NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Core compressor exit stage study, 2A total of two three-stage compressors were designed and tested to determine the effects of aspect ratio on compressor performance. The first compressor was designed with an aspect ratio of 0.81; the other, with an aspect ratio of 1.22. Both compressors had a hub-tip ratio of 0.915, representative of the rear stages of a core compressor, and both were designed to achieve a 15.0% surge margin at design pressure ratios of 1.357 and 1.324, respectively, at a mean wheel speed of 167 m/sec. At design speed the 0.81 aspect ratio compressor achieved a pressure ratio of 1.346 at a corrected flow of 4.28 kg/sec and an adiabatic efficiency of 86.1%. The 1.22 aspect ratio design achieved a pressure ratio of 1.314 at 4.35 kg/sec flow and 87.0% adiabatic efficiency. Surge margin to peak efficiency was 24.0% with the lower aspect ratio blading, compared with 12.4% with the higher aspect ratio blading.
Document ID
19800014823
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Behlke, R. F. (Pratt and Whitney Aircraft Group East Hartford, CT, United States)
Burdsall, E. A. (Pratt and Whitney Aircraft Group East Hartford, CT, United States)
Canal, E., Jr. (Pratt and Whitney Aircraft Group East Hartford, CT, United States)
Korn, N. D. (Pratt and Whitney Aircraft Group East Hartford, CT, United States)
Date Acquired
September 4, 2013
Publication Date
October 1, 1979
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
PWA-5561-66
NASA-CR-159812
Accession Number
80N23312
Funding Number(s)
CONTRACT_GRANT: NAS3-20578
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available