1)A gas turbine power plant operating on a Brayton cycle takes in atmospheric air at 14°C. The temperature of the air ri
Posted: Mon May 16, 2022 1:01 pm
1)A gas turbine power plant operating on a Brayton cycle takes
in atmospheric air at 14°C. The temperature of the air rises by
190°C over the compressor, and by a further 751°C over the
combustion chamber. If the heating value of the fuel burned in the
turbine is 54 MJ/kg, calculate the rate in kg/s at which fuel
must be burned for each MW of output from the power plant. Give
your answer to three decimal places. 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.
2)A plane flying at 367 m/s airspeed uses a turbojet engine to
provide thrust. At its operational altitude, the air has a pressure
of 37 kPa and a temperature of -11 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 49 MJ/kg. If the compressor pressure ratio is 14, 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. Use the same properties for air as in
question 1 and treat all components as ideal.
in atmospheric air at 14°C. The temperature of the air rises by
190°C over the compressor, and by a further 751°C over the
combustion chamber. If the heating value of the fuel burned in the
turbine is 54 MJ/kg, calculate the rate in kg/s at which fuel
must be burned for each MW of output from the power plant. Give
your answer to three decimal places. 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.
2)A plane flying at 367 m/s airspeed uses a turbojet engine to
provide thrust. At its operational altitude, the air has a pressure
of 37 kPa and a temperature of -11 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 49 MJ/kg. If the compressor pressure ratio is 14, 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. Use the same properties for air as in
question 1 and treat all components as ideal.