小型高涵道涡扇发动机叶片前缘受侵蚀压缩系统气动性能退化分析

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2023-04-21 DOI:10.1515/tjj-2023-0031

Lei Shi, Ruilin Jiang, Chen-lei Huang, Shuhan Guo, Guoshun Chen

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引用次数: 0

摘要

摘要选择DGEN380的整个压缩系统来研究前缘侵蚀引起的气动特性退化。对不同程度前缘侵蚀情况进行了数值模拟。研究发现，前缘侵蚀导致可操作性从70显著降低 % 叶片到叶尖的高度，并主要影响旁路中的后续流场。90 % 在叶片高度方面，前缘侵蚀叶片的等熵效率和总压比与原始叶片相比有所降低。然后，引入推力方程，分析了飞机不同工况下前缘烧蚀对推力损失的影响。在三种工况中，巡航工况的推力损失率最大，为后续评估叶片修复工况提供了参考。

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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The aerodynamic performance degradation analysis of a small high bypass turbofan engine compression system with fan rotor blade leading edge erosion

Abstract The entire compression system of DGEN380 was selected to study the degradation of aerodynamic characteristics caused by erosion of the leading edge. Numerical simulations under different degrees of leading edge erosion were performed. It was found that the leading edge erosion causes a significant decrease in operability from 70 % of the blade height to the tip, and mainly affects the subsequent flow field in the bypass. At 90 % of blade height, the isentropic efficiency and total pressure ratio of the blade with leading edge erosion are reduced compared to the origin blade. Afterwards, the thrust equation was introduced to analyze the effect of leading edge erosion on the thrust loss under different operating conditions of the aircraft. Among the three operating conditions, the thrust loss rate of the cruise condition was the largest, which provided a reference for the subsequent evaluation of the blade repair condition.

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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.