Inlet Boundary Layer Effects in an Axial Compressor Rotor: Part I—Blade-to-Blade Effects

[+] Author and Article Information
J. H. Wagner, R. P. Dring, H. D. Joslyn

United Technologies Research Center, East Hartford, Conn. 06108

J. Eng. Gas Turbines Power 107(2), 374-380 (Apr 01, 1985) (7 pages) doi:10.1115/1.3239734 History: Received January 06, 1984; Online October 15, 2009


This paper discusses experimental data measured on the blading and downstream of an isolated compressor rotor with thick inlet endwall boundary layers. The objective of the study was to compare these results with data acquired previously with thin inlet boundary layers and to assess the impact of inlet boundary layer thickness on the secondary flow. Flow visualization results showed the powerful impact of the hub corner stall and how at the same near stall flow coefficient where with thin inlet boundary layers the blade was separated at midspan, with thick inlet boundary layers it was attached. It was also shown that while secondary flow was very weak, it did produce sufficient radial redistribution to cause an apparent negative loss at the blade root.

Copyright © 1985 by ASME
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