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High-speed premixed flame furnace for supersonic burning research

A supersonic combustion and flame furnace technology, which is applied in combustion chambers, combustion methods, combustion equipment, etc., can solve the problems of expensive materials, complex structures, and high processing technology requirements, and achieve the effects of precise temperature control and improved control capabilities

Inactive Publication Date: 2012-10-10
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

The experimental device also has disadvantages such as complex structure, high requirements on processing technology, and expensive materials.

Method used

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  • High-speed premixed flame furnace for supersonic burning research
  • High-speed premixed flame furnace for supersonic burning research
  • High-speed premixed flame furnace for supersonic burning research

Examples

Experimental program
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Embodiment Construction

[0038] figure 1 It is a supersonic premixed flame furnace designed by the present invention, including a main flow mixing chamber 5, a supersonic nozzle 8, a wake chamber 6, and a low velocity nozzle 7, wherein the entire supersonic premixed flame furnace is a streamlined structure with small ends and a large middle, Along the longitudinal direction, it is evenly divided into two parts, one part is the supersonic mainstream side, and the other part is the subsonic wake side. Subsonic wake side.

[0039] Wherein on the supersonic main flow side, the entrance of the main flow mixing chamber 5 is connected with a three-way methane pipeline 4 and a three-way air or pure oxygen pipeline 3, and the outlet is connected with a supersonic nozzle 8, and in the main flow mixing chamber 5 from the entrance to the exit in sequence An electrothermal ceramic heater 12, an anti-temper interlayer 10 and a damping net 9 are provided.

[0040] Fuel methane and air or methane and oxygen enter t...

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Abstract

The invention relates to a high-speed premixed flame furnace for supersonic burning research. The high-speed premixed flame furnace comprises a main stream mixing chamber (5), a supersonic nozzle (8), a wake plenum chamber (6) and a low-speed nozzle (7), wherein the whole high-speed premixed flame furnace is of a streamline structure with two smaller ends and one larger middle; the high-speed premixed flame furnace is equally divided into two parts lengthways, namely a supersonic main stream side and a sub-sound velocity wake side; the main stream mixing chamber (5) and the supersonic nozzle (8) are positioned on the supersonic main stream side; and the wake plenum chamber (6) and the low-speed nozzle (7) are positioned on the sub-sound velocity wake side. The premixed flame furnace provided by the invention has the advantages of compact structure, simple processing technique, low test cost, short test period, accurate and adjustable premix equivalent ratio large range, large total temperature, total pressure and airflow mach number adjustable range and the like.

Description

technical field [0001] The invention relates to a test device for the research of an air-breathing supersonic combustion engine used in aviation and spaceflight, which can provide test conditions for the study of supersonic premixed combustion process, flame structure, flame stabilization mechanism and supersonic mixed layer combustion process. . Background technique [0002] Air and space superiority is the strategic commanding height for victory under the conditions of future high-tech warfare, and it is of great significance to ensuring national security and international status. As a combination of aerospace technology, scramjet technology involves many disciplines and is a highly comprehensive combination of many cutting-edge technologies. It is the most important alternative power for aerospace aircraft, hypersonic aircraft and hypersonic cruise missiles. The working process in the scramjet combustion chamber is extremely complex, involving fuel injection, penetration...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/42
Inventor 吴海燕林志勇周进
Owner NAT UNIV OF DEFENSE TECH
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