航空发动机二级滑油泵地面及高空特性试验

李澍; 胡剑平; 王静; 吕亚国; 谭逸; 吴楠

doi:10.13224/j.cnki.jasp.20240217

航空发动机二级滑油泵地面及高空特性试验

doi: 10.13224/j.cnki.jasp.20240217

西北工业大学动力与能源学院，西安 710072

基金项目: 国家科技重大专项（J2019-Ⅲ-0023-0067）

详细信息

作者简介:
李澍（1998-），男，博士生，研究领域为航空发动机润滑与空气系统流动与换热。E-mail：lis@mail.nwpu.edu.cn

通讯作者:
胡剑平（1984-），男，副教授，博士，研究领域为航空发动机润滑与空气系统流动与换热。E-mail：hujp@nwpu.edu.cn

中图分类号: V231.1
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出版历程
- 收稿日期: 2024-04-11
- 网络出版日期: 2024-11-07

Test of the ground and high-altitude performance on the two-stage lubricating oil pumps in aero-engine

School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China

摘要

摘要:
以某航空发动机双级滑油泵为研究对象，根据滑油泵组试验需求，搭建了纯油介质环境下的滑油泵流量性能试验系统；开展了纯油介质下滑油泵的性能试验，探究滑油泵的高空特性，得到了纯油介质下不同工况参数对滑油泵流量性能的影响规律。结果表明：在地面试验中，滑油泵转速在1003～4014 r/min范围内，出口压力不超过600 kPa时，两级泵的容积效率随出口压力的变化小于5%，流量与转速成线性关系，流量随着转速增加而增加，而容积效率随着转速增加而下降。在高空特性研究试验中，两级泵在不同入口压力下第二级泵抽吸的滑油流量及其容积效率比第一级泵略高，随着入口压力下降，两级泵的流量和容积效率均明显下降。当飞行高度小于高空8 km时，两级泵的流量和容积效率急剧下降。随着转速升高，滑油流量和容积效率下降速度越快；当飞行高度为12 km时，各个转速容积效率均低于50%。
- 双级滑油泵 /
- 地面特性 /
- 高空特性 /
- 流量性能 /
- 容积效率
Abstract:
Taking a two-stage lubricating oil pump for a specific aero-engine as the object, a testing system was developed to evaluate the flow performance under pure oil medium, meeting the test requirements of the oil pump. Performance tests under pure oil medium were conducted to explore the high-altitude performance of the pump and analyze the impact of various operating parameters on the flow performance of the lubricating oil pump. The results indicated that the volumetric efficiency of the two-stage pump fluctuated by less than 5% with changes in outlet pressure, with the rotational speed ranging from 1003 to 4014 r/min, and outlet pressure below 600 kPa in the ground tests. The oil flow rate demonstrated a linear relationship with rotational speed, increasing in conjunction with the rotational speed, while volumetric efficiency declined. During high-altitude tests, the oil flow rate and volumetric efficiency of the second-stage pump exhibited a slight increase compared with those of the first-stage pump at varying inlet pressures. The oil flow rate and volumetric efficiency of the two-stage pump significantly declined with the reduction in inlet pressure. The oil flow rate and volumetric efficiency of the two-stage pump exhibited a significant decrease at flight altitudes below 8 km. With the increase of rotational speed, the decrease in oil flow rate and volumetric efficiency accelerated. The volumetric efficiency remained below 50% at all rotational speeds until reaching a flight altitude of 12 km.
- two-stage lubricating oil pump /
- ground performance /
- high-altitude performance /
- flow performance /
- volumetric efficiency

HTML

图 1 航空发动机滑油泵试验系统示意图

Figure 1. Schematic diagram of test system for lubricating oil pump in aero-engine

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图 2 滑油泵系统实物图

Figure 2. Physical diagram of lubricating oil pump system

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图 3 滑油泵内部结构示意图

Figure 3. Schematic diagram of the internal structure of lubricating oil pump

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图 4 出口压力对流量的影响规律

Figure 4. Influence law of outlet pressure on flow rate

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图 5 出口压力对容积效率的影响规律

Figure 5. Influence law of outlet pressure on volumetric efficiency

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图 6 出口压力对扭矩的影响规律

Figure 6. Influence law of outlet pressure on torque

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图 7 转速对流量和容积效率的影响规律

Figure 7. Influence law of rotational speed on flow rate and volumetric efficiency

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图 8 入口压力对流量的影响规律

Figure 8. Influence law of inlet pressure on flow rate

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图 9 入口压力对泵扭矩的影响规律

Figure 9. Influence law of inlet pressure on torque

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图 10 高空工况转速对流量的影响规律

Figure 10. Influence law of high-altitude rotational speed on flow rate

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图 11 转速对容积效率的影响规律

Figure 11. Influence law of rotational speed on volumetric efficiency

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图 12 高空转速对扭矩的影响规律

Figure 12. Influence law of high-altitude rotational speed on torque

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表 1 滑油泵设计参数

Table 1. Design parameters of lubricating oil pump

滑油级	设计转速范围/ （r/min）	入口压力/ kPa	出口压力/ kPa
第一级	1000～4014	100±3	<600
第二级	1000～4014	100±3	<600

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表 2 重复性试验工况

Table 2. Repetitive test conditions

转速/ （r/min）	各级入口压力/ kPa	出口压力/ kPa	滑油温度/ ℃
2890±10	100±3	300±10	60±3

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表 3 滑油流量计重复性试验结果

Table 3. Repeatability test results of lubricating oil flow meter

试验编号	第一级流量/（L/min）	第二级流量/（L/min）
1	29.95	29.86
2	29.92	29.74
3	29.86	29.69
4	29.84	29.61
5	29.80	29.56
6	28.79	29.46
均值	29.693	29.653
标准差	0.44585	0.14109
相对不确度/%	1.305	0.413

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表 4 不同出口压力试验工况表

Table 4. Test condition of variable outlet pressure

序号	转速/ （r/min）	入口压力/ kPa	滑油温度/ ℃	节流阀开度/ %
1	1003	100±3	60±3	10～100
2	2007
3	3890
4	3412
5	4014

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表 5 变转速试验工况表

Table 5. Variable rotational speed test condition

转速范围/ （r/min）	入口压力/ kPa	滑油温度/ ℃	出口压力/ kPa
1000～4000	100±3	60±3	不作调整

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表 6 高空特性试验工况表

Table 6. High-altitude performance test condition

飞行高度/ km	入口压力/ kPa	转速/ （r/min）	滑油温度/ ℃	出口压力/ kPa
0	101.325	1000～4000	60±3	不作调整
1	89.88
2	79.50
3	70.12
4	61.66
5	54.05
6	47.22
7	41.11
8	35.65
9	30.80
10	26.50
11	22.70
12	19.40

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表 7 高空变转速试验工况表

Table 7. High-altitude variable rotational speed test condition

转速/（r/min）	入口压力/kPa	滑油温度/℃	出口压力/kPa
1000～4000	20～100	60±3	不作调整

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