反推力装置对民航飞机减速性能影响

黄敬杰; 张鑫; 孟超; 田琦楠; 徐丹

doi:10.13224/j.cnki.jasp.20210215

反推力装置对民航飞机减速性能影响

doi: 10.13224/j.cnki.jasp.20210215

中国航发沈阳发动机研究所，沈阳 110015

基金项目: 中国国家留学基金（201905345024）

详细信息

作者简介:
黄敬杰（1987-），女，工程师，硕士，主要从事反推力装置与飞发一体化研究。E-mail：jie0129@126.com

中图分类号: V231
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出版历程
- 收稿日期: 2021-05-07
- 网络出版日期: 2023-02-10

Effect of thrust reverser on the deceleration performance of civil aircraft

Shenyang Engine Research Institute， Aero Engine Corporation of China，Shengyang 110015，China

摘要

摘要:
为评估反推力装置提供的反向推力与其结构件质量增加对民航飞机减速性能的综合影响，借助克兰菲尔德大学发动机总体性能仿真软件Turbomatch，参考CFM56发动机建立正、反推力状态发动机模型，并以A320飞机为配装对象开展研究。将风扇及涡轮直径做为特征参数，完成推进系统质量的初步估算。对比飞机在干燥跑道及雨雪条件下常规着陆过程中滑跑距离及减速时间，完成反推排气角度、跑道条件等影响因素对反推力装置提升飞机减速性能收益分析。研究表明：配装反推力装置轴向排气角度越小，飞机减速性能更加。以55°排气角度为基础，减小10°的排气角度可带来约7%的减速收益。反推力装置在湿滑跑道的减速收益更大，比干燥跑道滑跑距离缩短约41%，滑跑时间缩短32%。
- 着陆减速距离 /
- 减速时间 /
- 反推力装置 /
- 涡扇发动机 /
- 排气角度
Abstract:
The combined effect of the reverse thrust and weight increase of the thrust reverser on the deceleration performance of a civil aircraft was analyzed. A hypothetical turbofan model based on the CFM56 engine was established by Turbomatch software from Cranfield University, with A320 aircraft taken as the model. The propulsion system weight was estimated using the fan and turbine diameter. After discussion of aircraft deceleration benefit on the dry runway or icy runway, effects of the deflection angle and runway condition on the deceleration distance during conventional landing phase were analyzed. It showed that the thrust reversers were more efficient with small deflection angel. Based on a deflection angle of 55°, 10° reduction resulted in a deceleration benefit of approximately 7%. And the thrust reversers were more beneficial on the wet/icy runway, with the distance and time down by about 41% and 32% compared with the dry runway.
- landing deceleration distance /
- deceleration time /
- thrust reverser /
- turbofan /
- deflection angle

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图 1 着陆过程发动机状态及刹车使用状态

Figure 1. Engine power and breaking system condition during landing phase

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图 2 发动机模型

Figure 2. Engine model components

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图 3 风扇工作点（反推力装置展开）

Figure 3. Fan operating points （thrust reverser deployed）

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图 4 反推力装置排气角度

Figure 4. Deflection angle of thrust reverser

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图 5 发动机推力

Figure 5. Engine thrust

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图 6 着陆减速过程受力分析

Figure 6. Forces during landing deceleration

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图 7 排气角度影响

Figure 7. Effect of deflection angle

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图 8 跑道条件的影响

Figure 8. Effect of runway condition

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表 1 常规着陆发动机状态

Table 1. Engine power condition during landing

速度/（km/h）	配装反推		配装喷管
速度/（km/h）	反推状态	发动机状态	发动机状态
0	收起	慢车	慢车
60	收起	慢车	慢车
110	收起	慢车	慢车
110	展开	最大反推	慢车
120	展开	最大反推	慢车
180	展开	最大反推	慢车
245	展开	最大反推	慢车
260	展开	最大反推	慢车

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表 2 发动机性能参数

Table 2. Engine performance parameters

发动机参数	起飞	慢车	最大反推
发动机流量/（kg/s）	408.1	129.09	370.63
净推力/kN	120.71	11.68	−31.65
耗油率/（g/（kN·s））	8.46	10.01	7.88
涵道比	5.7	7.07	6.16
风扇压比	1.64	1.07	1.54
总压比	27.64	5.5	22.43
涡轮前温度/K	1390	800	1270

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表 3 着陆质量

Table 3. Landing weight

项目	配装组件	质量/kg	增加量/%
推进系统质量	配装喷管	3106	12.0
推进系统质量	配装反推	3478	12.0
飞机总着陆质量	配装喷管	64500	1.2
飞机总着陆质量	配装反推	65243	1.2

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表 4 着陆减速距离与时间

Table 4. Landing deceleration distance and time

参数	滑跑距离/m	反推使用时间/s
A320着陆计算值	1410	17.47
A320着陆实际值	1490	18.00
偏差/%	5.35	2.93

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