Effects of Non-Axisymmetric Profiled End Wall Treatments on Performance of a Centrifugal Compressor

doi:10.13675/j.cnki.tjjs.190441

Journal of Propulsion Technology ›› 2020, Vol. 41 ›› Issue (6): 1286-1295.DOI: 10.13675/j.cnki.tjjs.190441

• Aero-thermodynamics • Previous Articles Next Articles

Effects of Non-Axisymmetric Profiled End Wall Treatments on Performance of a Centrifugal Compressor

1.School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China;2.Collaborative Innovation Center of Advanced Aero-Engine,Beijing 100191,China

Published:2021-08-15

非对称端壁造型对离心压气机性能的影响

郎进花¹，楚武利^1,2，张皓光¹，安光耀¹，马姗¹

1.西北工业大学动力与能源学院，陕西西安 710072;2.先进航空发动机协同创新中心，北京 100191

作者简介:郎进花，博士生，研究领域为叶轮机械气动热力学。E-mail：langjinhua1988@outlook.com
基金资助:
国家自然科学基金（51576162）；国家科技重大专项（2017-II-0005-0018）。

Abstract

Abstract: The application of non-axisymmetric endwall profiling on both axial compressors or turbines has been determined to be an effective way to increase the efficiency. In order to investigate the effects of non-axisymmetric end wall profiling on the performance of centrifugal compressors, four endwall contouring schemes according to the design experience of non-axisymmetric endwall profiling in axial compressors were performed on a vaned diffuser centrifugal compressor with the help of Autoblade and CFX software. Numerical investigations were conducted on a radial compressor with vane diffuser. The results showed that non-axisymmetric profiled endwall PEW1_10% which was convex near the pressure side and concave near the suction side extended the compressor characteristic performance curve to smaller and higher mass flow rate points which gave a 11.8% improvement of the operating range with no reduction of the efficiency compared with the original compressor. Analysis of the flow field showed that PEW1_10% caused a redistribution of the flux in the diffuser passage at the near surge condition, which further led to an increase of the radial velocity near the suction side and a decrease of the low-energy fluid. As a result, the flow condition in the diffuser passage was improved, and the surge was delayed.

Key words: Centrifugal compressor;Non-axisymmetric profiled end wall;Vaned diffuser;Reverse flow region;Working range enhancement

摘要： 非对称端壁造型应用在轴流压气机和涡轮中具有较好的提高效率的作用。为了探究非对称端壁造型对离心压气机性能的影响，借鉴非对称端壁造型在轴流压气机中的设计经验，借助Autoblade和CFX商用软件，设计了四种非对称端壁造型结构，并对带叶片式扩压器的离心压气机展开数值计算研究。研究发现，与原型压气机相比，采用压力面附近为凸曲率形状、吸力面附近为凹曲率形状的非对称端壁造型结构PEW1_10%（profiled end wall 1_10%）可以在保证全工况效率不降低的情况下，使离心压气机的性能曲线向小流量和大流量均有拓展，稳定工作范围扩大11.8%。通过分析流场发现，在近喘振工况，非对称端壁造型PEW1_10%使扩压器通道内流量重新分配，吸力面附近径向速度增大，低能流体减少，改善了扩压器通道的流动状况，进而推迟喘振的发生。

关键词: 离心压气机;非对称端壁造型;叶片式扩压器;回流区;扩稳

LANG Jin-hua¹, CHU Wu-li^1,2, ZHANG Hao-guang¹, AN Guang-yao¹, MA Shan¹. Effects of Non-Axisymmetric Profiled End Wall Treatments on Performance of a Centrifugal Compressor[J]. Journal of Propulsion Technology, 2020, 41(6): 1286-1295.

郎进花，楚武利，张皓光，安光耀，马姗. 非对称端壁造型对离心压气机性能的影响[J]. 推进技术, 2020, 41(6): 1286-1295.

