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Single-stage evaluation of highly-loaded high-Mach-number compressor stages 5. Data and performance of baseline, corner-blow wall suction and combined corner blow wall suction statorA single-stage compressor with a rotor tip speed of 1600 ft/sec and a 0.5 hub tip ratio was used to investigate the effects of several stator endwall treatment methods on stage range and performance. These endwall treatment methods consisted of stator corner-blow, annular wall suction upstream of stator leading edge, and combined corner-blow and annular wall suction. The overall stage performance with corner blow was essentially the same as the baseline performance. The performance for the annular wall suction and the combined corner-blow and wall suction showed a reduction in peak efficiency of 2.5 percentage points compared to the baseline data.
Document ID
19720015143
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Nikkanen, J. P.
(Pratt and Whitney Aircraft East Hartford, CT, United States)
Brooky, J. P.
(Pratt and Whitney Aircraft East Hartford, CT, United States)
Date Acquired
September 2, 2013
Publication Date
March 1, 1972
Subject Category
Propulsion Systems
Report/Patent Number
NASA-CR-120887
PWA-4312
Accession Number
72N22793
Funding Number(s)
CONTRACT_GRANT: NAS3-10482
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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