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A combustion chamber of a scramjet

A technology of scramjet and combustion chamber, which is applied in the direction of combustion chamber, continuous combustion chamber, combustion method, etc., can solve the problems of increasing the difficulty of thermal protection and high thermal load, so as to reduce the difficulty of thermal protection, reduce thermal load, and reduce resistance. Effect

Active Publication Date: 2022-07-19
XIAN AEROSPACE PROPULSION INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

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

Method used

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  • A combustion chamber of a scramjet
  • A combustion chamber of a scramjet
  • A combustion chamber of a scramjet

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Embodiment Construction

[0027] The present invention will be further described below with reference to the accompanying drawings and exemplary embodiments.

[0028] refer to Figure 1-3 , the present invention provides a combustion chamber of a scramjet, including a flow channel 1 in the combustion chamber and a flame stabilization device, the flame stabilization device includes a flame stabilization center cone 2, a plurality of mounting support plates 3 and a slope body 4; the The flame stabilizing center cone 2 is a hollow cone structure, the cone tip faces the supersonic airflow entering direction, 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 mounting support plates 3 are hollow structures, one end of the mounting support plate 3 is fixed on the wall surface of the flow channel 1 in the combustion chamber as a fuel inlet, and communicates with an external fuel supply s...

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Abstract

The invention relates to a generating device for combustion reaction in supersonic airflow, in particular to a combustion chamber of a scramjet. The purpose of the present invention is to solve the problem that the existing wall flame stabilization device causes too high thermal load to the wall position and increases the difficulty of thermal protection, and provides a combustion chamber of a scramjet engine, including a flow channel in the combustion chamber and a Flame stabilization device, the flame stabilization device includes a flame stabilization center cone, a plurality of mounting support plates and a slope body, the flame stabilization center cone is a hollow cone structure, the cone tip faces the inflow direction of the supersonic airflow, and the front half of the cone is on the side The wall is provided with a plurality of fuel injection holes; the plurality of mounting support plates and the slope are all hollow structures, one end of the mounting support plate is fixed on the flame stabilization center cone, and communicates with the interior of the flame stabilization center cone, and the other end It is communicated with an external fuel supply source; one end of the slope body is communicated with the interior of the flame stabilization center cone, and the other end is a closed end.

Description

technical field [0001] The invention relates to a generating device for combustion reaction in supersonic airflow, in particular to a combustion chamber of a scramjet. 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 systems and reusable aerospace power systems. [0003] The combustion chamber is one of the main components of the scramjet engine. Its main function is to achieve 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, so as to expand and accelerate the production. thrust, but due to the high airflow velocity in the combustion chamber of the scramjet, and the length of the combustion chamber is limited by factors such as weight, size, thermal protection, etc., the residence time of the fuel in the com...

Claims

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Application Information

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Patent Type & Authority Patents(China)
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
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