References

[1] 金磊. 涡轮增压离心压气机非对称有叶扩压器扩稳机理研究[D]. 北京：清华大学， 2014.
[2] Imamura H, Kurokawa J， Matsui J， et al. Passive Control of Rotating Stall in a Parallel Wall Vaned Diffuser by J-Grooves[J]. Journal of Turbomachinery， 2001， 123(3): 507-515.
[3] Jansen J， Carter A F， Swarden M C. Improvements in Surge Margin for Centrifugal Compressors[C]. USA: AGARD Conference Proceeding， 1980.
[4] Pampreen R C， Compressor Surge and Stall[M]. Norwich: Concepts Eti， Inc.， 1993.
[5] Zheng X， Liu A. Phenomenon and Mechanism of Two-Regime-Surge in a Centrifugal Compressor[J]. Journal of Turbomachinery， 2015， 137(8).
[6] Skoch G J. Experimental Investigation of Diffuser Hub Injection to Improve Centrifugal Compressor Stability[J]. Journal of Turbomachinery， 2005， 127(1): 107-117.
[7] Marsan A， Trébinjac I， Coste S， et al. Influence of Unsteadiness on the Control of a Hub-Corner Separation Within a Radial Vaned Diffuser[R]. ASME GT 2014-26985.
[8] 席光，周莉，丁海萍，等. 叶片扩压器进口安装角对离心压缩机性能影响的数值与实验研究[J]. 工程热物理学报， 2006， 27(1): 61-64.
[9] Spakovszky Z S， Roduner C H. Spike and Modal Stall Inception in an Advanced Turbocharger Centrifugal Compressor[J]. Journal of Turbomachinery， 2009， 131(3).
[10] Everitt J N， Spakovszky Z S. An Investigation of Stall Inception in Centrifugal Compressor Vaned Diffuser[J]. Journal of Turbomachinery， 2013， 135(1): 1737-1749.
[11] 赵家毅，王志恒，李学臣，等. 叶片扩压器小流量工况内部流动特性研究[J]. 工程热物理学报， 2017， 38(6): 52-58.
[12] Galloway L， Rusch D， Spence S W T， et al. An Investigation of Centrifugal Compressor Stability Enhancement Using a Novel Vaned Diffuser Recirculation Technique[J]. Journal of Turbomachinery， 2018， 140(12): 1-12.
[13] Rose M G. Non-Axisymmetric End Wall Profiling in the HPNGVs of an Axial Flow Gas Turbine[R]. ASME 94-GT-249.
[14] Hoeger M， Cardamone P， Fottner L. Influence of Endwall Contouring on the Transonic Flow in a Compressor Blade[R]. ASME GT 2002-30440.
[15] Harvey N W. Some Effects of Non-Axisymmetric End Wall Profiling on Axial Flow Compressor Aerodynamics， Part I： Linear Cascade Investigation[R]. ASME GT 2008-50990.
[16] Hergt A， Meyer R， Liesner K， et al. A New Approach for Compressor Endwall Contouring[R]. ASME GT 2011-45858.
[17] Reutter O， Hemmert-Pottmann S， Hergt A， et al. Endwall Contouring and Fillet Design for Reducing Losses and Homogenizing the Outflow of a Compressor Cascade[R]. ASME GT 2014-25277.
[18] Hergt A， Meyer R， Engel K. Effects of Vortex Generator Application on the Performance of a Compressor Cascade[J]. Journal of Turbomachinery， 2013， 135(2).
[19] 刘波，管继伟，陈云永，等. 用端壁造型减小涡轮叶栅二次流损失的数值研究［J］. 推进技术， 2008， 29（3）: 355-359.
[20] 那振喆，刘波，赵刚剑，等. 基于Bezier曲线的端壁造型设计方法研究[J]. 推进技术， 2014， 35(5): 624-631.
[21] Chu W， Li X， Wu Y， et al. Reduction of End Wall Loss in Axial Compressor by Using Non-Axisymmetric Profiled End Wall: A New Design Approach Based on End Wall Velocity Modification[J]. Aerospace Science and Technology， 2016， 55: 76-91.
[22] Li X， Chu W， Wu Y. Numerical Investigation of Inlet Boundary Layer Skew in Axial-Flow Compressor Cascade and the Corresponding Non-Axisymmetric End Wall Profiling[J]. Journal of Power Energy， 2014， 228(6): 638-656.
[23] Li X， Chu W， Wu Y， et al. Effective End Wall Profiling Rules for a Highly Loaded Compressor Cascade[J]. Journal of Power Energy， 2016， 230(6).
[24] Ziegler K U， Gallus H E, Niehuis R, et al. A Study on Impeller-Diffuser Interaction, Part I: Influence on the Performance[J]. Journal of Turbomachinery， 2003， 125(1).
[25] Ziegler K U， Gallus H E， Niehuis R. A Study on Impeller-Diffuser Interaction, Part II: Detailed Flow Analysis[J]. Journal of Turbomachinery， 2003， 125(1).
[26] Bourgeois J A， Martinuzzi R J， Savory E， et al. Assessment of Turbulence Model Predictions for an Aero-Engine Centrifugal Compressor[J]. Journal of Turbomachinery， 2011， 133(1).
[27] Benichou E， Trébinjac I. Numerical Analysis of an Alternate Stall in a Radial Vaned Diffuser[R]. ASME GT 2016-56485.
[28] Sivagnanasundaram S， Spence S， Early J. Map Width Enhancement Technique for a Turbocharger Compressor[J]. Journal of Turbomachinery， 2014， 136(6).
[29] Gibson L， Galloway L， Kim S I， et al. Assessment of Turbulence Model Predictions for a Centrifugal Assessment of Turbulence Model Predictions for a Centrifugal Compressor Simulation[J]. Journal of Global Power and Propulsion Society， 2017， 1: 142-156.
[30] 田兴江，常海萍，张镜洋，等. 基于参数化脊线的非轴对称端壁成型方法[J]. 推进技术， 2017， 38(6): 100-107.
[31] Dorfner C ， Hergt A ， Nicke E ， et al. Advanced Non-Axisymmetric Endwall Contouring for Axial Compressors by Generating an Aerodynamic Separator， Part I ：Principal Cascade Design and Compressor Application[J]. Journal of Turbomachinery， 2009， 133(2): 113-120.
[32] Li X， Spence S， Wu Y. The Interaction Between Inlet Guide Vanes and the Impeller Recirculating Flow in a Centrifugal Compressor and the Resulting Impact on Flow Range[R]. ASME GT 2018-75097.
[33] 郎进花，楚武利，安光耀，等. 跨声速轴流压气机的失速发展机理[J]. 航空动力学报， 2018， 33(8):1964-1973.
[34] Choi M， Vahdati M， Imregun M. Effects of Fan Speed on Rotating Stall Inception and Recovery[J]. Journal of Turbomachinery， 2011， 133(4): 1396-1402.

Effects of Non-Axisymmetric Profiled End Wall Treatments on Performance of a Centrifugal Compressor

非对称端壁造型对离心压气机性能的影响

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