离心压气机进口径向总压畸变不确定性分析  

Uncertainty Quantification of a Centrifugal Compressor Considering Uncertain Inlet Total Pressure Distortion

作　　者：徐永祥 琚亚平[1] 秦瑞鸿 李震[1] 刘艳 张楚华[1] XU Yongxiang;JU Yaping;QIN Ruihong;LI Zhen;LIU Yan;ZHANG Chuhua(School of Energy and Power Engineering,Xi’an Jiaotong University,Xi’an 710049,China;School of Aero-Engine,Shenyang Aerospace University,Shenyang 110136,China;School of Energy and Power Engineering,Dalian University of Technology,Dalian,Liaoning 116024,China)

机构地区：[1]西安交通大学能源与动力工程学院,西安710049 [2]沈阳航空航天大学航空发动机学院,沈阳110136 [3]大连理工大学能源与动力学院,辽宁大连116024

出　　处：《西安交通大学学报》2024年第8期69-79,共11页Journal of Xi'an Jiaotong University

基　　金：国家自然科学基金资助项目(52376030)。

摘　　要：针对离心压气机实际运行过程中的进口畸变不确定性问题,提出了一种离心压气机进口径向总压畸变不确定性参数化表征模型。以跨声速Radiver离心压气机为研究对象,采用非嵌入式多项式混沌法和Sobol敏感性分析方法,研究了压气机气动性能受叶尖畸变、轮毂畸变两类进口径向总压畸变不确定性的影响,获得了对压气机气动性能影响最为显著的不确定性因素,并分析了不确定性因素影响压气机气动性能的相关流动机理。结果表明:相比于均匀来流,叶尖畸变、轮毂畸变均使压气机级多变效率下降近1.0%;轮毂畸变、叶尖畸变分别对级总压比、扩压器总压损失系数带来的影响较为显著,级多变效率受轮毂畸变影响下降1.4%,叶尖畸变使损失系数增大11.0%;相较于轮毂侧和叶尖侧畸变峰之间的相对位置,压气机气动性能对畸变峰的数值大小更敏感;受进口径向总压畸变影响下的压气机的性能恶化与扩压器叶片进口冲角不均匀分布导致的流动分离现象密切相关。研究工作表明了进口畸变不确定性在离心压气机不确定性分析中的重要性,对未来发展离心压气机鲁棒优化设计具有一定的学术意义和工程应用价值。As for the effect of uncertain upstream distortion on the aerodynamic performance of in-service centrifugal compressors,this paper proposes a parametrization model of uncertain inlet radial total pressure distortion in the centrifugal compressor.Based on this model,the study adopts non-intrusive polynomial chaos and Sobol sensitivity analysis methods to perform the uncertainty quantification of Radiver,a transonic centrifugal compressor.The influence of two types of inlet total pressure distortion,i.e.,tip distortion and hub distortion uncertainties on the aerodynamic performance of the compressor is investigated,the most influential uncertain factor is obtained,and the flow mechanism under influence of uncertainties on the aerodynamic performance is analyzed.The results show that,compared with the uniform inflow,the considered two types of inlet total pressure distortion decrease the stage polytropic efficiency by nearly 1.0%,and the hub distortion and tip distortion have a significant impact on the stage total pressure ratio and the diffuser total pressure loss coefficient,respectively.The stage polytropic efficiency declines by 1.4% due to hub distortion and the loss coefficient increases by 11.0% due to tip distortion.The aerodynamic performance of the compressor is more sensitive to the magnitude of distortion peaks than to the relative position between distortion peaks in two sides(hub side and tip side).The performance degradation of the compressor induced by the two types of distortion is closely related to the flow separation caused by the non-uniform incidence distribution at the leading edge of the diffuser vane.The study highlights the importance of inlet distortion uncertainty in the uncertainty analysis of centrifugal compressors,and is of important academic and engineering application significance to the future robust optimization design of centrifugal compressors.

关 键 词：离心压气机 进口畸变 不确定性 敏感性分析 流动机理 

分 类 号：TK14[动力工程及工程热物理—热能工程]