Flame stabilizer with integrated design of new cooling structure
A flame stabilizer and cooling structure technology, which is applied in the field of turbo/ramjet combined engine and turbofan engine afterburner/ramjet combustion chamber, can solve the problems of the stabilizer being easily ablated, coke and blockage, etc., to avoid damage to the stabilizer, Increase the thickness and avoid the effect of nozzle coking
Inactive Publication Date: 2018-04-17
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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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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[0022] The present invention provides a stabilizer with an integrated design of a new cooling structure. In order to make the purpose, technical solution and effect of the present invention clearer and clearer, the present invention is further described in detail with reference to the accompanying drawings and examples. It should be understood that the specific implementations described here are only used to explain the present invention, not to limit the present invention.
[0023] Such as figure 1 As shown, the present invention provides a flame stabilizer with a novel cooling structure integrated design, including a fuel guide pipe 2, a fuel injection hole 3, a partition 4 and an outer casing 5, and the partition 4 is located in the outer casing 5 to The outer casing 5 is divided into a cold air chamber 1 and an impingement cooling chamber 8. The fuel guide pipe 2 is located in the cold air chamber 1. The fuel injection hole 3 is formed on the outer surface of the outer cas...
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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...
Claims
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IPC IPC(8): F23R3/20
CPCF23R3/20
Inventor 赵世龙范育新吕浩杰
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS