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meangen-17.4.f
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meangen-17.4.f
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C
C THE DIMENSIONS ARE SET BY THE FOLLOWING PARAMETER STATEMENT.:
C NG = TOTAL NUMBER OF POINTS USED ON THE STREAM SURFACE.
C NST = NUMBER OF STAGES.
C NSC = NUMBER OF BLADE SECTIONS TO BE GENERATED.
PARAMETER(NG=99, NST=20, NSC= 11)
C
DIMENSION
& HO(NG),V(NG),S(NG),P(NG),T(NG),G(NG),VS(NG),RHO(NG),
& WET(NG),PSI(NG),PHI(NG),RHOMID(NG),RHOEXIT(NG),HEXIT(NG),
& DHO(NG),U(NG),VXOUT(NG),SMID(NG),SEXIT(NG),VMRAT(NG),
& VXMID(NG),HOEXIT(NG),HOMID(NG),HMID(NG),PO(NG),PMID(NG),
& PEXIT(NG),ETA(NG),ASPN(NG),ASPR(NG),SPAN(NG),
& RMEANALL(NST,NG),XMEANALL(NST,NG),VMLOCALL(NST,NG),
& RHUBALL(NST,NG),RTIPALL(NST,NG),NLE1_ALL(NST),NTE1_ALL(NST),
& XHUBALL(NST,NG),XTIPALL(NST,NG),NLE2_ALL(NST),NTE2_ALL(NST),
& NSS_STG(NST),NLE1_STG(NST),NTE1_STG(NST),
& NLE2_STG(NST),NTE2_STG(NST),ALPHA_IN(NG),ALPHA_OUT(NG),
& ROWGAP(NST),STAGEGAP(NST),DEVN1(NG),DEVN2(NG),AINC1(NG),
& AINC2(NG)
C
COMMON /SET7/ HOIN,SI,RGAS,CPGAS,POIN,TOIN,GAMM
C
DIMENSION RHUB(NG),RTIP(NG),XHUB(NG),XTIP(NG),DHOIS(NG),VX(NG),
& REACN(NG),RDES(NG),VIN(NG),AXCHRD1(NG),AXCHRD2(NG),
& XSURFHUB(NG),XSURFTIP(NG),RSURFHUB(NG),RSURFTIP(NG),
& SDISTHUB(NG),SDISTTIP(NG)
C
DIMENSION NBLADE(NG),XSECT(NG),RSECT(NG),
& PSTATIN(NG),PSTATOUT(NG),PROTOUT(NG),
& HINLET(NG),SINLET(NG),PINLET(NG),VM(NG),
& XMEAN(NG),RMEAN(NG),VMER(NG),SDIST(NG),PITCH_ANGL(NG),
& FBLOCK_LE(NST),FBLOCK_TE(NST),FBLOCK(NG)
C
DIMENSION BIN_ROW1(NG),BOUT_ROW1(NG), BIN_ROW2(NG),BOUT_ROW2(NG),
& QLE_ROW1(NG),QTE_ROW1(NG),QLE_ROW2(NG),QTE_ROW2(NG)
C
DIMENSION RHOINLET(NG),HOINLET(NG),VXIN(NG),
& TIN(NG),TMID(NG),TEXIT(NG),POREL(NG),POABS(NG),
& VRELIN(NG),VABSIN(NG),VRELMID(NG),VABSMID(NG),
& VRELEX(NG),VABSEX(NG),RHUBIN(NG),RHUBMID(NG),
& RHUBEXIT(NG),RTIPIN(NG),RTIPMID(NG),RTIPEXIT(NG),
& TKMAX_S(NST,NSC),XTKMAX_S(NST,NSC),TINLET(NG),
& TKMAX_R(NST,NSC),XTKMAX_R(NST,NSC)
C
DIMENSION VABS(NG),VREL(NG),HOLOC(NG),SLOC(NG),PLOC(NG),
& TLOC(NG),RHOLOC(NG),PHI_LOC(NG),VM_LOC(NG),U_LOC(NG),
& VTLOC(NG)
C
REAL MACH_REL(NG),MACH_ABS(NG)
C
CHARACTER*10 IFSAME_RAD, IF_RDES, IFHUB,
& IFSAME_ADM, IFSAME_FLO, IFSAME_ANG, RADTYPE
CHARACTER*1 INTYPE, ASP_TYP, ROWTYP, TURBO_TYP,ANSTK,ANSFLO,
& IFSAME_ALL,ANSSS,ANS,ANSANGL, MIXTYP,ANSOUT,ANSIN,
& IFOUT(NG),IF_ROT
CHARACTER*3 FLO_TYP
CHARACTER*72 DUMMY_LINE
C
OPEN(UNIT=10, FILE= 'meangen.out')
OPEN(UNIT=11, FILE= 'meandesign.out')
!OPEN(UNIT=5, FILE= '/dev/tty')
C
PI = 3.14159
DEGRAD = PI/180.
RADDEG = 180./PI
DEG = PI/180.
C
WRITE(6,*)'*******************************************************
&*****************************************************************'
WRITE(6,*)'*******************************************************
&*****************************************************************'
WRITE(6,*)
WRITE(6,*)' WELCOME TO MEANGEN '
WRITE(6,*)
WRITE(6,*)'THIS IS AN INTERACTIVE PROGRAM FOR THE ONE-DIMENSIONAL'
WRITE(6,*)' DESIGN OF AXIAL TURBOMACHINES.'
WRITE(6,*)
WRITE(6,*)'ANSWER THE QUESTIONS AS THEY APPEAR ON THE SCREEN '
WRITE(6,*)'AND THE PROGRAM WILL WRITE A DATA SET FOR THE'
WRITE(6,*)'BLADE GEOMETRY PROGRAM "STAGEN" WHICH IN TURN WILL'
WRITE(6,*)'GENERATE A 3D DATASET FOR "MULTALL-OPEN".'
WRITE(6,*)
WRITE(6,*)'*******************************************************
&*****************************************************************'
WRITE(6,*)'*******************************************************
&*****************************************************************'
C
WRITE(6,*) ' INPUT FROM SCREEN OR FILE ? '
WRITE(6,*) ' ANSWER "S" or "F" .'
READ(5,*) ANSIN
IF(ANSIN.EQ.'F'.OR.ANSIN.EQ.'f') THEN
ANSIN = 'F'
CLOSE(5)
OPEN(UNIT=5, FILE='meangen.in' )
END IF
C
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
WRITE(6,*)
WRITE(6,*) ' IS THIS A COMPRESSOR OR A TURBINE ?'
WRITE(6,*) ' ANSWER "C" or "T" . '
READ(5,*) TURBO_TYP
IF(TURBO_TYP.EQ.'t') TURBO_TYP= 'T'
IF(TURBO_TYP.EQ.'c') TURBO_TYP= 'C'
WRITE(10,101) TURBO_TYP
101 FORMAT(A1,T25,' TURBO_TYP,"C" FOR A COMPRESSOR,"T" FOR A TURBINE')
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
C
WRITE(6,*)
C
WRITE(6,*) ' DO YOU WANT TO DESIGN AN AXIAL FLOW MACHINE WITH A
&CONSTANT RADIUS AT A FIXED SPANWISE POSITION ON EACH STAGE ?'
