/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
Module: FGTurbine.cpp
- Author: Jon S. Berndt
- Date started: 08/23/2002
+ Author: David Culp
+ Date started: 03/11/2003
Purpose: This module models a turbine engine.
- ------------- Copyright (C) 2002 Jon S. Berndt (jsb@hal-pc.org) --------------
+ ------------- Copyright (C) 2003 David Culp (davidculp2@comcast.net) ---------
This program is free software; you can redistribute it and/or modify it under
the terms of the GNU General Public License as published by the Free Software
FUNCTIONAL DESCRIPTION
--------------------------------------------------------------------------------
-This class descends from the FGEngine class and models a Turbine engine based
+This class descends from the FGEngine class and models a turbine engine based
on parameters given in the engine config file for this class
HISTORY
--------------------------------------------------------------------------------
-08/23/2002 JSB Created
+03/11/2003 DPC Created
+09/08/2003 DPC Changed Calculate() and added engine phases
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
INCLUDES
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
+#include <vector>
+#include <sstream>
+
#include "FGTurbine.h"
+namespace JSBSim {
+
static const char *IdSrc = "$Id$";
static const char *IdHdr = ID_TURBINE;
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
-FGTurbine::FGTurbine(FGFDMExec* exec, FGConfigFile* cfg) : FGEngine(exec)
+FGTurbine::FGTurbine(FGFDMExec* exec, FGConfigFile* cfg, int engine_number)
+ : FGEngine(exec, engine_number)
{
+ SetDefaults();
+
+ Load(cfg);
Debug(0);
}
FGTurbine::~FGTurbine()
{
+ unbind();
Debug(1);
}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+// The main purpose of Calculate() is to determine what phase the engine should
+// be in, then call the corresponding function.
+
+double FGTurbine::Calculate(void)
+{
+ TAT = (Auxiliary->GetTotalTemperature() - 491.69) * 0.5555556;
+ dt = State->Getdt() * Propulsion->GetRate();
+ ThrottlePos = FCS->GetThrottlePos(EngineNumber);
+ if (ThrottlePos > 1.0) {
+ AugmentCmd = ThrottlePos - 1.0;
+ ThrottlePos -= AugmentCmd;
+ } else {
+ AugmentCmd = 0.0;
+ }
+
+ // When trimming is finished check if user wants engine OFF or RUNNING
+ if ((phase == tpTrim) && (dt > 0)) {
+ if (Running && !Starved) {
+ phase = tpRun;
+ N2 = IdleN2 + ThrottlePos * N2_factor;
+ N1 = IdleN1 + ThrottlePos * N1_factor;
+ OilTemp_degK = 366.0;
+ Cutoff = false;
+ }
+ else {
+ phase = tpOff;
+ Cutoff = true;
+ EGT_degC = TAT;
+ }
+ }
+
+ if (!Running && Cutoff && Starter) {
+ if (phase == tpOff) phase = tpSpinUp;
+ }
+ if (!Running && !Cutoff && (N2 > 15.0)) phase = tpStart;
+ if (Cutoff && (phase != tpSpinUp)) phase = tpOff;
+ if (dt == 0) phase = tpTrim;
+ if (Starved) phase = tpOff;
+ if (Stalled) phase = tpStall;
+ if (Seized) phase = tpSeize;
+
+ switch (phase) {
+ case tpOff: Thrust = Off(); break;
+ case tpRun: Thrust = Run(); break;
+ case tpSpinUp: Thrust = SpinUp(); break;
+ case tpStart: Thrust = Start(); break;
+ case tpStall: Thrust = Stall(); break;
+ case tpSeize: Thrust = Seize(); break;
+ case tpTrim: Thrust = Trim(); break;
+ default: Thrust = Off();
+ }
+
+ // The thruster can modify the thrust, eg. thrust reverser
+ return Thrust = Thruster->Calculate(Thrust);
+}
+
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+double FGTurbine::Off(void)
+{
+ double qbar = Auxiliary->Getqbar();
+ Running = false;
+ FuelFlow_pph = Seek(&FuelFlow_pph, 0, 1000.0, 10000.0);
