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CCMD_Backup_July26th.F90
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! Last Update: June 27th, 2013
PROGRAM MEANLINE
!VARIABLE DECLARTIONS
IMPLICIT DOUBLE PRECISION (a-h,l,o-z)
IMPLICIT INTEGER (i-k,m,n)
PARAMETER (ncmax=20) !max number of components in mixture
DIMENSION x(ncmax),xliq(ncmax),xvap(ncmax),f(ncmax)
CHARACTER hrf*3, herr*255, OutFile*30, a*54
CHARACTER*255 hf(ncmax)
CHARACTER*7 hfmix
COMMON / Constant / PI, Target_PR, isteps, iPerformance,iAir,iCarbonDioxide, iDiffAnalysis, iVoluteAnalysis
COMMON / Geometric / r1h, r1s, r1m, r2, r3, r4, r6, A1, A2, tb1, tb, b1, b2, b3, b4, b6, &
LbImpeller, TipClearance, RoughnessImp, &
iFull, iSplitter, LbSplitter, Z, Lb, DeltaZ, CurveKm1, FlowCoefficient
COMMON / Geometric2 / r1h_min, r1h_max, r1s_min, r1s_max, r2_min, r2_max
COMMON / Velocity / U1, U2, C1, C2, Cu1, Cu2, Cm1, Cr2, W1, W2, W1s, W1h, Wu2
COMMON / Properties / Visc1, Visc2, zMdot, N, MaxIter, m, isolution,iDiffSteps
COMMON / Thermodynamic / rho01, rho02, rho1, rho2, P01, P1, P02, P2, T01, T2, T1
COMMON / FlowAngles / Beta1Prime, Alpha1, Alpha2, DiffuserLossFactor, VoluteLossFactor
COMMON / BladeAngles / Beta1, Beta2, Beta2m, Beta2guess
COMMON / Losses / LossesInternal, LossesParasitic, cf, Sigma, ShockLoss, LossIncidence, &
DiffusionLoss, ChokingLoss, BladeLoadingLoss, HSLoadingLoss, &
SkinFrictionLoss, TipClearanceLoss, LossMixing, SupercritMachNumberLoss
!INITIALIZE VARIABLES
MaxIter = 500
PI = 3.1415926535898
WRITE(*,*)" CENTRIFUGAL COMPRESSOR MEANLINE DESIGN"
WRITE(*,*)" "
WRITE(*,*)" CC"
WRITE(*,*)" CC CCC"
WRITE(*,*)" C CCCCCCCC"
WRITE(*,*)" CCCCCCCCCC DDDD"
WRITE(*,*)" CCCCCCCCCC DDDDDDD"
WRITE(*,*)" CCCCCCCCCC MMM DDDDDDDD"
WRITE(*,*)" CCCCCCCCC MMMMMMM DDDDDDDD"
WRITE(*,*)" CCCCCCCCC MMMMMMMMMMM DDDDDDDDD"
WRITE(*,*)" CCCCCCCCC MMMMMMMMMMMMM DDDDDDDDD"
WRITE(*,*)" CCCCCCCCC MMMMMMMMMMMMM DDDDDDDDD"
WRITE(*,*)" CCCCCCCCC MMMMMMMMMMMMM DDDDDDDDD"
WRITE(*,*)" CCCCCCCCC MMMMMMMMMMM DDDDDDDDD"
WRITE(*,*)" CCCCCCCCC MMMMMMM DDDDDDDDDD"
WRITE(*,*)" CCCCCCCCC MMM DDDDDDDDDD"
WRITE(*,*)" CCCCCCCC DDDDDDDDDDD"
WRITE(*,*)" CCCCC DDDDDDDDDDD"
WRITE(*,*)" DDDDDDDD D"
WRITE(*,*)" DDD DD "
WRITE(*,*)" DD "
WRITE(*,*)" "
WRITE(*,*)" CARLETON UNIVERSITY GAS TURBINE PROJECT"
WRITE(*,*)" ...Press Enter To Begin..."
