小型航空活塞二冲程发动机增压匹配及试验验证

沈晓晨; 董雪飞; 赵振峰; 白鹏

doi:10.13224/j.cnki.jasp.20240332

小型航空活塞二冲程发动机增压匹配及试验验证

doi: 10.13224/j.cnki.jasp.20240332

沈晓晨^1,,
董雪飞^{1, 3,*, ,},
赵振峰²,
白鹏³

1.
山西工程职业学院电气工程系，太原 030027
2.
北京理工大学机械与车辆学院，北京 100081
3.
北京航天无人机系统工程研究所，北京 100094

详细信息

作者简介:
沈晓晨（1985-），女，高级工程师，硕士，从事航空动力控制系统开发。E-mail：hmilylucky@126.com

通讯作者:
董雪飞（1985-），男，研究员级高级工程师，博士，从事航空动力总体设计开发。E-mail：04021410dyf@163.com

中图分类号: V234；TK411.8
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出版历程
- 收稿日期: 2024-05-23
- 网络出版日期: 2024-12-05

Turbocharging matching and experimental validation for small aviation two-stroke piston engine

SHEN Xiaochen^1
,,
DONG Xuefei^{1, 3,*
, ,},
ZHAO Zhenfeng²,
BAI Peng³

1.
Department of Electrical Engineering，Shanxi Engineering Vocational College，Taiyuan 030027，China
2.
School of Mechanical Engineering，Beijing Institute of Technology，Beijing 100081，China
3.
Beijing Aerospace UAV System Engineering Research Institute，Beijing 100094，China

摘要

摘要:
针对近程无人机高空动力衰减明显的问题开展二冲程航空活塞发动机增压技术研究。综合分析该技术在无人机平台的工程实际应用，提出了采用进气稳压、排气谐振、自润滑废气涡轮增压系统及闭环自适应控制系统的二冲程增压技术方案；建立了某二冲程增压发动机一维仿真模型；采用DOE（design of experiment）试验方法完成了进排气系统关键参数耦合关系分析，获得了最佳的进气稳压和排气谐振系统结构参数，并在不同海拔下进行了进排气增压系统增压匹配计算，增压前后在8 000 m海拔下的功质比由0.59 kW/kg提升至0.96 kW/kg；并依托某无人机平台对该技术方案进行了飞行试验验证，试验结果表明：最大飞行高度突破8 367 m，同等条件下较增压前提高了85%以上，二冲程增压技术高空动力性优势明显。
- 近程无人机 /
- 二冲程增压技术 /
- 进气稳压 /
- 排气谐振 /
- 增压匹配 /
- 飞行验证
Abstract:
In order to solve the dramatic power coastdown of short-range unmanned aerial vehicles at high altitudes, a turbocharging two-stroke aviation piston engine was studied. Based on comprehensive analysis of the turbocharging technology application in the unmanned aerial vehicle platform, a technical scheme including an intake pressure stabilizing system, an exhaust resonant system, a self-lubricating turbocharging system and a closed-loop adaptive control system, was proposed. A one-dimensional simulation model was established and calibrated for a turbocharging two-stroke engine. The DOE (design of experiment) test method was used to complete the coupling relationship analysis of the key parameters of the intake and exhaust system, and the best structural parameters of the intake pressure stabilizing system and exhaust resonance system were obtained. And the coupling and matching of the turbocharging system with the engine performance was performed. At an altitude of 8000 m the power-to-mass ratio before and after supercharging increased from 0.59 kW/kg to 0.96 kW/kg; and the proposed technical scheme was estimated through a flight test of a unmanned aerial vehicle platform. The results showed that, the maximum flight height exceeded 8367 m, which was 85% higher than that without this scheme. The two-stroke supercharging technology has obvious advantages in high-altitude power.
- short-range unmanned aerial vehicle /
- two-stroke supercharging technology /
- intake pressure stabilization system /
- exhaust resonance /
- turbocharger matching /
- flight validation

HTML

图 1 废气涡轮增压器剖面图

Figure 1. Turbocharger sectional view

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图 2 恒压涡轮增压系统示意图^[20]

Figure 2. Constant pressure turbocharging system diagram^[20]

