Numerical investigations of heat transfer characteristics using oblong fins and circular fins in a wedge channel

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2023-04-04 DOI:10.1515/tjj-2022-0055

Goveraiahgari Venkatesh, R. Meenakshi Reddy, Pabbisetty Mallikarjuna Rao

引用次数: 1

Abstract

Abstract Turbine inlet air temperatures are extremely high, which can result in blade material damage. As a result, cooling the turbine blades is required, and a variety of cooling techniques have been introduced. The majority of the previous research on pin fins has focused on circular fins using a wedge duct to apply a constant temperature and uniform heat flux to the end wall and pin fin surfaces. The present study compares seven oblong pin-fins to seven circular pin fins in a wedge duct with a Reynolds number range of 10,000–50,000 and a constant heat flux (surface) of 3280 W/m2 applied to the endwall and surfaces of the oblong pin fin. The results indicate that the friction factor for oblong fins is 14% lower than for circular pin fins. The thermal performance factor is increased by 11.4%. The thermal performance factor can be improved by using oblong pin fins with higher Reynolds numbers.

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楔形通道中长形翅片和圆形翅片传热特性的数值研究

摘要涡轮机进气温度极高，可能导致叶片材料损坏。因此，需要冷却涡轮机叶片，并且已经引入了各种冷却技术。以前对针翅式翅片的大多数研究都集中在圆形翅片上，该翅片使用楔形管道将恒定的温度和均匀的热通量施加到端壁和针翅式表面。本研究比较了楔形管道中的七个椭圆形销片和七个圆形销片，雷诺数范围为10000–50000，应用于椭圆形销片端壁和表面的恒定热通量（表面）为3280 W/m2。结果表明，长方形翅片的摩擦系数比圆销翅片低14%。热性能因数提高了11.4%。使用雷诺数更高的长方形销片可以提高热性能因数。

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

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.