The aerothermal performance of turbine blade squealer tip at various Reynolds numbers and Mach numbers with moving endwall

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2022-08-18 DOI:10.1515/tjj-2022-0040

Shaowen Chen, Cong Zeng, Zhi-yan Zhou, Weihang Li

引用次数: 0

Abstract

Abstract The changes of operating conditions can lead to variations in the aerodynamic conditions of the turbine blades. Then numerical studies are conducted to study the aerothermal performance of the turbine blade with a squealer tip at various Reynolds numbers (Re) and exit Mach numbers (Ma) with moving endwall. Besides, the effect of the rim height on the squealer tip is studied. The increasing of Reynolds numbers at Mach number = 0.78 enhances the heat-transfer at the tip of blade entirely, however, it has little impact on the leakage flow of the blade tip. The total heat flux increases with Mach number increasing from 0.78 to 0.96 and changes slightly with a further increasing of Mach number at a design Reynolds numbers. The height of squealer rim affects the tip leakage flow in the cavity and tip leakage vortex, and then affects the heat transfer distribution and the heat load of the blade tip.

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不同雷诺数和马赫数下涡轮叶片尖部的气动热性能

摘要运行条件的变化会导致涡轮叶片空气动力学条件的变化。然后进行了数值研究，研究了在不同雷诺数（Re）和端壁移动的出口马赫数（Ma）下，带尖尖叶片的气动热性能。此外，还研究了轮缘高度对尖部噪声的影响。在马赫数=0.78时，雷诺数的增加完全增强了叶尖的传热，但对叶尖的泄漏流影响不大。总热通量随着马赫数从0.78增加到0.96而增加，并且在设计雷诺数下随着马赫数的进一步增加而略有变化。尖叫边缘的高度影响叶尖在空腔内的泄漏流动和叶尖泄漏涡流，进而影响叶尖的传热分布和热负荷。

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.