_STLP_DECLSPEC complex<long double> _STLP_CALL pow(const complex<long double>& a,
const complex<long double>& b)
{ return powT(a, b); }
void Turbine_PSI_TMATS_body(double *y, const double *u, const double *CoolFlow, const Turbine_PSIStruct* prm)
{
double WIn = u[0]; /* Input Flow [pps] */
double htIn = u[1]; /* input enthalpy [BTU/lbm]*/
double TtIn = u[2]; /* Temperature Input [degR] */
double PtIn = u[3]; /* Pressure Input [psia] */
double FARcIn = u[4]; /* Compusted Fuel to Air Ratio [frac] */
double Nmech = u[5]; /* Mechancial Shaft Speed [rpm]*/
double psiMapIn = u[6]; /* PSI map [NA] */
double s_T_Nc = u[7]; /* Nc map scalar [NA] */
double s_T_Wc = u[8]; /* Wc map scalar [NA] */
double s_T_PR = u[9]; /* PR map scalar [NA] */
double s_T_Eff = u[10]; /* Eff map scalar [NA] */
int cfWidth = u[11]; /* Cooling Flow Vector Length */
/*--------Define Constants-------*/
double WOut, htOut, TtOut, PtOut, FARcOut, TorqueOut, NErrorOut;
double WcCalcin, WcMap, theta,delta, Pwrout, PRin, htin;
double Test, htIdealout, Sout, NcMap, Nc, EffMap, Eff;
double dHcools1, dHcoolout, Wfcools1, Wfcoolout, Ws1in,hts1in, Tts1in, FARs1in;
double Ss1in, Wcoolout, Wcools1, PRmapRead;
double C_Eff, C_PR, C_Nc, C_Wc, TtOutIdeal;
double WMap, psiMapI, delHtIdealMap, erT, erT_old, Ptoutg, Ptoutg_old;
double TtOutIdealg, WpqAcrit, WoWMap, Ptoutg_new;
int interpErr = 0;
double Wcool[100];
double htcool[100];
double Ttcool[100];
double Ptcool[100];
double FARcool[100];
int Vtest, i;
/* Verify input bleed vector is a multiple of 5 */
Vtest = cfWidth/5;
if(5*Vtest != cfWidth && prm->CoolFlwEn > 0.5 && *(prm->IWork+Er1)==0){
#ifdef MATLAB_MEX_FILE
printf("Error in %s, one or more of the cooling flow input vector eleements is missing(Vector form; 5x1: W,ht,Tt,Pt,FAR)\n",prm->BlkNm);
#endif
*(prm->IWork+Er1) = 1;
}
else if(prm->BldPosLeng != cfWidth/5 && prm->CoolFlwEn > 0.5 && *(prm->IWork+Er2)==0){
#ifdef MATLAB_MEX_FILE
printf("Errorin %s, number of cooling flow inputs does not match the length of the Cooling flow postion vector in the mask\n",prm->BlkNm);
#endif
*(prm->IWork+Er2) = 1;
}
/* unpack CoolFlow vector */
for (i = 0; i < cfWidth/5; i++)
{
if (prm->CoolFlwEn < 0.5){
Wcool[i] = 0;
htcool[i] = 0;
Ttcool[i] = 0;
Ptcool[i] = 0;
FARcool[i] = 0;
}
else {
Wcool[i] = CoolFlow[5*i];
Ttcool[i] = CoolFlow[5*i+2];
Ptcool[i] = CoolFlow[5*i+3];
FARcool[i] = CoolFlow[5*i+4];
htcool[i] = t2hc(Ttcool[i],FARcool[i]);
}
}
/* Initialize cooling flow sum constants */
dHcools1 = 0; /* enthalpy * mass cooling flow rate at stage 1 of turbine */
dHcoolout = 0; /* enthalpy * mass cooling flow rate at exit of turbine */
Wcools1 = 0; /* total cooling flow at stage 1 of turbine*/
Wcoolout = 0; /* total cooling flow at output of turbine */
Wfcools1 = 0; /* combusted fuel flow in cooling at stage 1 of turbine */
Wfcoolout = 0; /* combusted fuel flow in cooling at exit of turbine */
/* calc cooling flow constants for stage 1 and output of the turbine */
for (i = 0; i < cfWidth/5; i++)
{
if ((prm->T_BldPos[i] > 1 || prm->T_BldPos[i] < 0) && prm->CoolFlwEn > 0.5 && *(prm->IWork+Er3)==0){
