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3.15 EXERCISES E3 an A turbojet engine with a convergent nozle...
Please show full steps, will rate. A turbojet powered aircraft is flying at 250 m/s where...
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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...
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...
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)....
A single-spool turbofan engine has the following data Ambient temperature Ambient pressure BPR Overall pressure ratio...
A single-spool turbofan engine has the following data Ambient temperature Ambient pressure BPR Overall pressure ratio Fan pressure ratio Fuel heating value Turbine inlet temperature Diffuser pressure recovery factor Compressor efficiency Fan efficiency Combustion efficien Burner pressure recovery factor Turbine efficiency Nozzle efficiency Flight Mach number 288 K 101.3 kN/m2 0.7 25 3.375 44,000 kJ/kg 2000 K 0.9 0.89 0.91 0.98 0.95 0.98 1.0 0.3 Calculate 1. 2. 3. Thrust per unit mass flow rate TSFC Thermal, propulsive and overall...
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...
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...
Combined cycle power plants are common because of their high efficiency and scalability. They typically combine a gas turbine cycle (the Brayton Cycle) with a steam turbine cycle (the Rankine Cycle) [...
Combined cycle power plants are common because of their high efficiency and scalability. They typically combine a gas turbine cycle (the Brayton Cycle) with a steam turbine cycle (the Rankine Cycle) [1]. The goal of this project is to determine the operating efficiency and profitability of a realistic combined cycle power plant. The power plant is as follows: 1. A natural gas-fired Brayton cycle with mÛ air,Br = 1.25 kg s−1 . (a) Ambient air at 1 bar and 300...
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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...
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...
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)....
A single-spool turbofan engine has the following data Ambient temperature Ambient pressure BPR Overall pressure ratio Fan pressure ratio Fuel heating value Turbine inlet temperature Diffuser pressure recovery factor Compressor efficiency Fan efficiency Combustion efficien Burner pressure recovery factor Turbine efficiency Nozzle efficiency Flight Mach number 288 K 101.3 kN/m2 0.7 25 3.375 44,000 kJ/kg 2000 K 0.9 0.89 0.91 0.98 0.95 0.98 1.0 0.3 Calculate 1. 2. 3. Thrust per unit mass flow rate TSFC Thermal, propulsive and overall...
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...
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...
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