基于气候实验室的民机整机发动机低温启动实验

马建军; 吴敬涛; 杜文辉; 王嘉玺; 都亚鹏

doi:10.13224/j.cnki.jasp.20220163

基于气候实验室的民机整机发动机低温启动实验

doi: 10.13224/j.cnki.jasp.20220163

中国航空工业集团有限公司中国飞机强度研究所全尺寸飞机结构静力/疲劳航空科技重点实验室，西安 710065

基金项目: 基础科研（JCKY2020205B029）

详细信息

作者简介:
马建军（1989-），男，高级工程师，硕士，主要从事飞机气候环境适应性分析与实验技术研究

中图分类号: V216.5
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- 被引次数: 0
出版历程
- 收稿日期: 2022-03-28
- 网络出版日期: 2023-09-25

Full scale civil aircraft engine cold start experiment in climatic environmental test laboratory

Key Laboratory of Aeronautical Science and Technology for Static/Fatigue of Full-Size Aircraft Structures，China Aircraft Strength Research Institute， Aviation Industry Corporation of China，Limited， Xi’an 710065，China

摘要

摘要:
为解决在密闭大型气候实验室极端低温环境下，进行民机整机发动机低温启动实验带来的强扰动和安全性问题，基于实验室现有能力条件，从发动机尾气排放和极端低温空气补偿两方面开展了民机整机发动机低温启动实验技术研究。对于发动机尾气排放，提出了针对大涵道比涡扇发动机的尾气“分割排放”概念和排放质量流量预估方法，降低了从实验室排放的低温空气质量流量。对于空气补偿，采用液氮作为冷源将实验室外常温空气冷却至极端−50 ℃低温并持续补充进实验室，补偿排放损失、维持实验室内低温环境稳定和室内外压力平衡，保障实验安全。基于该项技术，在国内首次成功实施了民机整机−40 ℃发动机低温启动适航符合性实验，实验结果表明：飞机低温冷浸时间10 h，实验全过程室内温度波动在±3 ℃以内；与常温下相比发动机启动功能和性能无明显衰减。该项实验的成功为其他民机在实验室内开展发动机低温启动实验和相关适航标准规范的制定提供了实践依据和技术储备。
- 气候实验室 /
- 民机整机 /
- 冷浸透 /
- 大涵道比涡扇发动机 /
- 低温启动
Abstract:
In order to solve the strong disturbance and safety problems caused by the extreme low temperature start up experiment of the full-scale civil aircraft engine in the closed large climatic environmental test laboratory, based on existing capabilities of the laboratory, the aircraft engine cold start experiment technology was developed from two aspects: engine exhaust gas discharge and low temperature air make-up. In the aspect of engine exhaust gas discharge, a concept of “split discharge” and a discharge air flow rate estimation method for high bypass ration turbofan engines were proposed, which reduced the low temperature air flow discharged from the laboratory. In the aspect of low temperature air make-up, liquid N₂ was used as a cold source to cool down the normal temperature air outside the laboratory to extremely low temperature of −50 ℃ and continuously replenish it into the laboratory to make up for discharge losses, and maintain the stability of the low temperature environment in the laboratory and the balance of indoor and outdoor pressure for the experiment safety. For the first time in China, the airworthiness compliance experiment of the full-scale civil aircraft at −40 ℃ engine low temperature startup was successfully carried out. The experiment result showed that: the aircraft cold soak time continued 10 h and the experimental temperature fluctuated within ±3 ℃ during the whole experiment process; compared with normal temperature, the engine starting function and performance had no obvious degradation. The success of this experiment has provided a practical basis and technical reserve for other full-scale civil aircraft to carry out engine cold start experiment in the laboratory and formulate relevant airworthiness standards and specifications.
- climatic environmental test laboratory /
- full scale civil aircraft /
- cold soak /
- high bypass ratio turbofan engine /
- cold start

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图 1 A350XWB飞机在麦金利实验室气候环境实验

Figure 1. A350XWB climatic test in McKinley Climatic laboratory

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图 2 我国大型综合气候实验室

Figure 2. Large climatic test laboratory in China

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图 3 发动机尾气分割排放

Figure 3. Split discharge of engine exhaust gas

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图 4 排放流量ṁ_e与管道直径d和背压P_b的关系

Figure 4. Relationship of discharged mass flow rate ṁ_e, tube dimension d and back pressure P_b

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图 5 临界背压与管道直径的关系

Figure 5. Relationship of critical back pressure P_bc and tube dimension d

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图 6 发动机尾气分割排放计算模型

Figure 6. Geometrical model of engine exhaust gas split discharge

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图 7 网格划分

Figure 7. Mesh grid

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图 8 排放管道对发动机的影响

Figure 8. Effects of the dicharge tube on the engine

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图 9 自然状态尾气流动分布

Figure 9. Engine exhaust gas flow distribution in the free state

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图 10 自然状态L_tube=400 mm处径向位置尾气速度和温度

Figure 10. Velocity and temperature at radial position for L_tube=400 mm in the free state

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图 11 L_tube=400 mm、d=0.97 m排放参数理论与CFD对比

Figure 11. Theoretical and CFD discharge parameters for L_tube=400 mm and d=0.97 m

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图 12 尾气排放系统示意图

Figure 12. Schematic diagram of engine exhaust gas discharge system

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图 13 空气补偿系统原理图

Figure 13. Schematic diagram of air make-up system

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图 14 液氮-空气换热器

Figure 14. Liquid N₂-air heat exchanger

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图 15 液氮换热器冷却调试结果

Figure 15. Cooling results of the liquid N₂ heat exchanger in equipment debugging

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图 16 空气补偿系统布局

Figure 16. Layout of the air make-up system

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图 17 发动机启动时实验室内气流分布

Figure 17. Air distribution in the chamber during engine starting

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图 18 温度传感器布置

Figure 18. Location of the temperature sensors

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图 19 冷浸过程实验温度曲线

Figure 19. Experimental temperature during cold soak

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图 20 发动机启动实验期间的实验温度

Figure 20. Experimental temperature during engine starting

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图 21 发动机高温尾气排放红外成像

Figure 21. Infrared image of engine exhaust gas

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图 22 发动机启动及慢车时尾气排放系统参数

Figure 22. Patameters of the gas discharge system during engine starting and idle state

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图 23 常温与低温发动机启动参数对比

Figure 23. Engine starting partameters in room and cold temperatures

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表 1 某民机发动机主要参数

Table 1. Main parameters of certain civil aircraft engine

参数	数值或说明
T_a/℃	−40	−40	−40
状态	慢车	30%N₁	89%N₁
ṁ_in/（kg/s）	139.7	218.0	594.3
ṁ_s/（kg/s）	130.4	202.4	539.1
T_ts/℃	−38.0	−35.9	−10.9
ṁ/（kg/s）	8.0	14.2	53.5
T_t/℃	367.5	267.7	382.7

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