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7.4 Air flows through a combustor in a Rayleigh process. Inlet conditions 300K, and V, =...
8. Plot a Rayleigh line for air on the ts plane for the following inlet conditions:...
8. Plot a Rayleigh line for air on the ts plane for the following inlet conditions: pressure 3.5 105 N/m2, temperature 550 K, area 0.010 m2, and mass flow rate 30 kg/s. Plot this line for both the subsonic and supersonic region. Assume c, is constant 1004.8 J/kg-K, and that s 0 at 220 K. From the Rayleigh-line plot, determine the amount of fuel that must be burned in the air to raise its temperature to the maximum value. Assume...
Problem 3 Steam flows steadily through an adiabatic turbine. The inlet conditions of the steam are...
Problem 3 Steam flows steadily through an adiabatic turbine. The inlet conditions of the steam are 10 MPa, 400 C, and 80 m/s, and the exit conditions are 10 kPa, 92 percent quality, and 50 m/s. The mass flow rate of the steam is 12 kg/s. Determine (a) the change in kinetic energy, (b) the power output, and (c) the turbine inlet area. Pi = 10 MPa 7, = 400 °C V1 80 m/s No STEAM 3 12 kg/s ▼Sh...
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...
g through a nozzle. The inlet pressure is p 3.7 kPa (gage) air flowing and the air exhausts into the atmosphere. The...
g through a nozzle. The inlet pressure is p 3.7 kPa (gage) air flowing and the air exhausts into the atmosphere. The nozzle has an inlet diameter of 60 mm and an exit diameter of 10 mm, and the nozzle is connected to the supply pipe by flanges. Find the force required to hold the nozzle stationary. Assume the air has a constant density of 1.22 kg/m Neglect the weight of the nozzle. m Flanges Flow 2
g through a...
1) Air under standard conditions flows through a 5 mm diameter drawn tubing with an average...
1) Air under standard conditions flows through a 5 mm diameter drawn tubing with an average velocity of V 40 m/s. Determine the pressure drop (Ap) and head loss (h) if the length of tube is 10 cm. Assume minor losses are zero. Air density 1.23 kg/m3 Air viscosity 0.0000179 N.s/m2
A compressor is takes in air at an inlet pressure of P1 = 80 kPa and...
A compressor is takes in air at an inlet pressure of P1 = 80 kPa and an inlet temperature of T1 = 20oC and exhausts it at an outlet pressure of P2 =800 kPa and an outlet temperature of T1 = 200oC. Air flows through the compressor at a mass flow rate of m = 1 kg/s. Assume that the compressor is adiabatic. Find the power required to run the compressor. (Your answer will be in kW.)
Please help with a detailed solution. Problem 2 (1). (35 pts total) 2-0 The inlet volumetric...
Please help with a detailed solution.
Problem 2 (1). (35 pts total) 2-0 The inlet volumetric flow rate for an adiabatic compressor is 10 (L/s] of air. The inlet conditions are 120 [kPa) and 20 [deg C). The outlet conditions are 1000 [kPa] and 300 [deg C). Treat air as an ideal gas. Ignore changes in kinetic and potential energy. (a) (5 pts) What is the heat transfer into the system? v. 2.001m3 Answer = Answer = _ 0 '...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 360 Inlet pressure: P1 (kPa) = 583 Inlet Velocity: V1 (m/s) = 105 Area at inlet (cm^2) = 8.2 Mach number at the exit = 1.86 a) Determine...
Steam flows steadily through an adiabatic turbine. (c) BY-NC- Niel Crews, 2013 The inlet conditions of...
Steam flows steadily through an adiabatic turbine. (c) BY-NC- Niel Crews, 2013 The inlet conditions of the steam are: pressure = 10 MPa temperature = 450 °C velocity = 80 m/s The exit conditions are: pressure = 10 kPa quality = 0.92 velocity = 50 m/s a) What is the temperature of the fluid at the turbine exit? b) What is the power output of the turbine, per unit mass of the working fluid?
Air, initially at atmospheric conditions, flows through an atmospheric-pressure heat exchanger. Assume that the process in...
Air, initially at atmospheric conditions, flows through an atmospheric-pressure heat exchanger. Assume that the process in the heat exchanger can be discretized into 100 steps, where 5 kJ/kg of heat is added to the air at each step. a) Derive an equation that can be used to calculate the temperature of the air at each step. b) Derive an equation that can be used to calculate the exergy of air at each step. c) Implement the equations in MATLAB and...
8. Plot a Rayleigh line for air on the ts plane for the following inlet conditions: pressure 3.5 105 N/m2, temperature 550 K, area 0.010 m2, and mass flow rate 30 kg/s. Plot this line for both the subsonic and supersonic region. Assume c, is constant 1004.8 J/kg-K, and that s 0 at 220 K. From the Rayleigh-line plot, determine the amount of fuel that must be burned in the air to raise its temperature to the maximum value. Assume...
Problem 3 Steam flows steadily through an adiabatic turbine. The inlet conditions of the steam are 10 MPa, 400 C, and 80 m/s, and the exit conditions are 10 kPa, 92 percent quality, and 50 m/s. The mass flow rate of the steam is 12 kg/s. Determine (a) the change in kinetic energy, (b) the power output, and (c) the turbine inlet area. Pi = 10 MPa 7, = 400 °C V1 80 m/s No STEAM 3 12 kg/s ▼Sh...
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...
g through a nozzle. The inlet pressure is p 3.7 kPa (gage) air flowing and the air exhausts into the atmosphere. The nozzle has an inlet diameter of 60 mm and an exit diameter of 10 mm, and the nozzle is connected to the supply pipe by flanges. Find the force required to hold the nozzle stationary. Assume the air has a constant density of 1.22 kg/m Neglect the weight of the nozzle. m Flanges Flow 2
g through a...
1) Air under standard conditions flows through a 5 mm diameter drawn tubing with an average velocity of V 40 m/s. Determine the pressure drop (Ap) and head loss (h) if the length of tube is 10 cm. Assume minor losses are zero. Air density 1.23 kg/m3 Air viscosity 0.0000179 N.s/m2
Please help with a detailed solution.
Problem 2 (1). (35 pts total) 2-0 The inlet volumetric flow rate for an adiabatic compressor is 10 (L/s] of air. The inlet conditions are 120 [kPa) and 20 [deg C). The outlet conditions are 1000 [kPa] and 300 [deg C). Treat air as an ideal gas. Ignore changes in kinetic and potential energy. (a) (5 pts) What is the heat transfer into the system? v. 2.001m3 Answer = Answer = _ 0 '...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 360 Inlet pressure: P1 (kPa) = 583 Inlet Velocity: V1 (m/s) = 105 Area at inlet (cm^2) = 8.2 Mach number at the exit = 1.86 a) Determine...
Steam flows steadily through an adiabatic turbine. (c) BY-NC- Niel Crews, 2013 The inlet conditions of the steam are: pressure = 10 MPa temperature = 450 °C velocity = 80 m/s The exit conditions are: pressure = 10 kPa quality = 0.92 velocity = 50 m/s a) What is the temperature of the fluid at the turbine exit? b) What is the power output of the turbine, per unit mass of the working fluid?
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