Research on new integral squeeze film damper vibration control of micro turbojet engine at high speed

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2022-10-24 DOI:10.1515/tjj-2022-0032

Wenhao Wang, Lidong He, Yangliu Sun, Zijian Wang, Hua-Liang D. Zhang, Qiaoqiao Bao, Xingyun Jia, Hua-jun Dong

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引用次数: 0

Abstract

Abstract In view of the problem that the vibration of the centrifugal impeller of the compressor exceeds the standard when a micro turbojet engine crosses the first-order critical speed, this research proposes a vibration control technology for the engine rotor system based on the new integral squeeze film damper (NISFD) according to the unique structure and assembly characteristics of the rotor bearing seat of the micro turbojet engine. Through numerical analysis and experimental research, the dynamic characteristics of NISFD are analyzed, and the vibration reduction mechanism of NISFD is revealed. The engine test verification based on NISFD is carried out. The results show that NISFD has good damping characteristics, which can improve the bending stress and strain energy distribution of the rotor. The engine test proves that NISFD can well solve the problem of excessive vibration of the engine when passing through the first-order critical speed, greatly reduce the vibration level within the working speed range, and significantly improve the reliability of the engine during operation. It provides a solid theoretical basis for the design of aeroengine, and provides a reference for the practical engineering application of NISFD in aeroengine.

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微型涡喷发动机新型整体式挤压油膜阻尼器高速振动控制研究

摘要针对微型涡喷发动机在超过一阶临界转速时压缩机离心叶轮振动超标的问题，针对微型涡喷发动机转子轴承座的独特结构和装配特点，提出了一种基于新型整体挤压油膜阻尼器的发动机转子系统振动控制技术。通过数值分析和实验研究，对NISFD的动力学特性进行了分析，揭示了其减振机理。基于NISFD进行了发动机试验验证。结果表明，NISFD具有良好的阻尼特性，可以改善转子的弯曲应力和应变能分布。发动机试验证明，NISFD可以很好地解决发动机在通过一阶临界转速时振动过大的问题，大大降低工作转速范围内的振动水平，显著提高发动机运行的可靠性。为航空发动机的设计提供了坚实的理论基础，为NISFD在航空发动机中的实际工程应用提供了参考。

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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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.