WRITE(6,*) ' AND WITH REPEATING FLOW CONDITIONS.'
WRITE(6,*) ' OR A MIXED FLOW MACHINE WITH SIGNIFICANT CHANGES IN
& RADIUS THROUGH A STAGE ?'
WRITE(6,*) ' ANSWER "AXI" or "MIX" '
READ(5,*) FLO_TYP
IF(FLO_TYP.EQ.'axi') FLO_TYP = 'AXI'
IF(FLO_TYP.EQ.'mix') FLO_TYP = 'MIX'
WRITE(10,5) FLO_TYP
5 FORMAT(A3,T25, ' FLO_TYP FOR AXIAL OR MIXED FLOW MACHINE ')
C
WRITE(6,*)
WRITE(6,*)
& 'THE BLADE ROTATION MUST BE IN THE POSITIVE THETA DIRECTION.'
WRITE(6,*)
WRITE(6,*)
& 'ALL FLOW ANGLES ARE POSITIVE IF THE ASSOCIATED FLOW VECTOR HAS
& A POSITIVE COMPONENT IN THE DIRECTION OF ROTATION.'
ROTN = 1.0
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
WRITE(6,*)
C********************************************************************************
C********************************************************************************
C SET DEFAULTS
C********************************************************************************
C********************************************************************************
C
IF(TURBO_TYP.EQ.'T') THEN ! DEFAULTS FOR TURBINES.
TKLE = 0.04 ! LEADING EDGE THICKNESS/AXIAL CHORD.
TKTE = 0.04 ! TRAILING EDGE THICKNESS/AXIAL CHORD.
TKMAXS = 0.30 ! STATOR MAXIMUM THICKNESS/AXIAL CHORD.
TKMAXR = 0.25 ! ROTOR MAXIMUM THICKNESS/AXIAL CHORD.
XTKMAXS = 0.45 ! FRACTION OF AXIAL CHORD AT MAXIMUM THICKNESS FOR STATOR
XTKMAXR = 0.40 ! FRACTION OF AXIAL CHORD AT MAXIMUM THICKNESS FOR ROTOR
XMODLE = 0.02 ! FRACTION OF AXIAL CHORD OVER WHICH THE LE IS MODIFIED.
XMODTE = 0.01 ! FRACTION OF AXIAL CHORD OVER WHICH THE TE IS MODIFIED.
TK_TYP = 2.0 ! FORM OF BLADE THICKNESS DISTRIBUTION.
ZWEIFEL = 0.85 ! ZWEIFEL COEFFICIENT FOR TURBINES
EXPO = 1.0 ! EXPONENT FOR TRANSFORMING THE AXIAL POSITION. IT IS USED TO
C VARY THE CAMBER LINE SHAPE. INCREASING EXPO MOVES THE BLADE LOADING UPSTREAM.
QLE_ROW1(1) = 92.0 ! LEADING EDGE ANGLE TO AXIAL DIRECTION IN MERIDINAL VIEW ROW 1.
QTE_ROW1(1) = 88.0 ! TRAILING EDGE ANGLE TO AXIAL DIRECTION IN MERIDINAL VIEW ROW 1.
QLE_ROW2(1) = 88.0 ! LEADING EDGE ANGLE TO AXIAL DIRECTION IN MERIDINAL VIEW ROW 2.
QTE_ROW2(1) = 92.0 ! TRAILING EDGE ANGLE TO AXIAL DIRECTION IN MERIDINAL VIEW ROW 2.
END IF
C
IF(TURBO_TYP.EQ.'C') THEN ! DEFAULTS FOR COMPRESSORS.
TKLE = 0.02 ! LEADING EDGE THICKNESS/AXIAL CHORD.
TKTE = 0.01 ! TRAILING EDGE THICKNESS/AXIAL CHORD.
TKMAXS = 0.10 ! STATOR MAXIMUM THICKNESS/AXIAL CHORD.
TKMAXR = 0.075 ! ROTOR MAXIMUM THICKNESS/AXIAL CHORD.
XTKMAXS = 0.45 ! FRACTION OF AXIAL CHORD AT MAXIMUM THICKNESS FOR STATOR
XTKMAXR = 0.40 ! FRACTION OF AXIAL CHORD AT MAXIMUM THICKNESS FOR ROTOR
XMODLE = 0.02 ! FRACTION OF AXIAL CHORD OVER WHICH THE LE IS MODIFIED.
XMODTE = 0.01 ! FRACTION OF AXIAL CHORD OVER WHICH THE TE IS MODIFIED.
TK_TYP = 2.0 ! DETERMINES THE SHAPE OF THE BLADE THICKNESS DISTRIBUTION.TYPICALLY = 2,
C LARGER VALUES GIVE MORE UNIFORM THICKNESS.
ZWEIFEL = 0.5 ! ZWEIFEL COEFFICIENT FOR COMPRESSORS.
D_FAC = 0.35 ! DIFFUSION FACTOR FOR COMPRESSORS. THIS IS NOT NOW USED.
EXPO = 1.35 ! EXPONENT FOR TRANSFORMING THE AXIAL POSITION. IT IS USED TO
C VARY THE CAMBER LINE SHAPE. INCREASING EXPO MOVES THE BLADE LOADING UPSTREAM.
QLE_ROW1(1) = 88.0 ! LEADING EDGE ANGLE TO AXIAL DIRECTION IN MERIDINAL VIEW ROW 1.
QTE_ROW1(1) = 92.0 ! TRAILING EDGE ANGLE TO AXIAL DIRECTION IN MERIDINAL VIEW ROW 1.
QLE_ROW2(1) = 92.0 ! LEADING EDGE ANGLE TO AXIAL DIRECTION IN MERIDINAL VIEW ROW 2.
QTE_ROW2(1) = 88.0 ! TRAILING EDGE ANGLE TO AXIAL DIRECTION IN MERIDINAL VIEW ROW 2.
END IF
C
IPROPS = 1 ! USE PERFECT GAS PROPERTIES.
RGAS = 287.5 ! GAS CONSTANT, VALUE FOR AIR.
GAMM = 1.40 ! GAS SPECIFIC HEAT RATIO, VALUE FOR AIR.
AXCHRD1(1) = 0.05 ! AXIAL CHORD OF ROW 1, METRES.
AXCHRD2(1) = 0.04 ! AXIAL CHORD OF ROW 2, METRES.
ROWGAP(1) = 0.25 ! GAP BETWEEN BLADE ROWS AS A FRACTION OF THE AXIAL CHORD.
STAGEGAP(1)= 0.5 ! GAP BETWEEN STAGES AS A FRACTION OF THE AXIAL CHORD.
DEVN_1 = 5.0 ! DEVIATION ANGLE FROM ROW 1, DEGREES.
DEVN_2 = 5.0 ! DEVIATION ANGLE FRON ROW 2, DEGREES.
AINC_1 = -2.0 ! INCIDENCE ANGLE ON ROW 1, DEGREES.
AINC_2 = -2.0 ! INCIDENCE ANGLE ON ROW 2, DEGREES.
ETA(1) = 0.9 ! ISENTROPIC EFFICIENCY.
NSMOOTH = 5 ! NUMBER OF SMOOTHINGS OF THE STREAM SURFACE COORDINATES.
SFAC = 0.1 ! SMOOTHING FACTOR FOR THE STREAM SURFACE SMOOTHING.