#ifdef MATLAB_MEX_FILE
printf(" Error in %s, cooling flow postion element %i needs to be defined as a 0 or 1\n",prm->BlkNm,i+1);
#endif
*(prm->IWork+Er3) = 1;
}
/* calc mass flow for cooling flows */
Wcools1 = Wcools1 + Wcool[i]*(1-prm->T_BldPos[i]);
Wcoolout = Wcoolout + Wcool[i];
/* calc fuel mass flow for cooling flows*/
Wfcools1 = Wfcools1 + FARcool[i]*Wcool[i]*(1-prm->T_BldPos[i])*divby(1+FARcool[i]);
Wfcoolout = Wfcoolout + FARcool[i]*Wcool[i]*divby(1+FARcool[i]);
}
/*-- Compute Total Flow --------*/
Ws1in = WIn + Wcools1; /* mass flow at station 1 */
WOut = WIn + Wcoolout; /* mass flow at turbine exit */
/*-- Compute Fuel to Air Ratios ---*/
FARs1in = (FARcIn* WIn*divby(1+FARcIn) + Wfcools1)*divby(WIn*divby(1+FARcIn) + Wcools1- Wfcools1);
FARcOut = (FARcIn* WIn*divby(1+FARcIn)+ Wfcoolout)*divby(WIn*divby(1+FARcIn) + Wcoolout- Wfcoolout);
/* calc input enthalpy of cooling flow for stage 1 */
for (i = 0; i < cfWidth/5; i++)
{
/* Compute cooling flow dH at stage 1 */
dHcools1 = dHcools1 + htcool[i]*Wcool[i]*(1-prm->T_BldPos[i]);
/* Compute cooling flow dH for the exit of the turbine assuming input htcool = htcoolout for turbine rear bleeds */
dHcoolout = dHcoolout + htcool[i]*Wcool[i]*prm->T_BldPos[i];
}
/*-- Compute avg enthalpy at stage 1 --------*/
htin = t2hc(TtIn,FARcIn);
hts1in = (htin* WIn + dHcools1)*divby(Ws1in);
/*-- Compute stage 1 total temp--------*/
Tts1in = h2tc(hts1in,FARs1in);
/*-- Compute Stage 1 entropy, assuming PtIn = Pts1in --------*/
Ss1in = pt2sc(PtIn,Tts1in,FARs1in);
/*---- calculate misc. fluid condition related variables --------*/
delta = PtIn / C_PSTD;
theta = TtIn / C_TSTD;
/*------ Calculate corrected speed ---------*/
Nc = Nmech*divby(sqrtT(theta));
if(prm->IDes < 0.5)
C_Nc = Nc*divby(prm->NcDes);
else
C_Nc = s_T_Nc;
NcMap = Nc*divby(C_Nc);
/* ---- Calculate output entropy ----*/
Sout = Ss1in;
/*-- Compute Turbine Efficiency (from Turbine map) --------*/
psiMapI = interp2Ac(prm->X_T_PRpsiVec,prm->Y_T_NcpsiVec,prm->T_T_Map_psiArray,psiMapIn,NcMap,prm->B,prm->A,&interpErr);
if (interpErr == 1 && *(prm->IWork+Er4)==0){
#ifdef MATLAB_MEX_FILE
printf("Warning in %s, Error calculating psiMapI. Vector definitions may need to be expanded.\n", prm->BlkNm);
#endif
*(prm->IWork+Er4) = 1;
}
EffMap = psiMapIn*divby(psiMapI);
if(prm->IDes < 0.5)
C_Eff = prm->EffDes*divby(EffMap);
else
C_Eff = s_T_Eff;
Eff = EffMap * C_Eff;
/* ---- Ideal enthalpy ----*/
delHtIdealMap = psiMapI * (Nmech / 60)*(Nmech / 60);
htIdealout = hts1in - delHtIdealMap * prm->s_T_hi;
/* ensure enthalpy is >= 0 */
if(htIdealout < 0)
{
htIdealout = 0;
}
/* Determine Ideal exit temp */
TtOutIdeal = h2tc(htIdealout,FARs1in);
/* Determine starting point for iteration to find PR */
Ptoutg = PtIn*powT((TtOutIdeal*divby(TtIn)),(prm->gamma_T*divby(prm->gamma_T-1)));
TtOutIdealg = sp2tc(Sout,Ptoutg,FARs1in);
erT = 100*fabs(TtOutIdealg - TtOutIdeal)*divby(TtOutIdeal);
Ptoutg_new = Ptoutg;
/* iterate to find Ptout when TtOutIdeal guess = TtOutIdeal */
while (fabs(erT) > 0.05) {
erT_old = erT;
Ptoutg_old = Ptoutg;
