A Correlation of End Wall Losses in Plane Compressor Cascades

[+] Author and Article Information
W. T. Hanley

Pratt & Whitney Aircraft, Division of United Aircraft Corporation, East Hartford, Conn.

J. Eng. Power 90(3), 251-257 (Jul 01, 1968) (7 pages) doi:10.1115/1.3609183 History: Received December 18, 1967; Online August 25, 2011


Consideration of parameters suggested by the momentum integral equations has lead to a successful correlation relating (a) the change of the free stream component of the end wall boundary layer displacement thickness to chord ratio, and (b) a profile parameter as functions of free stream loading. For the range of investigation, both correlations were found to be insensitive to gap-chord ratio, camber, stagger, incidence, and airfoil shape. Maximum permissible loading limits for operation without excessive end wall loss are shown to decrease with increasing inlet displacement thickness to chord ratio.

Copyright © 1968 by ASME
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