2.-Consider a cylindrical combustion chamber where air enters at 480 kPa with a density of 3.05...
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...
2. Air is steadily discharged from a large chamber in which the pressure is 500 kPa, the temperature is 30°C, and the velocity is effectively zero through a nozzle, as shown in Fig. 2. Assuming one dimensional isentropic flow, find: (a) if the pressure at some section of the nozzle is 80 kPa, the Mach number, temperature, and velocity at this section. (b) if the nozzle has a circular cross-section with a diameter of 12 mm at the section discussed...
Air enters a diffuser at a constant 109 Kpa , 60 celcius and 292 meters per second. The air exits at 305 Kpa , 10 Celcius and 10 meters per second. The area of the inlet is 104 cm^2. You can assume the air is an ideal gas. CP and CV values are assumed constant. Steady flow. There is no change in Potential Energy. Ru=8.314 kj/kmol*k Mair = 28.97 kg/kmol cp=1.005 kj/kg*k cv=0.718 kj/kg*k Determine the average heat transfer time...
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...
UBAV Air flows through a converging-diverging nozzle diffuser. A normal shock stands in the diverging section of the nozzle. Assuming isentropie flow, air as an ideal gas, and constant specific heat determine the state at several locations in the system. Solve wsing equations rather than with the tables Note: The Specific heat ratio and gas constant for air are given as k-1 and R 0.287 kJ/kg-K respectively Give Values Inlet Temperature: TI(K)-340 Inlet pressure: P1 (kPa) - 550 Inlet Velocity:...
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) = 338 Inlet pressure: P1 (kPa) = 555 Inlet Velocity: V1 (m/s) = 121 Area at inlet (cm^2) = 9 Mach number at the exit = 1.56 a) Determine...
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 the system. Solve using equations rather than with the tables. 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) = 353 Inlet pressure: Pl (kPa) = 546 Inlet Velocity: V1 (m/s) = 61 Area at nozzle inlet: A1 (cm^2) = 7.24...
Air enters an adiabatic nozzle under the following conditions: pressure = 900 kPa temperature = 560°C velocity = 2.7 m/s The air leaves the nozzle at 850 kPa and 480 °C. What is the velocity at the exit of the nozzle? Assume the specific heat is constant and can be taken at the average temperature between the inlet and outlet. air (c) EYES Niel Crews, 2013
3. Air enters a constant area duct at a Mach number of 0.14, a pressure of 195 kPa, and a temperature of 25 °C. Heat is added to the air that flows through the duct at a rate of 65 kJ/kg of air. Assuming that the flow is steady and that the effects of wall friction can be ignored, find the temperature, pressure, and Mach number at which the air leaves the duct. Assume that the air behaves as a...
Air enters a well-insulated nozzle at 400 m/s, 7 kPa, and 417°C and exits at 700 m/s. The nozzle inlet diameter is 0.2 m. Assuming ideal gas behavior, calculate a) the mass flow rate of the air. Then, determine the exit temperature of the air two ways: b) using the air table (A-17, which automatically accounts for the variation of specific heat with temperature); and c) assuming constant specific heats at the inlet temperature of 417°C. i he comatn speche...