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; }
static void mdlOutputs(SimStruct *S, int_T tid) { /*--------Define Parameters-------*/ const real_T NcDes = *mxGetPr(NcDes_p(S)); const real_T PRDes = *mxGetPr(PRDes_p(S)); const real_T EffDes = *mxGetPr(EffDes_p(S)); const real_T RlineDes = *mxGetPr(RlineDes_p(S)); const real_T IDes = *mxGetPr(IDesign_p(S)); const real_T CustBldEn = *mxGetPr(CustBldEn_p(S)); const real_T FBldEn = *mxGetPr(FBldEn_p(S)); const real_T CustBldNm = *mxGetPr(CustBldNm_p(S)); const real_T FracBldNm = *mxGetPr(FracBldNm_p(S)); /* vector & array data */ const real_T *Y_C_Map_NcVec = mxGetPr(Y_C_Map_NcVec_p(S)); const real_T *X_C_RlineVec = mxGetPr(X_C_RlineVec_p(S)); const real_T *Z_C_AlphaVec = mxGetPr(Z_C_AlphaVec_p(S)); const real_T *T_C_Map_WcArray = mxGetPr(T_C_Map_WcArray_p(S)); const real_T *T_C_Map_PRArray = mxGetPr(T_C_Map_PRArray_p(S)); const real_T *T_C_Map_EffArray = mxGetPr(T_C_Map_EffArray_p(S)); const real_T *FracCusBldht = mxGetPr(FracCusBldht_p(S)); const real_T *FracCusBldPt = mxGetPr(FracCusBldPt_p(S)); const real_T *FracBldht = mxGetPr(FracBldht_p(S)); const real_T *FracBldPt = mxGetPr(FracBldPt_p(S)); const real_T *X_C_Map_WcSurgeVec = mxGetPr(X_C_Map_WcSurgeVec_p(S)); const real_T *T_C_Map_PRSurgeVec = mxGetPr(T_C_Map_PRSurgeVec_p(S)); /*------get dimensions of parameter arrays-------*/ const int_T A = mxGetNumberOfElements(Y_C_Map_NcVec_p(S)); const int_T B = mxGetNumberOfElements(X_C_RlineVec_p(S)); const int_T C = mxGetNumberOfElements(Z_C_AlphaVec_p(S)); const int_T D = mxGetNumberOfElements(X_C_Map_WcSurgeVec_p(S)); const int_T WcMapCol = *mxGetPr(WcMapCol_p(S)); const int_T PRMapCol = *mxGetPr(PRMapCol_p(S)); const int_T EffMapCol = *mxGetPr(EffMapCol_p(S)); const int_T WcMapRw = *mxGetPr(WcMapRw_p(S)); const int_T PRMapRw = *mxGetPr(PRMapRw_p(S)); const int_T EffMapRw = *mxGetPr(EffMapRw_p(S)); const int_T WcMapLay = *mxGetPr(WcMapLay_p(S)); const int_T PRMapLay = *mxGetPr(PRMapLay_p(S)); const int_T EffMapLay = *mxGetPr(EffMapLay_p(S)); /*---------Define Inputs for input port 1--------*/ 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]; /* Combusted Fuel to Air Ratio [frac] */ double Nmech = u[5]; /* Mechancial Shaft Speed [rpm] */ double Rline = u[6]; /* Rline [NA] */ double Alpha = u[7]; /* Alpha [NA] */ double s_C_Nc = u[8]; /* Nc map scalar [NA] */ double s_C_Wc = u[9]; /* Wc map scalar [NA] */ double s_C_PR = u[10]; /* PR map scalar [NA] */ double s_C_Eff = u[11]; /* Eff map scalar [NA] */ /*---------Define Inputs for input port 2--------*/ const real_T *Wcust = ssGetInputPortRealSignal(S, 1); int uWidth1 = CustBldNm; /*---------Define Inputs for input port 3--------*/ const real_T *FracWbld = ssGetInputPortSignal(S,2); int uWidth2 = FracBldNm; real_T *y = (real_T *)ssGetOutputPortRealSignal(S,0); /* Output Array port 1 */ real_T *y1 = (real_T *)ssGetOutputPortRealSignal(S,1); /* Output Array port 2 */ real_T *y2 = (real_T *)ssGetOutputPortRealSignal(S,2); /* Output Array port 3 */ /*--------Define Constants-------*/ double WOut, htOut, TtOut, PtOut, FARcOut, TorqueOut, NErrorOut; double C_Nc, C_Wc, C_PR, C_Eff; double htin, Sin, Wcin, WcCalcin, WcMap, theta,delta, Pwrout, Wbleeds, Wsumbleed; double TtIdealout, htIdealout, Test, Sout, NcMap, Nc, PRMap, PR, EffMap, Eff; double Wb4bleed, Pwrb4bleed, PwrBld; double SPR, SPRMap, SMavail, SMMap; /* Define Arrays for bleed calcs */ int MaxNumberBleeds = 100; double WcustOut[500]; double PtcustOut[500]; double TtcustOut[500]; double FARcustOut[500]; double WbldOut[500]; double FARbldOut[500]; double PtbldOut[500]; double TtbldOut[500]; double