READ(*,*)
!MUST Be Named CompressorDimensions With .txt Extension
OPEN(UNIT=20,FILE='CompressorDimensions.txt',STATUS='OLD')
DO iread=1,48
READ(20,*)
END DO
!Read File Formatting (A = Character String, Field Width = 54)
12 FORMAT (A54,I8) !I = Integer, Field Width = 8
13 FORMAT (A54,F14.7) !F = Real, Field Width = 14, and 7 Decimal Places9
14 FORMAT (A54,I3) !I = Integer, Field Width = 2
!Read Rotor Dimensions From Text File
READ(20,14) a,iAir
READ(20,14) a,iCarbonDioxide
READ(20,*)
READ(20,*)
READ(20,*)
READ(20,13) a,Target_PR
READ(20,12) a,N
READ(20,13) a,zMdot
READ(20,13) a,T01
READ(20,13) a,P01
READ(20,*)
READ(20,13) a,r2
!READ(20,13) a,LbImpeller
READ(20,13) a,LbSplitter
!READ(20,13) a,Lb
READ(20,13) a,tb1!Inlet Blade Thickness
READ(20,13) a,tb!Outlet Blade Thickness
READ(20,13) a,RoughnessImp
READ(20,13) a,TipClearance
READ(20,13) a,Alpha1
READ(20,13) a,CurveKm1
READ(20,*)
READ(20,14) a,iDiffAnalysis
READ(20,13) a,r4
READ(20,13) a,b4
READ(20,14) a,iVoluteAnalysis
READ(20,13) a,VoluteLossFactor
READ(20,13) a,r6
READ(20,13) a,b6
READ(20,*)
READ(20,*)
READ(20,*)
READ(20,*)
READ(20,14) a,iStep1!Check if 0
READ(20,*)
READ(20,13) a,r1h
READ(20,13) a,r1s
READ(20,13) a,b2
READ(20,*)
READ(20,14) a,iStep2!Check if 0
READ(20,*)
READ(20,14) a,iFull
READ(20,14) a,iSplitter
READ(20,*)
READ(20,14) a,iTPcond!Check if 0
READ(20,*)
READ(20,14) a,iSteps
READ(20,14) a,iDiffSteps
CLOSE(20)
!For Debugging The Inputs:
!WRITE(*,*) iAir
!WRITE(*,*) iCarbonDioxide
!WRITE(*,*)
!WRITE(*,*)
!WRITE(*,*)
!WRITE(*,*) Target_PR
!WRITE(*,*) N
!WRITE(*,*) zMdot
!WRITE(*,*) T01
!WRITE(*,*) P01
!WRITE(*,*)
!WRITE(*,*) r2
!WRITE(*,*) LbImpeller
!WRITE(*,*) LbSplitter
!WRITE(*,*) Lb
!WRITE(*,*) tb1!Inlet Blade Thickness
!WRITE(*,*) tb!Outlet Blade Thickness
!WRITE(*,*) RoughnessImp
!WRITE(*,*) TipClearance
!WRITE(*,*) Alpha1
!WRITE(*,*)
!WRITE(*,*) iDVAnalysis
!WRITE(*,*) DiffuserLossFactor
!WRITE(*,*) r4
!WRITE(*,*) b4
!WRITE(*,*) VoluteLossFactor
!WRITE(*,*) r6
!WRITE(*,*) b6
!WRITE(*,*)
!WRITE(*,*)
!WRITE(*,*)
!WRITE(*,*)
!WRITE(*,*)
!WRITE(*,*) r1h!Check if 0
!WRITE(*,*) r1h_min
!WRITE(*,*) r1h_max
!WRITE(*,*)
!WRITE(*,*)
!WRITE(*,*) r1s!Check if 0
!WRITE(*,*) r1s_min
!WRITE(*,*) r1s_max
!WRITE(*,*)
!WRITE(*,*)
!WRITE(*,*) iFull!Check if 0
!WRITE(*,*) iFull_Min
!WRITE(*,*) iFull_Max
!WRITE(*,*)
!WRITE(*,*)
!WRITE(*,*) iSplitter
!WRITE(*,*) iSplitter_Min
!WRITE(*,*) iSplitter_Max
!WRITE(*,*)
!WRITE(*,*)
!WRITE(*,*) DeltaZ!Check if 0
!WRITE(*,*) DeltaZ_Min
!WRITE(*,*) DeltaZ_Max
!WRITE(*,*)
!WRITE(*,*)
!WRITE(*,*) b2!Check if 0
!WRITE(*,*) b2_Min
!WRITE(*,*) b2_Max
!WRITE(*,*)
!WRITE(*,*) isteps
!READ(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*) 'Input Design Flow Coefficient:'
READ (*,*) FlowCoefficient
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*) 'Please Enter Output File Name (i.e. ConceptOne.txt):'
READ (*,*) Outfile
OPEN(UNIT=10,FILE=OutFile,STATUS='NEW')
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*)
WRITE(*,*) "Calculating Compressor Performance..."
m = 0
!~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
! FULL ROTOR PERFORMANCE ANALYSIS
!~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
IF (iStep1 == 0 .AND. iStep2 == 0 .AND. iTPCond == 0) THEN
iPerformance = 0
WRITE(10,*) ' Carleton University'
WRITE(10,*) ' Department of Mechanical and Aerospace Engineering'
WRITE(10,*) ' COMPRESSOR PERFORMANCE ANALYSIS RESULTS'
WRITE(10,*) ' Gas Turbine Project'
WRITE(10,*)
CALL PERFORMANCE()
CLOSE(10)
WRITE(*,*)
WRITE(*,*) "Analysis Complete! Please See Results File."
WRITE(*,*) "Press Any Key To Continue..."
