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 = 2110°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, V4 = V5. Calculate the gas temperature at the exit of the turbine.
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