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+// scilab Code Exa 7.4 Calculation on a single stage gas turbine

+

+gamma_g=1.33;

+gamma=1.4

+R_g=284.1;

+R=287;

+P=1e3; // Power Output in kW

+N1=3e3; // Speed in RPM

+n_t=0.87; // efficiency

+cp_g=1.145; // Specific Heat of gas at Constant Pressure in kJ/(kgK)

+cp_a=1.0045; // Specific Heat of air at Constant Pressure in kJ/(kgK)

+

+// part (a)mass flow rate of the gas through the turbine

+T01=1000;  // Entry Temperature in Kelvin

+p01=2.5; //  Entry Pressure in bar

+T01a=500;  // Entry Temperature of air in Kelvin

+p01a=2; //  Entry Pressure of air in bar

+p02=1; //  Exit Pressure in bar

+pr0=p01/p02;

+T02=T01*(pr0^(-((gamma_g-1)/gamma_g)));

+delh_s1=cp_g*(T01-T02)*n_t;

+m_g=P/delh_s1;

+disp("kg/s",m_g,"(a)mass flow rate of the gas through the turbine is")

+

+// part (b)speed, mass flow rate, pressure ratio and power required 

+N2=sqrt(1/2)*5*N1;

+disp("rpm",N2,"(b)(i)speed of a geometrically similar compressor is")

+a=0.2; // a=D2/D1;

+m2=(a^2)*sqrt(R_g/R)*sqrt(T01/T01a)*(p01a/p01)*m_g;

+disp("kg/s",m2,"(b)(ii)mass flow rate of a geometrically similar turbine is")

+delh_s2=0.5*delh_s1;

+P2=m2*delh_s2;

+disp("kW",P2,"(b)(iii)Power developed is")

+pr=(1-(delh_s2/(cp_a*T01a*n_t)))^(-1/((gamma-1)/gamma));

+disp(pr,"(b)(iv)pressure ratio of a geometrically similar turbine is")