READ(*,*)
END IF
!~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
! INLET OPTIMIZATION CHOSEN
!~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
IF (iStep1 == 1 .AND. iStep2 == 0 .AND. iTPCond == 0) THEN
r1h_min = r2*0.05
r1h_max = r2*0.5
r1s_min = r1h_min*1.1
r1s_max = r2*0.7
b2_min = (r1s_min - r1h_min)*0.5
b2_max = (r1s_max - r1h_min)*0.5
step3 = (b2_max - b2_min)/isteps
r1h = r1h_min
m3 = 0
isolution = 0
iPerformance = 1
WRITE(10,*) ' Carleton University'
WRITE(10,*) ' Department of Mechanical and Aerospace Engineering'
WRITE(10,*) ' INLET OPTIMIZATION DATA'
WRITE(10,*) ' Gas Turbine Project'
WRITE(10,*) '~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~'
WRITE(10,*) 'r1h r1s b2 M1_tip M2_rel dH_m Flow Co. Work Co. Efficiency'
DO WHILE (b2 <= b2_max)
b2 = b2_min + step3*m3
m3 = m3 + 1
m2 = 0
DO WHILE (r1s <= r1s_max)
r1s_min = r1h * 1.1
step2 = ((r1s_max-r1s_min)/isteps)
r1s = r1s_min + step2*m2
m2 = m2 + 1
m = 0
DO WHILE (r1h <= r1h_max)
r1h_max = r1s * 0.9
step = ((r1h_max-r1h_min)/isteps)
r1h = r1h_min + step*m
m = m + 1
isolution = isolution + 1
CALL PERFORMANCE()
END DO
r1h = r1h_min
r1h_max = r2*0.5
END DO
r1s = r1s_min
END DO
CLOSE(10)
WRITE(*,*)
WRITE(*,*) "Analysis Complete! Please See Results File."
WRITE(*,*) "Press Any Key To Continue..."
READ(*,*)
r1h=0
END IF
!~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
! NUMBER OF FULL BLADES CHOSEN
!~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
IF (iStep1 == 0 .AND. iStep2 == 1 .AND. iTPCond == 0) THEN
iPerformance = 2
WRITE(10,*) ' Carleton University'
WRITE(10,*) ' Department of Mechanical and Aerospace Engineering'
WRITE(10,*) ' NUMBER OF FULL BLADES ANALYSIS'
WRITE(10,*) ' Gas Turbine Project'
WRITE(10,*) '~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~'
WRITE(10,*) '#Blades M1_tip M2_rel dH_tip dH_hub dH_m Flow Co. Work Co. Efficiency Beta2'
iFull = 5
iFull_Max = 35
DO WHILE (iFull <= iFull_max)
CALL PERFORMANCE()
iFull = iFull + 1
END DO
CLOSE(10)
WRITE(*,*)
WRITE(*,*) "Analysis Complete! Please See Results File."
WRITE(*,*) "Press Any Key To Continue..."
READ(*,*)
iFull=0
END IF
!~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
! INLET CONDITIONS CHOSEN
!~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
IF (iStep1 == 0 .AND. iStep2 == 0 .AND. iTPCond == 1) THEN
iPerformance = 3
WRITE(10,*) ' Carleton University'
WRITE(10,*) ' Department of Mechanical and Aerospace Engineering'
WRITE(10,*) ' OUTLET PASSAGE WIDTH ANALYSIS'
WRITE(10,*) ' Gas Turbine Project'
WRITE(10,*) '~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~'
WRITE(10,*) ' T01 P01 M2_rel dH_tip dH_hub dH_m Flow Coeff. Work Co. Efficiency'
Tc = 304.25
Pc = 7380.0
T01max = T01
P01max = P01
!Step Sizes
PStep = (P01 - Pc)/isteps
TStep = (T01 - Tc)/isteps
inewsteps = isteps + 5
DO m=0,inewsteps
T01 = T01max - m*TStep
P01 = P01max - m*PStep
CALL PERFORMANCE()
END DO
CLOSE(10)
WRITE(*,*)
WRITE(*,*) "Analysis Complete! Please See Results File."
WRITE(*,*) "Press Any Key To Continue..."
