Calculation method of supersonic turbulent combustion flow based on flame surface/progress variable model

Abstract

The invention discloses a flame surface / progress variable model-based supersonic turbulent combustion flow calculation method, and belongs to the field of computational fluid dynamics (CFD). The method comprises the steps of establishing a flame surface database; performing RANS solving by using the flame surface database; and building a compressible scale model of a progress variable source item. In view of a flame surface / progress variable turbulent combustion model with self-ignition and flameout phenomena, a novel compressible scale model with a definite physical meaning is built for the progress variable source item, so that a corrected flame surface / progress variable model can accurately describe self-ignition and flameout processes; and the high Mach number effect of flow is effectively considered, so that the simulation precision of supersonic turbulent combustion flow is greatly improved. The technology is low in realization difficulty, can be used as compressible correction, and only needs to be added as a sub-program; and an original program is slightly modified during CFD program coupling calculation.

Description

technical field [0001] The invention belongs to the field of computational fluid dynamics (CFD), in particular to a supersonic turbulent combustion flow calculation method based on a flame surface / progress variable model. Background technique [0002] The combustion chamber is one of the key components of the scramjet engine, and accurate simulation of the turbulent combustion flow in the combustion chamber is a prerequisite for designing a high-performance combustion chamber to improve the overall performance of the scramjet engine. The flow in the scramjet combustion chamber is extremely complex, including the interaction of multi-scale and multi-physical processes such as compressible turbulence, combustion, shock wave / expansion wave system, etc. Therefore, the key to numerically simulating the combustion flow in the scramjet combustion chamber is to develop an accurate calculation method for turbulent combustion that can consider the high Mach number effect of the flow. ...

AI Technical Summary

Problems solved by technology

However, compared with the flame surface model, the flame surface / progress variable model needs to add the chemical reaction source term of the progress variable in the database, and the value of the chemical reaction source term is very sensitive to the flow high Mach number effect, so the flame surface / progress variables compressible modifier builds are more difficult

Until now, there is still a lack of an effective calculation method for the flame surface / progress variable model that can consider the effect of high Mach number

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