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Analytical correlation of centrifugal compressor design geometry for maximum efficiency with specific speedCentrifugal compressor performance was examined analytically to determine optimum geometry for various applications as characterized by specific speed. Seven specific losses were calculated for various combinations of inlet tip-exit diameter ratio, inlet hub-tip diameter ratio, blade exit backsweep, and inlet-tip absolute tangential velocity for solid body prewhirl. The losses considered were inlet guide vane loss, blade loading loss, skin friction loss, recirculation loss, disk friction loss, vaneless diffuser loss, and vaned diffuser loss. Maximum total efficiencies ranged from 0.497 to 0.868 for a specific speed range of 0.257 to 1.346. Curves of rotor exit absolute flow angle, inlet tip-exit diameter ratio, inlet hub-tip diameter ratio, head coefficient and blade exit backsweep are presented over a range of specific speeds for various inducer tip speeds to permit rapid selection of optimum compressor size and shape for a variety of applications.
Document ID
19720011352
Document Type
Other - NASA Technical Note (TN)
Authors
Galvas, M. R.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
March 1, 1972
Subject Category
Aerodynamics
Report/Patent Number
E-6638
NASA-TN-D-6729
Accession Number
72N19002
Funding Number(s)
PROJECT: RTOP 132-15
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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