FBLOCK_LE(1) = 0.0 ! BLOCKAGE FACTOR AT FIRST LEADING EDGE.
FBLOCK_TE(1) = 0.0 ! BLOCKAGE FACTOR AT SECOND BLADE TRAILING EDGE.
C
NOSECT = 3 ! NUMBER OS STREAM SURFACES TO BE GENERATED.
IM = 37 ! NUMBER OF GRID POINTS IN THE PITCHWISE DIRECTION.
KM = 37 ! NUMBER OF GRID POINTS IN THE SPANWISE DIRECTION.
NINTUP = 20 ! NUMBER OF MERIDIONAL GRID POINTS UPSTREAM OF THE LEADING EDGE.
NINTON = 70 ! NUMBER OF MERIDIONAL GRID POINTS ON THE BLADE.
NINTDWN = 15 ! NUMBER OF MERIDIONAL GRID POINTS BEHIND THE TRAILING EDGE.
NADDUP = 5 ! EXTRA MERIDIONAL GRID POINTS UPSTREAM OF ROW 1.
NADDWN = 5 ! EXTRA MERIIONAL GRID POINTS DOWNSTREAM OF THE LAST ROW.
FPRAT = 1.25 ! GRID EXPANSION RATIO IN THE PITCHWISE DIRECTION.
FPMAX = 20.0 ! MAXIMUM GRID EXPANSION IN THE PITCHWISE DIRECTION.
FRRAT = 1.25 ! GRID EXPANSION RATIO IN THE SPANWISE DIRECTION.
FRMAX = 20.0 ! MAXIMUM GRID EXPANSION IN THE SPANWISE DIRECTION.
C
C********************************************************************************
C********************************************************************************
C END OF SETTING DEFAULTS.
C********************************************************************************
C********************************************************************************
C
WRITE(6,*)
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
WRITE(6,*)
& 'INPUT THE GAS CONSTANT IN J/KG K, AND GAS SPECIFIC HEAT RATIO.'
WRITE(6,*)
&'THE DEFAULT VALUES ARE THOSE FOR AIR, RGAS = 287.15, GAMMA=1.4.'
WRITE(6,*) ' TYPE "A" TO ACCEPT THESE, OR TYPE IN NEW VALUES.'
READ(5,*,ERR=1111) RGAS, GAMM
1111 CONTINUE
WRITE(10,102) RGAS,GAMM
102 FORMAT(2F10.3,T25,' GAS PROPERTOES, RGAS, GAMMA ')
CPGAS = RGAS*GAMM/(GAMM-1.)
FGA = GAMM/(GAMM - 1.0)
C
WRITE(6,*)
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
WRITE(6,*)
WRITE(6,*)
& 'INPUT THE INLET STAGNATION PRESSURE IN BAR AND INLET TEMPERATURE
& IN DEG K'
READ(5,*) POIN, TOIN
WRITE(10,103)POIN,TOIN
103 FORMAT(2F10.3, T25, ' POIN, TOIN ')
HOIN = CPGAS*TOIN
PSTAGIN = POIN*1.0E05
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
C
WRITE(6,*)
WRITE(6,*) ' INPUT THE NUMBER OF STAGES IN THE MACHINE.'
READ(5,*) NSTAGES
WRITE(10,104) NSTAGES
104 FORMAT(I5,T25, ' NUMBER OF STAGES IN THE MACHINE ')
WRITE(6,*) ' NUMBER OF STAGES = ', NSTAGES
NROWS = 2*NSTAGES
WRITE(6,*)
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
WRITE(6,*)
WRITE(6,*) ' BASE THE DESIGN ON THE HUB, MEAN OR TIP RADIUS ? '
WRITE(6,*) ' INPUT "H" , "M" or "T" '
READ(5,*) IFHUB
IF(IFHUB.EQ.'h') IFHUB = 'H'
IF(IFHUB.EQ.'m') IFHUB = 'M'
IF(IFHUB.EQ.'t') IFHUB = 'T'
WRITE(10,106)IFHUB
106 FORMAT(A1,T25, ' CHOICE OF DESIGN POINT RADIUS, HUB, MID or TIP')
WRITE(6,*)
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
C
C**********************************************************************
C**********************************************************************
C CALL PROPS TO GET THE INLET STAGNATION CONDITIONS
C
HO(1) = HOIN
PO(1) = POIN
S(1) = 0.0
SI = 0.0
VIN(1) = 10.0
C
CALL PROPS(1,1,HO(1),S(1),PO(1),T(1),RHO(1),WET(1),
& VIN(1),G(1),VS(1),1,IPROPS,IWET)
C
C
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
WRITE(6,*)
WRITE(6,*) ' INLET STAGNATION PRESSURE = ', PO(1), ' BAR.'
WRITE(6,*) ' INLET STAGNATION TEMPERATURE = ', T(1) , ' K. '
WRITE(6,*) ' INLET STAGNATION DENSITY = ', RHO(1) , 'Kg/M3.'
WRITE(6,*)
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
C
C
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
WRITE(6,*)
WRITE(6,*)' INPUT THE ROTATION SPEED IN RPM, IT MUST BE POSITIVE.'
READ(5,*) RPM
WRITE(6,*) ' RPM = ', RPM
WRITE(10,107) RPM
107 FORMAT(F12.3,T25, ' ROTATION SPEED, RPM ')
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
WRITE(6,*)
C
C
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
WRITE(6,*)
WRITE(6,*) ' INPUT THE REQUIRED INLET MASS FLOW RATE IN kg/sec.'
READ(5,*) FLOWIN
WRITE(10,108) FLOWIN
108 FORMAT(F12.3,T25,' MASS FLOW RATE, FLOWIN. ')
WRITE(6,*) ' INLET FLOW = ', FLOWIN
FLOW = FLOWIN
WRITE(6,*)
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
C
OMEGA = RPM*PI/30.
DHO(1) = 0.0
DHOTOTAL = 0.0
C
C************************************************************************
C************************************************************************
C START THE LOOP OVER NSTG STAGES. RETURN TO "1100" AFTER EVERY STAGE.
C************************************************************************
C************************************************************************
C************************************************************************
NSTG = 0
1100 CONTINUE
C
C************************************************************************
C************************************************************************
NSTG = NSTG + 1
C
NROW = 2*NSTG -1
C
WRITE(6,*)
WRITE(6,*)'*******************************************************
&*****************************************************************'
WRITE(6,*)'*******************************************************
&*****************************************************************'
WRITE(6,*) ' STARTING STAGE NUMBER ', NSTG
WRITE(6,*)'*******************************************************
&*****************************************************************'
WRITE(6,*)'*******************************************************
&*****************************************************************'
WRITE(6,*)
C
C
IF(NSTG.GT.1) THEN
C
IFSAME_ALL = 'N'
C
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
WRITE(6,*)
WRITE(6,*) ' ARE THE ANGLES, MASS FLOW, DESIGN RADIUS,'
WRITE(6,*) ' EFFICIENCY, ETC, FOR THIS STAGE "ALL" THE SAME AS'
WRITE(6,*) ' FOR THE LAST STAGE ?'
