Coaxial injection continuously rotating detonation test device
A detonation test, coaxial technology, used in jet propulsion devices, rocket engine devices, machines/engines, etc.
Pending Publication Date: 2021-07-23
NAT UNIV OF DEFENSE TECH
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Problems solved by technology
[0004] At present, there are few studies linking continuous rotation detonation and tangentially unstable combustion
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[0034] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.
[0035] It should be noted that all directional indications (such as up, down, left, right, front, back...) in the embodiments of the present invention are only used to explain the relationship between the components in a certain posture (as shown in the accompanying drawings). Relative positional relationship, movement conditions, etc., if the specific posture changes, the directional indication will also change accordingly.
[0036] In addition, in t...
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The invention discloses a coaxial injection continuously rotating detonation test device. The device comprises an inner fuel cavity outer sleeve, an inner injection panel, a combustion chamber outer sleeve and a combustion chamber which are coaxially arranged, wherein the inner fuel cavity outer sleeve and the combustion chamber outer sleeve are connected to the two sides of the inner injection panel correspondingly; an outer ring air intake structure communicated with the combustion chamber is arranged between the inner injection panel and the combustion chamber outer sleeve, an inner ring air intake structure communicated with the combustion chamber is arranged in the middle of the inner injection panel, and air enters the combustion chamber through the outer ring air intake structure or / and the inner ring air intake structure; an inner fuel gas accumulation cavity is formed between the inner injection panel and the inner fuel cavity outer sleeve, and fuel in the inner fuel gas accumulation cavity enters the combustion chamber after the fuel is sprayed out through an inner nozzle; an outer fuel gas accumulation cavity is formed in the periphery of the combustion chamber outer sleeve, and fuel in the outer fuel gas accumulation cavity enters the combustion chamber after the fuel is sprayed out through outer fuel orifices; pressure holes are formed in the sidewall of the combustion chamber; and the head of the combustion chamber is coaxially provided with a spark plug. According to the device, a continuously rotating detonation proving test of tangential unstable combustion of a liquid propellant rocket engine can be conducted.
Description
technical field [0001] The invention relates to the technical field of rocket engine test equipment, in particular to a coaxial injection continuous rotation detonation test device. Background technique [0002] Although the liquid rocket engine organizes combustion in the isobaric mode, due to the poor mixing effect of the propellant adjacent to the injection panel, there is a combustible mixture layer between the isobaric combustion flame front and the injection panel, and the combustible mixture layer close to the isobaric combustion flame front With high temperature, affected by the inherent instability mechanism of the flow field, it is very easy to generate hot spots in this combustible mixture layer, thereby inducing the formation of rotational detonation. It is speculated that rotational detonation will lead to tangentially unstable combustion of the liquid rocket engine. Caused rocket launch mission to fail. [0003] The current research on rotating detonation main...
Claims
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IPC IPC(8): F02K9/96
CPCF02K9/96
Inventor 张海龙刘世杰刘卫东袁雪强彭皓阳蒋露欣
Owner NAT UNIV OF DEFENSE TECH