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4. Steady flow devices that result in a decrease in working fluid pressure from inlet to...
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)....
001: Ability to formulate and experimentally discover the energy balance accordingly to the first law of...
001: Ability to formulate and experimentally discover the energy balance accordingly to the first law of thermodynamics for a system. Numbers of engineering devices are designed to operate mainly under the same conditions for long periods, and it is known as steady flow devices. Given here are the examples of the flow devices. a. Nozzle and diffuser b. Turbine and compressor C. Throttling valve d. Mixing chamber e. Heat exchanger f. Pipe and duct flow 1. Briefly explain the function...
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...
1) A commercial refrigerator with refrigerant-134a as the working fluid is used to keep the refrigerated...
1) A commercial refrigerator with refrigerant-134a as the working fluid is used to keep the refrigerated space at -30°C by rejecting its waste heat to cooling water that enters the condenser at 16 °C at a rate of 0.25 kg/s and leaves at 26°C. The refrigerant enters the condenser at 1.2 MPa and 65°C and leaves at 42°C. The inlet state of the compressor is 60 kPa and -34°C and the compressor is estimated to gain a net heat of...
Consider a steady flow Carnot cycle with water as the working fluid. The maximum and minimum...
Consider a steady flow Carnot cycle with water as the working fluid. The maximum and minimum temperatures in the cycle are 350 and 50 C. The quality of water is 0.891 at the beginning of the heat rejection process and 0.1 at the end. Determine: (a) the thermal efficiency (how much percent). (b) The pressure at the turbine inlet (MPa). (c) The net work output (kJ/kg).
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...
Consider an air-standard Brayton cycle. At steady state, turbine inlet temperature is 1800 K. If pressure...
Consider an air-standard Brayton cycle. At steady state, turbine inlet temperature is 1800 K. If pressure and temperature at compressor inlet are 1 bar & 32 °C, determine net-work developed per unit mass flow (kJ/kg). Assuming the compressor pressure ratio to be 8, calculate the thermal efficiency.
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...
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...
An ideal reheat Rankine cycle with water as the working fluid operates the inlet of the...
An ideal reheat Rankine cycle with water as the working fluid operates the inlet of the high-pressure turbine at 8000 kPa and 450°C, the inlet of the low-pressure turbine at 300kPa and 500°C, and the condenser at 10 kPa. Determine the mass flow rate through the boiler needed for this system to produce a net 5000 kW of power and the thermal efficiency of the cycle.
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)....
001: Ability to formulate and experimentally discover the energy balance accordingly to the first law of thermodynamics for a system. Numbers of engineering devices are designed to operate mainly under the same conditions for long periods, and it is known as steady flow devices. Given here are the examples of the flow devices. a. Nozzle and diffuser b. Turbine and compressor C. Throttling valve d. Mixing chamber e. Heat exchanger f. Pipe and duct flow 1. Briefly explain the function...
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...
1) A commercial refrigerator with refrigerant-134a as the working fluid is used to keep the refrigerated space at -30°C by rejecting its waste heat to cooling water that enters the condenser at 16 °C at a rate of 0.25 kg/s and leaves at 26°C. The refrigerant enters the condenser at 1.2 MPa and 65°C and leaves at 42°C. The inlet state of the compressor is 60 kPa and -34°C and the compressor is estimated to gain a net heat of...
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...
Consider an air-standard Brayton cycle. At steady state, turbine inlet temperature is 1800 K. If pressure and temperature at compressor inlet are 1 bar & 32 °C, determine net-work developed per unit mass flow (kJ/kg). Assuming the compressor pressure ratio to be 8, calculate the thermal efficiency.
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...
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...
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