htbldOut[500]; double htcustOut[500]; double SMWcVec[500]; double SMPRVec[500]; int interpErr = 0; int 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); /*-- Compute output Fuel to Air Ratio ---*/ FARcOut = FARcIn; /*-- Compute Input enthalpy --------*/ htin = t2hc(TtIn,FARcIn); /*-- Compute Input entropy --------*/ Sin = pt2sc(PtIn,TtIn,FARcIn); /*---- calculate misc. fluid condition related variables and corrected Flow --*/ delta = PtIn / C_PSTD; theta = TtIn / C_TSTD; Wcin = WIn*sqrtT(theta)*divby(delta); /*------ Calculate corrected speed ---------*/ Nc = Nmech*divby(sqrtT(theta)); if (IDes < 0.5) C_Nc = Nc *divby(NcDes) ; else C_Nc = s_C_Nc; NcMap = Nc *divby(C_Nc); /*-- Compute Total Flow input (from Compressor map) --------*/ if(C > 1) WcMap = interp3Ac(X_C_RlineVec,Y_C_Map_NcVec,Z_C_AlphaVec,T_C_Map_WcArray,Rline,NcMap,Alpha,B,A,C,&interpErr); else WcMap = interp2Ac(X_C_RlineVec,Y_C_Map_NcVec,T_C_Map_WcArray,Rline,NcMap,B,A,&interpErr); if ((WcMapCol != B || WcMapRw != A || WcMapLay !=C) && ssGetIWork(S)[Er1]==0){ printf("Warning in %s, Error calculating WcMap. Table size does not match axis vector lengths.\n", BlkNm); ssSetIWorkValue(S,Er1,1); } else if (interpErr == 1 && ssGetIWork(S)[Er1]==0){ printf("Warning in %s, Error calculating WcMap. Vector definitions may need to be expanded.\n", BlkNm); ssSetIWorkValue(S,Er1,1); } if (IDes < 0.5) C_Wc = Wcin*divby(WcMap); else C_Wc = s_C_Wc; WcCalcin = WcMap * C_Wc; /*-- Compute Pressure Ratio (from Compressor map) --------*/ if(C > 1) PRMap = interp3Ac(X_C_RlineVec,Y_C_Map_NcVec,Z_C_AlphaVec,T_C_Map_PRArray,Rline,NcMap,Alpha,B,A,C,&interpErr); else PRMap = interp2Ac(X_C_RlineVec,Y_C_Map_NcVec,T_C_Map_PRArray,Rline,NcMap,B,A,&interpErr); if ((PRMapCol != B || PRMapRw != A || PRMapLay !=C) && ssGetIWork(S)[Er2]==0){ printf("Warning in %s, Error calculating PRMap. Table size does not match axis vector lengths.\n", BlkNm); ssSetIWorkValue(S,Er2,1); } else if (interpErr == 1 && ssGetIWork(S)[Er2]==0){ printf("Warning in %s, Error calculating PRMap. Vector definitions may need to be expanded.\n", BlkNm); ssSetIWorkValue(S,Er2,1); } if (IDes < 0.5) C_PR = (PRDes -1)*divby(PRMap-1); else C_PR = s_C_PR; PR = C_PR*(PRMap - 1) + 1 ; /*-- Compute Efficiency (from Compressor map) ---*/ if(C > 1) EffMap = interp3Ac(X_C_RlineVec,Y_C_Map_NcVec,Z_C_AlphaVec,T_C_Map_EffArray,Rline,NcMap,Alpha,B,A,C,&interpErr); else EffMap = interp2Ac(X_C_RlineVec,Y_C_Map_NcVec,T_C_Map_EffArray,Rline,NcMap,B,A,&interpErr); if ((EffMapCol != B || EffMapRw != A || EffMapLay !=C) && ssGetIWork(S)[Er3]==0){ printf("Warning in %s, Error calculating EffMap. Table size does not match axis vector lengths.\n", BlkNm); ssSetIWorkValue(S,Er3,1); } else if (interpErr == 1 && ssGetIWork(S)[Er3]==0){ printf("Warning in %s, Error calculating EffMap. Vector definitions may need to be expanded.\n", BlkNm); ssSetIWorkValue(S,Er3,1); } if (IDes < 0.5) C_Eff = EffDes*divby(EffMap); else C_Eff = s_C_Eff; Eff = EffMap * C_Eff; /*------ Compute pressure output --------*/ PtOut = PtIn*PR; /*------ enthalpy calculations ---------*/ /* ---- Ideal enthalpy ----*/ Sout = Sin; TtIdealout = sp2tc(Sout,PtOut,FARcIn); htIdealout = t2hc(TtIdealout,FARcIn); /* ---- Final enthalpy output ----*/ htOut = ((htIdealout - htin)*divby(Eff)) + htin; /*------ Compute Temperature output ---------*/ TtOut = h2tc(htOut,FARcIn); /* initalize Bleed sums components */ Wbleeds = 0; PwrBld = 0; /* compute customer Bleed components */ for (i = 0; i < uWidth1; i++) { /* if customer bleed = 0 or Cust bld is not enabled set outputs to zero */ if (Wcust[i] == 0 || CustBldEn < 