READ(*,*)
END IF
END PROGRAM MEANLINE
!~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
! SUBROUTINE: Meanline Performance Analysis
!~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
SUBROUTINE PERFORMANCE()
IMPLICIT DOUBLE PRECISION (a-h,l,o-z)
IMPLICIT INTEGER (i-k,m,n)
PARAMETER (ncmax=20) !max number of components in mixture
DIMENSION x(ncmax),xliq(ncmax),xvap(ncmax),f(ncmax)
CHARACTER hrf*3, herr*255, OutFile*30, a*54
CHARACTER*255 hf(ncmax)
CHARACTER*7 hfmix
COMMON / Constant / PI, Target_PR, isteps, iPerformance,iAir,iCarbonDioxide, iDiffAnalysis, iVoluteAnalysis
COMMON / Geometric / r1h, r1s, r1m, r2, r3, r4, r6, A1, A2, tb1, tb, b1, b2, b3, b4, b6, &
LbImpeller, TipClearance, RoughnessImp, &
iFull, iSplitter, LbSplitter, Z, Lb, DeltaZ, CurveKm1, FlowCoefficient
COMMON / Geometric2 / r1h_min, r1h_max, r1s_min, r1s_max, r2_min, r2_max
COMMON / Velocity / U1, U2, C1, C2, Cu1, Cu2, Cm1, Cr2, W1, W2, W1s, W1h, Wu2
COMMON / Properties / Visc1, Visc2, zMdot, N, MaxIter, m, isolution,iDiffSteps
COMMON / Thermodynamic / rho01, rho02, rho1, rho2, P01, P1, P02, P2, T01, T2, T1
COMMON / FlowAngles / Beta1Prime, Alpha1, Alpha2, DiffuserLossFactor, VoluteLossFactor
COMMON / BladeAngles / Beta1, Beta2, Beta2m, Beta2guess
COMMON / Losses / LossesInternal, LossesParasitic, cf, Sigma, ShockLoss, LossIncidence, &
DiffusionLoss, ChokingLoss, BladeLoadingLoss, HSLoadingLoss, &
SkinFrictionLoss, TipClearanceLoss, LossMixing, SupercritMachNumberLoss
!Re-Initialize for unknown black magic reasons
r1m = 0
A1 = 0
A2 = 0
Z = 0
U1 = 0
U1s = 0
U1h = 0
U2 = 0
C1 = 0
C1s = 0
C1h = 0
C2 = 0
Cu1 = 0
Cu2 = 0
Cm1 = 0
Cm1s = 0
Cm1h = 0
Cr2 = 0
W1 = 0
W1s = 0
W1h = 0
W2 = 0
Wu2 = 0
Visc1 = 0
Visc2 = 0
rho01 = 0
rho02 = 0
rho1 = 0
rho2 = 0
P1 = 0
P02 = 0
P2 = 0
T1 = 0
T2 = 0
Beta1prime = 0
Alpha2 = 0
Beta1 = 0
Beta2 = 0
Beta2guess = 0
kbeta = 0
!SETUP & CALL REFPROP for CO2 Properties
IF (iAir == 1) THEN
i=1
hf(1)='AIR.ppf'
hfmix='hmx.bnc'
hrf='DEF'
CALL SETUP (i,hf,hfmix,hrf,ierr,herr)
IF (ierr.ne.0) WRITE (*,*) herr
CALL INFO (1,wm,ttp,tnbp,tc,pc,dc,zc,acf,dip,rgas)
END IF
IF (iCarbonDioxide == 1) THEN
i=1
hf(1)='CO2.fld'
hfmix='hmx.bnc'
hrf='DEF'
CALL SETUP (i,hf,hfmix,hrf,ierr,herr)
if (ierr.ne.0) write (*,*) herr
CALL INFO (1,wm,ttp,tnbp,tc,pc,dc,zc,acf,dip,rgas)
END IF
!VARY ROTOR DIMENSIONS FOR OPTIMIZATION
!ROTOR INLET DIMENSIONS
D1h = r1h*2!m
D1s = r1s*2!m
b1 = r1s - r1h
A1=(PI*(r1s**2)-PI*(r1h**2))!m^2 / Rotor inlet area with blockage
r1m=(0.5*(r1s**2)+0.5*(r1h**2))**0.5!Inlet Meanline Radius (m)
D1=r1m*2
!ROTOR OUTLET DIMENSIONS
D2 = r2*2!Impeller Outlet Tip Diameter (m)
A2=(2*PI*r2-(iFull+iSplitter)*tb)*b2!m^2 / Rotor outlet area with blockage
!DESIGN POINT
CALL TPFLSH (T01,P01,x,d,dl,dv,xliq,xvap,q,e,H01,S01,cv,cp,w,ierr,herr)
R = rgas*1000/wm
