A plane flying at 284 m/s airspeed uses a turbojet engine to provide thrust. At its operational altitude, the air has a
Posted: Sun May 15, 2022 9:42 pm
A plane flying at 284 m/s airspeed uses a turbojet engine to
provide thrust. At its operational altitude, the air has a pressure
of 36 kPa and a temperature of -13 ºC. The fuel-air ratio is 0.6% -
that is, for every kg of air passing through the turbine, 0.006 kg
of fuel is burned – and the jet fuel used has a heating value of 43
MJ/kg. If the compressor pressure ratio is 15, and we assume that
flow speed is negligibly small between the compressor inlet and
turbine outlet, determine the temperature of the exhaust gases to
the nearest Kelvin. Take the specific heat capacity
cp of air to be 1.005 kJ/(kg K), and the ratio of
specific heats k to be 1.4. You may also assume that changes in the
properties of the air due to the addition and combustion of fuel
are negligible
provide thrust. At its operational altitude, the air has a pressure
of 36 kPa and a temperature of -13 ºC. The fuel-air ratio is 0.6% -
that is, for every kg of air passing through the turbine, 0.006 kg
of fuel is burned – and the jet fuel used has a heating value of 43
MJ/kg. If the compressor pressure ratio is 15, and we assume that
flow speed is negligibly small between the compressor inlet and
turbine outlet, determine the temperature of the exhaust gases to
the nearest Kelvin. Take the specific heat capacity
cp of air to be 1.005 kJ/(kg K), and the ratio of
specific heats k to be 1.4. You may also assume that changes in the
properties of the air due to the addition and combustion of fuel
are negligible