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Air at P1= 183 kPa and Ma1 =2.4 undergoes isentropic expansion. The pressure downstream is P2=...
Air undergoes an isentropic process from p1=1atm, T1=540R to a final state where the temperature is...
Air undergoes an isentropic process from p1=1atm, T1=540R to a final state where the temperature is T2=1160R. employing the ideal gas model, determine the final pressure p2, in atm. Assume a constant specific ratio k evaluated at the mean temperature.
Air at stagnation pressure of 700 kPa and temperature of 530 K enters a isentropic converging-diverging...
Air at stagnation pressure of 700 kPa and temperature of 530 K enters a isentropic converging-diverging nozzle. The throat area of the nozzle is 5 cm2, the exit area is 12.5 cm2. The back pressure is 350 kPa and a normal shock occurs within a diverging section. Determine (a) exit Mach number, (b) change in stagnation pressure, (c) upstream and downstream Mach number of shock (d) cross sectional area where shock occurs (e) back pressure if the flow were isentropic...
Air in a piston-cylinder assembly undergoes a polytropic expansion in which the pressure – specific volume...
Air in a piston-cylinder assembly undergoes a polytropic expansion in which the pressure – specific volume relation is p. V..2=constant. The initial volume is 0.5 m², the initial temperature is 500 K and initial pressure is 600 kPa. The final pressure is 300 kPa. Determine (a) the mass of air, in kg (b) the boundary work, in kJ (c) the final temperature in K and (d) the heat transfer, in kJ.
For air, y- 1.4, cp 1.005 k]/kg K, R- 0.287 kJ/kg K unless stated in question....
For air, y- 1.4, cp 1.005 k]/kg K, R- 0.287 kJ/kg K unless stated in question. 1. Air flows adiabatically through a duct. At point 1 the velocity is 240m/s, with T1 - 320 K and p1 170 kPa. Compute i. To ii. (Mach number) ii. At point 2 further downstream V2-290 m/s and P2-135 kPa. What is the stagnation pressure Po2 Hints: Given the properties it is easy to solve for the Mach number using the following formulas To/T...
A jet engine propels an aircraft at 254 m/s through air at 39 kPa and 273 K. The compressor pressure ratio is 9 and the temperature at the turbine inlet is 873 K. b) Taking the pressure in the combust...
A jet engine propels an aircraft at 254 m/s through air at 39 kPa and 273 K. The compressor pressure ratio is 9 and the temperature at the turbine inlet is 873 K. b) Taking the pressure in the combustion chamber as 843.5 kPa and the temperature at the turbine exit to be 518 K, determine the velocity of the exhaust gases. Give your answer in m/s to 2 decimal places. Assume ideal operation for all components and constant specific...
1.) Consider the gas turbine with air-standard Brayton cycle shown below Temperature, T and Pressure, P...
1.) Consider the gas turbine with air-standard Brayton cycle shown below Temperature, T and Pressure, P are measured at the following points in the cycle: Turbine: input: TH = 1200 K, PH = 800 kPa output: TL = 662.4 K, PL = 100 kPa Compressor: input Tc = 300 K, Pc = 100 kPa output: Th = 543.4 K, Ph = 800 kPa Note: the working fluid is air which has Cp = 1.005 kJ/kg.K, k = 1.4, R =...
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...
A jet engine propels an aircraft at 254 m/s through air at 39 kPa and 273 K. The compressor pressure ratio is 9 and the temperature at the turbine inlet is 873 K. a) Determine the temperature of the a...
A jet engine propels an aircraft at 254 m/s through air at 39 kPa and 273 K. The compressor pressure ratio is 9 and the temperature at the turbine inlet is 873 K. a) Determine the temperature of the air as it enters the exit nozzle. Give your answer in Kelvin to 2 decimal places Assume ideal operation for all components and constant specific heats at room temperature. Take the properties of air at room temperature to be R =...
A piston-cylinder assembly contains air modeled as an ideal gas. The air undergoes a power cycle...
A piston-cylinder assembly contains air modeled as an ideal gas. The air undergoes a power cycle consisting of four processes in series: • Process 1-2: Constant-temperature expansion at 600 K from p1 = 0.5 MPa to p2 = 0.4 MPa. • Process 2-3: Polytropic expansion with n = 1.3 to p3 = 0.3 MPa. • Process 3-4: Constant-pressure compression to ν4 = ν1. • Process 4-1: Constant-volume heating. a) Sketch the cycle on a p-ν diagram. b) Calculate the work...
An aircraft engine operates on a simple ideal Brayton cycle with a pressure ratio rp of...
An aircraft engine operates on a simple ideal Brayton cycle with
a pressure ratio rp of 9. Heat is added to the cycle at a rate of
490 kW; air passes through the engine at a rate of 1.1 kg/s; and
the air at the beginning of the compression is at P1 = 71 kPa and
T1 = 0 oC. Use constant specific heats at room temperature. The
properties of air at room temperature are cp =1.005 kJ/kg.K and k...
Air in a piston-cylinder assembly undergoes a polytropic expansion in which the pressure – specific volume relation is p. V..2=constant. The initial volume is 0.5 m², the initial temperature is 500 K and initial pressure is 600 kPa. The final pressure is 300 kPa. Determine (a) the mass of air, in kg (b) the boundary work, in kJ (c) the final temperature in K and (d) the heat transfer, in kJ.
For air, y- 1.4, cp 1.005 k]/kg K, R- 0.287 kJ/kg K unless stated in question. 1. Air flows adiabatically through a duct. At point 1 the velocity is 240m/s, with T1 - 320 K and p1 170 kPa. Compute i. To ii. (Mach number) ii. At point 2 further downstream V2-290 m/s and P2-135 kPa. What is the stagnation pressure Po2 Hints: Given the properties it is easy to solve for the Mach number using the following formulas To/T...
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...
An aircraft engine operates on a simple ideal Brayton cycle with
a pressure ratio rp of 9. Heat is added to the cycle at a rate of
490 kW; air passes through the engine at a rate of 1.1 kg/s; and
the air at the beginning of the compression is at P1 = 71 kPa and
T1 = 0 oC. Use constant specific heats at room temperature. The
properties of air at room temperature are cp =1.005 kJ/kg.K and k...
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