if(fabs(Ptoutg - Ptoutg_new) < 0.02)
Ptoutg = Ptoutg + 0.05;
else
Ptoutg = Ptoutg_new;
Ptoutg = Ptoutg + 0.05;
TtOutIdealg = sp2tc(Sout,Ptoutg,FARs1in);
erT = 100*(TtOutIdealg - TtOutIdeal)*divby(TtOutIdeal);
if (fabs(erT) > 0.05) {
/* determine next guess pressure by secant algorithm */
Ptoutg_new = Ptoutg - erT *(Ptoutg - Ptoutg_old)*divby(erT - erT_old);
}
}
PRin = PtIn*divby(Ptoutg);
/*------ Compute pressure output --------*/
if(prm->IDes < 0.5)
C_PR = (PRin - 1)*divby(prm->PRmapDes -1);
else
C_PR = s_T_PR;
PRmapRead = (PRin -1)*divby(C_PR) + 1;
PtOut = PtIn*divby(PRin);
/*-- Compute Total Flow input (from Turbine map) --------*/
WoWMap = interp2Ac(prm->X_T_PRwowVec,prm->Y_T_NcwowVec,prm->T_T_Map_WoWArray,PRmapRead,NcMap,prm->D,prm->C,&interpErr);
if (interpErr == 1 && *(prm->IWork+Er5)==0){
#ifdef MATLAB_MEX_FILE
printf("Warning in %s, Error calculating WoWMap. Vector definitions may need to be expanded.\n", prm->BlkNm);
#endif
*(prm->IWork+Er5) = 1;
}
WpqAcrit = sqrtT((prm->gamma_T*C_GRAVITY)*divby(prm->Rt_T*JOULES_CONST))*divby(powT((1+(prm->gamma_T-1)/2),((prm->gamma_T+1)*divby(2*(prm->gamma_T-1)))));
WMap = WoWMap * WpqAcrit * (PtIn*divby(sqrtT(Tts1in)));
WcMap = WMap * sqrtT(theta)*divby(delta);
if(prm->IDes < 0.5)
C_Wc = Ws1in*sqrtT(theta)*divby(delta)*divby(WcMap);
else
C_Wc = s_T_Wc;
WcCalcin = WcMap * C_Wc;
/*-Compute power output only takes into account cooling flow that enters at front of engine (stage 1)-*/
Pwrout = ((hts1in - htIdealout)*Eff)*Ws1in * C_BTU_PER_SECtoHP;
/* ---- enthalpy output ----*/
htOut = ((((htIdealout - hts1in)*Eff) + hts1in)*Ws1in + dHcoolout)*divby(WOut);
/*------ Compute Temperature output (empirical) ---------*/
TtOut = h2tc(htOut,FARcOut);
/*----- Compute output Torque to shaft ----*/
TorqueOut = C_HP_PER_RPMtoFT_LBF * Pwrout*divby(Nmech);
/* ----- Compute Normalized Flow Error ----- */
if (prm->IDes < 0.5 && prm->NDes == 0)
NErrorOut = 100;
else if (prm->IDes < 0.5)
NErrorOut = (Nmech - prm->NDes)*divby(prm->NDes);
else if (Ws1in == 0) {
NErrorOut = 100;
}
else {
NErrorOut = (Ws1in*sqrtT(theta)*divby(delta)-WcCalcin)*divby(Ws1in*sqrtT(theta)*divby(delta)) ;
}
Test = Wcool[0];
/*------Assign output values------------ */
y[0] = WOut; /* Outlet Total Flow [pps] */
y[1] = htOut; /* Outlet Enthalpy [BTU/lbm]*/
y[2] = TtOut; /* Outlet Temperature [degR] */
y[3] = PtOut; /* Outlet Pressure [psia] */
y[4] = FARcOut; /* Outlet Fuel to Air Ratio [NA] */
y[5] = TorqueOut; /* Torque Output [lbf*ft] */
y[6] = NErrorOut; /* Normalized turbine Error [frac]*/
y[7] = C_Nc; /* Corrected Shaft Speed Scalar */
y[8] = C_Wc; /* Corrected Flow Scalar */
y[9] = C_PR; /* Pressure Ratio Scalar */
y[10] = C_Eff; /* Efficiency Scalar */
y[11] = Test;
}
_STLP_DECLSPEC complex<long double> _STLP_CALL pow(const complex<long double>& z_in, int n)
{ return powT(z_in, n); }
_STLP_DECLSPEC complex<float> _STLP_CALL pow(const complex<float>& a, const complex<float>& b)
{ return powT(a, b); }
_STLP_DECLSPEC complex<float> _STLP_CALL pow(const complex<float>& z_in, int n)
{ return powT(z_in, n); }
