Circumferential Casing Treatment in a Transonic Fan

Document Type : Research Article

Authors

1 Department of Aerospace Engineering, Center of Excellence in Computational Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran

2 Institute of Mechanics and Fluid Dynamics, Technische Universität Bergakademie Freiberg,, Freiberg, Germany

Abstract

This paper reports on a numerical simulation of circumferential groove casing treatment in a high-speed axial fan. Four circumferential grooves of the same geometry are located over the tip of a NASA Rotor-67 and unsteady calculations are performed from choke to near-stall. Results show that circumferential grooves reduce the incidence angle near the pressure surface at the blade leading-edge. Furthermore, the passage shock and the leakage flow are pushed rearward in the passage. It is found that circumferential grooves increase the momentum in the streamwise direction (fluid is absorbed by the grooves from their downstream part and is injected from their upstream section). The grooves also provide a flow path between the suction and pressure surface, leading to a reduction in the pressure difference between them. At the near-stall point the flow field near the grooves was found to be highly unsteady. Maximum unsteadiness was observed in the first upstream groove: the circulated mass flow rate changed as high as roughly 30 percent of its time-averaged value. As a result, in order to simulate circumferential groove casing treatment in compressors, unsteady computations are required.

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References

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Amirkabir Journal of Mechanical Engineering
Volume 53, Issue 7
October 2021
Pages 4189-4202

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