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You are asked to perform preliminary calculations to model the effect of the compressor compression ratio...
A turbojet aircraft has its compressor rated at the pressure ratio of 10. Given that the aircraft...
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...
As a propulsion engineer, you are tasked with testing a turbojet engine to determine characterist...
As a propulsion engineer, you are tasked with testing a turbojet engine to determine characteristics. The turbojet engine consists of a diffuser, compressor, combustion chamber, turbine and nozzle. Consider the following cases: its performance 2. Air approaches the diffuser of the turbojet engine with a pressure of 20 kPa at a Mach number of 2. A normal shock occurs at the inlet of the channel The exit to inlet area ratio is 3. Determine the following: a. The loss of...
Please show full steps, will rate. A turbojet powered aircraft is flying at 250 m/s where...
Please show full steps, will rate.
A turbojet powered aircraft is flying at 250 m/s where the ambient temperature and pressure are -18 °C and 55 kPa, respectively. The pressure ratio for the compressor is 10, and the turbine inlet temperature is 1200 °C. The mass flow rate of air into the engine is 50 kg/s. a.) How much thrust does the engine develop? b.) How much heat must be added to the air in the combustor? c.) What is...
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...
In a combustion turbine using natural gas as the fuel, air enters the compressor at 98...
In a combustion turbine using natural gas as the fuel, air enters the compressor at 98 kPa and 300 "K. The pressure ratio in the compressor is 8 and the isentropic efficiency of the compressor is 85%. The outlet temperature of the combustion chamber is 1200 K. The pressure drops by 4 percent in the combustion chamber. The exit pressure of the turbine is 102 kPa and the isentropic efficiency of the turbine is 90%. Find: a) The exit temperature...
Α 4-stroke spark-ignition engine has a compression ratio of 10 and operates on the ideal constant...
Α 4-stroke spark-ignition engine has a compression ratio of 10 and operates on the ideal constant volume cycle with intake pressure of 50 kPa (throttled) and intake temperature of 300 K. The exhaust pressure is 100 kPa. The heat input from combustion is 2500 kJ/kg and γ = 1.3 for the working fluid. a. Draw the p-V diagram of the full cycle and indicate all the processes. b. Calculate the residual gas fraction and the temperature decrease during the exhaust...
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...
4.50 A compressor in a turbojet engine consur of shaft power to handle 100 kg/s of...
4.50 A compressor in a turbojet engine consur of shaft power to handle 100 kg/s of air a compressor total pressure ratio of 15.4 rate and create e and cre 100 kPa, the nie , TO 288 K. condition to the compressor is p2 calculate (a) the exit total temperature, T3, in K (b) compressor polytropic efficiency, ec : 1.4 and cpc-1004 J/kg-K Assume γ
2. An aircraft with a single turbojet engine (with an inlet area of 1 m2) is...
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)....
can you help me pls it's for 20 minutes 2 bann 27. Determine the minimum temperature...
can you help me pls it's for 20 minutes
2 bann 27. Determine the minimum temperature before of the turbine for the turbojet engine using the following parameters: e=2, Compression efficiency and Expansion efficiency equal to 0.9, the temperature at the engine inlet is 288K. 620K 0417.85K 580.4K 28. Determine the maximum pressure 26ann ratio in the compressor for the turbojet engine using the following parameters: Total temperature before turbine is 1200 K, Compression efficiency and Expansion efficiency equal to...
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...
As a propulsion engineer, you are tasked with testing a turbojet engine to determine characteristics. The turbojet engine consists of a diffuser, compressor, combustion chamber, turbine and nozzle. Consider the following cases: its performance 2. Air approaches the diffuser of the turbojet engine with a pressure of 20 kPa at a Mach number of 2. A normal shock occurs at the inlet of the channel The exit to inlet area ratio is 3. Determine the following: a. The loss of...
Please show full steps, will rate.
A turbojet powered aircraft is flying at 250 m/s where the ambient temperature and pressure are -18 °C and 55 kPa, respectively. The pressure ratio for the compressor is 10, and the turbine inlet temperature is 1200 °C. The mass flow rate of air into the engine is 50 kg/s. a.) How much thrust does the engine develop? b.) How much heat must be added to the air in the combustor? c.) What is...
In a combustion turbine using natural gas as the fuel, air enters the compressor at 98 kPa and 300 "K. The pressure ratio in the compressor is 8 and the isentropic efficiency of the compressor is 85%. The outlet temperature of the combustion chamber is 1200 K. The pressure drops by 4 percent in the combustion chamber. The exit pressure of the turbine is 102 kPa and the isentropic efficiency of the turbine is 90%. Find: a) The exit temperature...
4.50 A compressor in a turbojet engine consur of shaft power to handle 100 kg/s of air a compressor total pressure ratio of 15.4 rate and create e and cre 100 kPa, the nie , TO 288 K. condition to the compressor is p2 calculate (a) the exit total temperature, T3, in K (b) compressor polytropic efficiency, ec : 1.4 and cpc-1004 J/kg-K Assume γ
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)....
can you help me pls it's for 20 minutes
2 bann 27. Determine the minimum temperature before of the turbine for the turbojet engine using the following parameters: e=2, Compression efficiency and Expansion efficiency equal to 0.9, the temperature at the engine inlet is 288K. 620K 0417.85K 580.4K 28. Determine the maximum pressure 26ann ratio in the compressor for the turbojet engine using the following parameters: Total temperature before turbine is 1200 K, Compression efficiency and Expansion efficiency equal to...
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