Compensating cooling on the suction surface of the blade by the jets of the film holes on the endwall

IF 6.4 2区工程技术 Q1 THERMODYNAMICS

Case Studies in Thermal Engineering Pub Date : 2025-04-18 DOI:10.1016/j.csite.2025.106174

Changyu Zhao (赵长宇), Junyu Zhu (朱俊羽), Wei Zhang (张魏), Zhiqi Zhao (赵志奇), Guangchao Li (李广超), Chun Li (李春)

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Abstract

The coolant ejected from the film holes on the gill region of the blade deflects to the blade tip in the action of the cascade passage vortices, resulting in the local film cooling failure on the suction surface near the endwall. This paper introduces an improved strategy for compensating the film cooling on the suction surface near the endwall by using the passage vortices to entrain coolant inject from endwall jet. The film effectiveness of two rows of film holes on the gill region was measured by pressure-sensitive paint (PSP) technique to be as the baseline. Film hole layouts on the endwall were examined, including 3 single-hole cases, 3 double-hole cases, and 1 three-hole case, totaling 7 film hole layouts. The compensating improvement of film cooling on the suction surface was examined at the blowing ratios ranging from 0.50 to 1.75. The mechanism of compensating cooling was analyzed by numerical simulation. The correction equation of compensating cooling was established based on the experimental data. The results show that the compensating film effectiveness of single-hole B or hole C is higher than that of single-hole A in the film failure region at all blowing ratios. Single-hole C exhibits a significant improvement in film effectiveness by 0.032 at the high blowing ratio of 1.75. The film effectiveness of the combination of hole B and hole C is higher than those of the other combinations, with the largest improvement of film effectiveness by 0.028 at the blowing ratio of 1.75.

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通过端壁上膜孔的射流补偿叶片吸力面的冷却

从叶片鳃部薄膜孔喷出的冷却剂在级联通道漩涡的作用下偏转至叶片顶端，导致靠近端壁的吸气面局部薄膜冷却失效。本文介绍了一种改进策略，即利用通道涡流夹带从端面喷射的冷却剂，补偿端壁附近吸入面上的薄膜冷却。采用压敏涂料（PSP）技术测量了鳃区两排膜孔的膜效率，作为基线。研究了内壁上的膜孔布局，包括 3 个单孔、3 个双孔和 1 个三孔，共 7 种膜孔布局。在吹气比为 0.50 至 1.75 的条件下，考察了吸气面薄膜冷却的补偿改善效果。通过数值模拟分析了补偿冷却的机理。根据实验数据建立了补偿冷却的修正方程。结果表明，在所有吹气比下，单孔 B 或单孔 C 在薄膜失效区域的补偿膜效果均高于单孔 A。在高吹气比 1.75 时，单孔 C 的薄膜效果明显提高了 0.032。孔 B 和孔 C 组合的薄膜效率高于其他组合，在吹气比为 1.75 时，薄膜效率最大提高了 0.028。

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

Case Studies in Thermal Engineering Chemical Engineering-Fluid Flow and Transfer Processes

CiteScore

8.60

自引率

11.80%

发文量

812

审稿时长

76 days

期刊介绍： Case Studies in Thermal Engineering provides a forum for the rapid publication of short, structured Case Studies in Thermal Engineering and related Short Communications. It provides an essential compendium of case studies for researchers and practitioners in the field of thermal engineering and others who are interested in aspects of thermal engineering cases that could affect other engineering processes. The journal not only publishes new and novel case studies, but also provides a forum for the publication of high quality descriptions of classic thermal engineering problems. The scope of the journal includes case studies of thermal engineering problems in components, devices and systems using existing experimental and numerical techniques in the areas of mechanical, aerospace, chemical, medical, thermal management for electronics, heat exchangers, regeneration, solar thermal energy, thermal storage, building energy conservation, and power generation. Case studies of thermal problems in other areas will also be considered.