Engine starting ignition device and ignition method based on pre-installed intermediate medium
A technology for engine starting and ignition devices, which is applied to rocket engine devices, machines/engines, jet propulsion devices, etc., and can solve problems such as igniter freezing, ignition failure, and blockage of supply systems
Active Publication Date: 2022-03-04
XIAN AEROSPACE PROPULSION INST
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Problems solved by technology
[0004] The purpose of the present invention is to solve the technical problems of the existing liquid oxygen methane engine starting chemical ignition method, when using liquid methane to directly squeeze the igniter to ignite, it is easy to cause the igniter to freeze, block the supply system, and cause risks such as ignition failure. Engine starting ignition device and ignition method based on pre-installed intermediate medium
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[0023] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.
[0024] An engine starting ignition device based on pre-installed intermediate medium, including a check valve 1 located behind the engine fuel pump and an ignition conduit 2 pre-installed with igniting agent; it also includes a starter box 3, an intermediate medium pipeline 4, and a first valve 5 and a second valve 6; the starter box 3 is provided with a capsule 7, and the capsule 7 isolates the inner cavity of the starter box 3 into a mutually isolated air cavity a on the inlet side and an intermediate medium cavity b on the outlet side; The inlet of the air chamber a of the starter box 3 is connected to a high-pressure gas source, and the outlet of the intermediate medium chamber b of the starter box 3 is connected to the upstream end of the intermediate medium pipeline 4 through the first valve 5; the upstream end of the intermediate medium pipeline 4...
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The invention relates to an engine starting ignition device and ignition method based on preinstalled intermediate medium. The purpose of the present invention is to solve the technical problems of the existing liquid oxygen methane engine starting chemical ignition method, when using liquid methane to directly squeeze the igniter to ignite, it is easy to cause the igniter to freeze, block the supply system, and cause risks such as ignition failure. An engine starting ignition device and ignition method based on a pre-installed intermediate medium. Between the check valve of the existing engine and the ignition conduit pre-loaded with igniting agent, an intermediate medium supply section including a starter box, an intermediate medium pipeline, a first valve and a second valve is added. The freezing point of the intermediate medium is lower than The temperature of the pre-cooled fuel, whose boiling point is higher than the freezing point of the igniter, and the intermediate medium is used as a transition fuel to prevent direct contact between the fuel and the igniter, and to ensure that the intermediate medium will not freeze the igniter in a liquid state, and when in contact with the fuel It will not be frozen by fuel.
Description
technical field [0001] The invention relates to an engine starting ignition device and method, in particular to an engine starting ignition device and ignition method based on preinstalled intermediate medium. Background technique [0002] For liquid rocket engines with non-spontaneous propellants, a special ignition device is required to ignite the propellant. The commonly used engine ignition methods include gunpowder ignition, electric torch ignition and chemical ignition. [0003] Gunpowder ignition is a mature conventional ignition method, which has the advantages of large ignition energy and mature technology. However, for the future reuse of liquid oxygen methane engines, the residue adhesion produced by gunpowder gas will affect the reuse of the engine. Electric torch ignition is a commonly used ignition method for dual cryogenic engines, which has the advantages of being clean and easy to reuse. However, if it is used for high-thrust liquid oxygen methane engines at...
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IPC IPC(8): F02K9/95F02K9/42
CPCF02K9/95F02K9/42
Inventor 李春红刘站国高玉闪邢理想王君武晓欣陈文
Owner XIAN AEROSPACE PROPULSION INST