rho01=d*wm!kg/m^3
U1=r1m*2*PI*N/60!Blade Speed (m/s)
U2=r2*2*PI*N/60!Blade Speed (m/s)
PRr=Target_PR+0.2!Rotor Pressure Ratio Guess
Effr=0.9!Rotor Isentropic Efficiency Guess
DeltaZ = D2*(0.014 + 0.023*D2/D1h + 1.58*FlowCoefficient) !Empirical estimate from Aungier (2000 pg 113)
!ROTOR INLET
!ROTOR INLET VELOCITY TRIANGLE
!First iteration using stagnation conditions
C1=zMdot/(rho01*A1*COS(Alpha1*PI/180))
last=0
j=0
DO WHILE (ABS((C1 - last)/C1) .GT. 0.0000001)
j=j+1
last=C1
!Stagnation is an isentropic process
H1=H01-(C1**2)*wm/2000!J/mol
S1=S01
CALL HSFLSH (H1,S1,zz,T1,P1,rho1,Dl,Dv,x1,y,q,e,cv,cp,a_1,ierr,herr)
rho1=rho1*wm!kg/m^3
Angle = Alpha1*PI/180
C1=zMdot/(rho1*A1*COS(Angle))!Update C1
IF (j.GT.MaxIter) GOTO 1337
IF (ierr.NE.0) THEN!GOTO 1337
C1 = 28
WRITE(*,*) "Error Flag at Rotor Inlet: ",ierr
WRITE(*,*) "Error String: ",herr
END IF
END DO
CALL TRNPRP (T1,rho1/wm,x1,eta,tcx,ierr,herr)
IF (ierr.NE.0) THEN
WRITE(*,*) "Viscosity Error Flag at Rotor Inlet: ",ierr
WRITE(*,*) "Error String: ",herr
END IF
Visc1=eta/1000000!kg/m*s
!CONVERGED ROTOR INLET VELOCITY TRIANGLES
!Meanline
Cm1 = C1 * COS(Alpha1*PI/180)
Cu1 = C1 * SIN(Alpha1*PI/180)
Wu1 = Cu1 - U1
W1 = SQRT(Wu1**2+Cm1**2)
Beta1 = ATAN(Wu1/Cm1)*(180/PI)
U1m = r1m*2*PI*N/60
zM1rel = W1/a_1
!Shroud
Cm1s = Cm1*(1-CurveKm1*b1/2)!Aungier(2000)
U1s = r1s*2*PI*N/60
Cu1s = Cu1 !Assume Cu1 = Cu1s
Wu1s = Cu1s - U1s
W1s = SQRT(Cm1s**2+Wu1s**2)
C1s = SQRT(Cm1s**2+Cu1s**2)
Beta1s = ATAN(Wu1s/Cm1s)*(180/PI)
zM1rels = W1s/a_1
!Hub
Cm1h = Cm1*(1+CurveKm1*b1/2)!Aungier(2000)
U1h = r1h*2*PI*N/60
Cu1h = Cu1 !Assume Cu1 = Cu1h
Wu1h = Cu1h - U1h
W1h = SQRT(Cm1h**2+Wu1h**2)
C1h = SQRT(Cm1h**2+Cu1h**2)
Beta1h = ATAN(Wu1h/Cm1h)*(180/PI)
zM1relh = W1h/a_1
! IF(zM1rel.GT.1) THEN
! WRITE(*,*) "Inlet is choked at meridional."
! READ(*,*)
! ELSE IF(zM1rels.GT.1) THEN
! WRITE(*,*) "Inlet is choked at tip."
! READ(*,*)
! ELSE IF(zM1relh.GT.1) THEN
! WRITE(*,*) "Inlet is choked at hub."
! READ(*,*)
! END IF
PRrLast =0
k=0
DO WHILE (ABS((PRr - PRrLast)/PRr) .GT. 0.00000001)
k=k+1
PRrLast = PRr
IF (k.GT.MaxIter) GOTO 1337
!~~~~~~~~~~~~~~~~~~~~~~~~~~IMPELLER ANALYIS~~~~~~~~~~~~~~~~~~~~~~~~~~!
!The impeller analysis uses basic turbomachinery principles and
!an optimum set of loss models (Oh et al.) to correct for real effects
!~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~!
kbeta = 0
Beta2last = 100
DO WHILE (ABS((Beta2 - Beta2last)/Beta2) .GT. 0.0000001)
kbeta=kbeta+1
Beta2last = Beta2
IF (kbeta.GT.MaxIter) GOTO 1337
!Estimate of mean camber line length (Currently an input)
IF (ABS(Beta2) > 80 .AND. ABS(Beta2) <= 90) THEN!Prevents divergence
Beta2 = 40
END IF
Lb = (DeltaZ - b2/2) + (D2 - D1)/(2*COS(Beta2*PI/180))!Sjolander
Z = iFull + (LbSplitter/Lb)*iSplitter
!~~~~~~~~~~~~~~~~~~~~~ROTOR OUTLET~~~~~~~~~~~~~~~~~~~!
