Effect of multi-hole trench cooling on an adiabatic flat plate for gas turbine application

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE International Journal of Turbo & Jet-Engines Pub Date : 2023-01-30 DOI:10.1515/tjj-2022-0061

Ved Prakash, S. Chandel, D. Thakur, Ranjan Mishra

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引用次数: 1

Abstract

Abstract A 3D numerical analysis on an adiabatic flat plate for multi-hole trench cooling with forward, backward and mixed injection holes is performed in the current investigation. The numerical setup is validated before the performances of different cooling configurations are compared. The effect of three different multi-hole trench arrangements, square-diamond, long-diamond, and super-long-diamond with constant perforated percentage (3.27%), on film cooling performance is studied at blowing ratio 1.0. The row-to-row interaction between coolant jets and mainstream is analysed, and lateral film cooling effectiveness is calculated downstream. The dimensionless temperature contour overlaid with streamlines concluded that the SLD trench hole arrangement with forward injection forms a developed effusion layer due to counter-rotating vortex pairs, which helps in proper mixing of coolant jets into the mainstream and improves film cooling effectiveness in lateral as well as in longitudinal direction. It is observed that super-long-diamond arrangement with forward injection provides the highest film cooling effectiveness than square-diamond and long-diamond arrangements and favours early development of the coolant film layer.

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燃气轮机用绝热平板多孔沟槽冷却的影响

摘要对具有前、后、混合喷注孔的绝热平板进行了三维数值分析。在对不同冷却方式的性能进行比较之前，对数值设置进行了验证。在吹气比为1.0的条件下，研究了定孔率(3.27%)条件下，正方形金刚石、长金刚石和超长金刚石三种不同的多孔布置方式对气膜冷却性能的影响。分析了冷却剂射流与主流之间的相互作用，并计算了下游的侧膜冷却效率。由流线叠加的无因次温度曲线可知，前向喷射的SLD槽孔布置由于反向旋转的涡对形成了发达的射流层，有利于冷却剂射流在主流内的适当混合，提高了横向和纵向的气膜冷却效果。结果表明，前喷的超长菱形排列比方菱形排列和长菱形排列具有最高的冷却效果，有利于冷却液膜层的早期发育。

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来源期刊

International Journal of Turbo & Jet-Engines 工程技术-工程：宇航

CiteScore

1.90

自引率

11.10%

发文量

审稿时长

6 months

期刊介绍： The Main aim and scope of this Journal is to help improve each separate components R&D and superimpose separated results to get integrated systems by striving to reach the overall advanced design and benefits by integrating: (a) Physics, Aero, and Stealth Thermodynamics in simulations by flying unmanned or manned prototypes supported by integrated Computer Simulations based on: (b) Component R&D of: (i) Turbo and Jet-Engines, (ii) Airframe, (iii) Helmet-Aiming-Systems and Ammunition based on: (c) Anticipated New Programs Missions based on (d) IMPROVED RELIABILITY, DURABILITY, ECONOMICS, TACTICS, STRATEGIES and EDUCATION in both the civil and military domains of Turbo and Jet Engines. The　International Journal of Turbo & Jet Engines　is devoted to cutting edge research in theory and design of propagation of jet aircraft. It serves as an international publication organ for new ideas, insights and results from industry and academic research on thermodynamics, combustion, behavior of related materials at high temperatures, turbine and engine design, thrust vectoring and flight control as well as energy and environmental issues.