航空活塞发动机高空水冷系统研究

田亚明; 李茂强; 孙鹏晖; 吴玉平

doi:10.13224/j.cnki.jasp.20240300

航空活塞发动机高空水冷系统研究

doi: 10.13224/j.cnki.jasp.20240300

1.
北京科技职业大学航空工程学院，北京 100176
2.
中国航天空气动力技术研究院彩虹无人机科技有限公司，北京 100074
3.
重庆宗申航空发动机制造股份有限公司，重庆 401321

基金项目: 某型无人机作战能力提升研制项目（LZX2022005）

详细信息

作者简介:
田亚明（1992-），男，工程师，硕士，主要从事航空活塞发动机高空热管理研究。E-mail：zght6532@163.com

通讯作者:
李茂强（1984-），男，高级工程师，硕士，主要从事无人机总体设计。E-mail：15101050805@163.com

中图分类号: V233.5
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出版历程
- 收稿日期: 2024-05-12
- 网络出版日期: 2025-11-27

Study on water cooling system performance of aviation piston engines at high altitude

1.
College of Aviation Engineering，Beijing Polytechnic University，Beijing 100176，China
2.
Caihong Unmanned Aerial Vehicle Technology Company Limited，China Academy of Aerospace Aerodynamics，Beijing 100074，China
3.
Chongqing Zonsen Aero Engine Manufacturing Company Limited，Chongqing 401321，China

摘要

摘要:
为了提高航空活塞发动机的高空性能，从换热器一维理论校核计算、风道-换热器联合仿真、换热器地面台架试验、飞行试验4个方面开展了设计研究工作。利用效能-传热单元数法（ε-NTU）开展一维理论计算，提出了冷侧混合系数（η）概念，表示由翅片开窗导致的空气侧混合程度，并完成了换热器选型校核；搭建换热器地面试验台架，分析了换热器迎风面进风温度对发动机缸头温度的影响；利用风道-换热器联合仿真模型，开展了高空发动机出水温度预测，并完成飞行试验验证。研究结果表明：换热器迎风面进风温度直接影响发动机的缸头温度，且各缸头温度增大幅度与进风温度增大幅度基本一致。经飞行试验校核，风道-换热器联合仿真模型预测发动机缸头温度误差小于3.1%，能够满足工程计算要求。当风道-换热器联合设计结果可以满足无人机最高海拔起飞状态散热需求时，则发动机水冷系统设计可满足无人机全爬升工况使用需求。
- 航空活塞发动机 /
- 换热器 /
- 理论计算 /
- 联合仿真 /
- 高空散热 /
- 飞行试验
Abstract:
In order to improve the high-altitude performance of aviation piston engines, detailed design and research work were carried out from four aspects: one-dimensional theoretical verification calculation of heat exchanger, performance experiment, simulation of heat exchanger with air duct and UAV flight experiment. The one-dimensional theoretical calculation was carried out using the ε-NTU method. The concept of cold side mixing coefficient (η) was proposed, which represented the degree of air side mixing caused by the opening of fins. And the selection and verification of heat exchanger were completed; an engine ground performance experiment bench was built and the impact of the upwind temperature of the heat exchanger on the engine cylinder head temperature was analyzed. Besides, a joint simulation model of heat exchanger with air duct was used to predict the high-altitude effluent temperature of the engine, and flight experiment validation was completed. The results indicated that the temperature of the windward surface of the heat exchanger affected the engine cylinder head temperature directly, and the increase of cylinder head temperature was basically consistent with the increase of windward temperature. Validated by flight tests, the coupled simulation model for the air duct and heat exchanger exhibits a prediction error of less than 3.1% in terms of the engine cylinder head temperature, which is sufficient to meet the accuracy requirements for engineering calculations. If the joint design results of the heat exchanger with air duct can meet the heat dissipation requirements of engine at the highest altitude take off state, the engine water cooling system design can meet the full climbing usage requirements of UAV.
- aviation piston engine /
- heat exchanger /
- theoretical calculations /
- joint simulation /
- high altitude heat exchange /
- flight experiment

HTML

图 1 换热器外形图

Figure 1. Appearance of heat exchanger

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图 2 理论计算与试验结果对比

Figure 2. Comparison of theoretical calculation and experimental results

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图 3 进气风道外型

Figure 3. Appearance of intake air duct

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图 4 不同网格数量级下出口水温计算结果

Figure 4. Calculation results of outlet water temperature at different grid scales

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图 5 风道-换热器网格

Figure 5. Air duct-heat exchanger grid

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图 6 风道-换热器变形网格

Figure 6. Air duct-heat exchanger deformation grid

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图 7 台架原理图

Figure 7. Schematic diagram of experiment bench

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图 8 冷却液工作流程图

1 水泵；2 缸体+缸头；3 油冷器；4 膨胀壶 (0.17 MPa压力阀盖)；5 溢流瓶；6 节温器；7 水冷器。

Figure 8. Cooling fluid workflow diagram

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图 9 风速仪布置位置

Figure 9. Layout position of the anemometer

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图 10 缸头温度随换热器迎风温度的变化

Figure 10. Variation of cylinder head temperature with the upwind temperature of the heat exchanger

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图 11 计算温度与试验结果对比

Figure 11. Comparison of calculated temperature and experimental results

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图 12 风道-换热器安装位置

Figure 12. Installation position of air duct-heat exchanger

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图 13 爬升工况下缸头温度的变化情况

Figure 13. Variation of cylinder head temperature during climbing

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图 14 不同高度下飞行试验与仿真缸头温度对比

Figure 14. Cylinder head temperature comparison between flight experiment and simulation at different altitudes

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表 1 典型剖面边界条件

Table 1. Typical profile boundary conditions

参数	高度/km
参数	0	1	5	8
进风温度/℃	40	33.5	7.5	−12
来流速度/（m/s）	30	31.9	39.1	45.5
水流量/（L/min）	80	80	80	75
散热功率需求/kW	42	41	41	39

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表 2 计算结果输出

Table 2. Output of calculation results

参数	高度/km
参数	1	5	8
进风温度/℃	33.5	7.5	−12
来流速度/（m/s）	31.9	39.1	45.5
水流量/（L/min）	80	80	75
入水温度/℃	110	110	110
散热功率/kW	44.7	50.8	52.1
出水温度/℃	100.9	99.7	98.8

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表 3 换热器背风侧风速

Table 3. Leeward velocity of heat exchanger m/s

序号	Y₁	Y₂	Y₃
X₁	11.7	11.3	14.0
X₂	10.9	10.6	13.2
X₃	9.3	9.7	8.5

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表 4 115%油门开度、5800 r/min工况下试验结果

Table 4. Experimental results of the working condition with 115% throttle and 5800 r/min

参数	设定迎风温度/℃
参数	35	40	45
实际温度/℃	35.2	41.3	44.6
风机转速/（r/min）	1500	1500	1500
出水压力/kPa	97.5	109	117.7
发动机出水温度/℃	103.4	108.8	111.9
出水温度标准差σ₁/℃	0.31	0.53	0.35
发动机入水温度/℃	94.2	99.9	102.9
入水温度标准差σ₂/℃	0.21	0.37	0.23

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