Aerodynamic Investigations of High Pressure Ratio Centrifugal Compressor

Murugesan, K and Sankaranarayanan, S and Ramamurthy, S (1991) Aerodynamic Investigations of High Pressure Ratio Centrifugal Compressor. Project Report. NAL, NAL Bangalore. (Submitted)

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Abstract

A general purpose design methodology for high pressure ratio centrifugal compressor was developed.This includes realistic flow models and loss correlations.New analytic functions were evolved to define optimized blade geometry.Theoretical methods were developed and used to analyze the flow in the hub to shroud and blade to blade surfaces.A methodology was developed for estimating the simulated performance of the impeller in different mediums.Two different designs of impeller were chosen and fabricated for design validation.One of these impeller was tested in Closed Circuit Centrifugal compressor test rig(CLOCTER) for its performance.A pressure ratio of 6:1 with an impeller total to total peak efficiency of about 88% was achieved.This work was carried out at Propulsion Division,National Aerospace Laboratory,Bangalore-17 under a grant-in-aid project entitled "Aerodynamic Investigation of High pressure Ratio Centrifugal Compressor" funded by Aeronautical Research and Development Board.This project yielded useful data for the generation of design know-how and technology development for high pressure ratio centrifugal compressors.

Item Type: Proj.Doc/Technical Report (Project Report)
Subjects: AERONAUTICS > Aeronautics (General)
AERONAUTICS > Aircraft Propulsion and Power
Division/Department: Propulsion Division, Propulsion Division, Propulsion Division
Depositing User: Dr S Ramamurthy
Date Deposited: 24 Aug 2010 15:14
Last Modified: 24 Aug 2010 15:14
URI: http://nal-ir.nal.res.in/id/eprint/9017

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