initial commit / add all books

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+clc;

+N=10000; // Speed of gas turbine in rpm

+T01=700+273.15; // Total head temperature at nozzle entry in kelvin

+P01=4.5; //Total head pressure at nozzle entry in bar

+P02=2.6; // Outlet pressure from nozzle in bar

+p3=1.5;// Pressure at trbine outlet annulus in bar

+M=0.5; // Mach number at outlet

+alpha_2=70; // outlet nozzle angle in degrees

+D=64; // Blade mean diameter in cm

+m=22.5; // Mass flow rate in kg/s

+eff_T=0.99; // turbine mechanical efficiency

+Cp=1.147; // Specific heat in kJ/kg K

+r=1.33; // Specific heat ratio

+fl=0.03; // frictional loss

+R=284.6; // characteristic gas constant in J/kg K

+

+eff_N=1-fl; // Nozzle efficiency

+T_02=(P02/P01)^((r-1)/r)*T01; // Isentropic temperature after expansion

+T02=T01-eff_N*(T01-T_02); // Actual temperature after expansion

+c2=sqrt (2*Cp*10^3*(T01-T02)); // Absolute velocity

+u=(3.14*D*10^-2*N)/60; // Mean blade velocity

+// From velocity triangles

+wt2=c2*sind (alpha_2)-u;

+ca=c2*cosd (alpha_2);

+beta_2=atand((wt2)/ca);

+T3=T02/(P02/p3)^((r-1)/r); // Assuming rotor losses are negligible

+c3=M*sqrt (r*R*T3); // Absolute velocity

+beta_3=atand(u/c3);

+ct2=c2*sind(alpha_2);

+P=eff_T*m*(ct2)*u/1000; // Power developed

+

+disp ("degree",beta_3,"Gas angle at exit = ","degree",beta_2,"Gas angle at entry","(i).");

+disp ("kW   (roundoff error)",P,"Power developed = ","(ii).");