Method for improving combustion efficiency of scramjet based on aerodynamic virtual cavity

Abstract

The present application relates to a method for improving the combustion efficiency of a scramjet engine based on an aerodynamic virtual cavity. The method includes: according to preset scramjet engine parameters, establishing a jet shock wave structure model in the combustion chamber when gas is ejected from the nozzle hole arranged on the wall surface of the combustion chamber downstream of the fuel injection hole. According to the bow-shaped fundamental wave in the jet shock wave structure model and the parameters of the aerodynamic virtual concave cavity formed by the step trailing edge in the combustion chamber, the relationship function between the nozzle structure parameters of the nozzle and the engine combustion efficiency value is established. The nozzle structure parameters include position parameters, quantity parameters, airflow angle parameters, airflow velocity parameters and airflow flow parameters. The corresponding injection hole structure parameters are obtained according to the preset combustion efficiency target value, and the injection holes are arranged on the wall surface of the combustion chamber according to the obtained injection hole structure parameters. The above method can improve combustion efficiency, solve the problem of large internal resistance of the cold flow in the real concave cavity, and solve the problem of high thermal protection pressure at the trailing edge of the real concave cavity.

Description

technical field [0001] The present application relates to the technical field of scramjet design, in particular to a method for improving the combustion efficiency of a scramjet based on an aerodynamic virtual cavity. Background technique [0002] The working process of the traditional scramjet engine is as follows: the hypersonic incoming flow passes through the intake port and the isolation section after being compressed, then enters the combustion chamber at supersonic speed and is mixed with fuel for combustion; the combustion products are accelerated and discharged through the tail nozzle to generate thrust. The high-efficiency blending combustion technology of fuel and incoming flow in the supersonic combustion chamber is one of the key technologies of the scramjet engine, which is directly related to the performance of the engine. [0003] The concave cavity has been proved to be an effective structure for scramjet to promote mixing and combustion. The concave cavity ...

AI Technical Summary

Problems solved by technology

However, the use of a real concave cavity formed by the wall structure will increase the cold flow internal resistance of the combustion chamber on the one hand; on the other hand, the trailing edge of the real concave cavity is often the key area where shock waves gather and the combustion High protection pressure

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