火焰稳定器修形对发动机后向RCS的影响  

Influence of Flame Stabilizer Modification on Aero-engine Backward RCS

作　　者：姚伦标 杜凯 李宁 张琪 于明飞 YAO Lunbiao;DU Kai;LI Ning;ZHANG Qi;YU Mingfei(AECC Guiyang Engine Research Design Institute,Guiyang 550081,China)

机构地区：[1]中国航发贵阳发动机设计研究所,贵阳550081

出　　处：《南京航空航天大学学报》2021年第4期570-577,共8页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：基于某简化的排气腔体静态雷达散射截面积(Radar cross section,RCS)测试结果,分析了稳定器采用吸波材料后对发动机后向RCS的缩减效果;在不改变加力燃烧室传统结构基础上,针对现有某型稳定器结构从隐身修形设计角度建立了5种不同稳定器蒸发腔简化腔体RCS计算模型,分别在高频10 GHz、低频1.5 GHz下对比分析了不同稳定器蒸发腔结构的RCS特征、稳定器倾斜布置对腔体RCS的影响。结果表明:传统非隐身一体化设计的排气腔体结构中,高频下稳定器采用隐身措施后的RCS缩减效果显著;几种针对稳定器蒸发管式蒸发腔结构的修形设计,均能在高频下带来一定的RCS缩减收益,低频下缩减不明显;具有横向及纵向复合倾斜的平板结构蒸发腔较其他结构的RCS缩减效果好,同时可改善功能材料的使用工况,提高其使用可靠性;稳定器在0°~20°倾斜布置对后向腔体RCS有一定抑制作用。Based on a certain aero-engine simplified exhaust cavity radar cross section(RCS)test results,the contribution of the stabilizer taking the reduction measures to the engine’s rearward cavity RCS is analyzed.Based on the traditional structure of the afterburner,the simplified cavity RCS calculation models of five different stabilizer evaporation chambers are established for the existing structure.The RCS characteristics of different stabilizer evaporation chamber structures are compared at high frequency 10 GHz and low frequency 1.5 GHz.The results show that,in the traditional non-stealth integrated design of the exhaust cavity structure,the stabilizer can achieve an obvious reduction effect of RCS at high frequency after adopting stealth measures.Several kinds of modified design for the structure of evaporation chamber of the flame stabilizer can bring a certain reduction benefit at high frequency,and the reduction at low frequency is not obvious.The flat structure with transverse and longitudinal composite angle inclination(WDQ5)has better improvment on RCS reduction than other structure,and can improve the working condition of absorbing coating and its reliability.Stabilization of the stabilizer at 0°-20°has a certain inhibitory effect on the RCS of the backward cavity.

关 键 词：航空发动机隐身 火焰稳定器 迭代物理光学法 雷达散射截面积 雷达仿真 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]