A jet engine propels an aircraft at 289 m/s through air at 54 kPa and 267 K.
A jet engine propels an aircraft at 289 m/s through air at 54 kPa and 267 K. The compressor pressure ratio is 9 and the temperature at the turbine inlet is 885 K.
b) Taking the pressure in the combustion chamber as 843.5 kPa and the temperature at the turbine exit to be 518 K, determine the velocity of the exhaust gases.
Give your answer in m/s to 2 decimal places
Assume ideal operation for all components and constant specific heats at room temperature. Take the properties of air at room temperature to be R=0.287 kPa m3/kg
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A jet engine propels an aircraft at 289 m/s through air at 54 kPa and 267 K.
A jet engine propels an aircraft at 254 m/s through air at 39 kPa and 273 K. The compressor pressure ratio is 9 and the temperature at the turbine inlet is 873 K. b) Taking the pressure in the combust...
A jet engine propels an aircraft at 254 m/s through air at 39 kPa and 273 K. The compressor pressure ratio is 9 and the temperature at the turbine inlet is 873 K. b) Taking the pressure in the combustion chamber as 843.5 kPa and the temperature at the turbine exit to be 518 K, determine the velocity of the exhaust gases. Give your answer in m/s to 2 decimal places. Assume ideal operation for all components and constant specific...
A jet engine propels an aircraft at 254 m/s through air at 39 kPa and 273 K. The compressor pressure ratio is 9 and the temperature at the turbine inlet is 873 K. a) Determine the temperature of the a...
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A turbojet aircraft has its compressor rated at the pressure ratio of 10. Given that the aircraft...
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Air at 10 degree C and 80 kPa enters the diffuser of a jet engine steadily...
Air at 10 degree C and 80 kPa enters the diffuser of a jet engine steadily with a velocity of 200 m/s. The inlet area of the diffuser is 0.4 m^2.The air leaves the diffuser with a velocity that is very small compared with the inlet velocity. Determine the mass flow rate of the air and the temperature of the air leaving the diffuser. Air at 100 kPa and 280 K is compressed steadily to 600 kPa and 400 K....
If you could show all work with explanations that would be great!! Thanks!! #2. (30 pts)...
If you could show all work with explanations that would be
great!! Thanks!!
#2. (30 pts) A turbocharger boosts the inlet air pressure to an automobile engine. It consists of an exhaust gas-driven turbine directly connected to an air compressor, as shown in a below figure. For a certain engine load, the conditions are given in the below figure. Assume that both the turbine and the compressor are reversible and adiabatic, having also the same mass flow rate. Engine power...
A turbojet aircraft has its compressor rated at the pressure ratio of 10. Given that the aircraft flies with a velocity of 289 m/s at an altitude where the air is at a pressure of 29.5 kPa and temperature of-31.0·C. The air enters the compressor at 54 kg/s. The fuel used during the flight is rated to provide 39300 kJ of heat energy from every kilogram burnt and the temperature of the air entering the turbine is 1047.744 K. Calculate...
2. An aircraft with a single turbojet engine (with an inlet area of 1 m2) is flying at cruising condition with a flight Mach number of 0.7. The ambient temperature and pressure are 250 K and 100 kPa, respectively. The engine compressor pressure ratio is 12, and the turbine inlet temperature is 1200 K. Assume all mechanical components are operating at isentropic condition and the specific heat can be considered a constant (throughout the entire engine) of 1 kJ/(kg K)....
Q.4 Air at 26 kPa,230 K, and 220 m/s enters a turbojet engine in flight as shown below. The mass flow rate of air is 25 kg/s, the compression pressure ratio is 11, inlet temperature to the turbine is 1400 K, and air exits the nozzle at 26 kPa. The diffuser and nozzle processes are isentropic, but the compressor and turbine have isentropic efficiencies of 85 and 90 percent, respectively and there is no pressure drop for flow through the...
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Air at 10 degree C and 80 kPa enters the diffuser of a jet engine steadily with a velocity of 200 m/s. The inlet area of the diffuser is 0.4 m^2.The air leaves the diffuser with a velocity that is very small compared with the inlet velocity. Determine the mass flow rate of the air and the temperature of the air leaving the diffuser. Air at 100 kPa and 280 K is compressed steadily to 600 kPa and 400 K....
If you could show all work with explanations that would be
great!! Thanks!!
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