宽飞行剖面下机载滑油系统热负荷分析

doi:10.7527/S1000-6893.2025.32005

Abstract

Abstract:

In order to provide the heat input boundary conditions for the design of the new dual-system evaporation cycle subsystem of advanced helicopter and carry out the thermal management and temperature control of the environmental control system more accurately and effectively， the thermal load variation of the engine oil system under a wide flight profile was studied. First， the transmission mechanics of the engine drive system is analyzed， the mathematical model of the engine drive system is established， the friction power consumption of the engine heat generating parts under various working conditions is analyzed， and the theoretical calculation of friction loss is simplified. Then， taking oil temperature rise as the research object， the influence degree of heat generating and cooling components causing oil temperature change is analyzed. On this basis， simulation models of engine drive system and oil system are established by Amesim， and the heat load change of oil system under wide flight profile is simulated and analyzed. Finally， the experiment data and simulation results of a certain engine oil system are compared and analyzed. The results show that the system model meets the engineering design requirements and can provide reference for the subsequent thermal management technology research of environmental control system.

Key words: aeroengine bearing, oil system, thermal load, extended flight profile, environmental control system, evaporation cycle subsystem, advanced helicopter

CLC Number:

V233.4

Ying WANG, Yang LI, Chaoqian CHENG, Zongxia JIAO. Thermal load analysis for aeroengine oil system with extended flight profile[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(1): 632005.

Figures/Tables 21

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名称	参数	名称	参数
滚动体数量/mm	16	节圆直径/mm	125.260 1
滚动体直径/mm	22.225	公称接触角/（°）	40
内滚道直径/mm	102.793 8	轴承外径/mm	90
外滚道直径/mm	147.726 4	轴承内径/mm	160

名称	参数
滑油导热系数/（W·（m·K）^-1）	0.152
滑油的运动黏度/（mm²·s^-1）	40
滑油密度/（kg·m^-3）	909.972 7
滑油比热/（kJ·（kg·K）^-1）	1.84

发动机转速/%	滑油泵转速/ （r·min^-1）	发动机转速/%	滑油泵转速/（r·min^-1）
10	1 000	65	7 200
15	1 500	70	7 400
20	2 000	75	7 600
25	2 500	80	8 000
30	3 000	85	9 000
35	3 500	90	10 000
40	4 000	95	11 000
45	4 500	100	12 000
50	5 000	105	12 000
55	6 000	110	12 000
60	7 000	120	12 000

Thermal load analysis for aeroengine oil system with extended flight profile

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