WRITE(6,*)
IF(FLO_TYP.EQ.'AXI') THEN
WRITE(6,*) ' ANSWER "Y" or "N", OR ANSWER "C" TO CHANGE FROM'
WRITE(6,*) ' "FLO_TYP" = "AXI" TO "FLO_TYP" = "MIX".'
ELSE
WRITE(6,*) ' ANSWER "Y" or "N", OR ANSWER "C" TO CHANGE FROM'
WRITE(6,*) ' "FLO_TYP" = "MIX" TO "FLO_TYP" = "AXI".'
END IF
C
READ(5,*) IFSAME_ALL
WRITE(6,*) ' IFSAME_ALL= ', IFSAME_ALL
WRITE(10,109) IFSAME_ALL
IF(IFSAME_ALL.EQ.'y') IFSAME_ALL = 'Y'
IF(IFSAME_ALL.EQ.'n') IFSAME_ALL = 'N'
IF(IFSAME_ALL.EQ.'c') IFSAME_ALL = 'C'
C
IF(IFSAME_ALL.EQ.'C'.AND.(FLO_TYP.EQ.'AXI'))THEN
FLO_TYP = 'MIX'
GO TO 2000
END IF
IF(IFSAME_ALL.EQ.'C'.AND.(FLO_TYP.EQ.'MIX'))THEN
FLO_TYP = 'AXI'
MIXTYP = 'N'
GO TO 500
END IF
C
109 FORMAT(A1,T25,' IFSAME_ALL, SET = "Y" TO REPEAT THE LAST STAGE INP
&UT TYPE AND VELOCITY TRIANGLES, SET = "C" TO CHANGE INPUT TYPE.')
C
IF(FLO_TYP.EQ.'AXI'.AND.(IFSAME_ALL.EQ.'Y')) GO TO 600
IF(FLO_TYP.EQ.'MIX'.AND.(IFSAME_ALL.EQ.'Y')) GO TO 700
C
C END OF NSTAGE GT 1 LOOP
END IF
C
C RE ENTER HERE IF CHANGING THE ANGLES FOR THIS STAGE.
C
500 CONTINUE
C
C************************************************************************
C************************************************************************
C
IF(FLO_TYP.EQ.'MIX') GO TO 2000
C
C**********************************************************************
C**********************************************************************
C
C SET THE VELOCITY TRIANGLES FOR THE STAGE FOR FLO_TYP = "AXI".
C
WRITE(6,*)
WRITE(6,*)
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
WRITE(6,*)
WRITE(6,*) 'YOU MAY SPECIFY THE STAGE VELOCITY TRIANGLES IN ONE
&OF 3 WAYS '
WRITE(6,*)
WRITE(6,*) ' METHOD "A"-SPECIFY THE REACTION, FLOW COEFFICIENT AND
& STAGE LOADING COEFFICIENT'
WRITE(6,*)
WRITE(6,*) ' METHOD "B"- SPECIFY THE FLOW COEFFICIENT, THE STATOR
&EXIT ANGLE AND THE ROTOR EXIT ANGLE'
WRITE(6,*)
WRITE(6,*) ' METHOD "C"- SPECIFY THE FLOW COEFFICIENT, THE ROTOR
&INLET ANGLE AND THE ROTOR EXIT ANGLE'
WRITE(6,*)
WRITE(6,*) ' METHOD "D" SPECIFY THE STAGE REACTION,THE FIRST BLADE
&ROW INLET ANGLE AND THE FIRST BLADE ROW EXIT ANGLE'
WRITE(6,*)
C
WRITE(6,*)
WRITE(6,*) ' CHOOSE YOUT INPUT METHOD.'
WRITE(6,*) ' TYPE IN "A", "B", "C" or "D" '
C
READ(5,*) INTYPE
IF(INTYPE.EQ.'a') INTYPE ='A'
IF(INTYPE.EQ.'b') INTYPE ='B'
IF(INTYPE.EQ.'c') INTYPE ='C'
IF(INTYPE.EQ.'d') INTYPE ='D'
C
WRITE(10,110) INTYPE
110 FORMAT(A1,T25,' INTYPE, TO CHOOSE THE METHOD OF DEFINING THE VELOC
&ITY TRIANGLES')
C
WRITE(6,*)
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
C
C**************************************************************************************
C**************************************************************************************
C
IF(INTYPE.EQ.'A') THEN
WRITE(6,*) ' INTYPE = "A" CHOSEN.'
C
IF(TURBO_TYP.EQ.'T') WRITE(6,*) ' THIS IS A TURBINE.'
IF(TURBO_TYP.EQ.'C') WRITE(6,*) ' THIS IS A COMPRESSOR.'
WRITE(6,*)
WRITE(6,*) ' INPUT THE REACTION, FLOW COEFFICIENT AND STAGE LOADIN
&G COEFFICIENT. '
READ(5,*) REACN(NSTG), PHI(NSTG), PSI(NSTG)
WRITE(6,*) REACN(NSTG), PHI(NSTG), PSI(NSTG)
WRITE(10,111)REACN(NSTG), PHI(NSTG), PSI(NSTG)
111 FORMAT(3F7.3,T25,' REACTION, FLOW COEFF., LOADING COEFF.')
C
IF(TURBO_TYP.EQ.'T') THEN
BIN_ROW1(NSTG) =
& ATAN( (1.- REACN(NSTG) - 0.5*PSI(NSTG))/PHI(NSTG))
BOUT_ROW2(NSTG) =
& ATAN( TAN(BIN_ROW1(NSTG)) - 1.0/PHI(NSTG) )
BOUT_ROW1(NSTG) =
& ATAN( TAN(BIN_ROW1(NSTG)) + PSI(NSTG)/PHI(NSTG))
BIN_ROW2(NSTG) =
& ATAN( TAN(BOUT_ROW1(NSTG)) - 1.0/PHI(NSTG) )
WRITE(6,*)
WRITE(6,*) ' CALCULATED FLOW ANGLES FOR THIS STAGE '
WRITE(6,*) BIN_ROW1(NSTG)*RADDEG, BOUT_ROW1(NSTG)*RADDEG,
& BIN_ROW2(NSTG)*RADDEG, BOUT_ROW2(NSTG)*RADDEG
END IF
C
IF(TURBO_TYP.EQ.'C') THEN
BIN_ROW2(NSTG) =
& ATAN( (1. -REACN(NSTG) + 0.5*PSI(NSTG))/PHI(NSTG))
BOUT_ROW1(NSTG) =
& ATAN( TAN(BIN_ROW2(NSTG)) - 1.0/PHI(NSTG) )
BIN_ROW1(NSTG) =
& ATAN( TAN(BOUT_ROW1(NSTG)) - PSI(NSTG)/PHI(NSTG))
BOUT_ROW2(NSTG) =
& ATAN( TAN(BIN_ROW1(NSTG)) + 1.0/PHI(NSTG))
WRITE(6,*)
WRITE(6,*) ' CALCULATED FLOW ANGLES FOR THIS STAGE '
WRITE(6,*) BIN_ROW1(NSTG)*RADDEG, BOUT_ROW1(NSTG)*RADDEG,
& BIN_ROW2(NSTG)*RADDEG, BOUT_ROW2(NSTG)*RADDEG
END IF
C END OF INTYPE = "A" .