0.5){ WcustOut[i] = 0; htcustOut[i] = 0; TtcustOut[i] = 0; PtcustOut[i] = 0; FARcustOut[i] = 0; } else { /*-- Compute sum of customer Bleed Flow output --------*/ Wbleeds = Wbleeds + Wcust[i]; /* add to total bleed value */ WcustOut[i] = Wcust[i]; FARcustOut[i] = FARcIn; htcustOut[i] = htin + FracCusBldht[i]*(htOut - htin); /* calculate customer bleed enthalpy */ PtcustOut[i] = PtIn + FracCusBldPt[i]*(PtOut -PtIn); /* calculate customer bleed Total Pressure */ TtcustOut[i] = h2tc(htcustOut[i],FARcustOut[i]); /* calculate customer bleed Total Temp */ PwrBld = PwrBld + WcustOut[i]*(htcustOut[i]-htOut)*C_BTU_PER_SECtoHP; /* calculate customer bleed power */ } if (i > 4*MaxNumberBleeds && ssGetIWork(S)[Er4]==0){ printf("Error in %s, Number of bleeds in compressor exceeds 100... Array overflow! Reading Bad Data\n", BlkNm); ssSetIWorkValue(S,Er4,1); } } /*----Disable Fractional bleed when requested----*/ for (i = 0; i < uWidth2; i++) { if (FracWbld[i] <= 0 || FBldEn < 0.5 ){ WbldOut[i] = 0; htbldOut[i] = 0; FARbldOut[i] = 0; TtbldOut[i] = 0; PtbldOut[i] = 0; } else { /*-- Compute sum of Fractional Bleed Flow output --------*/ Wbleeds = Wbleeds + FracWbld[i]*WIn; /* add to total bleed value */ WbldOut[i] = FracWbld[i]*WIn; FARbldOut[i] = FARcIn; PtbldOut[i] = PtIn + FracBldPt[i]*(PtOut -PtIn); /* calculate bleed Total Pressure */ htbldOut[i] = htin + FracBldht[i]*(htOut - htin); /* calculate bleed enthalpy */ TtbldOut[i] = h2tc(htbldOut[i],FARbldOut[i]); /* calculate bleed Total Temp */ PwrBld = PwrBld + WbldOut[i]*(htbldOut[i]-htOut)*C_BTU_PER_SECtoHP; /* calculate bleed power */ } if (i > 4*MaxNumberBleeds && ssGetIWork(S)[Er4]==0){ printf("Error in %s, Number of bleeds in compressor exceeds 100... Array overflow! Reading Bad Data\n", BlkNm); ssSetIWorkValue(S,Er4,1); } } /*-- Compute Flows --------*/ Wb4bleed = WIn; WOut = WIn - Wbleeds; /*------ Compute Powers ---------*/ Pwrb4bleed = Wb4bleed * (htin - htOut) * C_BTU_PER_SECtoHP; Pwrout = Pwrb4bleed - PwrBld; /*----- Compute output Torque to shaft ----*/ TorqueOut = C_HP_PER_RPMtoFT_LBF * Pwrout*divby(Nmech); /* ----- Compute Normalized Flow Error ----- */ if (IDes < 0.5 && Rline == 0) NErrorOut = 100; else if (IDes < 0.5) NErrorOut = (Rline - RlineDes)*divby(Rline); else if (WIn == 0) NErrorOut = 100; else NErrorOut = (Wcin - WcCalcin)*divby(Wcin); /* Compute Stall Margin */ if (C > 1){ /* Define 1-D surge margin vectors based on alpha */ for (i = 0; i < D/C; i++){ SMWcVec[i] = interp1Ac(Z_C_AlphaVec, X_C_Map_WcSurgeVec + C*i, Alpha,C, &interpErr); if (interpErr == 1 && ssGetIWork(S)[Er5]==0){ printf("Warning in %s, Error calculating 1D SMWcVec. Vector definitions may need to be adjusted.\n", BlkNm); ssSetIWorkValue(S,Er5,1); } SMPRVec[i] = interp1Ac(Z_C_AlphaVec, T_C_Map_PRSurgeVec + C*i, Alpha,C, &interpErr); if (interpErr == 1 && ssGetIWork(S)[Er5]==0){ printf("Warning in %s, Error calculating 1D SMPRVec. Vector definitions may need to be adjusted.\n", BlkNm); ssSetIWorkValue(S,Er5,1); } } SPRMap = interp1Ac(SMWcVec, SMPRVec,WcMap,A,&interpErr); if (interpErr == 1 && ssGetIWork(S)[Er5]==0){ printf("Warning in %s, Error calculating 2D SPR. Vector definitions may need to be adjusted.\n", BlkNm); ssSetIWorkValue(S,Er5,1); } } else SPRMap = interp1Ac(X_C_Map_WcSurgeVec,T_C_Map_PRSurgeVec,WcMap,D,&interpErr); if (interpErr == 1 && ssGetIWork(S)[Er5]==0){ printf("Warning in %s, Error calculating SPR. Vector definitions may need to be expanded.