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RESEARCH PAPERS

Flow Through Cascades of Slotted Compressor Blades

[+] Author and Article Information
A. A. Mikolajczak, H. D. Weingold, J. P. Nikkanen

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

J. Eng. Power 92(1), 57-64 (Jan 01, 1970) (8 pages) doi:10.1115/1.3445300 History: Received December 16, 1968; Online July 14, 2010

Abstract

The performance of axial flow compressors can be improved when it becomes possible to achieve higher loading per stage than currently attainable. The major obstacles to attaining this objective are the limitations on loading in the end wall region and the limited range of operating incidence of compressor blades. A possible method of achieving a wide range of operating incidence is the use of slotted or multibody airfoils. An incompressible, two-dimensional, potential flow analysis for thick, highly cambered multibodies in cascade is presented. The analysis is extended to include compressibility. A boundary-layer calculation, including a wake model, is described and used to predict cascade losses. Theoretical predictions are compared against slotted and unslotted cascade and compressor stator experimental results and adequate agreement obtained. The slotted blade concept is shown to offer performance benefits, provided that end-wall loading limitations can be overcome.

Copyright © 1970 by ASME
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