Effect of the Return-channel Geometric Parameters on the Performance of a Centrifugal Compressor with a High-flow Coefficient

Document Type : Regular Article

Authors

1 School of Energy and Power Engineering, Dalian University of Technology, Dalian, Liaoning, 116024, China

2 Shenyang Blower Group Co., Ltd, Shenyang, Liaoning, 110869, China

Abstract

The return-channel of a preceding stage in a multi-stage centrifugal compressor has a significant effect on the aerodynamic performance of the current and subsequent stages. However, due to the relatively complex nature of the return-channel configuration with many geometric parameters, no general design guidance is available in the literature. In this study, numerical methods are used to study the effects of different geometric parameters of a return-channel on the performance of a high-flow-coefficient centrifugal compressor. A multi-objective genetic algorithm is applied to optimize the return-channel. The effects of different geometric parameters on the performance are then studied using a sensitivity analysis method. Calculation results show that the residual vortex intensity at the outlet of the return-channel is affected by the geometric angles of the inlet and outlet of the return-channel blades. The flow uniformity at the stage outlet is primarily affected by the geometric angle of the blade outlet and the number of blades. The overall performance of the compressor stage is primarily affected by the geometric angle of the blade inlet and the lateral inclination angle of the cover plate. Calculation results for a two-stage compressor consisting of the optimized first stage and its following stage show that the outlet flow field of the first stage is more uniform than the original first stage. Additionally, at the design operating condition, the polytropic efficiency and pressure ratio of the entire unit increase by 1.07% and 4.07%, respectively. The polytropic efficiency and pressure ratio for the second stage increase by 2.34% and 3.51%, respectively. The impeller head coefficient increases by 7.33%. The theoretical analysis shows that for high-flow-coefficient centrifugal compressors, reducing the residual vortex intensity of the outlet flow field of the return-channel in a stage can significantly improve the off-design performance of the following stage.

Keywords

Main Subjects

References

Aalburg, C., Sezal, I., Haigermoser, C., Simpson, A., Michelassi, V., & Sassanelli, G. (2011). Annular cascade for radial compressor development. Turbo Expo: Power for Land, Sea, and Air. https://doi.org/10.1115/GT2011-46834
Franz, H., Rube, C., Wedeking, M., & Jeschke, P. (2015). Numerical investigation of the return channel of a high-flow centrifugal compressor stage. Turbo Expo: Power for Land, Sea, and Air. https://doi.org/10.1115/GT2015-43640
Harada, H. (1988). Experimental study on the stage performance of a multistage centrifugal compressor. Nippon Kikai Gakkai Ronbunshu, B Hen;(Japan), 54(498). https://www.osti.gov/etdeweb/biblio/7030222
Harvey, S. (2019). Balancing the economies of scale. Hydrocarbon Engineering, (7), 24. https://www.nstl.gov.cn/paper_detail.html?id=67d27a8a4e3134d47bd350617d0f8c1e
Hildebrandt, A. (2011). Aerodynamic optimisation of a centrifugal compressor return channel and U-turn with genetic algorithms. Turbo Expo: Power for Land, Sea, and Air. https://doi.org/10.1115/GT2011-45076
Hildebrandt, A., & Schilling, F. (2016). Numerical and experimental investigation of return channel vane aerodynamics with 2D and 3D vanes. Turbo Expo: Power for Land, Sea, and Air. https://doi.org/10.1115/GT2016-57713
Jariwala, V., Larosiliere, L., & Hardin, J. (2016). Design exploration of a return channel for multistage centrifugal compressors. Turbo Expo: Power for Land, Sea, and Air, https://doi.org/10.1115/GT2016-57777
Lenke, L., & Simon, H. (1999). Numerical investigations on the optimum design of return channels of multi-stage centrifugal compressors. Turbo Expo: Power for Land, Sea, and Air. https://doi.org/10.1115/99-GT-103
Li, S., Liu, Y., Li, H., & Omidi, M. (2021). Numerical study of the improvement in stability and performance by use of a partial vaned diffuser for a centrifugal compressor stage. Applied Sciences, 11(15), 6980. https://doi.org/10.3390/app11156980
Nakane, I., Ariga, I., Hayata, T., & Uchida, M. (1987). Experimental Investigation on return passage of multi-stage compressor. JSME-B, 54(503), 1677-1684. https://doi.org/10.1299/kikaib.54.1677
Nishida, Y., Kobayashi, H., Nishida, H., & Sugimura, K. (2013). Performance improvement of a return channel in a multistage centrifugal compressor using multiobjective optimization. Journal of Turbomachinery, 135(3), 031026. https://doi.org/10.1115/1.4007518
Pazzi, S., Martelli, F., Michelassi, V., & Giachi, M. (2002). The use of artificial neural networks for performance prediction of return channels for industrial centrifugal compressors. Turbo Expo: Power for Land, Sea, and Air. https://doi.org/10.1115/GT2002-30392
Reddy, K. S., GV, R. M., & Dasgupta, A. (2010). Flow investigations in the crossover system of a centrifugal compressor stage. International Journal of Fluid Machinery and Systems, 3(1), 11-19. https://doi.org/10.5293/IJFMS.2010.3.1.011
Safari, M., Anbarsooz, M., & Niazmand, H. (2023). The effects of the return channel geometry on the aerodynamic performance of a centrifugal compressor: A numerical study. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 09576509231157229. https://doi.org/10.1177/0957650923115722
Simpson, A., Aalburg, C., Schmitz, M., Pannekeet, R., Larisch, F., & Michelassi, V. (2008). Design, validation and application of a radial cascade for centrifugal compressors. Turbo Expo: Power for Land, Sea, and Air. https://doi.org/10.1115/GT2008-51262
Sorokes, J. M. (2013). Range versus Efficiency-striking the proper balance. Proceedings of the 42nd Turbomachinery Symposium, https://doi.org/10.21423/R1BP89
Veress, A. R. d., & Van den Braembussche, R. (2004). Inverse design and optimization of a return channel for a multistage centrifugal compressor. Journal of Fluids Engineering, 126(5), 799-806. https://doi.org/10.1115/1.1792258
Weber, A., Morsbach, C., Kügeler, E., Rube, C., & Wedeking, M. (2016). Flow analysis of a high flowrate centrifugal compressor stage and comparison with test rig data. Turbo Expo: Power for Land, Sea, and Air. https://doi.org/10.1115/GT2016-56551
Wen, S., Hu, X., Zhang, Y., Wang, J., & Li, T. (2008). Optimal r/b ratio of bend channel in centrifugal compressor. Frontiers of Energy and Power Engineering in China, 2, 381-385. https://doi.org/10.1007/s11708-008-0084-4
Xi, G., Tian, Y., Guo, Y., Tang, Y., & Wang, Z. (2019). Experimental and numerical investigations on flow losses of a U-Bend and return channel system for centrifugal compressor. Turbo Expo: Power for Land, Sea, and Air. https://doi.org/10.1115/GT2019-90559
Xu, H., Yang, X. I., Jariwala, V., & Larosiliere, L. (2021). Comparative aerodynamic assessment of a multistage centrifugal compressor return channel based on rans and les. AIAA Scitech 2021 Forum. https://doi.org/10.2514/6.2021-0263
Zhao, P. F., Liu, Y., & Wang, X. F. (2017). Analysis of vortices and performance of different diffusers in a large mass flow coefficient centrifugal compressor. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 231(4), 253-273. https://doi.org/10.1177/09576509177013

Files

History

  • Received: 04 August 2023
  • Revised: 12 October 2023
  • Accepted: 29 October 2023
  • Available online: 01 January 2024

Share

How to cite

Statistics