基于适航标准的短舱进气道迎角特性数值研究  

Numerical study on attack angle characteristics of nacelle inlet based on airworthiness standard

作　　者：白杰[1] 郭重佳 傅文广 孙鹏 BAI Jie;GUO Chongjia;FU Wenguang;SUN Peng(College of Aeronautical Engineering,CAUC,Tianjin 300300,China;College of Safety Science and Engineering,CAUC,Tianjin 300300,China)

机构地区：[1]中国民航大学航空工程学院,天津300300 [2]中国民航大学安全科学与工程学院,天津300300

出　　处：《中国民航大学学报》2023年第1期1-6,34,共7页Journal of Civil Aviation University of China

基　　金：中央高校基本科研业务费专项(3122019170);中国民航大学科研启动基金项目(2020KYQD34)。

摘　　要：为研究运输类飞机在爬升阶段因大迎角造成短舱进气道内流动分离对进气性能产生的影响,以大涵道比涡扇发动机DGEN380的短舱进气道为研究对象,对其在0°~40°飞行迎角情况下的流场进行数值模拟,发现飞行迎角增大引起短舱进气道内低动量流体堆积和气流分离是引起总压畸变的主要原因。研究结果表明:随着飞行迎角增大,总压恢复系数减小,进气畸变指数增大;在28°~40°飞行迎角范围内,因气流在进气道内发生不同程度的分离,总压恢复系数和进气畸变指数对飞行迎角和马赫数的变化更加敏感,且在该范围内,同一飞行迎角情况下,马赫数越大,气流越容易发生分离。In order to study the effect of flow separation in the nacelle inlet caused by high attack angle of transport aircraft during climbing stage on the intake performance,the nacelle inlet of large bypass ratio turbofan engine DGEN380 is taken as the research object.The flow field at 0°-40°attack angle is simulated respectively.It is found that the low momentum fluid accumulation and flow separation in the nacelle inlet caused by the increase of attack angle are the main reasons for the total pressure distortion.The results show that with the increase of attack angle,the total pressure recovery coefficient decreases and the inlet distortion index increases.In the range of 28°-40°attack angle,the total pressure recovery coefficient and inlet distortion index are more sensitive to the changes of angle of attack(AOA)and Mach number due to different intensity of separation of air flow in the nacelle inlet.In this range,at the same attack angle,the greater the Mach number,the easier the separation of flow.

关 键 词：短舱进气道 迎角特性 进气畸变 适航标准 数值模拟 

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]