Accurate prediction of flow field is the most important factor during the design of high performance compressors. In some cases the agreement of pressure ratio and efficiency between predicted and measured is excellent, but it is common for the efficiency to be in error by perhaps one or two percent. This error is enough to render the calculation unable to replace expensive experiment testing. One of the important matters in need of more study is the mechanism of boundary layer transition from laminar to turbulent flow. The objective of this fundamental research work is to acquire the detailed structure of separation bubbles on the suction side of the blade by using the PIV and pressure taps. This paper presents an experimental study of the influence of 2d leading-edge geometry on behavior of separation bubbles. The measurements on a nose of enlarged blade were conducted on a special large-scale experimental facility, the pressure distribution and flowfield of flow were measured. The test model used in this study consists of circular leading edge and elliptic leading edge. Results are presented for a range of incidence. The measurement result indicated that the leading edge shape has a large influence on flow details separation and transition as well as the boundary layer properties after reattached point. The wedge angle appears to be an important role in leading edge geometry parameters.
Effect of Leading-Edge Geometry on Separation Bubble on a Compressor Blade
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Liu, H, Liu, B, Li, L, & Jiang, H. "Effect of Leading-Edge Geometry on Separation Bubble on a Compressor Blade." Proceedings of the ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference. Volume 6: Turbo Expo 2003, Parts A and B. Atlanta, Georgia, USA. June 16–19, 2003. pp. 387-395. ASME. https://doi.org/10.1115/GT2003-38217
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