EffrLast = 0
jEFF = 0
DO WHILE (ABS((Effr-EffrLast)/Effr).GT.0.000001)
jEFF = jEFF+1
EffrLast = Effr
IF (jEFF.GT.MaxIter) GOTO 1337
P02=PRr*P01!kPa
!Ideal (isentropic) compression to P02
S02ideal=S01!J/mol-K
CALL PSFLSH (P02,S02ideal,zz,T02ideal,rho02ideal,Dl,Dv,x,y,q,e,H02ideal,cv,cp,w,ierr,herr)
!Actual total enthalpy at rotor outlet
H02=H01+(H02ideal-H01)/Effr!J/mol
!Actual total conditions at rotor outlet
CALL PHFLSH (P02,H02,zz,T02,rho02,Dl,Dv,x,y,q,e,S02,cv,cp,w,ierr,herr)
rho02=rho02*wm!kg/m^3
!Actual total enthalpy across rotor
DeltaH0Rotor=(H02-H01)*1000/wm!J/kg or m/s
!From the Euler turbine equation
Cu2=(1/U2)*(DeltaH0Rotor+U1*Cu1)!m/s
!ROTOR OUTLET VELOCITY TRIANGLE
!First iteration using stagnation density
Cr2=zMdot/(rho02*A2)
last=0
i=0
C2 = 1
DO WHILE (ABS((C2 - last)/C2) .GT. 0.0000001)
i=i+1
last=C2
C2=SQRT(Cr2**2+Cu2**2)
!Stagnation is an isentropic process
H2=H02-(C2**2)*wm/2000!J/mol
S2=S02
CALL HSFLSH (H2,S2,zz,T2,P2,rho2,Dl,Dv,x2,y,q,e,cv,cp,a_2,ierr,herr)
rho2=rho2*wm!kg/m^3
Cr2=zMdot/(rho2*A2)!Update Cr2
IF (i.GT.MaxIter) GOTO 1337
IF (ierr.NE.0) THEN!GOTO 1337
Cr2 = 15
WRITE(*,*) "Error Flag at Rotor Outlet Meanline: ",ierr
WRITE(*,*) "Error String: ",herr
END IF
END DO
!CONVERGED ROTOR OUTLET VELOCITY TRIANGLE
C2=SQRT(Cr2**2+Cu2**2)
Alpha2=ATAN(Cu2/Cr2)*(180/PI)
Wu2=Cu2-U2
W2=SQRT(Wu2**2+Cr2**2)
Beta2=ATAN(Wu2/Cr2)*(180/PI)
aM2=C2/a_2!Absolute Mach Number
rM2=W2/a_2!Relative Mach Number
CALL TRNPRP (T2,rho2/wm,x2,eta,tcx,ierr,herr)
IF (ierr.NE.0) THEN
WRITE(*,*) "Viscosity Error Flag at Rotor Outlet: ",ierr
WRITE(*,*) "Error String: ",herr
END IF
Visc2 = eta/1000000!kg/m*s
!CALCULATE LOSS MODELS
CALL InternalLosses()
!Calculate Actual Discharge Enthalpy
H02real = H02ideal + LossesInternal*wm/1000
CALL HSFLSH (H02real,S02,zz,T02,P02,rho02,Dl,Dv,x,y,q,e,cv,cp,w,ierr,herr)
Effr = (H02ideal - H01)/(H02real - H01) !Updated Rotor Efficiency
END DO
!ROTOR DEHALLER NUMBER
dHm=W2/W1
dHh=W2/W1h
dHt=W2/W1s
Sigma = 1
SigmaLast = 0
Beta2m = Beta2
!Estimate Metal Angle Based on Slip Factor (Aungier 2000)
DO WHILE (ABS((Sigma-SigmaLast)/Sigma).GT.0.0000001)
!Sigma = 1 - ((PI/Z)*COS(Beta2m*PI/180))/(1-phi*TAN(Beta2m*PI/180))!(Stodola)
!Sigma = 1 - (0.63*PI/Z)/(1-phi*TAN(Beta2m*PI/180))!(Stanitz)
Sigma = 1 - (SQRT(ABS(COS(Beta2m*PI/180)))*SIN(Alpha2*PI/180)/Z**.7)!(Wiesner/Busemann)
SigmaStar = SIN(19+0.2*(Beta2m+90))
E_limit = (Sigma - SigmaStar)/(1 - SigmaStar)
IF (r1m/r2 .GT. E_limit) THEN
Sigma = Sigma*(1 - (((r1m/r2)-E_limit)/(1-E_limit))**(SQRT(ABS(90+Beta2m)/10)))
END IF
SigmaLast = Sigma
phi=Cr2/U2
Cu2i = Cu2/Sigma
Wu2i = Cu2i - U2
Beta2m = ATAN(Wu2i/Cr2)*(180/PI)
Alpha2 = ATAN(Cu2i/Cr2)*(180/PI)
END DO
!FINAL ROTOR OUTLET VELOCITY TRIANGLE (with slip factor)
Cu2= Cu2/Sigma
Wu2 = Cu2 - U2
Beta2m = ATAN(Wu2/Cr2)*180/PI
C2 = SQRT(Cr2**2+Cu2**2)
W2=SQRT(Wu2**2+Cr2**2)
Alpha2=ATAN(Cu2/Cr2)*(180/PI)
workcoeff = (H02real-H01)/(U2**2*wm/1000)
FlowCoeff = zMdot/(rho01*PI*(r2**2)*U2)
RotationalMach = U2/a_2
END DO
!~~~~~~~~~~~~~~~~~~~~IMPELLER PARASITIC LOSSES~~~~~~~~~~~~~~~~~~~~~~~!
