Aerospace Engineering > GATE 2014 > Centrifugal Compressors
Air at a stagnation temperature of 300K (ratio of specific heats, γ=1.4 and specific gas constant R =287 J/kgK) enters the impeller of a centrifugal compressor in axial direction. The stagnation pressure ratio between the diffuser outlet and impeller inlet is 4.0. The impeller blade radius is 0.3 m and it is rotating at 15000 rev/min. If the slip factor σs (Ratio of tangential component of air velocity at the blade tip to the blade tip speed) is 0.88, the overall efficiency (total-to-total) of the compressor (in %) is

Correct : 74 to 76

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centrifugal compressor efficiency GATE Aerospace Engineering 2014 stagnation temperature specific heats ratio specific gas constant air velocity compressor compressor blade radius compressor efficiency calculation slip factor total-to-total efficiency GATE 2014 aerospace compressors engineering turbomachinery efficiency aerospace engineering gate compressor performance GATE 2014 question 57

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