Question

Think about a turboprop engine (explained in the lecture). The turbine-compressor assembly drives a propeller for the propulsion and it delivers net power of 1.1 MW to the prop. This aircraft was designed to fly at 8km altitude with 550 km/h speed. The atmospheric condition up there is 236K and 0.36 bar. Air enters the diffuser and decelerates to 0 km/h for maximizing the ram effect. The compression ratio is 6.3 and the isentropic efficiency of the compressor is 83%. The turbine has 1360K inlet temperature, and the efficiency is also 83%. The pressure at the turbine exit is 10 kPa higher than the ambient pressure, and assume that the diffuser and nozzle show isentropic behaviors. Kinetic energy except for at the diffuser and the nozzle exit can be neglected. Determine:

a) The mass flow rate in kg/s.

b) The volumetric flow rate in m³/s.

c) The heat rate produced in the combustion in W.

d) The gas velocity leaves the nozzle in m/s.

Answer 1

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