Thermal protection method for scramjet engine fuel injection supporting plate by utilization of transpiration cooling

Abstract

The invention relates to a thermal protection method for a scramjet engine fuel injection supporting plate by the utilization of transpiration cooling. The method includes the following steps that (1), high temperature resistant material is used for manufacturing the injection supporting plate of a multi-tiny-hole structure, and a fuel pipe of a scramjet engine is communicated with the injection supporting plate; (2), by the utilization of the process that fuel leaks through holes of the injection supporting plate of the multi-tiny-hole structure, and heat convection is performed forcibly, so that the heat on the surface of the injection supporting plate is taken away; (3), it is utilized that the fuel leaks through the surface of the injection supporting plate to form a thin layer, so that main flows are prevented from performing heat transfer on the injection supporting plate. The multi-tiny-hole structure is manufactured on the injection supporting plate material, the concept of transpiration cooling is used, the fuel serves as a cooling agent, so that strong heat convection happens between the fuel and the injection supporting plate in the process that the fuel flows through the injection supporting plate, meanwhile, the fuel forms the thin layer on the surface of the injection supporting plate, heat transfer between the high temperature main flows and the surface of the injection supporting plate is obstructed, thermal protection on the injection supporting plate and particularly the front edge part of the injection supporting plate is achieved, and the injection supporting plate is prevented from being ablated and damaged. The thermal protection method can be widely applied to thermal protection performed on various ramjet injection supporting plate structures.

Description

technical field [0001] The invention relates to a thermal protection method for a high-temperature wall surface, in particular to a thermal protection method for a fuel injection support plate of a super-combustion engine by sweating and cooling in a high-temperature and high-speed airflow. Background technique [0002] As an aerospace technology that represents the frontier of modern science and technology development, due to its significance in national defense and space resource utilization, it has received great investment from many countries in the world and has driven the prosperity and development of related industries. In order to meet the higher and faster requirements of flying, the development of new and efficient engine technology has become an inevitable development of future aerospace vehicles. like figure 1 As shown, the ramjet engine is a kind of engine that does not have a complex blade structure with high-speed rotation, and realizes the deceleration and c...

AI Technical Summary

Problems solved by technology

However, the residence time of the fuel in the combustion chamber is only a few milliseconds, and an efficient device is required to provide fuel injection to achieve mixing between the fuel and the high-speed main flow

[0003] The injection branch plate structure is a common device in the combustion chamber to realize the effective mixing of fuel and high-speed main flow. The fuel is sprayed from the injection hole on the injection support plate and mixed with the high-speed main flow, which overcomes the incident penetration distance of the wall surface. short disadvantage

However, at the same time, the high-speed mainstream stagnates on the surface of the injection strut, resulting in serious aerodynamic heating, and the injection strut, especially the front edge, is prone to ablation damage. Effective active cooling must be used to reduce the surface temperature of the injection strut

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