END IF
C
C**************************************************************************************
C**************************************************************************************
C
IF(INTYPE.EQ.'B') THEN
WRITE(6,*) ' INTYPE = "B" CHOSEN. '
C
IF(TURBO_TYP.EQ.'T') WRITE(6,*) ' THIS IS A TURBINE.'
IF(TURBO_TYP.EQ.'C') WRITE(6,*) ' THIS IS A COMPRESSOR.'
WRITE(6,*)
WRITE(6,*) ' INPUT THE FLOW COEFFICIENT, STATOR EXIT ANGLE AND ROT
&OR EXIT ANGLE'
READ(5,*) PHI(NSTG), B2NOZ, B2ROT
WRITE(10,112) PHI(NSTG), B2NOZ, B2ROT
112 FORMAT(3F12.3, T25, ' FLOW COEFF, STATOR ANGLES ')
C
IF(TURBO_TYP.EQ.'T') THEN
BOUT_ROW1(NSTG) = B2NOZ*DEGRAD
BOUT_ROW2(NSTG) = B2ROT*DEGRAD
BIN_ROW2(NSTG) = ATAN( TAN(BOUT_ROW1(NSTG)) - 1.0/PHI(NSTG) )
BIN_ROW1(NSTG) = ATAN( TAN(BOUT_ROW2(NSTG)) + 1.0/PHI(NSTG) )
REACN(NSTG) =
& -0.5*PHI(NSTG)*(TAN(BIN_ROW2(NSTG)) + TAN(BOUT_ROW2(NSTG)))
PSI(NSTG) =
& 2*(1.0 - REACN(NSTG) - PHI(NSTG)*TAN(BIN_ROW1(NSTG)))
WRITE(6,*) BIN_ROW1(NSTG)*RADDEG, BOUT_ROW1(NSTG)*RADDEG,
& BIN_ROW2(NSTG)*RADDEG, BOUT_ROW2(NSTG)*RADDEG
WRITE(6,*) ' REACTION= ', REACN(NSTG), ' LOADING = ', PSI(NSTG)
END IF
C
IF(TURBO_TYP.EQ.'C') THEN
BOUT_ROW2(NSTG) = B2NOZ*DEGRAD
BOUT_ROW1(NSTG) = B2ROT*DEGRAD
BIN_ROW1(NSTG) = ATAN( TAN(BOUT_ROW2(NSTG)) - 1.0/PHI(NSTG))
BIN_ROW2(NSTG) = ATAN( TAN(BOUT_ROW1(NSTG)) + 1.0/PHI(NSTG))
REACN(NSTG) =
& -0.5*PHI(NSTG)*(TAN(BIN_ROW1(NSTG)) + TAN(BOUT_ROW1(NSTG)))
PSI(NSTG) =
& -2*(1.0 - REACN(NSTG) - PHI(NSTG)*TAN(BIN_ROW2(NSTG)))
WRITE(6,*) BIN_ROW1(NSTG)*RADDEG, BOUT_ROW1(NSTG)*RADDEG,
& BIN_ROW2(NSTG)*RADDEG, BOUT_ROW2(NSTG)*RADDEG
WRITE(6,*) ' REACTION= ', REACN(NSTG), ' LOADING = ', PSI(NSTG)
END IF
C
C END OF INTYPE = "B" .
END IF
C
C**************************************************************************************
C**************************************************************************************
C
IF(INTYPE.EQ.'C') THEN
WRITE(6,*) ' INPUT TYPE "C" CHOSEN.'
C
IF(TURBO_TYP.EQ.'T') WRITE(6,*) ' THIS IS A TURBINE.'
IF(TURBO_TYP.EQ.'C') WRITE(6,*) ' THIS IS A COMPRESSOR.'
WRITE(6,*)
WRITE(6,*) ' INPUT THE ROTOR INLET ANGLE, THE ROTOR EXIT ANGLE AND
& THE FLOW COEFFICIENT.'
READ(5,*) B1ROT, B2ROT, PHI(NSTG)
WRITE(10,113) B1ROT, B2ROT, PHI(NSTG)
113 FORMAT(3F12.3,T25,' ROTOR ANGLES, FLOW COEFF.')
C
IF(TURBO_TYP.EQ.'T') THEN
BIN_ROW2(NSTG) = B1ROT*DEGRAD
BOUT_ROW2(NSTG) = B2ROT*DEGRAD
BIN_ROW1(NSTG) = ATAN( TAN(BOUT_ROW2(NSTG)) + 1.0/PHI(NSTG))
BOUT_ROW1(NSTG) = ATAN( TAN(BIN_ROW2(NSTG)) + 1.0/PHI(NSTG))
REACN(NSTG) =
& -0.5*PHI(NSTG)*(TAN(BIN_ROW2(NSTG)) + TAN(BOUT_ROW2(NSTG)))
PSI(NSTG) =
& 2*(1.0 - REACN(NSTG) - PHI(NSTG)*TAN(BIN_ROW1(NSTG)))
WRITE(6,*) BIN_ROW1(NSTG)*RADDEG, BOUT_ROW1(NSTG)*RADDEG,
& BIN_ROW2(NSTG)*RADDEG, BOUT_ROW2(NSTG)*RADDEG
WRITE(6,*) ' REACTION= ', REACN(NSTG), ' LOADING = ', PSI(NSTG)
END IF
C
IF(TURBO_TYP.EQ.'C') THEN
BIN_ROW1(NSTG) = B1ROT*DEGRAD
BOUT_ROW1(NSTG) = B2ROT*DEGRAD
BIN_ROW2(NSTG) = ATAN( TAN(BOUT_ROW1(NSTG)) + 1.0/PHI(NSTG))
BOUT_ROW2(NSTG) = ATAN( TAN(BIN_ROW1(NSTG)) + 1.0/PHI(NSTG))
REACN(NSTG) =
& -0.5*PHI(NSTG)*(TAN(BIN_ROW1(NSTG)) + TAN(BOUT_ROW1(NSTG)))
PSI(NSTG) =
& -2*(1.0 - REACN(NSTG) - PHI(NSTG)*TAN(BIN_ROW2(NSTG)))
WRITE(6,*) BIN_ROW1(NSTG)*RADDEG, BOUT_ROW1(NSTG)*RADDEG,
& BIN_ROW2(NSTG)*RADDEG, BOUT_ROW2(NSTG)*RADDEG
WRITE(6,*) ' REACTION= ', REACN(NSTG), ' LOADING = ', PSI(NSTG)
END IF
C END OF INTYPE = "C" OPTION.
END IF
C
C**************************************************************************************
C**************************************************************************************
C
IF(INTYPE.EQ.'D') THEN
WRITE(6,*) 'INPUT TYPE "D" CHOSEN.'
C
IF(TURBO_TYP.EQ.'T') WRITE(6,*) ' THIS IS A TURBINE.'
IF(TURBO_TYP.EQ.'C') WRITE(6,*) ' THIS IS A COMPRESSOR.'
WRITE(6,*)
WRITE(6,*)' INPUT THE FIRST BLADE ROW INLET ANGLE, THE FIRST BLADE
& ROW EXIT ANGLE AND THE STAGE REACTION.'
