An Investigation of Axial Compressor Rotor Aerodynamics

[+] Author and Article Information
R. P. Dring

Gas Turbine Technology, United Technologies Research Center, East Hartford, Conn.

H. D. Joslyn, L. W. Hardin

United Technologies Research Center, East Hartford, Conn.

J. Eng. Power 104(1), 84-96 (Jan 01, 1982) (13 pages) doi:10.1115/1.3227270 History: Received December 04, 1980; Online September 28, 2009


The detailed nature of the three-dimensional flow over the blading, and in the wake, of an isolated compressor rotor has been studied experimentally in a large scale rotating rig. A variety of flow properties were measured including (1) blade profile and endwall surface flow visualization, (2) radial-circumferential arrays of pneumatic wake data acquired in the rotating frame and (3) full-span blade pressure distribution data. Data have been obtained over a wide range of blade loading and downstream location. These results show a hub corner stall at lower blade loadings and full-span blade separation at higher blade loadings. Under both conditions there is strong radial flow on the airfoil. The radial flow in the wake, however, increases dramatically when the blade undergoes full-span separation. The impact of these flow phenomena on the blade pressure distribution is also illustrated.

Copyright © 1982 by ASME
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