涵道比对二元俯仰矢量排气系统红外特征影响的实验研究  

Experimental Investigation of Infrared Radiation Characteristics of Two-Dimensional Convergent-Divergent Vectoring Nozzle Exhaust System on Different Bypass Ratio States

作　　者：卢浩浩[1] 吉洪湖[1] 刘健[1] 王浩[1] 王丁[1] LU HaoHao;JI Honghu;LIU Jian;WANG Hao;WANG Ding(College of Energy and Power, 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,江苏南京210016

出　　处：《红外技术》2017年第7期648-652,共5页Infrared Technology

摘　　要：通过改变外涵流量,实验研究了涵道比0.3和1时,相同结构的二元俯仰矢量排气系统几何偏转0?、10?、20?三种模型下壁面温度与红外辐射特征分布。结果表明:涵道比1相对涵道比0.3时,排气系统火焰稳定器下游壁面温度具有较大降幅,隔热屏、收敛段、侧壁、扩张段壁面温度分别降低170 K、317 K、227 K和153 K;涵道比0.3时,随着几何偏角增大,排气系统红外辐射强度增大,最大增幅70.2%;但涵道比1时,正好相反,随着几何偏角增大,排气系统红外辐射强度下降,最大降幅65%。涵道比增大,排气系统红外辐射特征下降,几何偏转0?、10?、20?时,正尾向分别降低33.3%、42.1%、60.9%。By changing bypass mass flow,the wall temperature distribution and infrared radiation characteristics of two dimensional convergent-divergent(2D-CD)vectoring nozzle exhaust system with geometric deflection angles of0,10,20are numerically studied,at bypass ratio(BPR)0.3and1.0.The results show that the wall temperatures downstream of the flame holder decrease significantly at BPR1.0,which decrease by170K,317K,227K and153K,respectively,at heat shield,convergent section,side wall section and divergent section than those at BPR0.3;at BPR0.3,the infrared radiation intensity of exhaust system increases as the geometric deflected angle increases,reaching a maximum amplification of70.2%,while at BPR1.0,the infrared intensity behaves in the opposite way,with a maximum drop of65%;the increase of BPR decreases the infrared radiation of exhaust system,especially in the tail direction where the drop is33.3%,42.1%and60.9%,respectively,at geometric deflection angles of0°,10°,20°.

关 键 词：二元俯仰喷管 涵道比 矢量偏转 红外隐身 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]