READ(5,*) BIN_ROW1(NSTG), BOUT_ROW1(NSTG), REACN(NSTG)
WRITE(10,114) BIN_ROW1(NSTG), BOUT_ROW1(NSTG), REACN(NSTG)
114 FORMAT(3F12.3,T25,' FIRST ROW ANGLES, REACTION')
BIN_ROW1(NSTG) = BIN_ROW1(NSTG)*DEGRAD
BOUT_ROW1(NSTG) = BOUT_ROW1(NSTG)*DEGRAD
C
IF(TURBO_TYP.EQ.'T') THEN
PHI(NSTG) =
& 2*(1.0-REACN(NSTG))/(TAN(BIN_ROW1(NSTG)) + TAN(BOUT_ROW1(NSTG)))
BIN_ROW2(NSTG) = ATAN( TAN(BOUT_ROW1(NSTG)) - 1.0/PHI(NSTG))
BOUT_ROW2(NSTG) = ATAN( TAN(BIN_ROW1(NSTG)) - 1.0/PHI(NSTG))
PSI(NSTG) =
7 2*(1.0 - REACN(NSTG) - PHI(NSTG)*TAN(BIN_ROW1(NSTG)))
WRITE(6,*) BIN_ROW1(NSTG)*RADDEG, BOUT_ROW1(NSTG)*RADDEG,
& BIN_ROW2(NSTG)*RADDEG, BOUT_ROW2(NSTG)*RADDEG
WRITE(6,*) ' PHI= ', PHI(NSTG), ' LOADING = ', PSI(NSTG)
END IF
C
IF(TURBO_TYP.EQ.'C') THEN
PHI(NSTG) =
& -2*REACN(NSTG)/(TAN(BIN_ROW1(NSTG)) + TAN(BOUT_ROW1(NSTG)))
BIN_ROW2(NSTG) = ATAN( TAN(BOUT_ROW1(NSTG)) + 1.0/PHI(NSTG))
BOUT_ROW2(NSTG) = ATAN( TAN(BIN_ROW1(NSTG)) + 1.0/PHI(NSTG))
PSI(NSTG) =
& -2*(1.0 - REACN(NSTG) - PHI(NSTG)*TAN(BIN_ROW2(NSTG)))
WRITE(6,*) BIN_ROW1(NSTG)*RADDEG, BOUT_ROW1(NSTG)*RADDEG,
& BIN_ROW2(NSTG)*RADDEG, BOUT_ROW2(NSTG)*RADDEG
WRITE(6,*) ' PHI= ', PHI(NSTG), ' LOADING = ', PSI(NSTG)
END IF
C END OF INTYPE = "D" OPTION.
END IF
C
C*********************************************************************************
C*********************************************************************************
C
C NEXT SET THE ROTATIONAL SPEED AND DESIGN RADIUS. FOR FLO_TYP = "AXI" .
C
C*********************************************************************************
C*********************************************************************************
C
WRITE(6,*)
WRITE(6,*) ' YOU MAY SET THE DESIGN RADIUS IN ONE OF 2 WAYS'
WRITE(6,*)
WRITE(6,*) ' METHOD "A". INPUT THE DESIGN RADIUS DIRECTLY.'
WRITE(6,*) ' METHOD "B". INPUT STAGE ENTHALPY CHANGE.'
WRITE(6,*)
WRITE(6,*) ' CHOOSE METHOD "A" OR "B".'
WRITE(6,*) ' TYPE IN "A" or "B". '
WRITE(6,*)
READ(5,*) RADTYPE
IF(RADTYPE.EQ.'a') RADTYPE = 'A'
IF(RADTYPE.EQ.'b') RADTYPE = 'B'
WRITE(6,*) ' RADTYPE = ', RADTYPE
WRITE(10,115) RADTYPE
115 FORMAT(A1,T25,' RADTYPE, TO CHOOSE THE DESIGN POINT RADIUS')
C
IF(RADTYPE.EQ.'A') THEN
WRITE(6,*) ' INPUT THE DESIGN RADIUS IN METRES.'
READ(5,*) RDES(NSTG)
WRITE(6,*) ' DESIGN POINT RADIUS =', RDES(NSTG)
WRITE(10,116) RDES(NSTG)
116 FORMAT(F12.3,T25, ' THE DESIGN POINT RADIUS ')
U(NSTG) = RDES(NSTG)*OMEGA
DHO(NSTG) = PSI(NSTG)*U(NSTG)*U(NSTG)
END IF
C
IF(RADTYPE.EQ.'B') THEN
WRITE(6,*) ' INPUT THE STAGE ACTUAL ENTHALPY CHANGE IN KJ/Kg. '
WRITE(6,*) ' THE ENTHALPY CHANGE IS ALWAYS TREATED AS POSITIVE.'
READ(5,*) DHO(NSTG)
WRITE(6,*) DHO(NSTG)
WRITE(10,117) DHO(NSTG)
117 FORMAT(F12.3,T25, ' STAGE ENTHALPY CHANGE, KJ/Kg')
DHO(NSTG) = 1000.0*DHO(NSTG)
U(NSTG) = SQRT(DHO(NSTG)/PSI(NSTG))
RDES(NSTG) = U(NSTG)/OMEGA
END IF
C
IF(TURBO_TYP.EQ.'T') DHO(NSTG) = -DHO(NSTG)
C
C********************************************************************************
C********************************************************************************
C
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
WRITE(6,*)
WRITE(6,*) ' STAGE NUMBER. ', NSTG
WRITE(6,*) ' INPUT THE FIRST AND SECOND BLADE ROW AXIAL CHORDS IN
& METRES '
WRITE(6,*) ' THE CURRENT VALUES ARE ', AXCHRD1(NSTG),AXCHRD2(NSTG)
WRITE(6,*) ' Press A to accept these, or type in new values.'
READ(5,*,ERR=20,END=20) AXCHRD1(NSTG),AXCHRD2(NSTG)
20 WRITE(6,*) ' STATOR AND ROTOR AXIAL CHORDS ARE ',
& AXCHRD1(NSTG),AXCHRD2(NSTG)
WRITE(10,120) AXCHRD1(NSTG),AXCHRD2(NSTG)
120 FORMAT(2F12.3,T25, ' BLADE AXIAL CHORDS IN METRES.')
WRITE(6,*)
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
C
C********************************************************************************
C********************************************************************************
C
WRITE(6,*) ' INPUT THE INTER ROW GAP AND INTER STAGE GAP AS FRACTI
&ONS OF THE FIRST ROW AXIAL CHORD '
WRITE(6,*) ' THE CURRENT VALUES ARE ', ROWGAP(NSTG),STAGEGAP(NSTG)
WRITE(6,*) ' Press A to accept these, or type in new values.'
READ(5,*,ERR=218,END=218) ROWGAP(NSTG), STAGEGAP(NSTG)
218 CONTINUE
WRITE(6,*) ' ROWGAP =', ROWGAP(NSTG),'STAGEGAP = ', STAGEGAP(NSTG)
WRITE(10,119) ROWGAP(NSTG),STAGEGAP(NSTG)
119 FORMAT(2F12.3,T25,' ROW GAP AND STAGE GAP ')
WRITE(6,*)
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
C
C*****************************************************************************
C*****************************************************************************
C JUMP TO HERE IF IFSAME_ALL = "Y" .
C SET THE AXIAL POSITIONS OF THE BLADES FOR IN_TYPE = "AXI" .
