涡轮叶栅空腔顶端的气动热效应

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2023-09-25 DOI:10.1515/tjj-2023-0066

Zuhao Liu, Yi Cao, Chao Zhou, Zhiyuan Cao

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引用次数: 0

摘要

高压涡轮的气动性能和热性能是高压涡轮设计的重要内容。本文研究了涡轮叶栅空腔末端吸力侧尖瓣开度的气动热效应。调查了四种情况，“腔”，“开口1”，“开口2”和“开口3”。对于开口面积为轴向弦长15%的开口1，开口出口主要通过与通道涡的相互作用影响近尖流动，近尖损失增加幅度小于3%。当开口面积为轴向弦的12%时，开口2的近叶尖损失低于开口1。通过进一步圆取开孔区域的边缘，开孔尖端的损失比空腔尖端高不到1%。然而，开口尖端可以实现减少吸力侧尖叫器内壁的热负荷高达19%。

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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Aerothermal effects of squealer openings on a cavity tip in a turbine cascade

Abstract Both the aerodynamic and thermal performance are important for a high-pressure turbine design. This paper investigates aerothermal effects of opening on the suction side squealer of a cavity tip in a turbine cascade. There are four cases investigated, ‘Cavity’, ‘Opening 1’, ‘Opening 2’ and ‘Opening 3’. For Opening 1 with an opening area at 15 % axial chord, the opening outflow affects the near-tip flow mainly by interacting with the passage vortex, and the near tip loss increases by less than 3 %. For Opening 2 with an opening area at 12 % axial chord, the near tip loss is lower than Opening 1. By further rounding the edge of the opening area, the loss of the tip with opening is less than 1 % higher than the cavity tip. Nevertheless, the opening tip can achieve a reduction of the thermal load of the suction side squealer inner wall by up to 19 %.

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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.