Simulation of underexpanded supersonic jet flows with chemical reactions  

作　　者：Fu Debin Yu Yong Niu Qinglin 

机构地区：[1]School of Aerospace Engineering,Beijing Institute of Technology

出　　处：《Chinese Journal of Aeronautics》2014年第3期505-513,共9页中国航空学报（英文版）

基　　金：supported by the National Natural Science Foundation of China (No. 51306019)

摘　　要：To achieve a detailed understanding of underexpanded supersonic jet structures influenced by afterburning and other flow conditions, the underexpanded turbulent supersonic jet with and without combustions are investigated by computational fluid dynamics （CFD） method. A program based on a total variation diminishing （TVD） methodology capable of predicting complex shocks is created to solve the axisymmetric expanded Navie^Stokes equations containing transport equations of species. The finite-rate ratio model is employed to handle species sources in chemical reactions. CFD solutions indicate that the structure of underexpanded jet is typically influenced by the pressure ratio and afterburning. The shock reflection distance and maximum value of Mach number in the first shock cell increase with pressure ratio. Chemical reactions for the rocket exhaust mostly exist in the mixing layer of supersonic jet flows. This tends to reduce the intensity of shocks existing in the jet, responding to the variation of thermal parameters.To achieve a detailed understanding of underexpanded supersonic jet structures influenced by afterburning and other flow conditions, the underexpanded turbulent supersonic jet with and without combustions are investigated by computational fluid dynamics （CFD） method. A program based on a total variation diminishing （TVD） methodology capable of predicting complex shocks is created to solve the axisymmetric expanded Navie^Stokes equations containing transport equations of species. The finite-rate ratio model is employed to handle species sources in chemical reactions. CFD solutions indicate that the structure of underexpanded jet is typically influenced by the pressure ratio and afterburning. The shock reflection distance and maximum value of Mach number in the first shock cell increase with pressure ratio. Chemical reactions for the rocket exhaust mostly exist in the mixing layer of supersonic jet flows. This tends to reduce the intensity of shocks existing in the jet, responding to the variation of thermal parameters.

关 键 词：COMBUSTION Finite-rate model Numerical simulation TVD method Underexpanded jet 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]