An Aerothermodynamic Study Of The Thrust Chamber In Hypersonic Flows

Hypersonic technology takes an important position in the development of modern aerospace. Varying degrees of aerodynamic heating is produced in hypersonic flows. Then a rocket engine thrust chamber will suffer that. The propellant in the cooling jacket will be heated for the thrust chamber which uses regenerative cooling technology, because of the strong effect of the aerodynamic heating. The reliability of the whole engine will be seriously affected, when the propellant rises to its decomposition temperature.This paper studies the aerodynamic heating environment of the thrust chamber in hypersonic flows. A theoretical analysis and prediction have been made for flow field and heat flux distribution of thrust chamber cavity. Then the impact factors of numerical simulation, such as difference scheme, the mesh of flow field and turbulence model, are discussed. A split field method for flow calculation is summed up, and confirmed by the experiment in shock tunnel. After that, a coupled numerical simulation for aerodynamic heating and thermal response of thrust chamber is conducted. Changes in the temperature of thrust chamber and propellant are analyzed and compared, in different flight conditions.This paper is in addition to the study of the aerodynamic heat transfer in hypersonic complex cavity flows. Hypersonic aerodynamic heating theory which used for thermal protection of thrust chamber has been improved. The security and environmental adaptability of the thrust chamber used regenerative cooling technology have been also improved.