+ N1 = Seek(&N1, qbar/10.0, N1/2.0, N1/2.0);
+ N2 = Seek(&N2, qbar/15.0, N2/2.0, N2/2.0);
+ EGT_degC = Seek(&EGT_degC, TAT, 11.7, 7.3);
+ OilTemp_degK = Seek(&OilTemp_degK, TAT + 273.0, 0.2, 0.2);
+ OilPressure_psi = N2 * 0.62;
+ NozzlePosition = Seek(&NozzlePosition, 1.0, 0.8, 0.8);
+ EPR = Seek(&EPR, 1.0, 0.2, 0.2);
+ Augmentation = false;
+ return 0.0;
+}
+
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-double FGTurbine::Calculate(double dummy)
+double FGTurbine::Run(void)
{
+ double idlethrust, milthrust, thrust;
+ double N2norm; // 0.0 = idle N2, 1.0 = maximum N2
+ idlethrust = MilThrust * ThrustTables[0]->TotalValue();
+ milthrust = (MilThrust - idlethrust) * ThrustTables[1]->TotalValue();
+
+ Running = true;
+ Starter = false;
+
+ N2 = Seek(&N2, IdleN2 + ThrottlePos * N2_factor, delay, delay * 3.0);
+ N1 = Seek(&N1, IdleN1 + ThrottlePos * N1_factor, delay, delay * 2.4);
+ N2norm = (N2 - IdleN2) / N2_factor;
+ thrust = idlethrust + (milthrust * N2norm * N2norm);
+ EGT_degC = TAT + 363.1 + ThrottlePos * 357.1;
+ OilPressure_psi = N2 * 0.62;
+ OilTemp_degK = Seek(&OilTemp_degK, 366.0, 1.2, 0.1);
+
+ if (!Augmentation) {
+ double correctedTSFC = TSFC * (0.84 + (1-N2norm)*(1-N2norm));
+ FuelFlow_pph = Seek(&FuelFlow_pph, thrust * correctedTSFC, 1000.0, 100000);
+ if (FuelFlow_pph < IdleFF) FuelFlow_pph = IdleFF;
+ NozzlePosition = Seek(&NozzlePosition, 1.0 - N2norm, 0.8, 0.8);
+ thrust = thrust * (1.0 - BleedDemand);
+ EPR = 1.0 + thrust/MilThrust;
+ }
+
+ if (AugMethod == 1) {
+ if ((ThrottlePos > 0.99) && (N2 > 97.0)) {Augmentation = true;}
+ else {Augmentation = false;}
+ }
+
+ if ((Augmented == 1) && Augmentation && (AugMethod < 2)) {
+ thrust = MaxThrust * ThrustTables[2]->TotalValue();
+ FuelFlow_pph = Seek(&FuelFlow_pph, thrust * ATSFC, 5000.0, 10000.0);
+ NozzlePosition = Seek(&NozzlePosition, 1.0, 0.8, 0.8);
+ }
+
+ if (AugMethod == 2) {
+ if (AugmentCmd > 0.0) {
+ Augmentation = true;
+ double tdiff = (MaxThrust * ThrustTables[2]->TotalValue()) - thrust;
+ thrust += (tdiff * AugmentCmd);
+ FuelFlow_pph = Seek(&FuelFlow_pph, thrust * ATSFC, 5000.0, 10000.0);
+ NozzlePosition = Seek(&NozzlePosition, 1.0, 0.8, 0.8);
+ } else {
+ Augmentation = false;
+ }
+ }
+
+ if ((Injected == 1) && Injection) {
+ thrust = thrust * ThrustTables[3]->TotalValue();
+ }
+
ConsumeFuel();
+ if (Cutoff) phase = tpOff;
+ if (Starved) phase = tpOff;
+
+ return thrust;
+}
+
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+double FGTurbine::SpinUp(void)
+{
+ Running = false;
+ FuelFlow_pph = 0.0;
+ N2 = Seek(&N2, 25.18, 3.0, N2/2.0);
+ N1 = Seek(&N1, 5.21, 1.0, N1/2.0);
+ EGT_degC = Seek(&EGT_degC, TAT, 11.7, 7.3);
+ OilPressure_psi = N2 * 0.62;
+ OilTemp_degK = Seek(&OilTemp_degK, TAT + 273.0, 0.2, 0.2);
+ EPR = 1.0;
+ NozzlePosition = 1.0;
return 0.0;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGTurbine::doInlet(void)
+double FGTurbine::Start(void)
{
+ if ((N2 > 15.0) && !Starved) { // minimum 15% N2 needed for start
+ Cranking = true; // provided for sound effects signal
+ if (N2 < IdleN2) {
+ N2 = Seek(&N2, IdleN2, 2.0, N2/2.0);
+ N1 = Seek(&N1, IdleN1, 1.4, N1/2.0);
+ EGT_degC = Seek(&EGT_degC, TAT + 363.1, 21.3, 7.3);
+ FuelFlow_pph = Seek(&FuelFlow_pph, IdleFF, 103.7, 103.7);
+ OilPressure_psi = N2 * 0.62;
+ ConsumeFuel();
+ }
+ else {
+ phase = tpRun;
+ Running = true;
+ Starter = false;
+ Cranking = false;
+ }
+ }
+ else { // no start if N2 < 15%
+ phase = tpOff;
+ Starter = false;
+ }
+
