NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
End wall flows in rotors and stators of a single stage compressorA solution of the flow in the rotor end wall region, including the effects of tip clearance flow, is presented. A method for leakage flow measurement at the tip of a compressor rotor blade is discussed. Measurements are given for a rotor hub wall boundary layer.
Document ID
19810019559
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Govindam, T. R. (Pennsylvania State Univ. University Park, PA, United States)
Lakshminarayana, B. (Pennsylvania State Univ. University Park, PA, United States)
Pandya, A. (Pennsylvania State Univ. University Park, PA, United States)
Pouagare, M. (Pennsylvania State Univ. University Park, PA, United States)
Date Acquired
September 4, 2013
Publication Date
August 1, 1981
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
PSU/TURBO-R81-7
NASA-CR-164635
Accession Number
81N28097
Funding Number(s)
CONTRACT_GRANT: NSG-3212
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