Question

(20 pts) At a given input to the thrust lever, after passing through the compressor, air enters to the

combustor of a jet engine with M1 (see data table) p1=7 atm and T1=570 K. Fuel is supplied through the
fuel nozzles with a fuel-air ratio by mass of 0. 5. The heat released during the combustion is HR (see data
table) J per kilogram of fuel. Assuming =1. 4 for fuel-air mixture, calculate the M2 ,p2 and T2 at the exit
of the combustor. Also, calculate the maximum fuel-air ratio beyond which the flow will be choked at the
exit. INFORMATION

M1(MACH)=0. 4

HR=9. 4*106

Answer 1

To calculate M2, p2, and T2 at the exit of the combustor, we can use the isentropic relations for a nozzle, assuming that the flow through the combustor is adiabatic and isentropic.

Using the isentropic relations, we can relate the Mach number, pressure, and temperature at the exit of the combustor to their values at the inlet of the combustor.

M2 = sqrt((2/(gamma-1))*((T1/(1+((gamma-1)/2)*M1^2))*(1+((gamma-1)/2)*M1^2*0.5*(gamma+1)*0.5*(1+0.5*(gamma-1)*M1^2)^(-1)*(1-0.5*(gamma-1)*M1^2*0.5*(gamma+1)*0.5*(1+0.5*(gamma-1)*M1^2)^(-1)*(1+0.5*(gamma-1)*M1^2*0.5*(gamma+1)*0.5*(1+0.5*(gamma-1)*M1^2)^(-1)*((gamma+1)/(2*gamma))^((gamma+1)/(2*(gamma-1))))))^(-1))

where gamma = 1.4 is the specific heat ratio of the fuel-air mixture.

Substituting the given values, we get:

M2 = sqrt((2/(1.4-1))*((570/(1+((1.4-1)/2)*0.4^2))*(1+((1.4-1)/2)*0.4^2*0.5*(1+0.5*(1.4-1)*0.4^2)^(-1)*(1-0.5*(1.4-1)*0.4^2*0.5*(1+0.5*(1.4-1)*0.4^2)^(-1)*(1+0.5*(1.4-1)*0.4^2*0.5*(1+0.5*(1.4-1)*0.4^2)^(-1)*((1.4+1)/(2*1.4))^((1.4+1)/(2*(1.4-1))))))^(-1)) = 0.818

p2 = p1*(1+0.5*(gamma

Step-by-step explanation: