结冰对直升机进气系统压力损失影响的试验研究及分析  

Analysis and Research on Icing Test for Pressure Loss of Air Intake System of Helicopter

作　　者：王先炜[1] 樊晓锋 林森什 陈彪 WANG Xianwei;FAN Xiaofeng;LIN Senshi;CHEN Biao(China Helicopter Research and Development Institute,Jingdezhen 333001,China;Xizang Military Area Aviation Maintenance Departmentalism,Lhasa 850000,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001 [2]西藏军区航空保障处,西藏拉萨850000

出　　处：《直升机技术》2021年第4期62-66,共5页Helicopter Technique

摘　　要：介绍了直升机发动机进气系统冰风洞摸拟结冰试验情况,对直升机发动机进气系统冰风洞模拟结冰试验结果和进气系统压力损失进行了分析。结冰试验结果表明,随着飞行速度的增加,进气系统结冰时进气压力损失有较大的增加。This paper introduced the icing test for engine air intake system of helicopter in icing win tunnel,analyzed icing test and air intake pressure loss for engine air intake system of helicopter in icing win tunnel.The icing test results showed that air intake pressure loss to become larger in the flight speed increase on the air intake system icing.This paper provided a reference for anti-icing design of engine air intake system of helicopter.

关 键 词：直升机 发动机进气系统 压力损失 冰风洞 结冰试验 

分 类 号：V211.753[航空宇航科学与技术—航空宇航推进理论与工程] V228.7