Sensitivity-Analysis-Guided Parameter Selection and Design Optimization for Non-Axisymmetric Endwall Contouring

FAN Zhuokun; GUO Zhendong; CAI Guohuang; GAO Jin; SONG Liming

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Sensitivity-Analysis-Guided Parameter Selection and Design Optimization for Non-Axisymmetric Endwall Contouring

更新时间：2026-10-08

- Sensitivity-Analysis-Guided Parameter Selection and Design Optimization for Non-Axisymmetric Endwall Contouring
- JOURNAL OF XI’AN JIAOTONG UNIVERSITY (2026)
- 作者机构：
  
  1.西安交通大学能源与动力工程学院，710049，西安
  2.东方汽轮机有限公司清洁高效透平动力装备全国重点实验室，618000，四川德阳
- 作者简介：
- 基金信息：
- DOI：
  CLC： TK471
- Received：01 August 2026，
  
  Revised：2026-09-15，
  
  Accepted：08 October 2026，
- 稿件说明：
移动端阅览
FAN Zhuokun, GUO Zhendong, CAI Guohuang, et al. Sensitivity-Analysis-Guided Parameter Selection and Design Optimization for Non-Axisymmetric Endwall Contouring[J/OL]. JOURNAL OF XI’AN JIAOTONG UNIVERSITY,2026-10-08. http://zkxb.xjtu.edu.cn/en/article/173272079/.
DOI：

FAN Zhuokun, GUO Zhendong, CAI Guohuang, et al. Sensitivity-Analysis-Guided Parameter Selection and Design Optimization for Non-Axisymmetric Endwall Contouring[J/OL]. JOURNAL OF XI’AN JIAOTONG UNIVERSITY,2026-10-08. http://zkxb.xjtu.edu.cn/en/article/173272079/. DOI：

摘要

为在不增加设计自由度的条件下提升非轴对称端壁造型参数对气动敏感区域的局部型面调控能力，提出了一种基于敏感性分析的非轴对称端壁造型参数选取与设计优化方法。以某型燃气轮机透平第一级为研究对象，首先采用基于SHAP(SHapley Additive exPlanations)的敏感性分析发现，叶栅出口附近端壁控制线对级总总效率和二次流影响十分显著；以之为基础，构建了控制点非均匀分布的端壁参数化模型，并开展非轴对称端壁气动设计优化。在采用相同寻优算法并保证总的性能评估次数相同的情况下，基于非均匀控制点和传统均匀控制点的端壁优化方案级总总效率相较原始设计分别提升0.094%和0.053%。进一步详细气动分析表明，基于敏感性分析所构建的控制点非均匀分布参数化模型可增强参数化方法对级气动性能敏感区域的调控；优化方案通过削弱通道中后部横向压力梯度，抑制了通道涡强度及其与边界层交互作用，进而使得级总总效率提升。

Abstract

To improve the local control capability of non-axisymmetric endwall contouring parameters in aerodynamically sensitive regions without increasing design degrees of freedom

a sensitivity analysis-based parameter selection and optimization method is proposed. A first-stage turbine of a gas turbine engine is investigated. SHAP (SHapley Additive exPlanations)-based sensitivity analysis identifies that the endwall control lines near the cascade exit have a significant impact on stage total-to-total efficiency and secondary flows. Based on this finding

a parameterization model with non-uniformly distributed control points is developed for aerodynamic optimization of the non-axisymmetric endwall contouring. With the same optimization algorithm and identical numbers of performance evaluations

the optimized designs using non-uniform and uniform control point distributions improve the stage total-to-total efficiency by 0.094% and 0.053%

respectively. Further analysis indicates that the proposed sensitivity-guided parameterization enhances the regulation capability in aerodynamically sensitive regions. The efficiency improvement is achieved by reducing the transverse pressure gradient in the downstream passage

weakening the passage vortex and its interaction with the boundary layer.

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references

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