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

XU Yongxiang; JU Yaping; QIN Ruihong; LI Zhen; LIU Yan; ZHANG Chuhua

doi:10.7652/xjtuxb202408008

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

更新时间：2025-07-28

- Uncertainty Quantification of a Centrifugal Compressor Considering Uncertain Inlet Total Pressure Distortion
- Vol. 58, Issue 8, Pages: 69-79(2024)
- 作者机构：
  
  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
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202408008
  CLC： TK14
- Online First：10 August 2024，
  
  Published：2024
- 稿件说明：
移动端阅览
XU Yongxiang, JU Yaping, QIN Ruihong, et al. Uncertainty Quantification of a Centrifugal Compressor Considering Uncertain Inlet Total Pressure Distortion[J]. 2024, 58(8): 69-79.
DOI：

XU Yongxiang, JU Yaping, QIN Ruihong, et al. Uncertainty Quantification of a Centrifugal Compressor Considering Uncertain Inlet Total Pressure Distortion[J]. 2024, 58(8): 69-79. DOI： 10.7652/xjtuxb202408008.

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。

Abstract

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.

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references

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