\n", BlkNm); ssSetIWorkValue(S,Er5,1); } SPR = C_PR*(SPRMap - 1) + 1; SMavail = (SPR - PR)*divby(PR) * 100; SMMap = (SPRMap - PRMap)*divby(PRMap) * 100; /* Test variable */ Test = SPRMap; /*------Assign output values port1------------*/ y[0] = WOut; /* Outlet Total Flow [pps] */ y[1] = htOut; /* Output Enthalpy [BTU/lbm] */ y[2] = TtOut; /* Outlet Temperature [degR] */ y[3] = PtOut; /* Outlet Pressure [psia] */ y[4] = FARcOut; /* Exit Combusted Fuel Flow [frac] */ y[5] = TorqueOut; /* Outlet Torque [lbf*ft] */ y[6] = NErrorOut; /* Normalized compressor Error [frac]*/ y[7] = SMavail; /* Available Stall Margin [%] */ y[8] = C_Nc; /* Corrected shaft speed scalar */ y[9] = C_Wc; /* Corrected flow scalar */ y[10] = C_PR; /* Pressure Ratio scalar */ y[11] = C_Eff; /* Efficiency scalar */ y[12] = Wcin; /* Corrected input flow [pps] */ y[13] = Nc; /* Corrected speed [rpm]*/ y[14] = PR; /* Pressure ratio */ y[15] = NcMap; /* Map corrected speed */ y[16] = WcMap; /* Map corrected flow */ y[17] = PRMap; /* Map pressure ratio */ y[18] = EffMap; /* Map efficiency */ y[19] = SPR; /* Surge pressure ratio */ y[20] = Wbleeds; /* Bleed flow [pps]*/ y[21] = Pwrb4bleed; /* Power if there was no bleed [hp]*/ y[22] = PwrBld; /* Power loss due to bleed [hp] */ y[23] = Pwrout; /* Output power [hp]*/ y[24] = SMMap; /* Stall margin calculated from map values [%]*/ y[25] = SPRMap; /* Map stall pressure ratio*/ y[26] = Test; /* test signal */ /*------Assign output values port2------------*/ /* Customer or flow based bleed*/ for (i = 0; i < uWidth1; i++) { *y1++ = WcustOut[i]; *y1++ = htcustOut[i]; *y1++ = TtcustOut[i]; *y1++ = PtcustOut[i]; *y1++ = FARcustOut[i]; } /*------Assign output values port3------------*/ /* fractional bleed, typically used for turbine cooling flow */ for (i = 0; i < uWidth2; i++) { *y2++ = WbldOut[i]; *y2++ = htbldOut[i]; *y2++ = TtbldOut[i]; *y2++ = PtbldOut[i]; *y2++ = FARbldOut[i]; } }
/*------ the following code uses secant method to calc static pressure ----*/ double calc_Pstatic(double PtOut, double TtOut, double Wout, double Aexit, double *FAR_vec, double *Rt_vec, double *Tt_vec, double *gamma_array, double FAR, int A1, int B1) { double Rt, gammat, tolerance; double x1, x2, x3, y1, y2, y3, z1, z2, z3, e1, e2, e3; int maxIters, ncount; int interpErr = 0; /*--- where gas constant is R = f(FAR), but NOT P & T ----*/ Rt = interp1Ac(FAR_vec,Rt_vec,FAR,A1, &interpErr); /* with FAR = 0 */ if (interpErr == 1){ printf("Warning in calc_Pstatic subroutine, Error calculating Rt. Vector definitions may need to be expanded.\n"); } /*---- gamma depends on FAR and temp -----*/ gammat = interp2Ac(FAR_vec,Tt_vec,gamma_array,FAR,TtOut,A1,B1, &interpErr); /* with FAR = 0 */ if (interpErr == 1){ printf("Warning in calc_Pstatic subroutine, Error calculating gammat. Vector definitions may need to be expanded.\n"); } /*------ iterate on Mach number until get computed flow = W ----*/ tolerance = 0.02; /* flow tolerance (pps) */ maxIters = 10; /*----- use these 2 points to start the solution ----*/ /* where x ==> MN, y ==> W, and z ==> Ps */ x1 = 0.2; x2 = 0.5; y1 = calc_WvsMN(x1,PtOut,TtOut,Rt,gammat,Aexit); /* with FAR = 0 */ z1 = calc_PsvsMN(x1,PtOut,gammat); y2 = calc_WvsMN(x2,PtOut,TtOut,Rt,gammat,Aexit); /* with FAR = 0 */ z2 = calc_PsvsMN(x2,PtOut,gammat); e1 = Wout - y1; e2 = Wout - y2; e3 = 999; /* force it into the while loop */ ncount = 0; /*---- iterate x until the error is within tolerance ----*/ while ((fabs(e3) > tolerance) && (ncount < maxIters)) { if (x2 - (e2*(x2-x1)*divby(e2-e1)) > 0.01) x3 = x2 - (e2*(x2-x1)*divby(e2-e1)); else x3 = 0.01; /*----- compute y3 value (W) for new x3 (MN) ----- */ /* also compute z3 value (Ps) for new x3 */ y3 = calc_WvsMN(x3,PtOut,TtOut,Rt,gammat,Aexit); /* with FAR = 0 */ z3 = calc_PsvsMN(x3,PtOut,gammat); /*------ calculate the new error -----*/ e3 = Wout - y3; /*---- want to keep solution bounded for next iteration ---*/ if (e1*e3 <= 0) { /* solution lies between x1 and x3, or at x3 */ x2 = x3; y2 = y3; e2 = e3; } else { /* solution lies between x2 and x3 */ x1 = x3; y1 = y3; e1 = e3; } ncount++; } return z3; }
