飞机舵面液压系统高压泵空化流动特性与优化

Abstract

Abstract:

To break the monopoly of key technologies for high-pressure piston pumps in the list of the United States， and aiming to satisfy the requirement for precise rudder control of large civil aircraft during navigation， this study conducts numerical simulations and optimization of internal flow characteristics in the pumps based on full cavitation models and compressible models. The numerical simulations are validated by a series of experiments. The causes of the formation of flow valleys and peaks are revealed by analyzing the flow characteristics， the way cavitation impacts flow pulsation is discovered， and a method to suppress cavitation in the piston chamber is proposed. Conclusions Backflow is the main cause of the drainage flow valley. The drainage flow peak （i.e.， pressure overshoot） is caused by two factors. First， the inertial impact of backflow hydraulic oil causes a sudden increase in cavity pressure. Second， hold pressure due to untimely and incomplete overflow after the end of the backflow induces the pressure overshoot. Gas bubbles in the piston chamber absorb the “intended boost” and prolong the back-up time， thus reducing the flow valley. A mathematical model for suppressing the cavitation of the piston chamber at the invariable theoretical flow rate is established by innovatively coupling the piston chamber flow rate equation and the pressure drop equation from the perspective of pressure drop to solve the problem of theoretical flow rate reduction resulted from suppressing the piston chamber cavitation. Based on the model， two methods are proposed to suppress the cavitation of the piston chamber without changing the theoretical flow rate， providing theoretical solutions for the development of military axial piston pumps.

Key words: cavitation, axial piston pumps, multiphase flow coupling, flowrate characteristics, valve plates

CLC Number:

V264.1

Xiaoyu SUO, Yi JIANG, Wenjie WANG, Dianrong GAO, Xinyu ZHANG. Cavitation flow characteristics and optimization of high-pressure pumps in hydraulic system of aircraft control surfaces[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(9): 127402-127402.

Figures/Tables 25

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参数	数值
柱塞腔半径/mm	10
分布圆半径/mm	40.5
配流盘外半径/mm	44.5
配流盘内半径/mm	36.5
斜盘倾角/（°）	15
额定压强/MPa	35
额定转速/（r·min^-1）	2 200
柱塞数	9

序号	柱塞腔半径r/m	分布圆半径R/m
1	0.010 50	0.036 734 693 877 55
2	0.010 25	0.038 548 483 045 80
3	0.010 00	0.040 500 000 000 00
4	0.009 75	0.042 603 550 295 85
5	0.009 50	0.044 875 346 260 38
6	0.009 25	0.047 333 820 306 79

序号	柱塞腔半径R/m	斜盘倾角正切tan β
1	0.036 734 693 877 55	0.260 381 788 045 7
2	0.038 548 483 045 80	0.248 130 264 005 0
3	0.040 500 000 000 00	0.236 173 957 411 1
4	0.042 603 550 295 85	0.224 512 868 263 9
5	0.044 875 346 260 38	0.213 146 996 563 5
6	0.047 333 820 306 79	0.202 076 342 309 9

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Cavitation flow characteristics and optimization of high-pressure pumps in hydraulic system of aircraft control surfaces

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