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Study of casing treatment stall margin improvement phenomenaThe results of a program of experimental and analytical research in casing treatments over axial compressor rotor blade tips are presented. Circumferential groove, axial-skewed slot, and blade angle slot treatments were tested. These yielded, for reduction in stalling flow and loss in peak efficiency, 5.8% and 0 points, 15.3% and 2.0 points, and 15.0% and 1.2 points, respectively. These values are consistent with other experience. The favorable stalling flow situations correlated well with observations of higher-then-normal surface pressures on the rotor blade pressure surfaces in the tip region, and with increased maximum diffusions on the suction surfaces. Annular wall pressure gradients, especially in the 50-75% chord region, are also increased and blade surface pressure loadings are shifted toward the trailing edge for treated configurations. Rotor blade wakes may be somewhat thinner in the presence of good treatments, particularly under operating conditions close to the baseline stall.
Document ID
19740012322
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Prince, D. C., Jr. (General Electric Co. Cincinnati, OH, United States)
Wisler, D. C. (General Electric Co. Cincinnati, OH, United States)
Hilvers, D. E. (General Electric Co. Cincinnati, OH, United States)
Date Acquired
September 3, 2013
Publication Date
March 1, 1974
Subject Category
Propulsion Systems
Report/Patent Number
R73AEG326
NASA-CR-134552
Accession Number
74N20435
Funding Number(s)
CONTRACT_GRANT: NAS3-15707
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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