Development of High Pressure ratio Centrifugal Compressor Stage

Ramamurthy, S and Sankaranarayanan, S and Murugesan, K and Ramachar, D and Rajendran, R Development of High Pressure ratio Centrifugal Compressor Stage. In: 4th National Conference on Air Breathing Engines and Aerospace Propulsion, 1998 December, Bangalore. (Submitted)

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A high-pressure ratio centrifugal compressor stage consisting of an impeller and a matched vaned diffuser were designed and tested in a closed circuit centrifugal compressor test facility. The detailed measurements were carried out both at subsonic and supersonic Mach numbers at impeller outlet. The stage characteristics showed achievement of compressor stage total to total pressure ratio of 6.5 with an efficiency of 85%. The vaned diffuser shows good static pressure recovery of the order of around 0.6 with total pressure loss less than 2% at design point. Some of the salient experimental results are discussed in this paper.

Item Type: Conference or Workshop Item (Lecture)
Uncontrolled Keywords: centrifugal compressor, vaned diffuser,
Subjects: AERONAUTICS > Aeronautics (General)
AERONAUTICS > Aircraft Propulsion and Power
Depositing User: Dr S Ramamurthy
Date Deposited: 10 Aug 2010 04:26
Last Modified: 10 Aug 2010 04:26

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