Optimization of Full-Endwall Non-Axisymmetric Contouring Design for Turbine Cascades Aimed at Enhancing Film Cooling Effectiveness

TAO Zhi; WANG Jie; LI Bolin; YAN Yifei; SONG Liming; LI Jun

doi:10.7652/xjtuxb202508007

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Optimization of Full-Endwall Non-Axisymmetric Contouring Design for Turbine Cascades Aimed at Enhancing Film Cooling Effectiveness

更新时间：2025-07-30

- Optimization of Full-Endwall Non-Axisymmetric Contouring Design for Turbine Cascades Aimed at Enhancing Film Cooling Effectiveness
- Journal of Xi’an Jiaotong University Vol. 59, Issue 8, Pages: 64-74(2025)
- 作者机构：
  
  1.西安交通大学能源与动力工程学院， 710049，西安
  2.太行实验室， 610299，成都
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202508007
  CLC： TK47
- Received：15 February 2025，
  
  Online First：07 May 2025，
  
  Published：10 August 2025
- 稿件说明：
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TAO Zhi, WANG Jie, LI Bolin, et al. Optimization of Full-Endwall Non-Axisymmetric Contouring Design for Turbine Cascades Aimed at Enhancing Film Cooling Effectiveness[J]. Journal of Xi’an Jiaotong University, 2025, 59(8): 64-74.
DOI：

TAO Zhi, WANG Jie, LI Bolin, et al. Optimization of Full-Endwall Non-Axisymmetric Contouring Design for Turbine Cascades Aimed at Enhancing Film Cooling Effectiveness[J]. Journal of Xi’an Jiaotong University, 2025, 59(8): 64-74. DOI： 10.7652/xjtuxb202508007.

摘要

为探索非轴对称端壁设计对端壁封严冷气和气膜孔气膜冷效的提升机制，提出一种基于周期性非均匀有理B样条曲面的全端壁非轴对称造型方法，解决了传统方法对叶栅前缘上游区域的几何约束限制。建立包含端壁槽缝与离散气膜孔的涡轮叶栅数值仿真模型，并通过试验数据验证仿真模型的可靠性。以端壁平均气膜冷却效率为目标，采用基于Kriging代理模型的全局优化算法开展端壁优化设计。仿真结果表明：相比原始轴对称端壁，3个吹风比下的非轴对称端壁平均气膜冷却效率分别提升了9.36%、10.68%和14.76%，叶栅出口总压损失系数基本不变；非轴对称端壁造型不仅改变了端区的压力分布，大幅降低了叶片前缘附近的静压及叶栅通道进口位置的横向压力梯度，使得冷却射流能够对叶片前缘附近及通道进口形成更宽的气膜覆盖范围，还削弱了端区横向二次流，抑制了其对冷却射流的卷吸作用，使得靠近叶片压力面侧端壁上的气膜覆盖得到强化。研究结果可为现代高气热负荷涡轮端壁的冷却防护提供理论依据和技术参考。

Abstract

To explore the enhancement mechanism of non-axisymmetric endwall design on both endwall sealing coolant and discrete-hole film cooling effectiveness

a full-endwall non-axisymmetric contouring method based on periodic non uniform rational B-spline surfaces is proposed

overcoming geometric constraints in traditional approaches for the upstream region of cascade leading edges. A numerical simulation model of turbine cascades incorporating endwall slots and discrete film cooling holes is established and validated against experimental data. Using endwall-averaged film cooling effectiveness as the objective function

a global optimization algorithm based on Kriging surrogate modeling is employed for endwall design optimization. Simulation results indicate that

compared to the original axisymmetric endwall

the average film cooling efficiency of the non-axisymmetric endwall increases by 9.36%

10.68%

and 14.76% at three different blowing ratios

while the total pressure loss coefficient at the cascade exit remains largely unchanged. The non-axisymmetric endwall design not only alters the pressure distribution in the end region but also significantly reduces the static pressure near the blade leading edge and the lateral pressure gradient at the inlet position of the cascade channel. This allows the cooling jet to achieve a broader film coverage area near the blade leading edge and channel inlet

while also weakening the lateral secondary flow in the end region

thus suppressing its entrainment effect on the cooling jet and enhancing the film coverage on the endwall near the pressure side of the blade. This research provides theoretical foundations and technical references for cooling protection of modern turbine endwalls under high thermal-mechanical loads.

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references

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Institute of Turbomachinery, Xi'an Jiaotong University

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西安交通大学叶轮机械研究所，710049，西安Institute of Turbomachinery, Xi'an Jiaotong University, Xi'an 710049, China

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