static void mdlOutputs(SimStruct *S, int_T tid) { /*--------parameters defined in S-function block--------*/ const real_T AFARc = *mxGetPr(AFARc_p(S)); /*-------- vector & array data -------*/ const real_T *X_A_AltVec = mxGetPr(X_A_AltVec_p(S)); const real_T *T_A_TsVec = mxGetPr(T_A_TsVec_p(S)); const real_T *T_A_PsVec = mxGetPr(T_A_PsVec_p(S)); const real_T *X_A_FARVec = mxGetPr(X_A_FARVec_p(S)); const real_T *T_A_RtArray = mxGetPr(T_A_RtArray_p(S)); const real_T *Y_A_TVec = mxGetPr(Y_A_TVec_p(S)); const real_T *T_A_gammaArray = mxGetPr(T_A_gammaArray_p(S)); /*------get dimensions of parameter arrays-------*/ const int_T A = mxGetNumberOfElements(X_A_AltVec_p(S)); const int_T B = mxGetNumberOfElements(X_A_FARVec_p(S)); const int_T C = mxGetNumberOfElements(Y_A_TVec_p(S)); /*---------Define Inputs--------*/ const real_T *u = (const real_T*) ssGetInputPortSignal(S,0); double AltIn = u[0]; /* Altitude(ft) */ double dTempIn = u[1]; /* delta Temperature [degF] */ double MNIn = u[2]; /* Mach Number (frac) */ real_T *y = (real_T *)ssGetOutputPortRealSignal(S,0); /* Output Array */ /*--------Define Constants-------*/ double PsOut, TsOut, TtOut, PtOut, VengOut, TsStDayOut, Vsound; double Ttg, Ptg, Vg, Vsg, MNg, Sout, htg, gammasg, Rs, Rt; double hs, htOut; double er, er_old, erthr, Ptg_new, Ptg_old, FAR, FAROut; int iter, maxiter; int interpErr = 0; /* ------- 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); FAR = AFARc; Rt = interp1Ac(X_A_FARVec,T_A_RtArray,FAR,B,&interpErr); if (interpErr == 1 && ssGetIWork(S)[0]==0){ printf("Warning in %s, Error calculating Rt. Vector definitions may need to be expanded.\n", BlkNm); ssSetIWorkValue(S,0,1); } Rs = Rt; /* Static Temperature */ TsStDayOut = interp1Ac(X_A_AltVec,T_A_TsVec,AltIn,A,&interpErr); if (interpErr == 1 && ssGetIWork(S)[1]==0){ printf("Warning in %s, Error calculating TsStDayOut. Vector definitions may need to be expanded.\n", BlkNm); ssSetIWorkValue(S,0,1); } TsOut = TsStDayOut + dTempIn; /* Static Pressure*/ PsOut = interp1Ac(X_A_AltVec,T_A_PsVec,AltIn,A,&interpErr); if (interpErr == 1 && ssGetIWork(S)[2]==0){ printf("Warning in %s, Error calculating PsOut. Vector definitions may need to be expanded.\n", BlkNm); ssSetIWorkValue(S,1,1); } /* Calc output entropy */ Sout = pt2sc(PsOut, TsOut, FAR); /* Determine Static enthalpy */ hs = t2hc(TsOut,FAR); /* Pt guess */ /*------ Total Temperature ---------*/ Ttg = TsOut * (1+MNIn*MNIn*(C_GAMMA-1)/2); /*------ Total Pressure ---------*/ Ptg = PsOut/(pow((TsOut/Ttg),(C_GAMMA/(C_GAMMA-1)))); /* calculate total temperature */ Ttg = sp2tc(Sout,Ptg,FAR); /* calculate total enthalpy */ htg = t2hc(Ttg,FAR); /* calculate velocity */ Vg = sqrt(2 * (htg - hs)*C_GRAVITY*JOULES_CONST); gammasg = interp2Ac(X_A_FARVec,Y_A_TVec,T_A_gammaArray,FAR,TsOut,B,C,&interpErr); if (interpErr == 1 && ssGetIWork(S)[3]==0){ printf("Warning in %s, Error calculating iteration gammasg. Vector definitions may need to be expanded.