2470	SIGN( v(k,j,i)**2 , v(k,j,i) )
2471	tend(k,j,i) = tend(k,j,i) + ( - rot_tend_y(k,j,i) &
2472	- tend_nac_y - tend_tow_y ) &
2473	* MERGE( 1.0_wp, 0.0_wp, &
2474	BTEST( wall_flags_0(k,j,i), 2 ) )
2475	ENDDO
2476	ENDDO
2477	ENDDO
2478	ENDIF
2479
2480	CASE ( 3 )
2481	!
2482	!-- Apply the z-component of the force to the w-component of the flow:
2483	IF ( simulated_time >= time_turbine_on ) THEN
2484	DO i = nxlg, nxrg
2485	DO j = nysg, nyng
2486	DO k = nzb+1, k_hub(1) + k_smear(1)
2487	tend(k,j,i) = tend(k,j,i) - rot_tend_z(k,j,i) &
2488	* MERGE( 1.0_wp, 0.0_wp, &
2489	BTEST( wall_flags_0(k,j,i), 3 ) )
2490	ENDDO
2491	ENDDO
2492	ENDDO
2493	ENDIF
2494
2495
2496	CASE DEFAULT
2497
2498	WRITE( message_string, * ) 'unknown prognostic variable: ', component
2499	CALL message( 'wtm_tendencies', 'PA04??', 1, 2, 0, 6, 0 )
2500
2501	END SELECT
2502
2503
2504	END SUBROUTINE wtm_tendencies
2505
2506
2507	!------------------------------------------------------------------------------!
2508	! Description:
2509	! ------------
2510	!> Application of the additional forces generated by the wind turbine on the
2511	!> flow components (tendency terms)
2512	!> Call for grid point i,j
2513	!------------------------------------------------------------------------------!
2514	SUBROUTINE wtm_tendencies_ij( i, j, component )
2515
2516
2517	IMPLICIT NONE
2518
2519	INTEGER(iwp) :: component !< prognostic variable (u,v,w)
2520	INTEGER(iwp) :: i !< running index
2521	INTEGER(iwp) :: j !< running index
2522	INTEGER(iwp) :: k !< running index
2523
2524	SELECT CASE ( component )
2525
2526	CASE ( 1 )
2527	!
2528	!-- Apply the x-component of the force to the u-component of the flow:
2529	IF ( simulated_time >= time_turbine_on ) THEN
2530
2531	DO k = nzb+1, k_hub(1) + k_smear(1)
2532	!
2533	!-- Calculate the thrust generated by the nacelle and the tower
2534	tend_nac_x = 0.5_wp * nac_cd_surf(k,j,i) * &
2535	SIGN( u(k,j,i)**2 , u(k,j,i) )
2536	tend_tow_x = 0.5_wp * tow_cd_surf(k,j,i) * &
2537	SIGN( u(k,j,i)**2 , u(k,j,i) )
2538	tend(k,j,i) = tend(k,j,i) + ( - rot_tend_x(k,j,i) &
2539	- tend_nac_x - tend_tow_x ) &
2540	* MERGE( 1.0_wp, 0.0_wp, &
2541	BTEST( wall_flags_0(k,j,i), 1 ) )
2542	ENDDO
2543	ENDIF
2544
2545	CASE ( 2 )
2546	!
2547	!-- Apply the y-component of the force to the v-component of the flow:
2548	IF ( simulated_time >= time_turbine_on ) THEN
2549	DO k = nzb+1, k_hub(1) + k_smear(1)
2550	tend_nac_y = 0.5_wp * nac_cd_surf(k,j,i) * &
2551	SIGN( v(k,j,i)**2 , v(k,j,i) )
2552	tend_tow_y = 0.5_wp * tow_cd_surf(k,j,i) * &
2553	SIGN( v(k,j,i)**2 , v(k,j,i) )
2554	tend(k,j,i) = tend(k,j,i) + ( - rot_tend_y(k,j,i) &
2555	- tend_nac_y - tend_tow_y ) &
2556	* MERGE( 1.0_wp, 0.0_wp, &
2557	BTEST( wall_flags_0(k,j,i), 2 ) )
2558	ENDDO
2559	ENDIF
2560
2561	CASE ( 3 )
2562	!
2563	!-- Apply the z-component of the force to the w-component of the flow:
2564	IF ( simulated_time >= time_turbine_on ) THEN
2565	DO k = nzb+1, k_hub(1) + k_smear(1)
2566	tend(k,j,i) = tend(k,j,i) - rot_tend_z(k,j,i) &
2567	* MERGE( 1.0_wp, 0.0_wp, &
2568	BTEST( wall_flags_0(k,j,i), 3 ) )
2569	ENDDO
2570	ENDIF
2571
2572
2573	CASE DEFAULT
2574
2575	WRITE( message_string, * ) 'unknown prognostic variable: ', component
2576	CALL message( 'wtm_tendencies', 'PA04??', 1, 2, 0, 6, 0 )
2577
2578	END SELECT
2579
2580
2581	END SUBROUTINE wtm_tendencies_ij
2582
2583	END MODULE wind_turbine_model_mod

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