The axial compressor has a stage temperature rise of 30k

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Reference no: EM13632062

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%

The axial compressor has a stage temperature rise of 30K, using a 50% reaction design with a stator outlet angle of 20. If the mean diameter of each single is 25cm and each stage is identical, calculate the required rotational speed. Assume a work done factor of 0.86 and a constant axial velocitiy of 150m/s.

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 fo the centrifugal compressor. Ambient conditions are 1.01 and 288K.

Reference no: EM13632062

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