反推气流对大涵道比涡扇发动机进口流场影响的数值模拟研究  

Numerical simulation study on influence of reverser flow on high bypass ratio turbofan engine inlet flow field

作　　者：赵海刚[1] ZHAO Hai-gang(Engine Flight Test Technology Institute of Chinese Flight Test Establishment,Xi’an 710089,China)

机构地区：[1]中国飞行试验研究院发动机所

出　　处：《燃气涡轮试验与研究》2019年第6期20-25,35,共7页Gas Turbine Experiment and Research

摘　　要：以一架配装有叶栅式反推装置的四发飞机为研究对象,数值模拟了不同着陆滑跑速度下的反推气流全机扰流流场,分析了反推气流在机身附近分布随滑跑速度的变化特点,和对内、外侧发动机进口流场的影响。结果表明:随着着陆滑跑速度的减小,反推气流对机身周围的影响区域逐渐扩大。当滑跑速度小于0.10马赫(约122 km/h)时,内、外侧发动机均会吸入反推气流,在发动机进口形成总温、总压畸变。该型反推装置的临界使用速度约为122 km/h,在反推装置飞行试验设计时应着重在该速度附近验证反推装置与发动机的匹配性;发动机进口流场总温分布能反映出反推气流的重吸入特征,测量方案设计应重点考虑发动机进口温度场的测量。Based on a four-engine aircraft model with cascade thrust reverser,the thrust reverser flow fields under different taxing velocity conditions during the landing process were obtained using numerical simula⁃tion.The analysis of the reverser flow distribution around the fuselage and the effect on the inlet flow of both inboard and outboard engine indicates that with the decrease of taxing velocity,the influence region of the re⁃verser flow keeps increasing.When the velocity decreases below Mach number 0.10(about 122 km/h),both in⁃board and outboard engine will ingest reverser flow and this will result in pressure and temperature distor⁃tion on the inlet face of the engines.The critical velocity of the thrust reverser is about 122 km/h,and the design of the thrust reverser flight test should assess the compatibility of the thrust reverser and the engine near that velocity.The total temperature field of the engine inlet can represent the feature of the reverser flow reingestion,so the total temperature field measurement is one major consideration in the measurement scheme design.

关 键 词：航空发动机 叶栅式反推装置 数值模拟 温度畸变 压力畸变 临界使用速度 飞行试验 

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]