\n", BlkNm); ssSetIWorkValue(S,3,1); } Vsg = sqrt(gammasg*Rs*TsOut*C_GRAVITY*JOULES_CONST); MNg = Vg/Vsg; er = MNIn - MNg; Ptg_new = Ptg + 0.05; maxiter = 15; iter = 0; erthr = 0.001; while (fabs(er) > erthr && iter < maxiter) { er_old = er; Ptg_old = Ptg; if(fabs(Ptg - Ptg_new) < 0.03) Ptg = Ptg + 0.05; else Ptg = Ptg_new; /* calculate Total emperature */ Ttg = sp2tc(Sout,Ptg,FAR); /* calculate total enthalpy */ htg = t2hc(Ttg,FAR); /* calculate velocity */ Vg = sqrt(2 * (htg - hs)*C_GRAVITY*JOULES_CONST); Vsg = sqrt(gammasg*Rs*TsOut*C_GRAVITY*JOULES_CONST); MNg = Vg/Vsg; er = MNIn - MNg; if (fabs(er) > erthr) { /* determine next guess pressure by secant algorithm */ Ptg_new = Ptg - er *(Ptg - Ptg_old)/(er - er_old); } iter = iter + 1; } if (iter == maxiter && ssGetIWork(S)[3]==0 ){ printf("Warning in %s, Error calculating Pt at input MN. There may be error in output pressure\n", BlkNm); ssSetIWorkValue(S,4,1); } htOut = htg; TtOut = Ttg; PtOut = Ptg; /*---- Engine Velocity ---------*/ Vsound = Vsg; VengOut = Vsound * MNIn; FAROut = FAR; /*------Assign output values------------*/ y[0] = htOut; /* Total enthalpy */ y[1] = TtOut; /* Total Temperature [degR] */ y[2] = PtOut; /* Total Pressure [psia] */ y[3] = FAROut; /* Fuel to Air Ratio */ y[4] = PsOut; /* Static Pressure [psia] */ y[5] = TsOut; /* Static Temperature [degR] */ y[6] = VengOut; /* Engine Velocity [ft/sec] */ }
static void mdlOutputs(SimStruct *S, int_T tid) { /*--------Define Parameters-------*/ const real_T s_T_Nc = *mxGetPr(s_T_Nc_p(S)); const real_T s_T_PR = *mxGetPr(s_T_PR_p(S)); const real_T s_T_Wc = *mxGetPr(s_T_Wc_p(S)); const real_T s_T_Eff = *mxGetPr(s_T_Eff_p(S)); 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] */ /*---------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); int cfWidth = ssGetCurrentInputPortDimensions(S, 1, 0); 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)[0]==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,0,1); } else if(BldPosLeng != cfWidth/5 && CoolFlwEn > 0.5 && ssGetIWork(S)[1]==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,1,1); } /* 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)[2]==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,2,1); } /* 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])/(1+FARcool[i]); Wfcoolout = Wfcoolout + FARcool[i]*Wcool[i]/(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/(1+FARcIn) + Wfcools1)/(WIn/(1+FARcIn) + Wcools1- Wfcools1); FARcOut = (FARcIn* WIn/(1+FARcIn)+ Wfcoolout)/(WIn/(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)/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/sqrt(theta); if(IDes < 0.5) C_Nc = Nc / NcDes; else C_Nc = s_T_Nc; NcMap = Nc / 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)[3]==0){ printf("Warning in %s, Error calculating psiMapI. Vector definitions may need to be expanded.\n", BlkNm); ssSetIWorkValue(S,3,1); } EffMap = psiMapIn/psiMapI; if(IDes < 0.5) C_Eff = EffDes / 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*pow((TtOutIdeal/TtIn),(gamma_T/(gamma_T-1))); TtOutIdealg = sp2tc(Sout,Ptoutg,FARs1in); erT = 100*abs_D(TtOutIdealg - TtOutIdeal)/TtOutIdeal; Ptoutg_new = Ptoutg; /* iterate to find Ptout when TtOutIdeal guess = TtOutIdeal */ while (abs_D(erT) > 0.05) { erT_old = erT; Ptoutg_old = Ptoutg; if(abs_D(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)/TtOutIdeal; if (abs_D(erT) > 0.05) { /* determine next guess pressure by secant algorithm */ Ptoutg_new = Ptoutg - erT *(Ptoutg - Ptoutg_old)/(erT - erT_old); } } PRin = PtIn/Ptoutg; /*------ Compute pressure output --------*/ if(IDes < 0.5) C_PR = (PRin - 1)/(PRmapDes -1); else C_PR = s_T_PR; PRmapRead = (PRin -1)/C_PR + 1; PtOut = PtIn/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)[4]==0){ printf("Warning in %s, Error calculating WoWMap. Vector definitions may need to be expanded.