燃气透平双肩壁凹槽叶顶流动传热性能优化研究

李浩玉; 何坤; 晏鑫

doi:10.7652/xjtuxb202606013

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燃气透平双肩壁凹槽叶顶流动传热性能优化研究

专题　多场景传热 | 更新时间：2026-06-12

- 燃气透平双肩壁凹槽叶顶流动传热性能优化研究
- Optimization of Flow and Heat Transfer Performance for Double-Rim Squealer Tip in Gas Turbines
- 西安交通大学学报 2026年60卷第6期页码：154-165
- 作者机构：
  
  西安交通大学能源与动力工程学院，710049，西安
- 作者简介：
  
  作者简介：李浩玉（1998—），男，博士生；
  晏鑫（通信作者），男，教授，博士生导师。
- 基金信息：
  
  国家科技重大专项资助项目(J2019-Ⅲ-0007-0050);陕西省自然科学基金资助项目(2023-JC-YB-340)
- DOI：10.7652/xjtuxb202606013
  中图分类号： TK47
- 收稿：2025-10-13，
  
  纸质出版：2026-06-10
- 稿件说明：
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李浩玉, 何坤, 晏鑫. 燃气透平双肩壁凹槽叶顶流动传热性能优化研究[J]. 西安交通大学学报, 2026,60(6):154-165.

LI Haoyu, HE Kun, YAN Xin. Optimization of Flow and Heat Transfer Performance for Double-Rim Squealer Tip in Gas Turbines[J]. Journal of Xi'an Jiaotong University, 2026, 60(6): 154-165.
李浩玉, 何坤, 晏鑫. 燃气透平双肩壁凹槽叶顶流动传热性能优化研究[J]. 西安交通大学学报, 2026,60(6):154-165. DOI： 10.7652/xjtuxb202606013.

LI Haoyu, HE Kun, YAN Xin. Optimization of Flow and Heat Transfer Performance for Double-Rim Squealer Tip in Gas Turbines[J]. Journal of Xi'an Jiaotong University, 2026, 60(6): 154-165. DOI： 10.7652/xjtuxb202606013.

摘要

为提升航空发动机透平级第一级动叶双肩壁凹槽叶顶的传热性能，对其叶顶结构进行了优化设计。采用Kriging近似模型和多目标遗传算法，以面平均传热系数与透平级等熵效率为优化目标，获得了一种具有优良气热性能的透平级双肩壁凹槽叶顶。通过定常与非定常数值模拟，对比分析了优化后的双肩壁凹槽叶顶、传统凹槽叶顶及2种典型双肩壁凹槽叶顶的气热特性。研究结果表明：优化后双肩壁凹槽叶顶的内肩壁高度低于外肩壁，且内肩壁吸力侧高度高于压力侧。定常计算结果表明：优化后的凹槽叶顶在保持透平级等熵效率不变的同时，可显著改善传热性能。与传统凹槽叶顶相比，凹槽底部、肩壁区域、叶顶整体的传热系数分别降低了30.36%、2.96%、9.52%。内肩壁结构可有效抑制腔室涡系尺寸，从而减弱高温泄漏流对凹槽底面的冲击。非定常计算表明：优化后的双肩壁凹槽叶顶有效降低了凹槽内部温度和压力波动幅值，同时优化后的内肩壁结构可抑制腔室涡的发展，从而使得其时均面平均传热系数降低了5.65%。该研究可为实际透平级第一级动叶的设计提供理论依据。

Abstract

To enhance the heat transfer performance of a double-rim squealer tip for the first-stage rotor blade in an aero-engine turbine，the squealer tip structure was optimized in this study.A Kriging surrogate model coupled with a multi-objective genetic algorithm（MOGA）was employed to optimize the area-averaged heat transfer coefficient and turbine-stage isentropic efficiency，giving rise to a turbine-stage double-rim squealer tip exhibiting favorable aero-thermal performance. Steady and unsteady numerical simulations were performed to compare and analyze the aero-thermal characteristics of the optimized double-rim squealer tip with those of a conventional squealer tip and two types of typical double-rim squealer tips.The study results showed that the optimized double-rim squealer tip featured an inner rim lower than the outer rim，and a greater inner rim height on the suction side than on the pressure side.Steady computation results indicated that，with the turbine-stage isentropic efficiency unchanged，the optimized squealer tip exhibited noticeably improved heat transfer performance，for it achieved reductions in heat transfer coefficient at the squealer bottom，in the rim area，and over the entire tip of 30.36%，2.96%，and 9.52%，respectively，relative to the conventional squealer tip.The inner rim structure was observed to effectively suppress the scale of the cavity vortex system，thereby mitigating the impingement of high-temperature leakage flow on the squealer bottom.Unsteady computation results suggested that the optimized double-rim squealer tip effectively reduced the amplitudes of temperature and pressure fluctuations within the squealer；furthermore，suppression of cavity vortex development by the optimized inner rim structure led to a 5.65%decrease in the time-averaged area-averaged heat transfer coefficient.The study is expected to provide a theoretical basis for the design of first-stage rotor squealer tips in practical turbine stages.

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references

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