v形槽活塞环的设计方法

IF 0.7 4区 工程技术 Q4 ENGINEERING, AEROSPACE
Le Zhang, Lidong He, Xiaodong Wang, Xinwei Huang, Xingyun Jia, Chunrui Liu
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引用次数: 0

摘要

摘要针对活塞环在高压高速下泄漏大、摩擦发热高等问题,在前人对V型槽活塞环研究的基础上,对V型沟活塞环的设计方法进行了深入研究。对活塞环V形槽的数量和深度进行了数值分析。利用高压高速旋转试验台对其影响规律进行了验证和分析。模拟和实验结果表明,4槽和8槽活塞环的泄漏量分别降低了14.9%和28.5%,温度分别降低了10.9%和4.7%;当活塞环上有8个V形槽时,泄漏量分别减少28.5%和21.7%;当V形槽深度为0.04和0.08mm时,温度降低了4.1%。然而,当V形沟深度为0.12mm时,与传统活塞环相比,泄漏增加了2.7%。适当的凹槽数量和凹槽深度可以实现低泄漏和低摩擦温升的协调设计。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
The design method of the V-shaped groove piston ring
Abstract Aiming at the problems of large leakage and high friction heat generation of the piston ring under high pressure and high speed, based on the previous research on the V-shaped groove piston ring, the research on the design method of the V-shaped groove piston ring is carried out in depth. The numerical analysis is carried out focusing on the number of V-shaped grooves and the depth of the V-shaped grooves of the piston ring. The influence law is verified and analyzed by using a high-pressure and high-speed rotating test bench. The simulation and experimental results show that the leakage of 4 grooves and 8 grooves piston ring is reduced by 14.9 and 28.5%, and the temperature is reduced by 10.9 and 4.7%; When there are 8 V-shaped grooves on the piston ring, the leakage is reduced by 28.5 and 21.7%; when the V-shaped groove depth is 0.04 and 0.08 mm, the temperature is reduced by 4.1%. However, when the V-shaped groove depth is 0.12 mm, the leakage is increased by 2.7% compared with the traditional piston ring. Appropriate groove number and groove depth can realize the coordinated design of low leakage and low friction temperature rise.
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来源期刊
International Journal of Turbo & Jet-Engines
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
36
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.
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