static void mdlOutputs(SimStruct *S, int_T tid)
{
/*--------Define Parameters-------*/
const real_T NcDes = *mxGetPr(NcDes_p(S));
const real_T PRmapDes = *mxGetPr(PRmapDes_p(S));
const real_T EffDes = *mxGetPr(EffDes_p(S));
const real_T NDes = *mxGetPr(NDes_p(S));
const real_T IDes = *mxGetPr(IDesign_p(S));
const real_T s_T_hi = *mxGetPr(s_T_hi_p(S));
const real_T gamma_T = *mxGetPr(gamma_T_p(S));
const real_T Rt_T = *mxGetPr(Rt_T_p(S));
const int_T BldPosLeng = *mxGetPr(BldPosLeng_p(S));
const int_T CoolFlwEn = *mxGetPr(CoolFlwEn_p(S));
/* vector & array data */
const real_T *Y_T_NcpsiVec = mxGetPr(Y_T_NcpsiVec_p(S));
const real_T *X_T_PRpsiVec = mxGetPr(X_T_PRpsiVec_p(S));
const real_T *Y_T_NcwowVec = mxGetPr(Y_T_NcwowVec_p(S));
const real_T *X_T_PRwowVec = mxGetPr(X_T_PRwowVec_p(S));
const real_T *T_T_Map_WoWArray = mxGetPr(T_T_Map_WoWArray_p(S));
const real_T *T_T_Map_psiArray = mxGetPr(T_T_Map_psiArray_p(S));
const real_T *T_BldPos = mxGetPr(T_BldPos_p(S));
/*------get dimensions of parameter arrays-------*/
const int_T A = mxGetNumberOfElements(Y_T_NcpsiVec_p(S));
const int_T B = mxGetNumberOfElements(X_T_PRpsiVec_p(S));
const int_T C = mxGetNumberOfElements(Y_T_NcwowVec_p(S));
const int_T D = mxGetNumberOfElements(X_T_PRwowVec_p(S));
/*---------Define Inputs--------*/
const real_T *u = (const real_T*) ssGetInputPortSignal(S,0);
double WIn = u[0]; /* Input Flow [pps] */
double htIn = u[1]; /* input enthalpy [BTU/lbm]*/
double TtIn = u[2]; /* Temperature Input [degR] */
double PtIn = u[3]; /* Pressure Input [psia] */
double FARcIn = u[4]; /* Compusted Fuel to Air Ratio [frac] */
double Nmech = u[5]; /* Mechancial Shaft Speed [rpm]*/
double psiMapIn = u[6]; /* PSI map [NA] */
double s_T_Nc = u[7]; /* Nc map scalar [NA] */
double s_T_Wc = u[8]; /* Wc map scalar [NA] */
double s_T_PR = u[9]; /* PR map scalar [NA] */
double s_T_Eff = u[10]; /* Eff map scalar [NA] */
int cfWidth = u[11]; /* Cooling Flow Vector Length */
/*---------Define Inputs for input port 2--------*/
/* N 5x1 vectors consisting of W, ht, Tt, Pt and FAR, where N is the number of cooling flows */
const real_T *CoolFlow = ssGetInputPortRealSignal(S, 1);
real_T *y = (real_T *)ssGetOutputPortRealSignal(S,0); /* Output Array */
/*--------Define Constants-------*/
double WOut, htOut, TtOut, PtOut, FARcOut, TorqueOut, NErrorOut;
double WcCalcin, WcMap, theta,delta, Pwrout, PRin, htin;
double TtIdealout, Test, htIdealout, Sout, NcMap, Nc, EffMap, Eff;
double dHcools1, dHcoolout, Wfcools1, Wfcoolout, Ws1in,hts1in, Tts1in, Pts1in, FARs1in;
double Ss1in, dHout, Wcoolout, Wcools1, PRmapRead;
double C_Eff, C_PR, C_Nc, C_Wc, TtOutIdeal;
double WMap, psiMapI, delHtIdealMap, erT, erT_old, Ptoutg, Ptoutg_old;
double TtOutIdealg, WpqAcrit, WoWMap, Ptoutg_new;
int interpErr = 0;
double Wcool[100];
double htcool[100];
double Ttcool[100];
double Ptcool[100];
double FARcool[100];
int Vtest, i;
/* ------- get strings -------------- */
char * BlkNm;
int_T buflen;
int_T status;
/* Get name of block from dialog parameter (string) */
buflen = mxGetN(BN_p(S))*sizeof(mxChar)+1;