! Follows the method overviewed in Aungier (2000)
!~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~!
!~~~~~~~~~~~~~~~ Disk Friction Work (Daily and Nece) ~~~~~~~~~~~~~~~~!
!First determine the flow conditions in the clearance gap as follows:
r_bar = (r1m + r2)/2
b_bar = (b1 + b2)/2
!Average pressure difference across the blade in the clearance gap
Pcl = zMdot*(r2*Cu2-r1m*Cu1)/(Z*r_bar*b_bar*Lb)
!Velocity of the clearance gap leakage flow
Ucl = 0.816*SQRT(2*Pcl/rho2)
!Blade clearance gap leakage mass flow rate for all the blades
clMdot = rho2*Ucl*(Z*TipClearance*Lb)
Tcl = T2!Assume temperature at the rotor outlet is the same as clearance gap
CALL TPFLSH (Tcl,Pcl,x,rhocl,dl,dv,xliq,xvap,q,e,hs,ss,cv,cp,w,ierr,herr)
CALL TRNPRP (Tcl,rhocl,x,eta,tcx,ierr,herr)
IF (ierr.NE.0) THEN
WRITE(*,*) "Viscosity Error Flag for Disk Friction Calc: ",ierr
WRITE(*,*) "Error String: ",herr
END IF
Visc_cl = eta/1000000 !kg/m*s
ReDF = ABS(rho2*U2*r2/Visc_cl)
IF (ReDF.LT.300000) THEN
f_df = 2.67/(ReDF**0.5)
ELSE
f_df = 0.0622/(ReDF**0.2)
END IF
rho_bar = (rho1+rho2)/2
DiskFriction = f_df * rho_bar * r2**2 * U2**3 / (4*zMDot)
!~~~~~~~~~~~~~~~~~~~ Leakage Work (Aungier)~~~~~~~~~~~~~~~~~~~~~~~~~~~!
LeakageWork = clMdot*Ucl*U2/(2*zMdot)!Assuming an open impeller
!~~~~~~~~~~~~~~~~~~~~~~~ Recirculation Work ~~~~~~~~~~~~~~~~~~~~~~~~~~~!
Df = 1-W2/W1s+(0.75*(U2*Cu2-U1*Cu1)/U2**2)/((W1s/W2)*((Z/PI)*(1-r1s/r2)+(2*r1s/r2)))
RecirculationWork = 0.000008*SINH(3.5*(ATAN(Cu2/Cr2))**3)*Deq**2*U2**2
!~~~~~~~~~~~~~~~ SUM PARASITIC LOSS COEFFICIENTS ~~~~~~~~~~~~~~~~~~~~~~!
LossesParasitic = DiskFriction + LeakageWork + RecirculationWork
PRr = P02/P01 !Rotor Pressure Ratio
H02real = H02real + LossesParasitic*wm/1000
S02ideal = S01
CALL PSFLSH (P02,S02ideal,zz,T02ideal,rho02ideal,Dl,Dv,x,y,q,e,H02ideal,cv,cp,w,ierr,herr)
Effr = (H02ideal - H01)/(H02real - H01)
!~~~~~~~~~~~~~~~~~~ END OF IMPELLER ANALYSIS ~~~~~~~~~~~~~~~~~~~~~~~~~~!
IF (iDiffAnalysis == 0 .AND. iVoluteAnalysis == 0) THEN !(If only impeller analysis is specified)
PRs = PRr
Effs = Effr
END IF
IF (iDiffAnalysis == 1) THEN
!~~~~~~~~~~~~~~~~~~~~~~~~~~DIFFUSER ANALYIS~~~~~~~~~~~~~~~~~~~~~~~~~~!
!The diffuser analysis currently just uses an inputted loss factor.
!For a full analysis method see Aungier (2000), or Roberts (2003).
!~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~!
!Assume flow properties at rotor outlet are the same as diffuser inlet
Cu3 = Cu2
Cm3 = Cr2
C3 = C2
r3 = r2
b3 = b2
H03 = H02real
H3 = H2
S03 = S02
S3 = S2
P03 = P02
P3 = P2
T03 = T02
T3 = T2
rho03 = rho02
rho3 = rho2
!Initial Conditions
PLast = P3*1000
P0 = P03*1000
T = T3
H0 = H03
H = H3
S0 = S03
S = S3
rho = rho3
rhoLast = rho
blast=b3
rlast = r3
Alpha = (ATAN((r4-r3)/((b3/2)-(b4/2))))*(180/PI)!Assuming constant taper. With respect to tangent.
