Numerical Simulation of Mixing and Combustion Characteristics based on Air Turbine Rocket Engine Rocket Afterburner

Shangchun Wang; Yang Liu; Yue Wu; Zheng Ni

doi:10.54097/hset.v1i.444

Authors

Shangchun Wang
Yang Liu
Yue Wu
Zheng Ni

DOI:

https://doi.org/10.54097/hset.v1i.444

Keywords:

Numerical imulation, Afterburner, Chemical reaction, Air Turbo Rocket (ATR)

Abstract

The gas combustion efficiency of the afterburner of the Air Turbo Rocket (ATR) engine directly affects the performance of the engine. In order to study the reaction mechanism of mixing combustion of gas and air in the afterburner, the paper numerically simulates the turbulent mixing and combustion process of rich fuel gas and air, and analyzes the influence of air intake mode and intake parameters on engine performance. The results show that: The both sides air intake is better than the one sides air intake; The air incidence angle is 90°, the engine performance is ideal; The air intake position is selected between the length to diameter ratio of the afterburner from 1.0 to 1.5, and the combustion efficiency of the afterburner is higher.

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