BlkNm = mxMalloc(buflen);
status = mxGetString(BN_p(S), BlkNm, buflen);
/* Verify input bleed vector is a multiple of 5 */
Vtest = cfWidth/5;
if(5*Vtest != cfWidth && CoolFlwEn > 0.5 && ssGetIWork(S)[Er1]==0){
printf("Error in %s, one or more of the cooling flow input vector eleements is missing(Vector form; 5x1: W,ht,Tt,Pt,FAR)\n",BlkNm);
ssSetIWorkValue(S,Er1,1);
}
else if(BldPosLeng != cfWidth/5 && CoolFlwEn > 0.5 && ssGetIWork(S)[Er2]==0){
printf("Errorin %s, number of cooling flow inputs does not match the length of the Cooling flow postion vector in the mask\n",BlkNm);
ssSetIWorkValue(S,Er2,1);
}
/* unpack CoolFlow vector */
for (i = 0; i < cfWidth/5; i++)
{
if (CoolFlwEn < 0.5){
Wcool[i] = 0;
htcool[i] = 0;
Ttcool[i] = 0;
Ptcool[i] = 0;
FARcool[i] = 0;
}
else {
Wcool[i] = CoolFlow[5*i];
Ttcool[i] = CoolFlow[5*i+2];
Ptcool[i] = CoolFlow[5*i+3];
FARcool[i] = CoolFlow[5*i+4];
htcool[i] = t2hc(Ttcool[i],FARcool[i]);
}
}
/* Initialize cooling flow sum constants */
dHcools1 = 0; /* enthalpy * mass cooling flow rate at stage 1 of turbine */
dHcoolout = 0; /* enthalpy * mass cooling flow rate at exit of turbine */
Wcools1 = 0; /* total cooling flow at stage 1 of turbine*/
Wcoolout = 0; /* total cooling flow at output of turbine */
Wfcools1 = 0; /* combusted fuel flow in cooling at stage 1 of turbine */
Wfcoolout = 0; /* combusted fuel flow in cooling at exit of turbine */
/* calc cooling flow constants for stage 1 and output of the turbine */
for (i = 0; i < cfWidth/5; i++)
{
if ((T_BldPos[i] > 1 || T_BldPos[i] < 0) && CoolFlwEn > 0.5 && ssGetIWork(S)[Er3]==0){
printf(" Error in %s, cooling flow postion element %i needs to be defined as a 0 or 1\n",BlkNm,i+1);
ssSetIWorkValue(S,Er3,1);
}
/* calc mass flow for cooling flows */
Wcools1 = Wcools1 + Wcool[i]*(1-T_BldPos[i]);
Wcoolout = Wcoolout + Wcool[i];
/* calc fuel mass flow for cooling flows*/
Wfcools1 = Wfcools1 + FARcool[i]*Wcool[i]*(1-T_BldPos[i])*divby(1+FARcool[i]);
Wfcoolout = Wfcoolout + FARcool[i]*Wcool[i]*divby(1+FARcool[i]);
}
/*-- Compute Total Flow --------*/
Ws1in = WIn + Wcools1; /* mass flow at station 1 */
WOut = WIn + Wcoolout; /* mass flow at turbine exit */
/*-- Compute Fuel to Air Ratios ---*/
FARs1in = (FARcIn* WIn*divby(1+FARcIn) + Wfcools1)*divby(WIn*divby(1+FARcIn) + Wcools1- Wfcools1);
FARcOut = (FARcIn* WIn*divby(1+FARcIn)+ Wfcoolout)*divby(WIn*divby(1+FARcIn) + Wcoolout- Wfcoolout);
/* calc input enthalpy of cooling flow for stage 1 */
for (i = 0; i < cfWidth/5; i++)
{
/* Compute cooling flow dH at stage 1 */
dHcools1 = dHcools1 + htcool[i]*Wcool[i]*(1-T_BldPos[i]);
/* Compute cooling flow dH for the exit of the turbine assuming input htcool = htcoolout for turbine rear bleeds */
dHcoolout = dHcoolout + htcool[i]*Wcool[i]*T_BldPos[i];
}
/*-- Compute avg enthalpy at stage 1 --------*/
htin = t2hc(TtIn,FARcIn);
hts1in = (htin* WIn + dHcools1)*divby(Ws1in);
/*-- Compute stage 1 total temp--------*/
Tts1in = h2tc(hts1in,FARs1in);
/*-- Compute Stage 1 entropy, assuming PtIn = Pts1in --------*/
Ss1in = pt2sc(PtIn,Tts1in,FARs1in);
