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Ramjet combustion chamber

A sub-combustion ramjet and combustion chamber technology is applied in the field of sub-combustion ramjet combustion chambers, which can solve the problems of difficult ignition and stable combustion of sub-combustion ramjets, and achieve the effects of convenient and rapid participation in combustion, good mixing effect and fast ignition speed.

Inactive Publication Date: 2015-10-07
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The technical problem to be solved by the present invention is: in order to solve the difficult problem of sub-combustion ramjet ignition and stable combustion

Method used

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Embodiment Construction

[0024] The specific implementation manners of the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0025] In the description of the present invention, it should be noted that unless otherwise specified, the meaning of "plurality" is two or more; the terms "upper", "lower", "left", "right", "inner ", "outside", "front end", "rear end", "head", "tail", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and Simplified descriptions, rather than indicating or implying that the device or element referred to must have a particular orientation, be constructed and operate in a particular orientation, and thus should not be construe...

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Abstract

The invention belongs to the technical field of ramjets, and discloses a ramjet combustion chamber. The combustion chamber comprises an isolation segment, a sudden expansion segment, a cavity, a constant section segment and a tail spraying pipe which are arranged in sequence and are communicated in sequence. The distances from bottom plates of the isolation segment, the sudden expansion segment and the cavity to the top are sequentially increased; and a supporting plate cavity is formed in a supporting plate structure, and a fuel flow-in opening, a high-temperature airflow leading inlet and a plurality of jet holes communicated with the supporting plate cavity are formed in the supporting plate structure. A combination of the sudden expansion segment, the cavity and the supporting plate structure is adopted, and the mixing effect of fuel and incoming flow air is good; the supporting plate structure is arranged in an inclining manner, and the distribution range of fuel mixed gas sprayed out of the supporting plate structure in a runner is wide; the fuel and the high-temperature led airflow are contact in a supporting plate cavity in advance, the fuel obtains energy, and participates in combustion conveniently and rapidly, and the ignition speed is high; and a continuous stable flame is formed in the cavity, and diffusion and flame stabilizing are facilitated.

Description

technical field [0001] The invention relates to the technical field of a sub-combustion ramjet engine, in particular to a combustion chamber of a sub-combustion ramjet engine. Background technique [0002] The ramjet engine is an air jet engine that relies on the deceleration and supercharging of the high-speed oncoming air flow to work. It has a simple structure and does not have complex rotating parts like the compressor and turbine of the turbojet engine. The air entering the engine is compressed by high-speed Obtained by stagnation of airflow (ram boost). Ramjets can be mainly divided into two types: sub-combustion ramjet (subsonic combustion ramjet) and scramjet (supersonic combustion ramjet). [0003] The combustion chamber is the core component of the sub-combustion ramjet engine. Since the sub-combustion ramjet engine works at high altitude, the ambient temperature is low, the air density in the combustion chamber is very low, and the airflow velocity at the combust...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/42
Inventor 林鹏方祥军黎军王霄王亚妹陶佳欣
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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