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Three-column fuel supply structure for hypersonic aircraft scramjet

A scramming and hypersonic technology, applied in the direction of combustion chamber, combustion method, combustion equipment, etc., can solve the problem that the fuel supply structure cannot work for a long time, solve the problem of aerodynamic heat load and aerodynamic stagnation, and realize the cooling demand and flow distribution, improve the effect of reliability

Active Publication Date: 2019-11-08
HARBIN INST OF TECH
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

[0004] In order to solve the problem that the fuel supply structure in the hypersonic aircraft scramjet cannot work for a long time, the present invention proposes a porous three-column fuel supply structure for the hypersonic aircraft scramjet, using three metal particles to sinter porous materials The hollow columnar structure is made to inject fuel at the same time, while the fuel is supplied, the fuel is used to fully cover the supply structure for sweat cooling, and the design of the three-column structure is used to balance the relationship between cooling demand and flow distribution

Method used

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  • Three-column fuel supply structure for hypersonic aircraft scramjet
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  • Three-column fuel supply structure for hypersonic aircraft scramjet

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specific Embodiment approach 1

[0026] Specific implementation mode one: see Figure 1-Figure 5 This embodiment will be described. The three-column fuel supply structure for hypersonic aircraft scramjet described in this embodiment includes three column structures and a base 6, and the upper parts of the three column structures are all arranged above the base 6, The lower part runs through the base 6, and the arrangement of the three columnar structures is in a straight line, with a distance of 5mm between them; the columnar structure includes a porous shell 1 and a hollow support rod 3, and the porous shell 1 is wrapped in a hollow The top of the support rod 3 is sintered into a cylindrical structure, and the hollow support rod 3 penetrates the base 6; the porous shell 1 is a hollow cylindrical structure with a cavity 2 inside, and the porous shell 1 is sintered with metal particles The material composition of the metal particles is 06Cr17Ni12Mo2, the size of the metal particles is 25 to 35 microns, the po...

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Abstract

The invention provides a three-column fuel supply structure for a hypersonic aircraft scramjet. The three column structures of the three-column fuel supply structure are arranged on a base in a straight line, and the distance between the adjacent two column structures is 5 mm; a porous shell is made of porous medium materials sintered by metal particles, and is wrapped on the top of a hollow support rod and sintered into a columnar structure; and fuels are distributed to the three column structures and enter a cavity of the porous shell through an injection port at the bottom of the hollow support rod. The three-column fuel supply structure for the hypersonic aircraft scramjet solves the problem that an existing fuel supply structure in the hypersonic aircraft scramjet cannot work for a long time, the hollow columnar structure made of the porous materials sintered by the three metal particles is adopted to simultaneously inject the fuels, the full-coverage sweating and cooling are carried out by utilizing the fuels while supplying the fuels, and meanwhile, the relationship between cooling requirements and flow distribution is balanced by utilizing the design of the three-column structure.

Description

technical field [0001] The invention relates to a three-column fuel supply structure for a scramjet engine of a hypersonic aircraft, which is used for supplying hydrocarbon fuel to a combustion chamber inside the scramjet engine of a hypersonic aircraft, and belongs to the technical field of scramjet engines. Background technique [0002] The thermal protection of scramjet is the focus and difficulty in the research of hypersonic vehicle propulsion technology in all countries in the world. It is generally believed that the ramjet engine of a supersonic vehicle works between flight Mach 2 and 5, while the scramjet engine of a hypersonic vehicle works at a flight Mach number above 5. The characteristics of the scramjet engine are: due to the high flight Mach number, the total temperature of the engine intake air is extremely high, even as high as 2000K, and the intake port cannot compress the incoming flow to subsonic speed to prevent the static temperature from being too high...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/28
CPCF23R3/283F23R3/286
Inventor 周伟星肖雪峰张军龙赵广播
Owner HARBIN INST OF TECH
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