+ return 0.0;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGTurbine::doCompressor(void)
+double FGTurbine::Stall(void)
{
+ double qbar = Auxiliary->Getqbar();
+ EGT_degC = TAT + 903.14;
+ FuelFlow_pph = IdleFF;
+ N1 = Seek(&N1, qbar/10.0, 0, N1/10.0);
+ N2 = Seek(&N2, qbar/15.0, 0, N2/10.0);
+ ConsumeFuel();
+ if (ThrottlePos < 0.01) phase = tpRun; // clear the stall with throttle
+
+ return 0.0;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGTurbine::doBleedDuct(void)
+double FGTurbine::Seize(void)
{
+ double qbar = Auxiliary->Getqbar();
+ N2 = 0.0;
+ N1 = Seek(&N1, qbar/20.0, 0, N1/15.0);
+ FuelFlow_pph = IdleFF;
+ ConsumeFuel();
+ OilPressure_psi = 0.0;
+ OilTemp_degK = Seek(&OilTemp_degK, TAT + 273.0, 0, 0.2);
+ Running = false;
+ return 0.0;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGTurbine::doCombustor(void)
+double FGTurbine::Trim(void)
{
+ double idlethrust, milthrust, thrust, tdiff;
+ idlethrust = MilThrust * ThrustTables[0]->TotalValue();;
+ milthrust = (MilThrust - idlethrust) * ThrustTables[1]->TotalValue();
+ thrust = (idlethrust + (milthrust * ThrottlePos * ThrottlePos))
+ * (1.0 - BleedDemand);
+ if (AugmentCmd > 0.0) {
+ tdiff = (MaxThrust * ThrustTables[2]->TotalValue()) - thrust;
+ thrust += (tdiff * AugmentCmd);
+ }
+
+ return thrust;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGTurbine::doTurbine(void)
+double FGTurbine::CalcFuelNeed(void)
{
+ return FuelFlow_pph /3600 * State->Getdt() * Propulsion->GetRate();
+}
+
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+double FGTurbine::GetPowerAvailable(void) {
+ if( ThrottlePos <= 0.77 )
+ return 64.94*ThrottlePos;
+ else
+ return 217.38*ThrottlePos - 117.38;
+}
+
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+double FGTurbine::Seek(double *var, double target, double accel, double decel) {
+ double v = *var;
+ if (v > target) {
+ v -= dt * decel;
+ if (v < target) v = target;
+ } else if (v < target) {
+ v += dt * accel;
+ if (v > target) v = target;
+ }
+ return v;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGTurbine::doConvergingNozzle(void)
+void FGTurbine::SetDefaults(void)
{
+ Name = "Not defined";
+ N1 = N2 = 0.0;
+ Type = etTurbine;
+ MilThrust = 10000.0;
+ MaxThrust = 10000.0;
+ BypassRatio = 0.0;
+ TSFC = 0.8;
+ ATSFC = 1.7;
+ IdleN1 = 30.0;
+ IdleN2 = 60.0;
+ MaxN1 = 100.0;
+ MaxN2 = 100.0;
+ Augmented = 0;
+ AugMethod = 0;
+ Injected = 0;
+ BleedDemand = 0.0;
+ ThrottlePos = 0.0;
+ AugmentCmd = 0.0;
+ InletPosition = 1.0;
+ NozzlePosition = 1.0;
+ Augmentation = false;
+ Injection = false;
+ Reversed = false;
+ Cutoff = true;
+ phase = tpOff;
+ Stalled = false;
+ Seized = false;
+ Overtemp = false;
+ Fire = false;
+ EGT_degC = 0.0;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGTurbine::doTransition(void)
+bool FGTurbine::Load(FGConfigFile *Eng_cfg)
{
+ string token;
+
+ Name = Eng_cfg->GetValue("NAME");
+ Eng_cfg->GetNextConfigLine();
+ int counter=0;
+
+ while ( ((token = Eng_cfg->GetValue()) != string("/FG_TURBINE")) &&
+ (token != string("/FG_SIMTURBINE")) ) {
+ *Eng_cfg >> token;
+
+ if (token[0] == '<') token.erase(0,1); // Tables are read "<TABLE"
+
+ if (token == "MILTHRUST") *Eng_cfg >> MilThrust;
+ else if (token == "MAXTHRUST") *Eng_cfg >> MaxThrust;
+ else if (token == "BYPASSRATIO") *Eng_cfg >> BypassRatio;
+ else if (token == "BLEED") *Eng_cfg >> BleedDemand;
+ else if (token == "TSFC") *Eng_cfg >> TSFC;
+ else if (token == "ATSFC") *Eng_cfg >> ATSFC;
+ else if (token == "IDLEN1") *Eng_cfg >> IdleN1;
+ else if (token == "IDLEN2") *Eng_cfg >> IdleN2;
