Integrally-designed flame stabilizer with novel cooling structure

Abstract

The invention discloses an integrally-designed flame stabilizer with a novel cooling structure. The integrally-designed flame stabilizer comprises a cold air cavity, a fuel guide pipe, fuel injection holes, a partition plate, a shell, impact holes of the shell and cooling holes of the shell. The integrally-designed flame stabilizer with the novel cooling structure has the functions of adjusting the position and size of a backflow area behind the stabilizer and controlling the wall temperature of the bottom end of the stabilizer besides the function of being capable of providing the backflow area facilitating flame stabilization under different work conditions. On the one hand, cooling gas flowing out of the cooling holes in the bottom end face of the stabilizer cools the wall face, the structural reliability of the stabilizer in high-temperature gas is improved, and the service life of the stabilizer in the high-temperature gas is prolonged; and on the other hand, the pressure and flow of the cooling gas are adjusted, and therefore the axial position and size of the backflow area can be controlled, the downstream combustion character of the stabilizer can be actively controlled, the flame stabilization performance in high-temperature and high-speed gas flow can be improved, and oscillating combustion can be restrained.

Description

Technical field: [0001] The invention belongs to the technical field of turbo / ramjet combined engine and turbofan engine booster / ramjet combustor, and in particular relates to a flame stabilizer with integrated design of a novel cooling structure. Background technique: [0002] The turbo / ramjet combined engine has attracted much attention for its performance advantages of widening the flight envelope, realizing conventional take-off and landing, and reusability. It is also considered to be the most potential hypersonic vehicle power plant at this stage. In order to achieve a larger thrust-to-weight ratio in modern advanced turbofan engines, the temperature rise of the main combustion chamber is large, the temperature of the gas in front of the turbine is significantly increased, the gas flow rate is large, and the flow velocity is faster, making it possible to enter the turbofan afterburner or ram / afterburner The temperature and speed of the incoming flow in the combustion c...

AI Technical Summary

Problems solved by technology

[0003] The problem to be solved by the present invention is that in the high-temperature air flow and combustion area, the stabilizer is easily ablated, and the fuel injection pipe is easily blocked by coking. In order to ensure the reliability of the working performance of the flame stabilizer, the present invention provides an integrated The flame stabilizer with optimized design can cool the fuel nozzle, reduce the temperature of the outer wall surface of the stabilizer, realize active control of the recirculation combustion zone, and improve the working stability and reliability of the stabilizer

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