C
600 CONTINUE
C
IF(NSTG.EQ.1) THEN
XMEAN(1) = -1.0*AXCHRD1(NSTG)
XMEAN(2) = -0.5*AXCHRD1(NSTG)
XMEAN(3) = 0.0
XMEAN(4) = XMEAN(3) + AXCHRD1(NSTG)
XMEAN(5) = XMEAN(4) + 0.5*ROWGAP(NSTG)*AXCHRD1(NSTG)
XMEAN(6) = XMEAN(4) + ROWGAP(NSTG)*AXCHRD1(NSTG)
XMEAN(7) = XMEAN(6) + AXCHRD2(NSTG)
XMEAN(8) = XMEAN(7) + 0.5*STAGEGAP(NSTG)*AXCHRD2(NSTG)
XMEAN(9) = XMEAN(7) + STAGEGAP(NSTG)*AXCHRD2(NSTG)
IF(NSTG.EQ.NSTAGES) XMEAN(8) = XMEAN(7) + 0.5*AXCHRD2(NSTG)
IF(NSTG.EQ.NSTAGES) XMEAN(9) = XMEAN(7) + AXCHRD2(NSTG)
ELSE
C
C SET THE LOCATION OF THE FIRST POINT IF THE INPUT TYPE HAS BEEN CHANGED FROM "MIX" TO "AXI"
XMEAN1 = XMEAN(7)
IF(IFSAME_ALL.EQ.'C') XMEAN1 = XMEANTE
C
XMEAN(1) = XMEAN1 + 0.333*STAGEGAP(NSTG)*AXCHRD1(NSTG)
XMEAN(2) = XMEAN1 + 0.667*STAGEGAP(NSTG)*AXCHRD1(NSTG)
XMEAN(3) = XMEAN1 + STAGEGAP(NSTG)*AXCHRD1(NSTG)
XMEAN(4) = XMEAN(3) + AXCHRD2(NSTG)
XMEAN(5) = XMEAN(4) + 0.5*ROWGAP(NSTG)*AXCHRD2(NSTG)
XMEAN(6) = XMEAN(4) + ROWGAP(NSTG)*AXCHRD2(NSTG)
XMEAN(7) = XMEAN(6) + AXCHRD2(NSTG)
XMEAN(8) = XMEAN(7) + 0.5*STAGEGAP(NSTG)*AXCHRD2(NSTG)
XMEAN(9) = XMEAN(8) + STAGEGAP(NSTG)*AXCHRD2(NSTG)
IF(NSTG.EQ.NSTAGES) XMEAN(8) = XMEAN(7) + 0.5*AXCHRD2(NSTG)
IF(NSTG.EQ.NSTAGES) XMEAN(9) = XMEAN(7) + AXCHRD2(NSTG)
C
END IF
C
DO N=1,8
RMEAN(N) = RDES(NSTG)
VMRAT(N) = 1.0
END DO
C
NSS = 8
NLE1 = 3
NTE1 = 4
NLE2 = 6
NTE2 = 7
PHI_REF = PHI(NSTG)
C
WRITE(6,*)
WRITE(6,*) ' MEAN LINE COORDINATES, STAGE NUMBER',NSTG
WRITE(6,*) ' XMEAN ',(XMEAN(N),N=1,NSS)
WRITE(6,*) ' RMEAN ',(RMEAN(N),N=1,NSS)
WRITE(6,*) ' VMRAT ',(VMRAT(N),N=1,NSS)
WRITE(6,*)
WRITE(6,*) 'NLE1,NTE1,NLE2,NTE2', NLE1,NTE1,NLE2,NTE2
WRITE(6,*)
C
C**********************************************************************************
C**********************************************************************************
C GO TO 3000 IF FLO_TYP = "AXI"
C
GO TO 3000
C
C********************************************************************************
C********************************************************************************
C RE ENTER HERE IF FLO_TYP = "MIX"
C
2000 CONTINUE
C
C*********************************************************************************
C*********************************************************************************
C********************************************************************************
C********************************************************************************
C NOW INPUT DATA FOR FLO_TYP = "MIX" .
C
C*********************************************************************************
C*********************************************************************************
WRITE(6,*)' FOR FLO_TYP= "MIX" YOU HAVE A CHOICE OF TWO INPUT METH
&ODS'
WRITE(6,*)
WRITE(6,*)' EITHER INPUT ALL 4 BLADE ANGLES.'
WRITE(6,*)
WRITE(6,*)'OR'
WRITE(6,*)
WRITE(6,*)'INPUT THE ABSOLUTE FLOW ANGLES AT STAGE INLET AND EXIT'
WRITE(6,*)'AND THE FLOW COEFFICIENT AND STAGE LOADING COEFFICIENT'
WRITE(6,*)
WRITE(6,*)' INPUT "A" FOR THE FIRST METHOD, "B" FOR THE SECOND'
READ(5,*) MIXTYP
WRITE(10,410) MIXTYP
410 FORMAT(A1,T25,' MIXTYP = INPUT TYPE FOR FLO_TYP = "MIX" .')
IF(MIXTYP.EQ.'a') MIXTYP = 'A'
IF(MIXTYP.EQ.'b') MIXTYP = 'B'
C
C********************************************************************************
C********************************************************************************
C
IF(MIXTYP.EQ.'A') THEN
C
WRITE(6,*) ' INPUT THE STATOR INLET AND EXIT FLOW ANGLES, IN DEG.'
READ(5,*) STATOR_IN, STATOR_OUT
WRITE(10,411) STATOR_IN, STATOR_OUT
411 FORMAT(2F10.3,T25,' ANGLES, STATOR_IN, STATOR_OUT')
C
WRITE(6,*)
WRITE(6,*) ' INPUT THE ROTOR INLET AND EXIT RELATIVE FLOW ANGLES,
& IN DEGREES.'
READ(5,*) ROTOR_IN, ROTOR_OUT
WRITE(10,412) ROTOR_IN, ROTOR_OUT
412 FORMAT(2F10.3,T25,'ANGLES, ROTOR_IN, ROTOR_OUT')
C
IF(TURBO_TYP.EQ.'C') THEN
BIN_ROW1(NSTG) = ROTOR_IN*DEGRAD
BOUT_ROW1(NSTG) = ROTOR_OUT*DEGRAD
BIN_ROW2(NSTG) = STATOR_IN*DEGRAD
BOUT_ROW2(NSTG) = STATOR_OUT*DEGRAD
PHI_STG1 = 1.0/(TAN(BIN_ROW2(NSTG))
& - TAN(BOUT_ROW1(NSTG)))
ELSE
BIN_ROW1(NSTG) = STATOR_IN*DEGRAD
BOUT_ROW1(NSTG) = STATOR_OUT*DEGRAD
BIN_ROW2(NSTG) = ROTOR_IN*DEGRAD
BOUT_ROW2(NSTG) = ROTOR_OUT*DEGRAD
PHI_STG1 = 1.0/(TAN(BOUT_ROW1(NSTG))
& - TAN(BIN_ROW2(NSTG)))
END IF
C
C END OF MIXTYP = "A" LOOP.
END IF
C********************************************************************************
C********************************************************************************
C********************************************************************************
C********************************************************************************
IF(MIXTYP.EQ.'B') THEN
C
IF(NSTG.EQ.1) THEN
WRITE(6,*)
WRITE(6,*) ' INPUT THE FLOW COEFFICIENT AT THE FIRST ROTOR LEADING
& EDGE.'
