initial commit / add all books

1 files changed, 38 insertions, 0 deletions

diff --git a/3511/CH6/EX6.2/Ex6_2.sce b/3511/CH6/EX6.2/Ex6_2.sce
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+clc;

+p01=1; // Air inlet pressure in bar

+T01=7+273;// Air inlet temperature in kelvin

+p02=4; // Pressure at state 2 in bar

+eff_c=0.82;// Isentropic efficiency of compressor

+T03=800+273; // Maximum temperature at the turbine inlet in kelvin

+eff_T=0.85; // Isentropic efficiency of the turbine

+CV=43.1; // calorific value of fuel in MJ/kg

+Cpa=1.005;// Specific heat of air  at constant pressure in kJ/kg K

+Cpg=1.147;// Specific heat of fuel at constant pressure in kJ/kg K

+rg=1.33;// Specific heat ratio of fuel

+r=1.4; // Specific heat ratio of air

+LS=0.85;

+mf=1; // Let assume mass of fuel to be 1 kg

+

+T_02=T01*(p02/p01)^((r-1)/r); // from T-S diagram

+T02=T01+(T_02-T01)/eff_c; // Temperature after compression

+Wc=Cpa*(T02-T01); // Work of compression

+Q=Cpg*(T03-T02); // Heat supplied

+p04=p01;p03=p02;

+T_04=T03*(p04/p03)^((rg-1)/rg);

+T04=T03-eff_T*(T03-T_04);

+WT=Cpg*(T03-T04); // Turbine work

+WN=WT-Wc; // Net work done

+eff_th=WN/(Q/LS); // The thermal efficiency

+ma_mf=(LS*CV*10^3/Q)-1; // AIR FUEL ratio

+ma=mf*ma_mf;

+sfc=(3600/(ma_mf*WN)); // specific fuel consumption

+Wc_WT=(Wc*ma)/(WT*(ma+mf)); // work ratio

+

+disp ("kJ/kg of air",Wc,"(i).Compressor work = ");

+disp ("kJ/kg of air",Q,"(ii).Heat supplied = ");

+disp ("kJ/kg of air",WT,"(iii).Turbine work = ");

+disp ("kJ/kg of air",WN,"(iv).Net work = ");

+disp ("%",eff_th*100,"(v).Thermal Efficiency = ");

+disp (ma_mf,"(vi).Air/Fuel ratio = ")

+disp ("kg/kWh",sfc,"(vii).Specific fuel consumption =");

+disp (Wc_WT,"(viii).Ratio of compressor work to turbine work = ");