DiffuserLength = r4 - r2
LengthM = DiffuserLength*SIN(Alpha*PI/180)
DeltaM = LengthM/iDiffSteps
CurrentLengthM = DeltaM
C = C3
CmLast = Cm3
CuLast = Cu3
CLast = C3
Slast = 5
!Initialize boundary layer information
Del = b3*(1-(b3/r3)**0.15)/2 !Initial boundary layer thickness estimate
rCue = rlast * CuLast !Assume this is conserved until boundary layers fill the passage
Blockage = Del/(4*blast)
Dmax = 0.4*((b3/LengthM)**0.35)*SIN(Alpha*PI/180) !Diffusion divergence parameter
i=0
DO WHILE (i /= iDiffSteps)
!Get next downstream radius and diffuser width
radius = DeltaM*SIN(Alpha*PI/180) + rLast
b = b3 + (b4-b3)/(r4-r3)*(radius-r3)
! Calculate next downstream station whirl velocity
!Cu = ABS(radius*CuLast/(radius+DeltaM)) - ABS(radius*C*Cu*cf*DeltaM/(b*Cm)) !S.Roberts
Cu = -(DeltaM*rlast*CLast*CuLast*cf)/(radius*(blast*CmLast))+(rlast*CuLast/radius)
IF (Cu.LT.0) THEN
Cu = 0
END IF
!Estimate radial (meridional velocity) from continuity equation
Cm = zMdot / (2*PI*radius*rho*b*(1-Blockage))
k=0
DO WHILE (ABS((Cm-CmLastIter)/Cm).GT.0.000001)
k=k+1
CmLastIter = Cm
C = SQRT(Cu**2+Cm**2)
H = H0 - (C**2)*wm/2000!J/mol
CALL HSFLSH (H,S,zz,T,P,rho,Dl,Dv,x,y,q,e,cv,cp,w,ierr,herr)
rho=rho*wm!kg/m^3
Cm = zMDot / (2*PI*radius*rho*b*(1-Blockage))
Slast=S
IF (k.GT.MaxIter) THEN
GOTO 1337
WRITE(*,*) "Max iteration reached in Diffuser - Cm"
ELSE IF (ierr.NE.0) THEN
WRITE(*,*) "Error Flag at Diffuser: ",ierr
WRITE(*,*) "Error String: ",herr
END IF
END DO
!Calculate next downstream station static pressure
P = DeltaM*rhoLast*((CuLast**2)*SIN(Alpha*PI/180)/rLast - CmLast*(Cm-CmLast)/DeltaM &
- CLast*CmLast*cf/blast & !- DeltaId/DeltaM - dIc (Aungier's additional loss terms)
) + Plast
P = P/1000 !kPa
CALL PHFLSH (P,H,zz,T,rho,Dl,Dv,x,y,q,e,S,cv,cp,a_4,ierr,herr)
P = P*1000!Pa
rho=rho*wm!kg/m^3
!and the corresponding total conditions are
H0 = H + (C**2)*wm/2000!J/mol
S0 = S
CALL HSFLSH (H0,S0,zz,T0,P0,rho0,Dl,Dv,x,y,q,e,cv,cp,w,ierr,herr)
P0 = P0*1000!Pa
rho0 = rho0*wm
! Calculate boundary layer thickness at next downstream station:
Del = 2.25*b*(1-(radius*Cu/rCue))
! Obviously, the boundary layers cannot be greater than the passage width or negative:
IF (Del > b/2) THEN
Del = b/2
END IF
IF (Del < 0) THEN
Del = 0
END IF
! Calculate blockage factor at next downstream station:
Blockage = Del/(4*b)
IF (Del /= 0) THEN
CALL TRNPRP (T,rho/wm,zz,eta,tcx,ierr,herr)
IF (ierr.NE.0) THEN
WRITE(*,*) "Viscosity Error Flag at Diffuser: ",ierr
WRITE(*,*) "Error String: ",herr
END IF
ViscDiff = eta/1000000!kg/m*s
! Calculate skin friction coefficient:
Re = rho*Cm*b/ViscDiff
dHdif = 2*Del
CALL SkinFrictionCoefficient(Re,dHdif,RoughnessImp)
END IF
! Store last velocities and other variables:
CuLast = Cu
CmLast = Cm
CLast = C
PLast = P
rhoLast = rho
rLast = radius
dIdLast = dId
blast = b
CurrentLengthM = CurrentLengthM + DeltaM
i = i+1
END DO
H04 = H0
S04 = S0
P04 = P0/1000
T04 = T0
rho04 = rho0
H4 = H
S4 = S
P4 = P/1000
T4 = T
rho4 =rho
Cu4 = Cu
Cm4 = Cm
C4=SQRT(Cm4**2+Cu4**2)
Alpha4=ATAN(Cu4/Cm4)*(180/PI)
aM4=C4/a_4!Absolute Mach Number
PRd = P04/P01
S04ideal = S01