射流缝对激波诱导矢量喷管三维流场影响的数值模拟

推进技术 ›› 2009, Vol. 30 ›› Issue (1): 63-66.

射流缝对激波诱导矢量喷管三维流场影响的数值模拟

雷金春,金捷

北京航空航天大学能源与动力工程学院航空发动机数值仿真研究中心;北京航空航天大学能源与动力工程学院航空发动机数值仿真研究中心

发布日期:2021-08-15

Computational investigation of slot geometric structure effects on the flow-field of shock-induced fluidic vectoring nozzle

Coll.of Energy and Power Engineering,Aeroengine Numerical Simulation Research Center,Beijing Univ.of Aeronautics and Astronautics,Beijing 100191,China;Coll.of Energy and Power Engineering,Aeroengine Numerical Simulation Research Center,Beijing Univ.of Aeronautics and Astronautics,Beijing 100191,China

Published:2021-08-15

摘要/Abstract

摘要： 在设计工况下,采用RNGk-ε湍流模型对扩张段不同射流缝几何结构的激波诱导轴对称气动矢量喷管进行了数值模拟。结果表明,流场结构的主要特征是在扩张段有一个主分离涡与一个旋向相反的射流角涡及次流与出口截面之间有一个较大的回流区。周向角,射流缝距出口截面轴向距离和轴向角是射流缝结构优化的三个关键参数,周向角为45°,射流缝距喷管出口截面轴向距离为19 mm,次流注入方向与主流方向相反时产生大的有效矢量角。

关键词: 气动矢量喷管+;射流缝几何结构+;气动特性;数值仿真

Abstract: Numerical simulation employing the RNG k-ε model has been conducted to determine the internal flow-field parameters of a shock induced axisymmetric fluidic vectoring nozzle with different slot geometric structure in its divergent section in design situation.A separate vortex and an opposite revolving jet vortex exist in the divergent section.A large recirculation region locates between the secondary flow injection and the outlet.Circumferential angle(θ),distance between the slot and outlet section(SX) and axial angle(Ψ)are the key parameters of the slot geometric structure.When θ=45°,SX=19 mm,Ψ reverse to the primary flow,it has efficient thrust vectoring angle.

Key words: Fluidic vectoring nozzle+;Slot geometric structure+;Aerodynamic characteristic;Numerical simulation

雷金春,金捷. 射流缝对激波诱导矢量喷管三维流场影响的数值模拟[J]. 推进技术, 2009, 30(1): 63-66.