膜冷却与混合冷却的流动结构比较：CFD研究

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2023-05-10 DOI:10.1515/tjj-2022-0058

R. Panda, A. K. Pujari, B. Gudla

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引用次数: 1

摘要

摘要气膜和射流冲击冷却是燃气轮机叶片和叶片冷却中广泛应用的技术。本文研究并比较了薄膜冷却平板和混合冷却方案的流动结构。混合冷却方案结合了冲击孔和膜孔，被称为组合冲击膜（IFC）冷却。在具有薄膜孔的平板上进行了实验验证和计算分析。比较了两种情况下平板不同区域的不同流动参数，如速度模式、湍流动能和流线流动结构。观察到，混合方案显示出优于薄膜冷却的优点。射流-射流相互作用、射流横流相互作用和涡流的形成是影响膜冷却性能的主要因素。有一个52 % 与膜孔出口处的膜冷却相比，混合冷却的湍流动能的下降。FC情况下观察到的冷却剂和主流相互作用中的混合比IFC情况下更多。

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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Flow structure comparison of film cooling versus hybrid cooling: a CFD study

Abstract Film and jet impingement cooling are widely used techniques in gas turbine vane and blade cooling. The present work investigates and compares the flow structure of a film-cooled flat plate with a hybrid cooling scheme. The hybrid cooling scheme combines both impingement hole and film holes and is named combined impingement-film (IFC) cooling. Experimental validation and computational analyses are carried out on a flat plate with film holes. Different flow parameters, such as velocity pattern, Turbulent kinetic energy, and streamline flow structure, are compared for the two cases in different regions of the flat plate. It is observed that the hybrid scheme shows advantages over film cooling. The jet-to-jet interaction, jet crossflow interaction, and vortex formation are the main factors affecting film cooling performance. There is a 52 % drop in turbulent kinetic energy for the hybrid cooling compared to the film cooling at the film hole exit. More mixing in the coolant and mainstream interaction is observed for the FC case than in the IFC.

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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.