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+// scilab Code Exa 18.1 Gas Turbine nozzle row 

+

+T1=600;  // Entry Temperature of the gas in Kelvin

+p1=10; // Inlet Pressure in bar

+gamma_g=1.3;

+delT=32; // Temperature drop of the gas(T1-T2) in K

+cp_g=1.23*1e3; // Specific Heat of gas at Constant Pressure in kJ/(kgK)

+pr1_2=1.3; // pressure ratio(p1/p2)

+T2s=T1/(pr1_2^((gamma_g-1)/gamma_g));

+delTs=T1-T2s;

+

+// part(a) nozzle efficiency

+n_N=delT/delTs;

+disp("%",n_N*100,"(a) nozzle efficiency is")

+

+// part(b)

+disp("(b)(i)for ideal flow:")

+p2=p1/pr1_2;

+h_01=cp_g*T1;

+h2s=cp_g*T2s;

+c_2s=sqrt((h_01-h2s)/0.5);

+disp("m/s",c_2s,"the nozzle exit velocity is")

+R_g=cp_g*((gamma_g-1)/gamma_g);

+M_2s=c_2s/(sqrt(gamma_g*R_g*T2s));

+disp(M_2s,"and the Mach number is")

+disp("(b)(ii)for actual flow:")

+T2=T1-delT;

+a2=sqrt(gamma_g*R_g*T2);

+c_2=sqrt((cp_g*delT)/0.5);

+disp("m/s",c_2,"the nozzle exit velocity is")

+M2=c_2/a2;

+disp(M2,"and the Mach number is")

+

+// part(c) stagnation pressure loss across the nozzle

+p01=p1;

+p02=p2/0.79; // from isentropic gas tables p2/p02=0.79 at gamma=1.3 and M2=0.613

+delp0=p01-p02;

+disp("bar",delp0,"(c)the stagnation pressure loss across the nozzle is")

+

+// part(d) nozzle efficiency based on stagnation pressure loss

+delp=p1-p2;

+n_N_a=1-(delp0/delp);

+disp("%",n_N_a*100,"(d)the nozzle efficiency based on stagnation pressure loss is")