Investigation on Scramjet Thermal environment and Thermal Structure

Paper number

IAC-06-C2.P.2.06

Author

Dr. Liming Zheng, Beijing University of Aeronautics and Astronautics, China

Coauthor

Mr. Bing Sun, Beijing University of Aeronautics and Astronautics, China

Year

2006

Abstract

Scramjet is used on hypersonic vehicle, which works under high Mach. The wall heat flow of scramjet is very high, and then air oxidizability is strengthened on account of high temperature. The thermal environment is inclement with shortage scramjet coolant. Thermal protection technology is one of the key technologies of Scramjet.

Research on the thermal environment is basis of scramjet thermal protection. Computational fluid dynamics (CFD) is a necessary method in the thermal environment research. In order to avoid serious influence of combustion models on the reliability of the thermal environment computational result, a new method of thermal environment research was provided. The computation model of scramjet thermal environment was established based on the two-dimensional N-S equations and one-dimensional heating laws according with Rayleigh Distribution. The simulation of thermal environment of a model engine was performed. Internal flow field data and wall heat flux distribution of the scramjet were obtained. The result showed that the new method is effective for thermal environment computation, and multiform oil injection modes can be simulated by adjusting heating laws.

Based on the thermal environment computation research, the coupling computation program was compiled containing scramjet thermal environment, regenerative cooling structure and coolant. Three-dimensional thermal structure model was performed in regenerative cooling structure, and one-dimensional pipe flow model was implemented on the aspect of coolant heat exchange. Regenerative cooling structures were optimized based on the conception of ‘coolant precise admeasure’. The result revealed that coolant was decreased in optimized regenerative cooling structures.

The investigation of this paper offers gist for the scramjet thermal protection and thermal structure design.

Abstract document

IAC-06-C2.P.2.06.pdf

Manuscript document

IAC-06-C2.P.2.06.pdf (🔒 authorized access only).

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