/*---- calculate misc. fluid condition related variables --------*/
delta = PtIn / C_PSTD;
theta = TtIn / C_TSTD;
/*------ Calculate corrected speed ---------*/
Nc = Nmech*divby(sqrtT(theta));
if(IDes < 0.5)
C_Nc = Nc*divby(NcDes);
else
C_Nc = s_T_Nc;
NcMap = Nc*divby(C_Nc);
/* ---- Calculate output entropy ----*/
Sout = Ss1in;
/*-- Compute Turbine Efficiency (from Turbine map) --------*/
psiMapI = interp2Ac(X_T_PRpsiVec,Y_T_NcpsiVec,T_T_Map_psiArray,psiMapIn,NcMap,B,A,&interpErr);
if (interpErr == 1 && ssGetIWork(S)[Er4]==0){
printf("Warning in %s, Error calculating psiMapI. Vector definitions may need to be expanded.\n", BlkNm);
ssSetIWorkValue(S,Er4,1);
}
EffMap = psiMapIn*divby(psiMapI);
if(IDes < 0.5)
C_Eff = EffDes*divby(EffMap);
else
C_Eff = s_T_Eff;
Eff = EffMap * C_Eff;
/* ---- Ideal enthalpy ----*/
delHtIdealMap = psiMapI * (Nmech / 60)*(Nmech / 60);
htIdealout = hts1in - delHtIdealMap * s_T_hi;
/* ensure enthalpy is >= 0 */
if(htIdealout < 0)
{
htIdealout = 0;
}
/* Determine Ideal exit temp */
TtOutIdeal = h2tc(htIdealout,FARs1in);
/* Determine starting point for iteration to find PR */
Ptoutg = PtIn*powT((TtOutIdeal*divby(TtIn)),(gamma_T*divby(gamma_T-1)));
TtOutIdealg = sp2tc(Sout,Ptoutg,FARs1in);
erT = 100*fabs(TtOutIdealg - TtOutIdeal)*divby(TtOutIdeal);
Ptoutg_new = Ptoutg;
/* iterate to find Ptout when TtOutIdeal guess = TtOutIdeal */
while (fabs(erT) > 0.05) {
erT_old = erT;
Ptoutg_old = Ptoutg;
if(fabs(Ptoutg - Ptoutg_new) < 0.02)
Ptoutg = Ptoutg + 0.05;
else
Ptoutg = Ptoutg_new;
Ptoutg = Ptoutg + 0.05;
TtOutIdealg = sp2tc(Sout,Ptoutg,FARs1in);
erT = 100*(TtOutIdealg - TtOutIdeal)*divby(TtOutIdeal);
if (fabs(erT) > 0.05) {
/* determine next guess pressure by secant algorithm */
Ptoutg_new = Ptoutg - erT *(Ptoutg - Ptoutg_old)*divby(erT - erT_old);
}
}
PRin = PtIn*divby(Ptoutg);
/*------ Compute pressure output --------*/
if(IDes < 0.5)
C_PR = (PRin - 1)*divby(PRmapDes -1);
else
C_PR = s_T_PR;
PRmapRead = (PRin -1)*divby(C_PR) + 1;
PtOut = PtIn*divby(PRin);
/*-- Compute Total Flow input (from Turbine map) --------*/
WoWMap = interp2Ac(X_T_PRwowVec,Y_T_NcwowVec,T_T_Map_WoWArray,PRmapRead,NcMap,D,C,&interpErr);
if (interpErr == 1 && ssGetIWork(S)[Er5]==0){
printf("Warning in %s, Error calculating WoWMap. Vector definitions may need to be expanded.\n", BlkNm);
ssSetIWorkValue(S,Er5,1);
}
WpqAcrit = sqrtT((gamma_T*C_GRAVITY)*divby(Rt_T*JOULES_CONST))*divby(powT((1+(gamma_T-1)/2),((gamma_T+1)*divby(2*(gamma_T-1)))));
WMap = WoWMap * WpqAcrit * (PtIn*divby(sqrtT(Tts1in)));
WcMap = WMap * sqrtT(theta)*divby(delta);
if(IDes < 0.5)
C_Wc = Ws1in*sqrtT(theta)*divby(delta)*divby(WcMap);
else
C_Wc = s_T_Wc;
WcCalcin = WcMap * C_Wc;
/*-Compute power output only takes into account cooling flow that enters at front of engine (stage 1)-*/
Pwrout = ((hts1in - htIdealout)*Eff)*Ws1in * C_BTU_PER_SECtoHP;
/* ---- enthalpy output ----*/
htOut = ((((htIdealout - hts1in)*Eff) + hts1in)*Ws1in + dHcoolout)*divby(WOut);
/*------ Compute Temperature output (empirical) ---------*/
TtOut = h2tc(htOut,FARcOut);
/*----- Compute output Torque to shaft ----*/
