实验流体力学2012，Vol.26Issue(5)：31-35,5.
民机涡扇发动机重吸入特性风洞试验
Wind tunnel test for turbo-fan engine re-ingestion characteristic of civil aircraft
李达新 1赵克良 1王奇志 1盛鸣剑 1黄勇 2张美红1
作者信息
- 1. 上海飞机设计研究院,上海201210
- 2. 中国空气动力研究与发展中心,四川绵阳 621000
- 折叠
摘要
Abstract
For civil aircraft it is common method to use thrust reverser to improve the deceleration and the safety during landing run. However, if the ground running speed of the aircraft is too low, the forward moving plume flow can be re-ingested by the engine. The temperature of the plume flow is much higher than ambient temperature since it gains energy from fan compressor. As a result the re-ingestion may lead to the temperature distortion for inlet flow causing the flutter of the fan blade, thus harming the engine life and safety. Therefore, for a new turbo-fan aircraft it is necessary to obtain the re-ingestion characteristic of the engine through wind tunnel test in order to determine the turn-off speed limit for thrust reverser. This paper mainly states the method to get the A/C's re-ingestion characteristics from the wind tunnel test and acquire the thrust reverser cut-off taxiing speeds.
关键词
重吸入/反推力/风洞试验/发动机Key words
re-ingestion/thrust reverser/wind tunnel test/engine分类
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李达新,赵克良,王奇志,盛鸣剑,黄勇,张美红..民机涡扇发动机重吸入特性风洞试验[J].实验流体力学,2012,26(5):31-35,5.
