Calculate the gas temperature at the exit of the turbine.
For the same engine in Prob. 9.21, calculate the Mach number at the nozzle exit. From this result, comment on the Mach number regime of the type of aircraft that might use this engine. Prob. 9.21 For the same engine in Probs. 9.18-9.20, the pressure at the exit of the nozzle is 2116lb/ft2. The pressure at the inlet to the compressor is also 2116lb/ft2. The flow velocity entering the nozzle is 1500 sec. Calculate the flow velocity at the nozzle exit. Prob. 9.18 The pressure ratio across the compressor of a given turbojet engine is 11.7. The temperature of the air entering the compressor is T2 = 585°R. The mass flow through the compressor is 200 /sec. Assume that the flow velocities entering and leaving the compressor are equal, that is, V2 = V3. Calculate the power (in horsepower) provided by the compressor. where w. is the compressor work per unit mass of gas. Probs. 9.20. In a simple turbojet engine, the turbine provides the power that drives the compressor. For the same engine treated in Probs. 9.18 and 9.19, the temperature of the gas entering the turbine is the same as the temperature of the gas leaving the combustor, namely T4 = 2ll0°R. Assuming no mechanical losses, the work provided by the turbine is equal to the work done by the compressor. Assume that the flow velocity entering the turbine is equal to the velocity leaving the turbine, that is, v. = V5• Calculate the gas temperature at the exit of the turbine. Prob. 9.18 The pressure ratio across the compressor of a given turbojet engine is 11.7. The temperature of the air entering the compressor is T2 = 585°R. The mass flow through the compressor is 200 /sec. Assume that the flow velocities entering and leaving the compressor are equal, that is, V2 = V3. Calculate the power (in horsepower) provided by the compressor. where w. is the compressor work per unit mass of gas. Probs. 9.19 For the same engine in Prob. 9.18, fuel is injected and burned in the combustor. The gas temperature at the exit of the combustor is 2ll0°R. Assuming that the heat released per pound of fuel is 1.4 x 107 ., the fuel consumption in /sec. Prob. 9.18 The pressure ratio across the compressor of a given turbojet engine is 11.7. The temperature of the air entering the compressor is T2 = 585°R. The mass flow through the compressor is 200 /sec. Assume that the flow velocities entering and leaving the compressor are equal, that is, V2 = V3. Calculate the power (in horsepower) provided by the compressor. where w. is the compressor work per unit mass of gas.
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