Effect of Recirculation Channel on Aerodynamic Performance of a Single-Stage Transonic Axial Compressor
Main Article Content
Abstract
This paper investigates the effects of recirculation channel on the performance of a single-stage transonic axial compressor, NASA Stage 37, such as pressure ratio, adiabatic efficiency, and operating range. Numerical analysis was conducted by solving three-dimensional steady Reynolds-averaged Navier-Stokes equations with the k-epsilon turbulence model. The recirculation channel bled the high-pressure flow from the stator shroud domain and injected it into the rotor tip clearance domain to increase the aerodynamic performance. The locations and widths of the injection and bleed ports were selected as parameters for the study to find the optimum recirculation channel design. The results indicated that, in general, the stall margin and operating range were significantly extended by from 0.45% to 2.38%, and from 3.72% to 12.7%, respectively, as compared to the performance of the smooth case without recirculation channel.
Keywords
Single-stage transonic axial compressor, recirculation channel, reynolds-averaged navier-stokes analysis, total pressure ratio, adiabatic efficiency, stall margin, stable range extension
Article Details
References
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[9] Dinh, C. T., Ma, S. B., and Kim, K. Y., Aerodynamic Optimization of a Single-Stage Axial Compressor with Stator Shroud Air Injection, AIAA Journal 2017, Vol. 55, No. 8, pp 2739–2754.
[2] Wu, Y., Chu, W., Zhang, H., and Li, Q., 2010, Parametric Investigation of Circumferential Grooves on Compressor Rotor Performance, Journal of Fluids Engineering, Vol. 132, 121103.
[3] Kim, J. H., Choi, K. J., and Kim, K. Y., 2013, Aerodynamic analysis and optimization of a transonic axial compressor with casing grooves to improve operating stability, Aerospace Science and Technology, Vol. 29(1), pp 81–91.
[4] Kim, D. W., Kim, J. H., and Kim, K. Y., 2013, Aerodynamic Performance of an Axial Compressor with a Casing Groove Combined with Injection, Transactions of the Canadian Society for Mechanical Engineering, Vol. 37, No. 3, pp 283–292.
[5] Kim, J. H., Kim, D. W., and Kim, K. Y., 2013, Aerodynamic Optimization of a Transonic Axial Compressor with a Casing Groove combined with Tip Injection, Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, Vol. 227(8), pp 869–884.
[6] Weichert, S., Day, I., and Freeman, C., 2011, Self-Regulating Casing Treatment for Axial Compressor Stability Enhancement, Proceedings of ASME Turbo Expo 2011, GT2011-46042.
[7] Strasizar, A. J., Bright, M. M., Thorp, S., Culley, D. E., and Suder, K. L., 2004, Compressor Stall Control Through Endwall Recirculation, Proceedings of ASME Turbo Expo 2004, GT2004-54295.
[8] Hathaway, M. D., 2002, Self-Recirculating Casing Treatment Concept for Enhanced Compressor Performance, Proceedings of ASME Turbo Expo 2002, GT2002-30368.
[9] Dinh, C. T., Ma, S. B., and Kim, K. Y., Aerodynamic Optimization of a Single-Stage Axial Compressor with Stator Shroud Air Injection, AIAA Journal 2017, Vol. 55, No. 8, pp 2739–2754.