Aerodynamic Performance of a Single-stage Transonic Axial Compressor using Recirculation-Bleeding Channels
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Abstract
This paper investigates the recirculation channel with an addition of bleeding channels located on shroud surface of recirculation channel in the rotor domain, where the bleeding system consists of 36 channels distributed on the recirculation channel. This study focuses on its effects on aerodynamic performance of a single-stage transonic axial compressor, NASA Stage 37. Validation of numerical results was performed using experimental data for a single-stage transonic axial compressor. A parametric study with only three position of the bleeding channels were performed in a single-stage transonic axial compressor, NASA Stage 37. The numerical results showed the aerodynamic performance of a single-stage transonic axial compressor was increased, such as total pressure ratio, adiabatic efficiency, stall margin as compared to the smooth casing.
Keywords
Single-stage transonic axial compressor, Recirculation-bleeding channels, Reynolds-averaged Navier-Stokes analysis, Total pressure ratio, Adiabatic efficiency, Stall margin
Article Details
References
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[2] Koff, S. G., Mazzawy, R. S., Nikkanen, J. P., and Nolcheff, N. A., 1994, Case Treatment for Compressor Blades, U.S. Patent (5,282,718).
[3] Hobbs, D. E., 1995, Active Vaneed Passage Casing Treatment, U.S. Patent (5,431,533).
[4] Nolcheff, N. A., 1996, Flow Aligned Plenum Endwall Treatment for Compressor Blades, U.S. Patent (5,586,859).
[5] Hathaway, M. D., 2002, Self-Recirculating Casing Treatment Concept for Enhanced Compressor Performance, In Proceedings of ASME Turbo Expo 2002, Amsterdam, Netherlands, GT-2002-30368.
[6] Strasizar, A. J., Bright, M. M., Thorp, S., Culley, D. E., and Suder K. L., 2004, Compressor Stall Control Through Endwall Recirculation, In Proceeding of ASME Turbo Expo 2004, Vienna, Austria, GT2004-54295.
[7] Dinh, C. T., Ma, S. B., and Kim, K. Y., 2017, Effects of a Circumferential Feed-Back Channel on Aerodynamic Performance of a Single-Stage Transonic Axial Compressor, In Proceedings of ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT2017-63536.
[8] Reid, L., and Moore, R. D., 1987, Design and Overall Performance of Four Highly Loaded, High-Speed Inlet Stages for an Advanced High-Pressure Ratio Core Compressor, NASA Technical Paper 1337, Lewis Research Center, Cleveland, Ohio 44135.
[9] ANSYS CFX-19.1, 2018, ANSYS Inc.