+ else if (token == "MAXN1") *Eng_cfg >> MaxN1;
+ else if (token == "MAXN2") *Eng_cfg >> MaxN2;
+ else if (token == "AUGMENTED") *Eng_cfg >> Augmented;
+ else if (token == "AUGMETHOD") *Eng_cfg >> AugMethod;
+ else if (token == "INJECTED") *Eng_cfg >> Injected;
+ else if (token == "MINTHROTTLE") *Eng_cfg >> MinThrottle;
+ else if (token == "TABLE") {
+ if (counter++ == 0) Debug(2); // print engine specs prior to table read
+ ThrustTables.push_back( new FGCoefficient(FDMExec) );
+ ThrustTables.back()->Load(Eng_cfg);
+ }
+ else cerr << "Unhandled token in Engine config file: " << token << endl;
+ if (token == "EOF") return false;
+ }
+
+ // Pre-calculations and initializations
+
+ delay = 60.0 / (BypassRatio + 3.0);
+ N1_factor = MaxN1 - IdleN1;
+ N2_factor = MaxN2 - IdleN2;
+ OilTemp_degK = (Auxiliary->GetTotalTemperature() - 491.69) * 0.5555556 + 273.0;
+ IdleFF = pow(MilThrust, 0.2) * 107.0; // just an estimate
+
+ bindmodel();
+ return true;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+string FGTurbine::GetEngineLabels(string delimeter)
+{
+ std::ostringstream buf;
+
+ buf << Name << "_N1[" << EngineNumber << "]" << delimeter
+ << Name << "_N2[" << EngineNumber << "]" << delimeter
+ << Thruster->GetThrusterLabels(EngineNumber, delimeter);
-bool FGTurbine::Load(FGConfigFile *AC_cfg)
+ return buf.str();
+}
+
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+string FGTurbine::GetEngineValues(string delimeter)
{
+ std::ostringstream buf;
+
+ buf << N1 << delimeter
+ << N2 << delimeter
+ << Thruster->GetThrusterValues(EngineNumber, delimeter);
+
+ return buf.str();
+}
+
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+void FGTurbine::bindmodel()
+{
+ char property_name[80];
+
+ snprintf(property_name, 80, "propulsion/engine[%u]/n1", EngineNumber);
+ PropertyManager->Tie( property_name, &N1);
+ snprintf(property_name, 80, "propulsion/engine[%u]/n2", EngineNumber);
+ PropertyManager->Tie( property_name, &N2);
+ snprintf(property_name, 80, "propulsion/engine[%u]/fuel-flow", EngineNumber);
+ PropertyManager->Tie( property_name, &FuelFlow_pph);
+}
+
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+void FGTurbine::unbind()
+{
+ char property_name[80];
+
+ snprintf(property_name, 80, "propulsion/engine[%u]/n1", EngineNumber);
+ PropertyManager->Untie(property_name);
+ snprintf(property_name, 80, "propulsion/engine[%u]/n2", EngineNumber);
+ PropertyManager->Untie(property_name);
+ snprintf(property_name, 80, "propulsion/engine[%u]/fuel-flow", EngineNumber);
+ PropertyManager->Untie( property_name);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
if (from == 0) { // Constructor
}
+ if (from == 2) { // called from Load()
+ cout << "\n Engine Name: " << Name << endl;
+ cout << " MilThrust: " << MilThrust << endl;
+ cout << " MaxThrust: " << MaxThrust << endl;
+ cout << " BypassRatio: " << BypassRatio << endl;
+ cout << " TSFC: " << TSFC << endl;
+ cout << " ATSFC: " << ATSFC << endl;
+ cout << " IdleN1: " << IdleN1 << endl;
+ cout << " IdleN2: " << IdleN2 << endl;
+ cout << " MaxN1: " << MaxN1 << endl;
+ cout << " MaxN2: " << MaxN2 << endl;
+ cout << " Augmented: " << Augmented << endl;
+ cout << " AugMethod: " << AugMethod << endl;
+ cout << " Injected: " << Injected << endl;
+ cout << " MinThrottle: " << MinThrottle << endl;
+
+ cout << endl;
+ }
}
if (debug_lvl & 2 ) { // Instantiation/Destruction notification
if (from == 0) cout << "Instantiated: FGTurbine" << endl;
}
}
}
-
+}
projects / flightgear.git / blobdiff