Optimization of turbocharging system for aviation piston pump based on entropy production theory

被引：0
|
作者：
Chen Y. [1 ]
Chen J. [1 ]
Pan Y. [1 ]
Yan M. [1 ]
机构：
[1] School of Mechanical Engineering, Guangxi University, Nanning
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2024年 / 45卷 / 04期
基金：
中国国家自然科学基金;
关键词：
aviation piston pump; energy loss; entropy theory; structural optimization; turbocharging;
D O I：
10.7527/S1000-6893.2023.29015
中图分类号：
学科分类号：
摘要：
The integration of turbocharging system at the inlet end of aviation piston pump is conducive to improving the integration of aviation hydraulic system，and solving the problems of cavitation and boot removal caused by insuffi⁃ cient oil absorption of the plunger pump at high speed. Aiming at the optimization design of blades and pressurized chamber flow channels in turbocharging system，the energy loss and spatial distribution in the pressurized system are studied based on the entropy production theory，and the fluid domain model of the turbo self-boosting axial piston pump is constructed to explore the changes of pressurized chamber form，section shape，inlet width，section area，and the relationship between turbine blade form and entropy yield. The structure of the turbocharging system is opti⁃ mized to minimize the entropy production，ie. when the turbine adopts twisted blades，the pressurized water chamber adopts a spiral shape，the cross-section shape adopts a circular arc，the inlet width of the pressurized water chamber adopts 8mm，and the cross-section area change law is U-shaped，the total entropy production of the pressurized sys⁃ tem decreases by about 0. 032 W/K，which is 13% lower than before optimization，and the boost value increases by about 0. 22 bar，7% more than before optimization. Finally，the prototype was used to build the test system，and the turbocharging values in the form of straight blades and twisted blades were tested，and the test results were basically consistent with the simulation results. © 2024 Chinese Society of Astronautics. All rights reserved.
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