Assuming an axial velocity at the eye of the impeller an

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A helicopter gas turbine requires an overall compressor P.R. of 10:1. This is to be obtained using a two-spool layout consisting of a 4 stage axial compressor followed by a single-stage centrifugal compressor. The polytropic efficiency of the axial compressor is 92% and hat of the contrifugal is 83%

Assuming an axial velocity at the eye of the impeller, an impeller tip diameter of 33cm, a slip factor of 0.90 and a power input factor of 1.04, calculate the rotational speed required for the centrifugal compressor. Ambient conditions are 1.01 and 288K.

Reference no: EM13632269

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