Combustion chamber of scramjet engine
A technology of scram stamping and combustion chamber, which is applied in the direction of combustion chamber, continuous combustion chamber, combustion method, etc., can solve the problems of high heat load and increase the difficulty of thermal protection, so as to reduce thermal load, reduce the difficulty of thermal protection and reduce resistance Effect
Active Publication Date: 2021-07-20
XIAN AEROSPACE PROPULSION INST
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Problems solved by technology
[0005] The purpose of the present invention is to solve the disadvantages that the existing wall surface flame stabilization device will cause too high heat load on the wall surface and increase the difficulty of thermal protection, and provide a combustion chamber of a scramjet
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[0027] The present invention will be further described below in conjunction with the accompanying drawings and exemplary embodiments.
[0028] refer to Figure 1-3 , the present invention provides a combustion chamber of a scramjet engine, including a flow channel 1 in the combustion chamber and a flame stabilization device, the flame stabilization device includes a flame stabilization central cone 2, a plurality of mounting support plates 3 and a slope body 4; Flame-stabilizing center cone 2 is a hollow cone structure, the tip of the cone faces the direction of supersonic airflow, and is coaxial with the flow channel 1 in the combustion chamber. The bottom is sealed, and a cavity is formed inside. A plurality of fuel injection holes 5; the plurality of installation support plates 3 is a hollow structure, one end of the installation support plate 3 is fixed on the wall surface of the flow channel 1 in the combustion chamber as a fuel inlet, and is communicated with an external...
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The invention relates to a generation device for combustion reaction in supersonic airflow, in particular to a combustion chamber of a scramjet engine. Aiming at overcoming the defects that an existing wall face flame stabilizing device causes overhigh thermal load on the wall face position, and the thermal protection difficulty is increased, the invention provides the combustion chamber of the scramjet engine; the combustion chamber of the scramjet engine comprises a combustion chamber inner flow passage and a flame stabilizing device; the flame stabilizing device comprises a flame stabilizing center cone, a plurality of mounting supporting plates and a slope body. the flame stabilizing center cone is of a hollow cone structure, the cone tip faces the supersonic airflow inflow direction, and a plurality of fuel injection holes are formed in the side wall of the front half section of the cone; the multiple mounting supporting plates and the slope body are of a hollow structures, one end of each mounting supporting plate is fixed to the flame stabilizing center cone and communicates with the interior of the flame stabilizing center cone, and the other end of each mounting supporting plate communicates with an external fuel supply source; and one end of the slope body communicates with the interior of the flame stabilizing center cone, and the other end of the slope body is a closed end.
Description
technical field [0001] The invention relates to a device for generating combustion reaction in a supersonic airflow, in particular to a combustion chamber of a scramjet engine. Background technique [0002] Due to the advantages of simple structure, low cost, high specific impulse and long range, scramjet has become one of the research hotspots of hypersonic power system and reusable aerospace power system. [0003] The combustion chamber is one of the main components of the scramjet engine. Its main function is to realize the efficient mixing of fuel and supersonic air, convert the chemical energy of the fuel into heat energy to the greatest extent, and provide high-temperature gas for the tail nozzle to accelerate the expansion. thrust, but due to the high air velocity in the combustion chamber of the scramjet engine, and the length of the combustion chamber is limited by factors such as weight, size, and thermal protection, the residence time of the fuel in the combustion...
Claims
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Login to View More IPC IPC(8): F23R3/28F23R3/04
CPCF23R3/28F23R3/04
Inventor 豆飞龙刘昊杜泉张忠利闫志勇蔡锋娟张玫
Owner XIAN AEROSPACE PROPULSION INST