An Investigation of Axial Compressor Rotor Aerodynamics

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) radia...

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Bibliographic Details
Published in:Journal of engineering for gas turbines and power 1982-01, Vol.104 (1), p.84-96
Main Authors: Dring, R. P, Joslyn, H. D, Hardin, L. W
Format: Article
Language:English
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Summary: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.
ISSN:0742-4795
0022-0825
1528-8919
DOI:10.1115/1.3227270