基于适航符合性的短舱风扇一体化迎角与侧风特性  

Integrated attack angle and crosswind characteristics of nacelle-and-fan based on airworthiness compliance

作　　者：傅文广 郭重佳 孙鹏 陶立权 FU Wenguang;GUO Chongjia;SUN Peng;TAO Liquan(College of Safety Science and Engineering,Civil Aviation University of China,Tianjin 300300,China;Marine Engineering College,Dalian Maritime University,Dalian Liaoning 116026,China)

机构地区：[1]中国民航大学安全科学与工程学院,天津300300 [2]大连海事大学轮机工程学院,辽宁大连116026

出　　处：《航空动力学报》2024年第3期77-89,共13页Journal of Aerospace Power

基　　金：天津市多元投入基金项目青年项目(21JCQNJC00930)。

摘　　要：以某小型涡扇发动机为研究对象,采用数值模拟方法对0°、15°、25°迎角和±10、±20、±30 m/s的90°横向侧风条件下短舱风扇一体化的特性及流场进行研究。结果表明:随着迎角的增大,相同风速条件下逆向侧风对短舱进气道和风扇性能的负面影响更大,依据机动性、风速和喘振/失速特性的适航条款要求,得到迎角为25°时,短舱风扇一体化性能可承受的正、逆向侧风范围分别约为0~23 m/s和0~18 m/s,相应得到侧风速度为±30 m/s时,所允许的机动迎角范围分别约为0°~3°和0°~2°。By taking turbofan engine as the research object,the characteristics and flow field of nacelle and fan integration under the conditions of 0°,15°,25°attack angle and 90°crosswind of±10,±20 m/s and±30 m/s were studied by numerical simulation.The results showed that with the increase of attack angle,the negative effect of the reverse crosswind on the performance of the nacelle inlet and fan was greater under the same wind speed.According to the airworthiness clause requirements of maneuverability,wind speed and surge/stall characteristics,when the attack angle was 25°,the forward and reverse crosswind ranges that the nacelle and fan integration performance can withstand were about 0−23 m/s and 0−18 m/s,respectively,and when the crosswind speed was±30 m/s,the allowable maneuvering attack angle ranges were about 0°−3°and 0°−2°,respectively.

关 键 词：进气畸变 喘振/失速 短舱进气道 风扇 适航符合性 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]