READ(5,*) PHI_REF
WRITE(10,82) PHI_REF
82 FORMAT(F10.4,T25,
& ' FLOW COEFFICIENT AT THE FIRST ROTOR LEADING EDGE.')
WRITE(6,*) ' FLOW COEFFICIENT = ', PHI_REF
WRITE(6,*)
END IF
C
C********************************************************************************
C********************************************************************************
C
WRITE(6,*) ' INPUT THE INLET AND EXIT ABSOLUTE FLOW ANGLES FOR THE
& WHOLE STAGE.'
READ(5,*) ALPHA_IN(NSTG), ALPHA_OUT(NSTG)
WRITE(10,81) ALPHA_IN(NSTG), ALPHA_OUT(NSTG)
81 FORMAT(2F10.3,T25,' STAGE INLET AND OUTLET ABSOLUTE FLOW ANGLES.')
WRITE(6,*) ' STAGE INLET & EXIT ANGLES',
& ALPHA_IN(NSTG), ALPHA_OUT(NSTG)
ALPHA_IN(NSTG) = ALPHA_IN(NSTG)*DEGRAD
ALPHA_OUT(NSTG) = ALPHA_OUT(NSTG)*DEGRAD
C
C********************************************************************************
C********************************************************************************
C
WRITE(6,*)
WRITE(6,*)' INPUT THE STAGE LOADING COEFFICIENT BASED ON THE BLADE
& SPEED AT THE ROTOR LEADING EDGE '
READ(5,*) PSI(NSTG)
WRITE(10,83) PSI(NSTG)
83 FORMAT(F10.4,T25, ' STAGE LOADING COEFFICIENT AT THE ROTOR LEADING
& EDGE.')
WRITE(6,*) ' STAGE LOADING COEFFICIENT = ', PSI(NSTG)
C
C END OF MIXTYP = "B" LOOP.
END IF
C
C**********************************************************************************
C**********************************************************************************
C**********************************************************************************
C**********************************************************************************
C RE ENTER HERE IF FLO_TYP = "MIX" AND THE ANGLES, ETC,
C WERE THE SAME AS FOR THE LAST STAGE.
C
700 CONTINUE
C**********************************************************************************
C**********************************************************************************
C NOW INPUT THE STREAM SURFACE COORDINATES. FOR FLO_TYP = "MIX" .
C
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
WRITE(6,*)' THE STREAM SURFACE COORDINATES AND MERIDIONAL VELOCITY
& RATIOS MUST NOW BE INPUT '
C
WRITE(6,*)
WRITE(6,*) ' THE NEW VALUES MUST FORM A SMOOTH CONTINUATION OF
& THE LAST STREAM SURFACE '
WRITE(6,*)
WRITE(6,*)'******************************************************'
WRITE(6,*)'******************************************************'
C
WRITE(6,*)
WRITE(6,*)'INPUT THE NUMBER OF POINTS ON THE MEAN STREAM SURFACE'
IF(NSTG.GT.1) THEN
WRITE(6,*)'LAST NSS = ', NSS
WRITE(6,*)'PRESS "A" TO ACCEPT THE PREVIOUS VALUE OR TYPE IN A NEW
& VALUE'
END IF
READ(5,*,ERR=134) NSS
134 CONTINUE
WRITE(6,*) ' NSS = ', NSS
C
WRITE(6,*)
WRITE(6,*) 'INPUT ',NSS, ' AXIAL COORDINATES OF THE MEAN SS '
IF(NSTG.GT.1) THEN
WRITE(6,*) 'LAST XMEAN = ', (XMEAN(NP),NP=1,NSS )
WRITE(6,*) 'PRESS "A" TO ACCEPT THE PREVIOUS VALUES OR TYPE IN NEW
& VALUES'
END IF
IF(ANSIN.EQ.'F') READ(5,*) DUMMY_LINE
READ(5,*,ERR=135) (XMEAN(NP),NP=1,NSS)
135 CONTINUE
WRITE(6,*) ' XMEAN=',(XMEAN(NP),NP=1,NSS )
C
WRITE(6,*)
WRITE(6,*)' INPUT ',NSS, ' RADIAL COORDINATES OF THE MEAN SS '
IF(NSTG.GT.1) THEN
WRITE(6,*)' LAST RMEAN = ', (RMEAN(NP),NP=1,NSS )
WRITE(6,*)' PRESS "A" TO ACCEPT THE PREVIOUS VALUES OR TYPE IN NEW
& VALUES.'
END IF
IF(ANSIN.EQ.'F') READ(5,*) DUMMY_LINE
READ(5,*,ERR=136) (RMEAN(NP),NP=1,NSS )
136 CONTINUE
WRITE(6,*) ' RMEAN=',(RMEAN(NP),NP=1,NSS )
C
WRITE(6,*)
WRITE(6,*) ' INPUT ',NSS, ' MERIDIONAL VELOCITY RATIOS ON THE MEAN
& STREAM SURFACE.'
WRITE(6,*)' THESE ARE RELATIVE TO THE VALUE AT THE LEADING EDGE OF
& THE FIRST ROTOR.'
IF(NSTG.GT.1) THEN
WRITE(6,*) 'LAST VMRAT = ', (VMRAT(NP),NP=1,NSS )
WRITE(6,*) 'PRESS "A" TO ACCEPT THE PREVIOUS VALUES OR TYPE IN NEW
& VALUES'
END IF
IF(ANSIN.EQ.'F') READ(5,*) DUMMY_LINE
READ(5,*,ERR=137) (VMRAT(NP),NP=1,NSS )
137 CONTINUE
WRITE(6,*) ' VMRAT=', (VMRAT(NP),NP=1,NSS )
C
WRITE(6,*)
WRITE(6,*) ' INPUT THE POINT NUMBERS OF THE LEADING AND TRAILING
& EDGES, 4 POINTS IN TOTAL.'
IF(NSTG.GT.1) THEN
WRITE(6,*) ' THE PREVIOUS VALUES WERE ',NLE1,NTE1,NLE2,NTE2
WRITE(6,*) ' PRESS "A" TO ACCEPT THESE OR TYPE IN NEW VALUES'
END IF
READ(5,*,ERR = 139) NLE1,NTE1,NLE2,NTE2
139 CONTINUE
WRITE(6,*) ' NLE1,NTE1,NLE2,NTE2 ', NLE1,NTE1,NLE2,NTE2
WRITE(6,*)
C
WRITE(6,*)
WRITE(6,*)' NEW XMEAN = ', (XMEAN(NP),NP=1,NSS )
WRITE(6,*) ' NEW RMEAN = ', (RMEAN(NP),NP=1,NSS )
WRITE(6,*) ' NEW VMRAT = ', (VMRAT(NP),NP=1,NSS )
WRITE(6,*) ' NEW NLE1,ETC', NLE1,NTE1,NLE2,NTE2
C
C SET THE LAST POINT COORDINATES FOR USE IF CHANGING FROM "MIX" TO "AXI"
XMEANTE = XMEAN(NTE2)
WRITE(6,*) ' SETTING XMEANTE = ', XMEANTE
C
C
ANSSS = 'N'
WRITE(6,*) ' DO YOU WANT TO CHANGE THE NEW STREAM SURFACE COORDINA
&TES ? '