Abstract
The paper investigates the effect of a single circumferential groove casing treatment (CGCT) on a transonic compressor rotor numerically. In particular, the effect of the groove at different axial locations on the flow field is studied in detail and stall margin improvement is also discussed. The present results show that the groove close to the leading edge plays a crucial role in stabilizing the near stall flow structures and, hence, improves the stall margin. The groove at the mid-chord-section of the blade can help exchange and transfer momentums between different directions, and suppress the flow unsteadiness, leading to increased efficiency in rotor performance and extended operation range. The groove located near the blade trailing edge has limited effects on stall margin improvement and may cause additional penalty in efficiency. Through comparison with the recent work on CGCT, some common flow physics can be observed.
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