前缘点对非对称前缘压气机翼型气动性能的影响

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE International Journal of Turbo & Jet-Engines Pub Date : 2022-05-27 DOI:10.1515/tjj-2021-0054

Guanhua Yang, Limin Gao, Haohao Wang, Longrui Chang

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引用次数: 2

摘要

摘要前缘在压气机流动中起着重要的作用。非对称前缘在叶片气动性能上优于对称前缘。然而，style设计参数的影响规律仍然不明确。本文通过数值计算研究了LE点曲率和位置的影响。结果表明:yle叶片的工作范围随着LE点曲率的减小而扩大，有助于调节LE流加速，而LE点位置主要影响工作范围;结果表明，单轴LE曲率峰值应接近LE点，并应限制单轴LE曲率最大值。

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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Influence of leading edge point on aerodynamic performance of asymmetric leading edge compressor airfoils

Abstract Leading edge (LE) plays a prominent role in compressor flow. The asymmetric leading edge (ASYLE) has shown superiorities to symmetric LE in blade aerodynamic performance. However, the influencing rules of ASYLE design parameters are still ambiguous. In this work, numerical calculations were conducted to investigate the influencing effects of LE point curvature and position. The results show that the operating range of ASYLE blades expand with the decrease of LE point curvature, which helps to moderate LE flow acceleration, while the LE point position mainly affects the operating range. It is also revealed that the SSLE curvature peak is supposed to be close to LE point, and the maximum value of PSLE curvature should be restricted.

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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.