The pressure ratio across the compressor of a given turbojet engine is 11.7. The temperatu...

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 lbm/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. Hint: Because compressor work is done on the gas between the inlet (point 2) and exit (point 3) of the compressor, the energy equation given by Eq. (4.42) is modified to include the compressor work as follows:

where wc is the compressor work per unit mass of gas.