Exploration of the Design Space for Non-Axisymmetric Endwall/Blade ThroughIntegration of Multi-Source Data Mining Techniques

GUO Zhendong; WANG Jie; CHEN Yun; JIANG Shoumin; SONG Liming; LI Jun

doi:10.7652/xjtuxb202401003

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Exploration of the Design Space for Non-Axisymmetric Endwall/Blade ThroughIntegration of Multi-Source Data Mining Techniques

更新时间：2025-05-13

- Exploration of the Design Space for Non-Axisymmetric Endwall/Blade ThroughIntegration of Multi-Source Data Mining Techniques
- Vol. 58, Issue 1, Pages: 30-41(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. 中国航发沈阳发动机研究所,沈阳,110015
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202401003
  CLC： TK421.4
- Online First：10 January 2024，
  
  Published：2024
- 稿件说明：
移动端阅览
GUO Zhendong, WANG Jie, CHEN Yun, et al. Exploration of the Design Space for Non-Axisymmetric Endwall/Blade ThroughIntegration of Multi-Source Data Mining Techniques[J]. 2024, 58(1): 30-41.
DOI：

GUO Zhendong, WANG Jie, CHEN Yun, et al. Exploration of the Design Space for Non-Axisymmetric Endwall/Blade ThroughIntegration of Multi-Source Data Mining Techniques[J]. 2024, 58(1): 30-41. DOI： 10.7652/xjtuxb202401003.

摘要

为厘清联合成型设计空间各造型方法对涡轮叶栅性能提升的贡献

将基于总变差分析的全局敏感性分析方法与平行坐标系及直方图、散点图等可视化技术相结合

提出了将多源数据挖掘信息进行融合的设计空间知识挖掘框架

并利用该框架对某小展弦比叶栅端壁/叶身联合成型设计空间进行知识挖掘。结果表明:叶栅气动损失增减对基元型线微调十分敏感; 非轴对称端壁所带来的损失减少量与型线微调接近

但设计空间内不同非轴对称端壁样本性能波动较小

导致其重要性被全局敏感性分析方法低估; 虽然单独采用弯叶片难以整体降低小展弦比叶栅损失

但将弯、型线微调和非轴对称端壁造型相结合可获得“1+1+1>3”的性能增益; 在端壁/叶身联合成型设计空间内

将基元型线朝着后加载方向微调

并采用喉部附近下凹较深的非轴对称端壁造型及反弯叶片设计

可获得气动损失较小的叶栅设计。研究结果明晰了端壁/叶身联合成型设计空间优化解特征

可为类似小展弦比叶栅设计优化提供借鉴。

Abstract

To enhance understanding of the role different cascade profiling techniques play in improving turbine cascade performance within the combined design space

a knowledge mining framework is proposed. This framework integrates data mining information through the analysis of variance-based global sensitivity analysis method and employs visualization techniques like parallel axis

histogram and scatterplot. By using this framework

knowledge mining of the non-axisymmetric endwall/blade combined parameterization design space of a low aspect ratio cascade is conducted. It reveals that the aerodynamic loss of the cascade is highly influenced by the section profiling. The reduction in loss achieved through the implementation of a non-axisymmetric endwall is comparable to that of section profiling. However

it is observed that the performance variations among different samples of non-axisymmetric endwall are relatively small

leading to the underestimation of its significance by the global sensitivity analysis method. Furthermore

it is found that utilizing only a bending curved blade is unlikely to yield a reduction in cascade loss. However

by combining blade bending

section profiling and non-axisymmetric endwall

it is possible to achieve a performance gain that exceeds the sum of the individual contributions(“1+1+1>3”). Within the combined design space of non-axisymmetric endwall/blade parameterization

it is observed that a cascade with low aerodynamic loss can be achieved by adjusting the section profile towards an after-loading style and incorporating a non-axisymmetric endwall with deep concave near the throat and negatively bending blade as well. In conclusion

this research has successfully elucidated the characteristics of optimized solutions within the end-wall/blade joint forming design

offering reference for the design optimization of similar low aspect ratio cascades. The above findings have effectively clarified the characteristics of the optimized solutions within the endwall/blade combined design space

offering guidance for the design optimization of similar low aspect ratio cascades.

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references

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