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The "combustor" noted in the sketch below is modeled as a heat exchanger that adds heat...
Steam Generator air (inlet) - 320°C P. = 100 kPa th =0.5 kg/s heat exchanger -...
Steam Generator air (inlet) - 320°C P. = 100 kPa th =0.5 kg/s heat exchanger - water (inlet) T = 20°C Pw = 100 kPa m = 0.025 kg/s Problem sketch Solve with EES. Document all necessary balances The problem sketch illustrates a heat exchanger in which hot air is used to generate steam. Air enters the heat exchanger at 1a, in = 320C, Pa = 100 kPa, and ma -0.5 kg/s. Model air as an ideal gas with constant...
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...
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...
A combined cycle gas turbine/vapor power plant uses the turbine exhaust as the energy source for...
A combined cycle gas turbine/vapor power plant uses the turbine exhaust as the energy source for the boiler. Each power system uses a single turbine. The gas power system is modeled as an ideal air-standard Brayton cycle. The vapor power system is modeled as an ideal Rankine cycle. Given specific operating conditions determine the temperature and pressure at each state, the rate of heat transfer in the boiler, the power output of each turbine, and the overall efficiency. --Given Values--...
Sulfur dioxide flows through a heat exchanger at 45 moles/hr. The inlet to the isobaric heat...
Sulfur dioxide flows through a heat exchanger at 45 moles/hr. The inlet to the isobaric heat exchanger is 100°C and 1bar and the heat rate is 1,300 kJ/hr. Assume an ideal gas with a Cp 0.05791T with T in K. mol K a. b. c. Determine the exit temperature for this heat exchanger. Determine the total rate change of entropy of the exit to inlet to the heat exchanger? Is the process of increasing SO2 temperature reversible? Prove with the...
A combined cycle gas turbine / vapor power plant uses the turbine exhaust as the energy...
A combined cycle gas turbine / vapor power plant uses the turbine exhaust as the energy source for the boiler. Each power system uses a single turbine. The gas power system is modeled as an ideal air-standard Brayton cycle. The vapor power system is modeled as an ideal Rankine cycle. Given specific operating conditions determine the temperature and pressure at each state, the rate of heat transfer in the boiler, the power output of each turbine, and the overall efficiency....
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...
A turbojet engine consists of a diffuser, compressor, combustor, turbine and a converging nozzle. The engine...
A turbojet engine consists of a diffuser, compressor, combustor, turbine and a converging nozzle. The engine is operating on an aircraft flying at 260 m/s at an altitude where the air is at 61 kPa and -11 °C. The inlet diameter of this engine is 1.6 m; the thrust produced by the engine under ideal cruising conditions is 93,625 N; and the temperature at the turbine inlet is 750 °C. Assume constant specific heat values at room temperature, choked flow...
1. The nozzle shown in the sketch below is designed to accelerate the flow of CO2...
1. The nozzle shown in the sketch below is designed to accelerate the flow of CO2 from a velocity close to zero to one that is rather high. The inlet temperature and pressure are 1000K and 614.705 kPa, respectively, and the nozzle exhausts to the atmosphere at 100 kPa. Using the ideal Gas Tables Determine the outlet velocity and temperature when the expansion through the nozzle is considered to be ideal (reversible); a. b. Calculate the temperature and velocity at...
Heat exchanger 5 Comb. Compressor Turbine A gas turbine for an automobile is designed with a...
Heat exchanger 5 Comb. Compressor Turbine A gas turbine for an automobile is designed with a regenerator. Air enters the compressor of this engine at 100 kPa and 20°C. The compressor pressure ratio is 7.8; the maximum cycle temperature is 865°C; and the cold air stream leaves the regenerator 10°C cooler than the hot air stream at the inlet of the regenerator. Assuming both the compressor and the turbine to be isentropic, determine the rates of heat addition and rejection...
Steam Generator air (inlet) - 320°C P. = 100 kPa th =0.5 kg/s heat exchanger - water (inlet) T = 20°C Pw = 100 kPa m = 0.025 kg/s Problem sketch Solve with EES. Document all necessary balances The problem sketch illustrates a heat exchanger in which hot air is used to generate steam. Air enters the heat exchanger at 1a, in = 320C, Pa = 100 kPa, and ma -0.5 kg/s. Model air as an ideal gas with constant...
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...
Sulfur dioxide flows through a heat exchanger at 45 moles/hr. The inlet to the isobaric heat exchanger is 100°C and 1bar and the heat rate is 1,300 kJ/hr. Assume an ideal gas with a Cp 0.05791T with T in K. mol K a. b. c. Determine the exit temperature for this heat exchanger. Determine the total rate change of entropy of the exit to inlet to the heat exchanger? Is the process of increasing SO2 temperature reversible? Prove with the...
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...
A turbojet engine consists of a diffuser, compressor, combustor, turbine and a converging nozzle. The engine is operating on an aircraft flying at 260 m/s at an altitude where the air is at 61 kPa and -11 °C. The inlet diameter of this engine is 1.6 m; the thrust produced by the engine under ideal cruising conditions is 93,625 N; and the temperature at the turbine inlet is 750 °C. Assume constant specific heat values at room temperature, choked flow...
1. The nozzle shown in the sketch below is designed to accelerate the flow of CO2 from a velocity close to zero to one that is rather high. The inlet temperature and pressure are 1000K and 614.705 kPa, respectively, and the nozzle exhausts to the atmosphere at 100 kPa. Using the ideal Gas Tables Determine the outlet velocity and temperature when the expansion through the nozzle is considered to be ideal (reversible); a. b. Calculate the temperature and velocity at...
Heat exchanger 5 Comb. Compressor Turbine A gas turbine for an automobile is designed with a regenerator. Air enters the compressor of this engine at 100 kPa and 20°C. The compressor pressure ratio is 7.8; the maximum cycle temperature is 865°C; and the cold air stream leaves the regenerator 10°C cooler than the hot air stream at the inlet of the regenerator. Assuming both the compressor and the turbine to be isentropic, determine the rates of heat addition and rejection...
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