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The diffuser in a jet engine is designed to decrease the kinetic energy of the air entering the j...
The diffuser in a jet engine is designed to decrease the kinetic energy of the air...
The diffuser in a jet engine is designed to decrease the kinetic energy of the air entering the engine compressor without any work or heat interactions. Calculate the velocity at the exit of a diffuser when air at 100 kPa and 30°C enters it with a velocity of 358 m/s and the exit state is 200 kPa and 90°C. The specific heat of air at the average temperature of 60°C = 333 K is cp = 1.007 kJ/kg·K.
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....
A turboprop engine consists of a diffuser, compressor, combustor, turbine, and nozzle. The turbine drives a...
A turboprop engine consists of a diffuser, compressor, combustor, turbine, and nozzle. The turbine drives a propeller as well as the compressor. Air enters the diffuser with a volumetric flow rate of 63.7 m3/s at 40 kPa, 240 K, and a velocity of 180 m/s, and decelerates essentially to zero velocity. The compressor pressure ratio is 9 and the compressor has an isentropic efficiency of 85%. The turbine inlet temperature is 1240 K, and its isentropic efficiency is 85%. The...
Air steadily enters the diffuser section of a jet engine at a velocity of 270 m/s...
Air steadily enters the diffuser section of a jet engine at a velocity of 270 m/s at 85 kPa and at 250 °C. There is heat addition from the diffuser walls to the air. The air exits the diffuser at 1/3 of its inlet velocity. The heat addition per kg air entering the diffuser is 13 kJ/kg. What is the change in the specific enthalpy of the air (kJ/kg)?
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...
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 air as it enters the exit nozzle. Give your answer in Kelvin 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 =...
please solve h to m .A-7 The gas turbine engines that are used on a military...
please solve h to m
.A-7 The gas turbine engines that are used on a military jet air plane likely consists of a diffuser, compressor, combustor, turbine, afterburmer, and nozzle that are arranged in series as shown in Figure 4.A-7(a) and flying with a velocity of 350 mph. The analysis will be carried out on a component-by component basis. Model the air as an ideal gas and assume that it has constant c and cp R 287.1 Ikg-K and c-1005...
3. Exhaust Velocity A jet engine that operates on Brayton cycle is at an altitude (30,000...
3. Exhaust Velocity A jet engine that operates on Brayton cycle is at an altitude (30,000 ft) where the engine entrance temperature is 228 K and the pressure is 30.8 kPa. We also know that the engine compressor pressure ratio is rp= 10 and the fuel to air mass flowrate ratio is 0.03. If the aircraft is moving at a velocity of 305 m/s and uses fuel with LHV 44,102 kJ/kg calculate the engine exhaust velocity. (Note that cp 1.0035...
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...
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...
Air enters a nozzle in a jet engine at a pressure of 500 kPa, temperature of...
Air enters a nozzle in a jet engine at a pressure of 500 kPa, temperature of 650K, and velocity of 75 m/s. The air exits the nozzle at a pressure of 100 kPa, and the isentropic nozzle efficiency is 82%. a). Determine the velocity of the air at the nozzle exit. b). Determine the rate of entropy generation in the nozzle per kg of air flowing in kW/kgK
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....
please solve h to m
.A-7 The gas turbine engines that are used on a military jet air plane likely consists of a diffuser, compressor, combustor, turbine, afterburmer, and nozzle that are arranged in series as shown in Figure 4.A-7(a) and flying with a velocity of 350 mph. The analysis will be carried out on a component-by component basis. Model the air as an ideal gas and assume that it has constant c and cp R 287.1 Ikg-K and c-1005...
3. Exhaust Velocity A jet engine that operates on Brayton cycle is at an altitude (30,000 ft) where the engine entrance temperature is 228 K and the pressure is 30.8 kPa. We also know that the engine compressor pressure ratio is rp= 10 and the fuel to air mass flowrate ratio is 0.03. If the aircraft is moving at a velocity of 305 m/s and uses fuel with LHV 44,102 kJ/kg calculate the engine exhaust velocity. (Note that cp 1.0035...
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