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
傅文广 1郭重佳 2孙鹏 1陶立权1
作者信息
- 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
- 折叠
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、±30m/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0～23m/s和0～18m/s,相应得到侧风速度为±30m/s时,所允许的机动迎角范围分别约为0°～3°和0°～2°.
Abstract
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Key words
inlet distortion/surge/stall/nacelle inlet/fan/airworthiness compliance引用本文复制引用
基金项目
天津市多元投入基金青年项目(21JCQNJC00930)
出版年
2024
NETL
NSTL
万方数据