Question

MENG 0312- Thermodynamics II Test # 5 1. A turbojet aircraft flying with a velocity of 320 m/s has a turbine inlet temperature and pressure of 1380 K and 400 kPa, respectively. Assume isentropic efficiency of the turbine and the nozzle. The mass flow rate of air is 23 kg/s. a) What is the enthalpy of the gas coming out of turbine in kJ/kg, assuming the compressor work is 280 kJ/kg? b) What is the pressure in kPa at the exhaust from turbine? c) If the ambient pressure is 32 kPa, what are the enthalpy and velocity of gas at the exit of the nozzle? d) What is the propulsive efficiency if the amount of heat input is 2.3 x 104 kJ/s? 1. Write your units clearly

          MENG 0312- Thermodynamics II
Test # 5
1. A turbojet aircraft flying with a velocity of 320 m/s has a turbine inlet temperature
and pressure of 1380 K and 400 kPa, respectively. Assume isentropic efficiency
of the turbine and the nozzle. The mass flow rate of air is 23 kg/s.
a) What is the enthalpy of the gas coming out of turbine in kJ/kg, assuming the
compressor work is 280 kJ/kg?
b) What is the pressure in kPa at the exhaust from turbine?
c) If the ambient pressure is 32 kPa, what are the enthalpy and velocity of gas at
the exit of the nozzle?
d) What is the propulsive efficiency if the amount of heat input is 2.3 x 104 kJ/s?
1. Write your units clearly

MENG 0312- Thermodynamics II
Test # 5
1. A turbojet aircraft flying with a velocity of 320 m/s has a turbine inlet temperature
and pressure of 1380 K and 400 kPa, respectively. Assume isentropic efficiency
of the turbine and the nozzle. The mass flow rate of air is 23 kg/s.
a) What is the enthalpy of the gas coming out of turbine in kJ/kg, assuming the
compressor work is 280 kJ/kg?
b) What is the pressure in kPa at the exhaust from turbine?
c) If the ambient pressure is 32 kPa, what are the enthalpy and velocity of gas at
the exit of the nozzle?
d) What is the propulsive efficiency if the amount of heat input is 2.3 x 104 kJ/s?
1. Write your units clearly

Added by Carol S.

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