TorqueOut = C_HP_PER_RPMtoFT_LBF * Pwrout*divby(Nmech);
/* ----- Compute Normalized Flow Error ----- */
if (IDes < 0.5 && NDes == 0)
NErrorOut = 100;
else if (IDes < 0.5)
NErrorOut = (Nmech - NDes)*divby(NDes);
else if (Ws1in == 0) {
NErrorOut = 100;
}
else {
NErrorOut = (Ws1in*sqrtT(theta)*divby(delta)-WcCalcin)*divby(Ws1in*sqrtT(theta)*divby(delta)) ;
}
Test = Wcool[0];
/*------Assign output values------------ */
y[0] = WOut; /* Outlet Total Flow [pps] */
y[1] = htOut; /* Outlet Enthalpy [BTU/lbm]*/
y[2] = TtOut; /* Outlet Temperature [degR] */
y[3] = PtOut; /* Outlet Pressure [psia] */
y[4] = FARcOut; /* Outlet Fuel to Air Ratio [NA] */
y[5] = TorqueOut; /* Torque Output [lbf*ft] */
y[6] = NErrorOut; /* Normalized turbine Error [frac]*/
y[7] = C_Nc; /* Corrected Shaft Speed Scalar */
y[8] = C_Wc; /* Corrected Flow Scalar */
y[9] = C_PR; /* Pressure Ratio Scalar */
y[10] = C_Eff; /* Efficiency Scalar */
y[11] = Test;
}
static void mdlOutputs(SimStruct *S, int_T tid)
{
/*--------Define Parameters-------*/
const real_T s_V_Ae_vlv = *mxGetPr(s_V_Ae_vlv_p(S));
const real_T s_V_Ae_byp = *mxGetPr(s_V_Ae_byp_p(S));
const real_T s_V_Ae_th = *mxGetPr(s_V_Ae_th_p(S));
/*-------- vector & array data -------*/
const real_T *X_V_FAR_vec = mxGetPr(X_V_FAR_vec_p(S));
const real_T *T_V_Rt_vec = mxGetPr(T_V_Rt_vec_p(S));
const real_T *Y_V_Tt_vec = mxGetPr(Y_V_Tt_vec_p(S));
const real_T *T_V_gamma_array = mxGetPr(T_V_gamma_array_p(S));
/*------get dimensions of parameter arrays-------*/
const int_T A1 = mxGetNumberOfElements(X_V_FAR_vec_p(S));
const int_T B1 = mxGetNumberOfElements(Y_V_Tt_vec_p(S));
/*---------Define Inputs--------*/
const real_T *u = (const real_T*) ssGetInputPortSignal(S,0);
double WbyIn = u[0]; /* Bypass flow path flow rate [pps] */
double TtbyIn = u[1]; /* Bypass Temperature [degR] */
double PtbyIn = u[2]; /* Bypass disch. pressure [psia] */
double FARcbyIn = u[3]; /* Bypass combusted fuel to air ratio [frac] */
double VlvPosIn = u[4]; /* Valve Position [frac, 0-1] */
double WmfpIn = u[5]; /* Main flow path flow rate [pps] */
double TtmfpIn = u[6]; /* Main flow path Temprature [degR] */
double PtmfpIn = u[7]; /* Main flow path Pressure Input [psia] */
double FARcmfpIn= u[8]; /* Main flow path combusted fuel to air ratio [frac] */
real_T *y = (real_T *)ssGetOutputPortRealSignal(S,0); /* Output Array */
/*--------Define Constants-------*/
double Ath, Rb, gamb, Cpb, Pe, Me, Tcr_o_Te, Ae_o_Acr, Ath_o_Acr;
double Mth0, Mth1, Tcr_o_Tth0, Tcr_o_Tth1, Ath_o_Acr0, Ath_o_Acr1, err0, err1, err;
double Mth, Tcr_o_Tth_it, Ath_o_Acr_it, Tcr_o_T0, Tth_o_T0, Tth, Pth, rhoth, Vth, Wth, Wbyp_noz, Whpc;
double MthOut, Test, WthOut;
int interpErr = 0;
int count;
/* ------- get strings -------------- */
char * BlkNm;
int_T buflen;
int_T status;
/* Get name of block from dialog parameter (string) */
buflen = mxGetN(BN_p(S))*sizeof(mxChar)+1;
BlkNm = mxMalloc(buflen);
status = mxGetString(BN_p(S), BlkNm, buflen);
/* Input validation */
if ((WbyIn <= 0 || WmfpIn <= 0) && ssGetIWork(S)[Er1]==0){