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图 3 CFD仿真模型

Figure 3. CFD simulation model

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图 4 发动机扫气曲线

Figure 4. Engine scavenging curve

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图 5 试验台架总体布置图

Figure 5. General arrangement of the engine test bench

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图 6 仿真模型校验

Figure 6. Simulation model validation

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图 7 二冲程增压发动机一维仿真模型

Figure 7. 1D simulation model of a two-stroke supercharged engine

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图 8 二冲程发动机排气谐振结构示意图

Figure 8. Schematic diagram of exhaust resonance structure of two-stroke engine

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图 9 进气稳压腔容积对发动机功率的影响

Figure 9. Effect of the volume of the intake regulator chamber on the engine power

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图 10 排气谐振结构参数对发动机功率的影响

Figure 10. Effect of exhaust resonant structural parameters on engine power

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图 11 排气总长与发动机功率的关系

Figure 11. Relationship between the total length of the exhaust and the engine power

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图 12 排气系统三维结构示意图

Figure 12. 3D structure of exhaust system

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图 13 发动机与废气涡轮增压器联合运行曲线

Figure 13. Combined running curves of engine and turbocharger

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图 14 三款发动机仿真结果对比

Figure 14. Comparison of simulation results of three engines

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图 15 三款发动机搭载飞行试验情况

Figure 15. Flight test situation of three engines

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图 16 搭载增压发动机的飞行高度与爬升率情况

Figure 16. Flight altitude and climb rate of supercharged engine

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表 1 发动机主要结构参数

Table 1. Basic parameters of engine

参数	数值及说明
排量/mL	626
缸径/mm	76
行程/mm	69
几何压缩比	10.6
扫气方式	曲轴箱扫气
扫气口开	123.7°（上止点后）
扫气口关	251°（上止点后）
排气口开	94.4°（上止点后）
排气口关	272.5°（上止点后）

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表 2 进气、排气谐振结构参数初始值设置

Table 2. Initial value setting of intake and exhaust structure parameters

进气、排气谐振结构参数	初始值
进气稳压腔容积V/L	2
排气歧管长度L₁/mm	130
排气管扩张段入口直径D₁/mm	55
排气管扩张段出口直径D₂/mm	110
排气管扩张段长度L₂/mm	300
排气管稳压段长度L₃/mm	400
排气管收缩段长度L₄/mm	150
排气尾管长度L₅/mm	100

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表 3 排气系统结构参数DOE试验各自变量取值

Table 3. DOE test variable settings for exhaust system structural parameters

自变量	水平1	水平2	水平3	水平4	水平5	水平6
D₁/mm	40	45	50	55	60	65
D₂/mm	75	85	95	105	115	125
L₁/mm	70	85	100	115	130	145
L₂/mm	240	280	320	360	400	440
L₃/mm	300	320	340	360	380	400
L₄/mm	150	160	170	180	190	200
L₅/mm	50	70	90	110	130	150

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表 4 进排气系统结构参数DOE试验最优结果

Table 4. Optimal results of DOE test of structural parameters of intake and exhaust system

试验号	水平值							功率/kW
试验号	D₁	D₂	L₁	L₂	L₃	L₄	L₅	功率/kW
19	4	1	2	3	4	5	6	36.73
25	5	1	2	3	4	5	6	37.08
31	6	1	2	3	4	5	6	37.33

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表 5 排气系统结构参数DOE试验点

Table 5. DOE test point of exhaust system structural parameters mm

工况	D₀	D₁	D₂
1, 7, 13, 19, 25, 31, 37, 43, 49	40	48	105
2, 8, 14, 20, 26, 32, 38, 44, 50	45	54	115
3, 9, 15, 21, 27, 33, 39, 45, 52	50	60	130
4, 10, 16, 22, 28, 34, 40, 46, 52	55	66	145
5, 11, 17, 23, 29, 35, 41, 47, 53	60	72	155
6, 12, 18, 24, 30, 36, 42, 48, 54	65	78	170

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表 6 三款发动机性能参数

Table 6. Three engine performance parameters

方案	地面实测功率/kW	净质量/kg	排量/mL
626 mL自吸	32	18.6	626
626 mL增压	51	31.	626
996 mL自吸	55	32	996

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