Research on the cooling performance and thermal stress characteristic of turbine blade with typical array film holes

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology Pub Date : 2025-10-03 DOI:10.1016/j.ast.2025.111035

Chengliang Lv , Longfei Wang , Junkui Mao , Yiming Liu , Xinzi Liu , Dewei Zhang , Zhongran Chi

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引用次数: 0

Abstract

A real turbine stator is selected as the research object, and cooling performance and thermal stress characteristic of blades with varying film cooling hole geometries-namely circular holes, shaped holes, and 7–7–7 holes-are studied through high temperature experiment and numerical simulation. Compared to circular hole blade, the cooling efficiency of shaped hole blade is improved by 12.99 %, the overall thermal stress is reduced by 17.12 %, and the thermal stress in the maximum 10 % interval is reduced by 24.34 %. It is an optimal scheme for the film holes with great cooling efficiency and low thermal stress. The ability of the shaped hole and 7–7–7 hole blades to improve blade cooling efficiency and reduce surface thermal stress is similar, but the former is slightly better at reducing thermal stress in the blade root and suction-side film hole outflow regions. The aerothermal parameters under different engine operating conditions impact the ability of the shaped hole blades to enhance the cooling efficiency and lower the surface thermal stress. Improvement of blade cooling efficiency is more significant at small temperature ratio and small blowing ratio, and the reduction of the blade surface thermal stress is more obvious at large temperature ratio or large blowing ratio. As the blowing ratio varies along with the engine operating conditions, thermal stress on blade pressure side and suction side with shaped holes are obviously reduced, and the drastic changes of thermal stress in the local area of blade leading edge are also effectively mitigated.

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典型阵列膜孔涡轮叶片冷却性能及热应力特性研究

选取实际涡轮定子作为研究对象，通过高温实验和数值模拟，研究了不同气膜冷却孔几何形状（圆孔、形孔和7-7-7孔）叶片的冷却性能和热应力特性。与圆孔叶片相比，形孔叶片的冷却效率提高了12.99%，整体热应力降低了17.12%，最大10%区间的热应力降低了24.34%。这是一种冷却效率高、热应力小的膜孔优化方案。形孔和7-7-7孔叶片提高叶片冷却效率和降低表面热应力的能力相似，但形孔叶片在降低叶根和吸力侧膜孔流出区热应力方面稍好。不同工况下的气动热参数影响着异形孔叶片提高冷却效率和降低表面热应力的能力。在小温度比和小吹风比下，叶片冷却效率的提高更为显著；在大温度比和大吹风比下，叶片表面热应力的降低更为明显。随着发动机工况的变化，随着吹气比的变化，叶片压力侧和形孔吸力侧的热应力明显减小，叶片前缘局部区域热应力的剧烈变化也得到了有效的缓解。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

Aerospace Science and Technology 工程技术-工程：宇航

CiteScore

10.30

自引率

28.60%

发文量

654

审稿时长

54 days

期刊介绍： Aerospace Science and Technology publishes articles of outstanding scientific quality. Each article is reviewed by two referees. The journal welcomes papers from a wide range of countries. This journal publishes original papers, review articles and short communications related to all fields of aerospace research, fundamental and applied, potential applications of which are clearly related to: • The design and the manufacture of aircraft, helicopters, missiles, launchers and satellites • The control of their environment • The study of various systems they are involved in, as supports or as targets. Authors are invited to submit papers on new advances in the following topics to aerospace applications: • Fluid dynamics • Energetics and propulsion • Materials and structures • Flight mechanics • Navigation, guidance and control • Acoustics • Optics • Electromagnetism and radar • Signal and image processing • Information processing • Data fusion • Decision aid • Human behaviour • Robotics and intelligent systems • Complex system engineering. Etc.