不同温控模式下直升机惰化系统性能对比

白文涛; 刘国田; 邹博; 王晨臣; 陈广豪; 冯诗愚

doi:10.13700/j.bh.1001-5965.2021.0073

不同温控模式下直升机惰化系统性能对比

doi: 10.13700/j.bh.1001-5965.2021.0073

1.
南京航空航天大学航空学院飞行器环境控制与生命保障工业和信息化部重点实验室, 南京 210016
2.
陆军航空兵研究所, 北京 101121
3.
中国航空工业集团有限公司南京机电液压工程研究中心航空机电系统综合航空科技重点实验室, 南京 211106

基金项目:

国家自然科学基金 U1933121

南京航空航天大学研究生创新基地（实验室）开放基金 kfjj20200110

中央高校基本科研业务费专项资金

江苏高校优势学科建设工程

详细信息

通讯作者:
冯诗愚, E-mail: shiyuf@nuaa.edu.cn

中图分类号: V37;V219
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出版历程
- 收稿日期: 2021-02-08
- 录用日期: 2021-05-04
- 网络出版日期: 2021-05-18
- 整期出版日期: 2022-10-20

Performance comparison of helicopter inerting system under different temperature control modes

1.
Key Laboratory of Aircraft Environmental Control and Life Support Industry and Information Technology, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
Army Aviation Research Institute, Beijing 101121, China
3.
Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration, Nanjing Engineering Institute of Aircraft Systems, Aviation Industry Corporation of China, Nanjing 211106, China

Funds:

National Natural Science Foundation of China U1933121

Nanjing University of Aeronautics and Astronautics Postgraduate Innovation Base (Laboratory) Open Fund kfjj20200110

The Fundamental Research Funds for the Central Universities

Priority Academic Program Development of Jiangsu Higher Education Institutions

More Information

Corresponding author: FENG Shiyu, E-mail: shiyuf@nuaa.edu.cn

摘要

摘要:
以某直升机机载中空纤维膜惰化系统为研究对象，设计了电控阀控温和变频风扇控温2种系统。基于AMESim平台以分离膜数学模型计算数据为基础，搭建机载惰化系统，在飞行包线下，研究了2种温控模式的控温效果、不同飞行阶段的惰化系统性能变化及关键参数对其影响。计算结果表明：电控阀控温系统在整个飞行过程均能将引气温度维持在目标温度90℃，在起飞之后富氮气体（NEA）氮体积分数全程维持在91.5%~96.4%之间，所需引气流量为40~243 kg/h，空载燃油箱气相空间氧体积分数可在180 s内降至9%，且保持全程低于9%；变频风扇控温系统在满足爬升、加速、俯冲高温阶段控温惰化要求的选型前提下，在低速、高速巡航阶段，引气被过度冷却至0℃左右，虽然所需引气流量低至26 kg/h，但NEA氮体积分数大幅下降至81%，燃油箱气相空间氧体积分数高达18%，在巡航阶段，飞行速度越大，引气温降越大，且巡航高度越低，为满足控温效果所需的最低巡航速度越低。
- 中空纤维膜惰化 /
- 燃油箱 /
- 飞行包线 /
- 温度控制 /
- 富氮气体(NEA)氮体积分数 /
- 氧体积分数
Abstract:
The airborne hollow fiber membrane inerting system of a helicopter is taken as the research subject.in this paper. Two temperature control systems using an electric valve and a frequency conversion fan have been designed. Based on the AMESim platform and the calculated data of the separation membrane mathematical model, an airborne inerting system was built. Under the flight mission, the temperature control effect of the two systems, the variation of the performance of the inerting system at different flight stages, and the influence of key parameters were all studied. The results show that: the system with an electronic valve can maintain the bleed air temperature at the desired level of 90℃ throughout the flight. After take-off, the nitrogen concentration of nitrogen enriched air (NEA) is maintained between 91.5%-96.4%, the required bleed air flow rate is maintained between 40 kg/h-243 kg/h, and the oxygen volume fraction on ullage can be reduced to 9% within 180 s and kept below 9% throughout the flight. Under the premise of the heat exchanger selection that meets the temperature control and inerting requirements during the high temperature stages such as climb, acceleration, and descent, the bleed air is overcooled to about 0℃ during the cruise stage of the system with the variable frequency fan, although the required bleed air flow rate dropped to 26 kg/h, the concentration of NEA is greatly reduced to 81%, and the oxygen volume fraction on ullage rose to 18%. The larger the flying speed, the greater the temperature drop of bleed air and the lower the cruising altitude, the lower the minimum cruising speed required to meet the temperature control effect are all valid during the cruise phase of the system with the variable frequency fan.
- hollow fiber membrane inerting /
- fuel tank /
- flight mission /
- temperature control /
- nitrogen molar concentration of nitrogen enriched air (NEA) /
- oxygen volume fraction

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图 1 控温系统示意图

Figure 1. Schematic diagram of temperature control system

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图 2 两种控温系统的AMESim模型

Figure 2. Two temperature control system models based on AMESim

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图 3 飞行高度、引气压力及引气温度随时间变化关系

Figure 3. Flight altitude, pressure and temperature of bleed air with time

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图 4 中空纤维膜模型准确性验证

Figure 4. Verification of accuracy of hollow fiber membrane

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图 5 不同温度、压力下的分离特性

Figure 5. Separation characteristics at different temperatures and pressures

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图 6 两种系统控温效果对比

Figure 6. Comparison of temperature control effect of two systems

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图 7 NEA氮体积分数随时间变化

Figure 7. Variation of N₂ volume fraction in NEA with time

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图 8 NEA流量、引气流量、分离效率随时间变化

Figure 8. Variation of NEA, bleed air flowrate and separation efficiency with time

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图 9 气相空间氧体积分数随时间变化

Figure 9. Variation of O₂ volume fraction on ullage with flight time

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图 10 风扇转速、马赫数、冲压空气流量随时间变化

Figure 10. Variation of rotational speed, Mach number and flow rate of bleed air with flight tim

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图 11 不同巡航高度、马赫数下的控温效果

Figure 11. Temperature control ability at different cruise altitude and Mach number

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图 12 不同巡航高度、马赫数下的冲压空气流量

Figure 12. Impressed flow rate of bleed air at different cruise altitude and Mach number

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表 1 换热器尺寸

Table 1. Size of heat exchanger

参数	电控阀控温系统	变频风扇控温系统
冷边流道当量直径/mm	1.12	1.083
热边流道当量直径/mm	0.583	0.56
冷边空气流通面积/mm²	11 773.1	5 616
热边空气流通面积/mm²	756	1 500.8
冷边对流换热面积/mm²	2 451 710	2 830 850
热边对流换热面积/mm²	1 703 810	2 126 850

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