亚声速等膨胀平面射流的初始流场结构

推进技术 ›› 2012, Vol. 33 ›› Issue (4): 591-596.

亚声速等膨胀平面射流的初始流场结构

张焕好,陈志华,黄振贵,韩珺礼

南京理工大学瞬态物理国家重点实验室,江苏南京 210094;南京理工大学瞬态物理国家重点实验室,江苏南京 210094;南京理工大学瞬态物理国家重点实验室,江苏南京 210094;南京理工大学瞬态物理国家重点实验室,江苏南京 210094 ;北京机电研究所,北京 100012

发布日期:2021-08-15
作者简介:张焕好(1985—),女,博士生,研究领域为计算燃烧与超声速流研究。E-mail:zhanghuanhao9@163.com
基金资助:
高等学校博士学科点专项科研基金(20103219110037);江苏省“青蓝工程”中青年学术带头人培养项目。

Initial Flow Structures of an Iso-expanded Subsonic Plane Jet

National Key Laboratory of Transient Physics, Nanjing University of Science and Technology, Nanjing, 210094,China;National Key Laboratory of Transient Physics, Nanjing University of Science and Technology, Nanjing, 210094,China;National Key Laboratory of Transient Physics, Nanjing University of Science and Technology, Nanjing, 210094,China;National Key Laboratory of Transient Physics, Nanjing University of Science and Technology, Nanjing, 210094,China;Beijing Institute of Electromechanical Technology, Beijing 100012,China

Published:2021-08-15

摘要/Abstract

摘要： 基于大涡模拟方法与5阶精度混合TCD/WENO格式,对等膨胀射流在马赫数为Ma=0.6条件下的初始流场结构进行了数值模拟。数值结果描述了射流等膨胀过程中,射流初始流场的形成、变化及发展过程。并发现了射流初始流场中涡核为射流失稳的起始点,研究了射流混合层与涡核剪切层上涡的产生、发展与破碎以及它们卷吸环境气体并与射流气体混合的整个过程,揭示了射流初始过程中涡核与涡环直径的变化趋势,得到了射流轴向速度与压力的分布。数值结果可为相关发动机的设计提供重要参考。

关键词: 亚声速射流; 大涡模拟; 涡环;混合层

Abstract: Based on LES (Large-eddy simulation), combined with the 5th-order hybrid TCD-WENO scheme, the initial flow field of an iso-expanded subsonic jet at Ma=0.6 was simulated numerically. The numerical results described the formation, variation and development process of the initial structures of the jet flow. Moreover, it is found that the vortex core is the original source of the jet flow instability, and the generating, developing and breaking processes of the mixing layers of the jet flow and the shear layer of vortex core, and their entrainments of environment gases as well as the mixing processes were studied. The developing tendencies of the vortex ring and its core diameter were shown. The streamwise velocity and pressure distributions of the jet flow along with its symmetrical axis were obtained. The numerical results can provide important guide for some corresponding engine design.

Key words: Subsonic jet flow; LES; Vortex ring; Mixing layer

张焕好,陈志华,黄振贵,韩珺礼. 亚声速等膨胀平面射流的初始流场结构[J]. 推进技术, 2012, 33(4): 591-596.

参考文献

[2] Meyer T R, Dutton J C, Lucht R P.Experimental Study of the Mixing Transition in a Gaseous Axisymmetric Jet[R].AIAA 99-3585.
[3] Brownell C J, Su L K.Planar Imaging Measurements of Three Scalars in a Turbulent Jet[R].AIAA 2010-104.
[4] Arakeri J H, Das D, Krothapalli A, et al.Vortex Ring Formation at the Open End of a Shock Tube:A Particle Image Velocimetry Study[J].Physics of Fluids, 4,6(4):1008-1019.
[5] Alkislar M B, Choutapalli I, Krothapalli A, et al.The Structure of a Pulsed Jet, a PIV Study[R].AIAA 2005-1274.
[6] An R, Kontis K, Edwards J A.Compressible Vortex-ring Interaction Studies with a Number of Generic Body Configurations[R].AIAA 2005-1044.
[7] Behtash H Z, Kontis K, Takayama K.Compressible Vortex Loops Studies in a Shock Tube with Various exit Geometries[R].AIAA 2008-362.
[8] Behtash H Z, Kontis K, Orozco N G.Experimental Investigations of Compressible Vortex Loops[J].Physics of Fluids, 8,0.
[9] 李军,曹从咏,徐强.固体火箭燃气射流近场形成与发展的数值模拟[J].推进技术, 3,4(5):410-413.(LI Jun, CAO Cong-yong, Xu Qian.Numerical Simulation of the form and Development of Rocket Gas Near Flow Field[J].Journal of Propulsion Technology, 3,4(5):410-413.)
[10] 张焕好,陈志华,孙晓晖,等.突扩管爆轰推进及其喷管推力性能数值模拟[J].高压物理学报, 0,4(6):415-422.
[11] Hill D J, Pullin D I.Hybrid Tuned Center-difference-WENO Method for Large Eddy Simulations in the Presence of Strong Shocks[J].Journal of Computational Physics, 4,4:435-450.
[12] Pantano C, Deiterding R, Hill D J, et al.A Low Numerical Dissipation Patch-Based Adaptive Mesh Refinement Method for Large-eddy Simulation of Compressible Flows[J].Journal of Computational Physics, 7,1:63-87.
[13] Kosloff R, Kosloff D.Absorbing Boundary Conditions for Wave Propagation Problems[J].Journal of Computational Physics, 6,3:363-376.