Research on Uncertainty Quantification of the Effect of Film Cooling Hole Defects on Cooling Performance

HAO Mingyang; LI Zhigang; LI Jun

doi:10.7652/xjtuxb202605012

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Research on Uncertainty Quantification of the Effect of Film Cooling Hole Defects on Cooling Performance

更新时间：2026-04-27

- Research on Uncertainty Quantification of the Effect of Film Cooling Hole Defects on Cooling Performance
- Journal of Xi'an Jiaotong University Vol. 60, Issue 5, Pages: 120-130(2026)
- 作者机构：
  
  西安交通大学叶轮机械研究所，710049，西安
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202605012
  CLC： V231.1
- Received：26 June 2025，
  
  Published：10 May 2026
- 稿件说明：
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HAO Mingyang, LI Zhigang, LI Jun. Research on Uncertainty Quantification of the Effect of Film Cooling Hole Defects on Cooling Performance[J]. Journal of Xi'an Jiaotong University, 2026, 60(5): 120-130.
DOI：

HAO Mingyang, LI Zhigang, LI Jun. Research on Uncertainty Quantification of the Effect of Film Cooling Hole Defects on Cooling Performance[J]. Journal of Xi'an Jiaotong University, 2026, 60(5): 120-130. DOI： 10.7652/xjtuxb202605012.

摘要

针对高压涡轮全气膜冷却叶片因气膜孔加工几何偏差（气膜孔几何缺陷）所导致的实际冷却性能难以量化评估的问题，提出了整体参数评估、流动参数降维、流动分区量化的三重不确定性量化策略，以实现其高效精准量化。以锥型气膜孔参数化模型为气膜孔模型，三重不确定性量化策略为不确定性表征方法，混沌多项式展开为量化算法，构建了气膜孔几何缺陷下冷却性能不确定性量化框架。以近实际运行工况的第一级进口导叶端壁为研究对象，详细阐述了所提不确定性量化策略的逐层修正的量化思想以及数理依据，并通过冷却性能统计矩表明其差异性及适用性。研究结果表明：当气膜孔几何偏差影响显著时，采取多气膜孔及独立加工的设计理念以充分利用气膜孔偏差分散性，冷却性能鲁棒性可提高30%以上。对比结果表明：在冷气射流主导工况下，流动参数降维策略不确定性预测偏差在3%以下。通过统计矩演化趋势论证了在二次流主导工况下，基于涡系/二次流的流动分区量化可实现可靠的不确定性量化。该研究结果验证了所提不确定性量化策略的准确性和可靠性，可为发展高鲁棒性的涡轮叶栅冷却布局提供高效的评估工具。

Abstract

To address the difficulty in quantitatively evaluating the actual cooling performance of high-pressure turbine full-coverage film-cooling vanes caused by geometric deviations (i.e.

film hole geometric imperfections) during film hole processing

a triple uncertainty quantification strategy

integrating overall parameter evaluation

flow parameter dimensionality reduction

and flow partitioning quantification

was proposed to achieve efficient and accurate assessment. A framework for uncertainty quantification of cooling performance under film hole geometric imperfections was established

employing a parameterized conical nozzle film hole imperfection model as the film hole model

the triple uncertainty quantification strategy as the uncertainty characterization approach

and polynomial chaos expansion as the quantification algorithm. Taking the endwall of the first-stage inlet guide vane under near-actual operating conditions as the research subj ect

the progressive refinement philosophy and theoretical basis of the proposed uncertainty quantification strategy were elaborated

and the differences and applicability were demonstrated through statistical moments of cooling performance. The results indicate that when the impact of film cooling hole geometric deviations is significant

adopting a design philosophy of multiple film cooling holes and independent processing to leverage the dispersion of hole deviations can improve the robustness of cooling performance by more than 30%. Comparative results show that under conditions dominated by coolant jet flow

the uncertainty prediction deviation of the flow parameter dimensionality reduction strategy is below 3%. The evolution trends of statistical moments demonstrate that under conditions dominated by secondary flows

flow partitioning quantification based on vortex/secondary flow structures can achieve reliable uncertainty quantification. The findings validate the accuracy and reliability of the proposed uncertainty quantification strategy

providing an efficient evaluation tool for developing highly robust cooling configurations in turbine cascades.

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references

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