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Core compressor exit stage study, volume 6Rear stage blading designs that have lower losses in their endwall boundary layer regions were studied. A baseline Stage A was designed as a low-speed model of stage 7 of a 10-stage compressor. Candidate rotors and stators were designed which have the potential of reducing endwall losses relative to the baseline. Rotor B uses a type of meanline in the tip region that unloads the leading edge and loads the trailing edge relative to the baseline rotor A designs. Rotor C incorporates a more skewed (hub strong) radial distribution of total pressure and smoother distribution of static pressure on the rotor tip than those of rotor B. Candidate stator B embodies twist gradients in the endwall region. Stator C embodies airfoil sections near the endwalls that have reduced trailing edge loading relative to stator A. The baseline and candidate bladings were tested using four identical stages to produce a true multistage environment. Single-stage tests were also conducted. The test data were analyzed and performances were compared. Several of the candidate configurations showed a performance improvement relative to the baseline.
Document ID
19820019434
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Wisler, D. C. (General Electric Co. Cincinnati, OH, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1981
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-CR-165553
NAS 1.26:165554
GE-R81AEG288
Accession Number
82N27310
Funding Number(s)
PROJECT: RTOP 505-32-2A
CONTRACT_GRANT: NAS3-20070
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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