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+// scilab Code Exa 18.13 Turbojet Gas Turbine Engine

+

+T1=223.15; // in Kelvin

+n_C=0.75; // Compressor Efficiency

+c1=85; // entry velocity in m/s

+m=50; // mass flow rate of air in kg/s

+R=287;

+n_B=0.98; // Combustion chamber Efficiency

+Qf=43*1e3; // Calorific Value of fuel in kJ/kg;

+T03=1220;  // Turbine inlet stagnation temp in Kelvin

+n_T=0.8; // Turbine Efficiency

+gamma=1.4; // Specific Heat Ratio

+n_m=0.98; // Mechanical efficiency

+sigma=0.5; // flight to jet speed ratio(u/ce)

+n_N=0.98; // exhaust nozzle efficiency

+cp=1.005; // Specific Heat at Constant Pressure in kJ/(kgK)

+u=886/3.6; // flight speed of a turbo prop aircraft in m/s

+delT=200; // temperature rise through the compressor(T02-T01) in K

+pi=.701; // Initial Pressure in bar

+n_D=0.88; // inlet diffuser efficiency

+a1=sqrt(gamma*R*T1);

+M1=u/a1; // Mach number at the compressor inlet

+T1_01=0.881; // (T1/T01)from isentropic flow gas tables at M1 and gamma values

+T01=T1/T1_01;

+T1=T01-(0.5*(c1^2)/(cp*1e3));

+

+// part(a) compressor pressure ratio

+T02s=T01+(delT*n_C);

+r_oc=(T02s/T01)^(gamma/(gamma-1)); //compressor pressure ratio(p02/p01)

+disp(r_oc,"(a)compressor pressure ratio is")

+

+// part(b)

+T02=T01+delT;

+f=((cp*T03)-(cp*T02))/((Qf*n_B)-(cp*T03)); // f=(ma/mf);energy balance in the combustion chamber 

+disp(1/f,"(b)Air-Fuel Ratio is")

+

+// part(c) turbine pressure ratio

+// turbine power input P_T=n_m*(ma+mf)*cp*(T03-T01)

+// power input to the compressor P_C=ma*cp*(T02-T01)

+T04s=T03-(delT/(n_m*n_T*(1+f))); // from energy balance P_T=P_C

+r_ot=(T03/T04s)^(gamma/(gamma-1)); //turbine pressure ratio(p03/p04)

+disp(r_ot,"(c)turbine pressure ratio is")

+

+// part(d)exhaust nozzle pressure ratio

+ce=u/sigma; // jet velocity at the exit of the exhaust nozzle

+T04=T03-(delT/(n_m*(1+f)));

+Te=T04-(0.5*(ce^2)/(cp*1e3));

+Tes=T04-((T04-Te)/n_N);

+r_N=(T04/Tes)^(gamma/(gamma-1)); //exhaust nozzle pressure ratio(p04/pe)

+disp(r_N,"(d)exhaust nozzle pressure ratio is")

+ae=sqrt(gamma*R*Te);

+Me=ce/ae; // Mach number

+disp(Me,"and the Mach Number is")

+

+