\n", BlkNm); ssSetIWorkValue(S,4,1); } WpqAcrit = sqrt((gamma_T*C_GRAVITY)/(Rt_T*JOULES_CONST))/pow((1+(gamma_T-1)/2),((gamma_T+1)/(2*(gamma_T-1)))); WMap = WoWMap * WpqAcrit * (PtIn/sqrt(Tts1in)); WcMap = WMap * sqrt(theta)/delta; if(IDes < 0.5) C_Wc = Ws1in*sqrt(theta)/delta / 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)/WOut; /*------ Compute Temperature output (empirical) ---------*/ TtOut = h2tc(htOut,FARcOut); /*----- Compute output Torque to shaft ----*/ TorqueOut = C_HP_PER_RPMtoFT_LBF * Pwrout/Nmech; /* ----- Compute Normalized Flow Error ----- */ if (IDes < 0.5 && NDes == 0) NErrorOut = 100; else if (IDes < 0.5) NErrorOut = (Nmech - NDes)/NDes; else if (Ws1in == 0) { NErrorOut = 100; } else { NErrorOut = (Ws1in*sqrt(theta)/delta-WcCalcin)/(Ws1in*sqrt(theta)/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) { /*--------parameters defined in S-function block--------*/ const real_T AthroatIn = *mxGetPr(AthroatIn_p(S)); /* input throat area (sq-in) */ const real_T MNIn = *mxGetPr(MNIn_p(S)); /* input throat area (sq-in) */ const int_T SolveType = *mxGetPr(SolveType_p(S)); /* 0-solve based on Ath, 1-solve based on MNIn*/ /*-------- vector & array data -------*/ const real_T *X_FARVec = mxGetPr(X_FARVec_p(S)); const real_T *T_RtArray = mxGetPr(T_RtArray_p(S)); const real_T *Y_TtVec = mxGetPr(Y_TtVec_p(S)); const real_T *T_gammaArray = mxGetPr(T_gammaArray_p(S)); /*------get dimensions of parameter arrays-------*/ const int_T A = mxGetNumberOfElements(X_FARVec_p(S)); const int_T B = mxGetNumberOfElements(Y_TtVec_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]; /* enthaply [BTU/lbm] */ double TtIn = u[2]; /* Temperature Input [degR] */ double PtIn = u[3]; /* Pressure Input [psia] */ double FARcIn = u[4]; /* Combusted Fuel to Air Ratio [frac] */ real_T *y = (real_T *)ssGetOutputPortRealSignal(S,0); /* Output Array */ /*--------Define Constants-------*/ double PsOut, TsOut, rhosOut, MNOut, AthOut; double Sin, htin; double Rt, Rs; double TsMNg, PsMNg, MNg; double Tsg, Psg, Psg_new, Psg_old, Acalc, erA, erA_old; double gammatg, gammasg, hsg, rhosg, Vg; double erMN_old, erMN, PsMNg_old, PsMNg_new; double erthr; int maxiter, iter; int interpErr = 0; /* ------- 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); /* Calc entropy */ Sin = pt2sc(PtIn, TtIn, FARcIn); /*-- Compute Input enthalpy --------*/ htin = t2hc(TtIn,FARcIn); /* Where gas constant is R = f(FAR), but NOT P & T */ Rt = interp1Ac(X_FARVec,T_RtArray,FARcIn,A,&interpErr); if (interpErr == 1 && ssGetIWork(S)[0]==0){ printf("Warning in %s, Error calculating Rt. Vector definitions may need to be expanded.\n", BlkNm); ssSetIWorkValue(S,0,1); } Rs = Rt; /* Solve for Ts and Ps when MN is known*/ if (SolveType == 1) { /*---- set MN = MNIn and calc SS Ps for iteration IC --------*/ MNg = MNIn; gammatg = interp2Ac(X_FARVec,Y_TtVec,T_gammaArray,FARcIn,TtIn,A,B,&interpErr); if (interpErr == 1 && ssGetIWork(S)[1]==0){ printf("Warning in %s, Error calculating gammatg. Vector definitions may need to be expanded.\n", BlkNm); ssSetIWorkValue(S,1,1); } TsMNg = TtIn /(1+MNg*MNg*(gammatg-1)/2); PsMNg = PtIn*pow((TsMNg/TtIn),(gammatg/(gammatg-1))); PcalcStat(PtIn, PsMNg, TtIn, htin, FARcIn, Rt, &Sin, &TsMNg, &hsg, &rhosg, &Vg); gammasg = interp2Ac(X_FARVec,Y_TtVec,T_gammaArray,FARcIn,TsMNg,A,B,&interpErr); if (interpErr == 1 && ssGetIWork(S)[2]==0){ printf("Warning in %s, Error calculating gammasg. Vector definitions may need to be expanded.