An Axial Compressor End-Wall Boundary Layer Theory

[+] Author and Article Information
G. L. Mellor

Department of Aerospace and Mechanical Sciences, Princeton University, Princeton, N. J.

G. M. Wood

Pratt & Whitney Aircraft Division, United Aircraft Corp., East Hartford, Conn.

J. Basic Eng 93(2), 300-314 (Jun 01, 1971) (15 pages) doi:10.1115/1.3425231 History: Received February 02, 1970; Online October 27, 2010


The essential ingredient missing in existing prediction methods for the performance of multistage axial compressors is that which would account for the effect of end-wall boundary layers. It is, in fact, believed that end-wall boundary layers play a major role in compressor performance and the absence of an adequate theory represents a handicap to turbomachinery designers that might be likened to the handicap that designers of wings, for example, would face if Prandtl had not introduced the idea of a boundary layer. In this paper a new theory is developed which retains all elements of classical boundary layer theory; for example, we discuss variables such as momentum thickness and wall shear stress. However, the present theory introduces new concepts such as axial and tangential defect force thickness, a rotor exit-stator inlet “jump condition” and the importance of these concepts is demonstrated. Inherent in the derivation is an identification of the role of secondary flow and tip clearance flow. A proper means of matching the boundary layer calculations to conventional main stream calculations is suggested. Independent of empirical parametization it appears that the theory is capable of correctly modeling boundary layer blockage, losses, and end-wall stall. Near stall, the main stream-boundary layer interaction is very strong.

Copyright © 1971 by ASME
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