Effect of Circumferential Groove Casing Treatment on Surge Margin for Axial Flow Compressor
Abstract
In the design of axial compressors, which are widely used in aviation, one of the primary goals is to achieve the maximum compression ratio with few components. Stall margin and efficiency are also considered. Although the design is optimized to achieve maximum pressure ratio, the stall margin may not be at desired levels. One of the methods to increase stall margin is the geometric modifications at the blade tip casing. Circumferential groove casing treatment is one of these methods. Although the aim of circumferential groove is to widen the stall margin, it is not desired to reduce efficiency. In this paper, a total of 5 circumferential groove geometries with different depth and width were applied to the Rotor-67 casing, which is a well-known axial compressor in literature. The effects of circumferential groove casing treatment on the stall margin were investigated with computational flow analysis. A total of 5 analyses were performed with groove depths of 5, 10, 15 mm and groove widths of 3 and 4 mm. In all analyses, it was observed that the stall margin has increased significantly. When the groove depth increased from 3 mm to 4 mm, no beneficial increase in the stall margin was observed.
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References
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