反推改型气动矢量喷管设计及数值模拟  

Design and numerical simulation of a fluidic vectoring nozzle with thrust reverser

作　　者：张玉顶 徐惊雷[1,2] 潘睿丰 张玉琪 黄帅 ZHANG Yuding;XU Jinglei;PAN Ruifeng;ZHANG Yuqi;HUANG Shuai(State Key Laboratory of Mechanics and Control for Aerospace Structures,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院 [2]南京航空航天大学航空航天结构力学及控制全国重点实验室

出　　处：《航空动力学报》2024年第12期78-93,共16页Journal of Aerospace Power

基　　金：国家科技重大专项(2019-Ⅱ-0007-0027);基础加强计划项目(2022-JCJQ-ZD-115-00);基础科研计划资助(JCKY2019605D001);先进航空动力创新工作站(HKCX2020-02-011);江苏省“卓博计划”。

摘　　要：针对飞行器高速高机动、缩短降落距离的需求,将反推力装置与旁路式双喉道气动矢量喷管(bypass dual throat nozzle,BDTN)相结合,提出了一种反推改型气动矢量喷管(BDTN-TR)。型面优化前后的二维数值计算结果表明该喷管能在保持喷管矢量、非矢量性能优异性的同时缩短飞行器降落距离:平飞模态时,喷管推力系数和流量系数均在0.92以上;推力矢量模态时,凹腔回流区压力下降,主流上下游压差变大,喷管推力系数保持在0.93以上、流量系数保持在0.83以上,喷管落压比在2~10范围内时,推力矢量角达到了14.4°以上;反推模态时,反推效率在0.61以上,反推通道宽度对喷管反推性能的影响占主导。Considering the demand of high-speed,high maneuverability and shortening the landing distance of aircraft,a fluidic vectoring nozzle with thrust reverser(BDTN-TR)was proposed by combining the thrust reverser with the bypass dual throat nozzle(BDTN).The two-dimensional numerical simulation results showed that BDTN-TR can shorten the landing distance of aircraft while other performance was basically unchanged.The thrust coefficient and discharge coefficient of BDTN-TR above 0.92 could be obtained in cruise mode.In thrust vectoring mode,due to the pressure drop of separation region in the cavity,the pressure distribution of the mainstream became larger than BDTN,the thrust coefficient of BDTN-TR was above 0.93,the discharge coefficient was above 0.83,and the thrust vectoring angle reached more than 14.4°when the nozzle pressure ratio was within the range of 2 to 10.In thrust reversing mode,the thrust reverser efficiency was above 0.61,and the width of the reverse flow channel played an important role on the aerodynamic performance of the thrust reverser.

关 键 词：旁路式双喉道气动矢量喷管(BDTN) 反推力装置 推力矢量 排气系统 气动性能 

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]