Comparative analysis on relief grooves of high-speed and high-pressure aeroengine fuel gear pumps

被引：0
|
作者：
Qi G. [1 ,2 ,3 ]
Wu B. [2 ,3 ]
Fu J. [4 ]
机构：
[1] AECC Xi’an Engine Control Technology Co. Ltd., Xi’an
[2] Key Laboratory of High-Performance Manufacturing for Aero Engine, Ministry of Industry and Information Technology, Northwestern Polytechnical University, Xi’an
[3] Engineering Research Center of Advanced Manufacturing Technology for Aero Engine, Ministry of Education, Northwestern Polytechnical University, Xi’an
[4] School of Power and Energy, Northwestern Polytechnical University, Xi’an
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2024年 / 45卷 / 05期
关键词：
aeroengines; cavitation; fuel gear pumps; relief grooves; trapped oil;
D O I：
10.7527/S1000-6893.2023.29666
中图分类号：
学科分类号：
摘要：
The relief groove is the most effective measure to alleviate oil trapping of gear pumps；therefore，its design directly affects the working efficiency and service life of the gear pump. This paper presents a performance analysis method for relief grooves based on computational fluid dynamics. A comparative study was conducted to evaluate the performance of different structural forms of relief grooves，focusing on technical indicators such as trapped oil pressure，gas volume fraction，outlet flow rate，and the flow rate non-uniformity coefficient. The results show that the relief groove F，with a flow non-uniformity of only 5. 25% and a trapped oil pressure peak of 18 MPa，outperforms the rectangular，circular，and unloading slot E in terms of overall performance，exhibiting advantages of low trapped oil pressure，high volumetric efficiency，and high flow quality. These characteristics make it well-suited for the design of high-speed and high-pressure fuel gear pumps. In addition，increasing the size of the relief groove and positioning it towards the low-pressure chamber can reduce cavitation，oil entrapment，and flow pulsation. Designing the new unloading slot F with these factors in mind can improve its overall performance. © 2024 Chinese Society of Astronautics. All rights reserved.
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