\n", BlkNm); ssSetIWorkValue(S,2,1); } MNg = Vg/sqrt(gammasg*Rs*TsMNg*C_GRAVITY*JOULES_CONST); if (Vg > 0.0001){ Acalc = WIn/(Vg * rhosg/C_SINtoSFT);} else { Acalc = 999; /* if velocity is close to zero assume a very large Ath */} erMN = MNIn - MNg; PsMNg_new = PsMNg + 0.05; maxiter = 15; iter = 0; erthr = 0.0001; /* if Ps is not close enough to Ps at MN = MNIn, iterate to find Ps at MN = MNIn */ while (fabs(erMN) > erthr && iter < maxiter) { erMN_old = erMN; PsMNg_old = PsMNg; if(fabs(PsMNg - PsMNg_new) < 0.003) PsMNg = PsMNg + 0.005; else PsMNg = PsMNg_new; PcalcStat(PtIn, PsMNg, TtIn, htin, FARcIn, Rt, &Sin, &TsMNg, &hsg, &rhosg, &Vg); gammasg = interp2Ac(X_FARVec,Y_TtVec,T_gammaArray,FARcIn,TsMNg,A,B,&interpErr); if (interpErr == 1 && ssGetIWork(S)[3]==0){ printf("Warning in %s, Error calculating iteration gammasg. Vector definitions may need to be expanded.\n", BlkNm); ssSetIWorkValue(S,3,1); } MNg = Vg/sqrt(gammasg*Rs*TsMNg*C_GRAVITY*JOULES_CONST); /* calculated Area */ if (Vg > 0.0001){ Acalc = WIn/(Vg * rhosg/C_SINtoSFT);} else { Acalc = 999; /* if velocity is close to zero assume a very large Ath */} erMN = MNIn - MNg; if (fabs(erMN) > erthr) { /* determine next guess pressure by secant algorithm */ PsMNg_new = PsMNg - erMN *(PsMNg - PsMNg_old)/(erMN - erMN_old); } iter = iter + 1; } if (iter == maxiter && ssGetIWork(S)[4]==0 ){ printf("Warning in %s, Error calculating Ps at MN = MNIn. There may be error in block outputs\n", BlkNm); ssSetIWorkValue(S,4,1); } TsOut = TsMNg; PsOut = PsMNg; rhosOut = rhosg; MNOut = MNIn; AthOut = Acalc; } /* Solve for Ts and Ps when Ath is known*/ else if (SolveType == 0) { /* guess Psout and calculate an initial Area error */ MNg = 0.4; gammatg = 1.4; Tsg = TtIn /(1+MNg*MNg*(gammatg-1)/2); Psg = PtIn*pow((Tsg/TtIn),(gammatg/(gammatg-1))); PcalcStat(PtIn, Psg, TtIn, htin, FARcIn, Rt, &Sin, &Tsg, &hsg, &rhosg, &Vg); Acalc = WIn/(Vg * rhosg/C_SINtoSFT); MNg = Vg/sqrt(gammasg*Rs*Tsg*C_GRAVITY*JOULES_CONST); /* determine guess error for static pressure iteration */ erA = (AthroatIn - Acalc)/AthroatIn; /* determine iteration constants */ iter = 0; maxiter = 1000; Psg_new = Psg + 0.05; erthr = 0.0001; while ( fabs(erA) > erthr && iter < maxiter){ erA_old = erA; Psg_old = Psg; if(fabs(Psg - Psg_new) < 0.0003) { Psg = Psg + 0.0005; } else { Psg = Psg_new; } /* calculate flow velocity and rhos */ PcalcStat(PtIn, Psg, TtIn, htin, FARcIn, Rt, &Sin, &Tsg, &hsg, &rhosg, &Vg); gammasg = interp2Ac(X_FARVec,Y_TtVec,T_gammaArray,FARcIn,Tsg,A,B,&interpErr); if (interpErr == 1 && ssGetIWork(S)[3]==0){ printf("Warning in %s, Error calculating iteration gammasg. Vector definitions may need to be expanded.\n", BlkNm); ssSetIWorkValue(S,3,1); } MNg = Vg/sqrt(gammasg*Rs*Tsg*C_GRAVITY*JOULES_CONST); if (Vg > 0.0001) { /* calculated Area */ Acalc = WIn/(Vg * rhosg/C_SINtoSFT); /*determine error */ erA = (AthroatIn - Acalc)/AthroatIn; } else { erA = 0; Psg = PtIn; Tsg = TtIn; Acalc = 999; } if (fabs(erA) > erthr) { /* determine next guess pressure by secant algorithm */ Psg_new = Psg - erA *(Psg - Psg_old)/(erA - erA_old); /* limit algorthim change */ if (Psg_new > 1.001*Psg) { Psg_new = 1.002 * Psg; } else if (Psg_new < 0.999 * Psg) { Psg_new = 0.998 * Psg; } } iter = iter + 1; } TsOut = Tsg; PsOut = Psg; rhosOut = rhosg; MNOut = MNg; AthOut = Acalc; } else { if (ssGetIWork(S)[5]==0 ){ printf("Warning in %s, SolveType_M is not valid. There may be error in block outputs\n", BlkNm); ssSetIWorkValue(S,5,1); } TsOut = TtIn; PsOut = PtIn; rhosOut = 1; MNOut = 0; AthOut = 100; } /*------Assign output values------------*/ y[0] = TsOut; /* static Temperature [degR] */ y[1] = PsOut; /* static Pressure [psia] */ y[2] = rhosOut; /* static rho [lbm/ft3]*/ y[3] = MNOut; /* mach number [frac]*/ y[4] = AthOut; /* throat area [in^2] */ }
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 */ }