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A turbojet engine consists of a diffuser, compressor, combustor, turbine and a converging nozzle. The engine...
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...
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)....
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...
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...
What are the purposes of nozele design of an engine?(15 %) Prob. 4 A turbojet aireraft...
What are the purposes of nozele design of an engine?(15 %) Prob. 4 A turbojet aireraft is flying under the following conditions, please calculates the net thrust and the effective velocity. (20 %) Prob. 5 Aireraft fly speed-400 mph Inlet airflow-100 lb/s Exhaust nozzle area 3 ft Exhaust nozzle pressure 40 psia Exhaust gas velocity 1000 mph Fuel flow 3 lb/s steady speed of 900km/hr at an altitude where the temperature is 1700K. nies
What are the purposes of nozele...
Problem-2 (200) Air at 30 kPa, 200 K, and 250 m/s enters a turbojet engine in...
Problem-2 (200) Air at 30 kPa, 200 K, and 250 m/s enters a turbojet engine in flight. The air mass flow rate is 28 kg/s. The compressor pressure ratio is 13, the turbine inlet temperature is 1460 K, and air exits the nozzle at 30 kPa. The diffuser and nozzle processes are isentropic, the compressor and turbine have isentropic efficiencies of 81% and 88%, respectively, and there is no pressure drop for flow through the combustor. Kinetic energy is negligible...
Q.4 Air at 26 kPa,230 K, and 220 m/s enters a turbojet engine in flight as...
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...
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...
Quantitative: In the 1950s liquid hydrogen was considered as a fuel for a new type of...
Quantitative: In the 1950s liquid hydrogen was considered as a fuel for a new type of aircraft being developed, the SR-71 Blackbird (shown in Figure 1). Figure 1: The SR-71 Blackbird Early research on the project focused on which fuel to use for the Blackbird. Pratt & Whitney had a J-57 engine that was designed for kerosene and being considered for implementation on the Blackbird. The J-57 only took 5 months to convert to running on liquid hydrogen, however tests...
estion 9- Ramjet Operation (15 Points): You are asked to calculate the operational parameters of an ideal ramjet engine. flame holder combustion zone Me inlet diffuser nozzle e- Nozzle exit throa...
estion 9- Ramjet Operation (15 Points): You are asked to calculate the operational parameters of an ideal ramjet engine. flame holder combustion zone Me inlet diffuser nozzle e- Nozzle exit throat-M-1 Normal shock wave Ramjet 3-Burner exit 2- Diffuser exit 00 K. Flight altitude is 10 knm Flight Mach number is 2.0. Burner exit temperature is 17 Make the following assumptions: Assume that the Mach number in the combustor is zero (stations 2 and 3) Ignore pressure losses in the...
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)....
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...
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...
What are the purposes of nozele design of an engine?(15 %) Prob. 4 A turbojet aireraft is flying under the following conditions, please calculates the net thrust and the effective velocity. (20 %) Prob. 5 Aireraft fly speed-400 mph Inlet airflow-100 lb/s Exhaust nozzle area 3 ft Exhaust nozzle pressure 40 psia Exhaust gas velocity 1000 mph Fuel flow 3 lb/s steady speed of 900km/hr at an altitude where the temperature is 1700K. nies
What are the purposes of nozele...
Problem-2 (200) Air at 30 kPa, 200 K, and 250 m/s enters a turbojet engine in flight. The air mass flow rate is 28 kg/s. The compressor pressure ratio is 13, the turbine inlet temperature is 1460 K, and air exits the nozzle at 30 kPa. The diffuser and nozzle processes are isentropic, the compressor and turbine have isentropic efficiencies of 81% and 88%, respectively, and there is no pressure drop for flow through the combustor. Kinetic energy is negligible...
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...
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...
Quantitative: In the 1950s liquid hydrogen was considered as a fuel for a new type of aircraft being developed, the SR-71 Blackbird (shown in Figure 1). Figure 1: The SR-71 Blackbird Early research on the project focused on which fuel to use for the Blackbird. Pratt & Whitney had a J-57 engine that was designed for kerosene and being considered for implementation on the Blackbird. The J-57 only took 5 months to convert to running on liquid hydrogen, however tests...
estion 9- Ramjet Operation (15 Points): You are asked to calculate the operational parameters of an ideal ramjet engine. flame holder combustion zone Me inlet diffuser nozzle e- Nozzle exit throat-M-1 Normal shock wave Ramjet 3-Burner exit 2- Diffuser exit 00 K. Flight altitude is 10 knm Flight Mach number is 2.0. Burner exit temperature is 17 Make the following assumptions: Assume that the Mach number in the combustor is zero (stations 2 and 3) Ignore pressure losses in the...
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