printf("Flow rates must be nonzero !!");
ssSetIWorkValue(S,Er1,1);
}
if (VlvPosIn > 0){
if (VlvPosIn < 0.001)
VlvPosIn = 0.001;
Ath = VlvPosIn*s_V_Ae_th; /* throat area [in^2] */
/* define gas constants for booster discharge air */
Rb = interp1Ac(X_V_FAR_vec,T_V_Rt_vec,FARcmfpIn,A1,&interpErr);
if (interpErr == 1 && ssGetIWork(S)[Er2]==0){
printf("Warning in %s, Error calculating Rb. Vector definitions may need to be expanded.\n", BlkNm);
ssSetIWorkValue(S,Er2,1);
}
gamb = interp2Ac(X_V_FAR_vec,Y_V_Tt_vec,T_V_gamma_array,FARcmfpIn,TtmfpIn,A1,B1,&interpErr);
if (interpErr == 1 && ssGetIWork(S)[Er3]==0){
printf("Warning in %s, Error calculating gamb. Vector definitions may need to be expanded.\n", BlkNm);
ssSetIWorkValue(S,Er3,1);
}
Cpb = Rb*gamb*divby(gamb-1);
/* determine static pressure at the exit plane (entering fan); */
/* assume bypass flow >> bleed flow */
Pe = calc_Pstatic(PtbyIn,TtbyIn,WbyIn,s_V_Ae_byp,X_V_FAR_vec,T_V_Rt_vec,Y_V_Tt_vec,T_V_gamma_array,FARcbyIn,A1,B1);
/* compute exit to critical area ratio */
Me = sqrtT(2*divby(gamb-1)*(powT(Pe*divby(PtmfpIn), (1-gamb)*divby(gamb))-1));
Tcr_o_Te = (2*divby(gamb+1))*(1 + 0.5*(gamb-1)*Me*Me);
Ae_o_Acr = powT(Tcr_o_Te, (gamb+1)*divby(2*(gamb-1)))*divby(Me);
/* obtain throat to critical area ratio */
Ath_o_Acr = Ae_o_Acr*Ath*divby(s_V_Ae_vlv);
/* determine throat Mach no. iteratively; initialize guesses, errors */
Mth0 = 0.1; /* subsonic guess values */
Mth1 = 0.2;
Tcr_o_Tth0 = (2*divby(gamb+1))*(1 + 0.5*(gamb-1)*Mth0*Mth0);
Tcr_o_Tth1 = (2*divby(gamb+1))*(1 + 0.5*(gamb-1)*Mth1*Mth1);
Ath_o_Acr0 = powT(Tcr_o_Tth0, (gamb+1)*divby(2*(gamb-1)))*divby(Mth0);
Ath_o_Acr1 = powT(Tcr_o_Tth1, (gamb+1)*divby(2*(gamb-1)))*divby(Mth1);
err0 = Ath_o_Acr - Ath_o_Acr0;
err1 = Ath_o_Acr - Ath_o_Acr1;
err = 100;
count = 0;
while (fabs(err) > 0.002 && (err0 - err1) != 0 && count < 100){
/* compute new Mach no. guess */
Mth = Mth0 - err0*(Mth0 - Mth1)*divby(err0 - err1);
if (Mth > 1.0)
Mth = 1.0;
/* compute error to drive solution towards specified area ratio */
Tcr_o_Tth_it = (2*divby(gamb+1))*(1 + 0.5*(gamb-1)*Mth*Mth);
Ath_o_Acr_it = powT(Tcr_o_Tth_it, (gamb+1)*divby(2*(gamb-1)))*divby(Mth);
err = Ath_o_Acr - Ath_o_Acr_it;
/* propagate errors & guesses */
Mth1 = Mth0;
err1 = err0;
Mth0 = Mth;
err0 = err;
count++;
}
/* compute throat static pressure, temperature and Mach no.; */
/* modify if choked */
Tcr_o_T0 = 2*divby(gamb+1);
Tth_o_T0 = 1*divby(1 + 0.5*(gamb-1)*Mth*Mth);
if (Tth_o_T0 < Tcr_o_T0)
Tth_o_T0 = Tcr_o_T0;
Tth = TtmfpIn*Tth_o_T0;
Pth = PtmfpIn*powT(Tth_o_T0, gamb*divby(gamb-1));
/* recompute the actual flow rate, assume no pressure loss */
rhoth = Pth*144*divby(Rb*JOULES_CONST*Tth); /* [lb/ft^3] */
Vth = sqrtT(2*Cpb*C_GRAVITY*JOULES_CONST*(TtmfpIn - Tth)); /* [ft/s] */
Wth = rhoth*Ath/144*Vth; /* [lb/s] */
Mth = Vth*divby(sqrtT(gamb*Rb*C_GRAVITY*JOULES_CONST*Tth));
}
else {
Wth = 0;
Mth = 0;
}
WthOut = Wth;
Test = Vth;
/*------Assign output values------------*/
y[0] = WthOut; /* Valve throat flow [pps] */
y[1] = MthOut; /* Mach no. at throat */
y[2] = Test; /* Output Test Point */
}