Injection device, combustor, and rocket engine
US-2018320634-A1 · Nov 8, 2018 · US
Injection apparatus for a rocket engine
US11111882B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11111882-B2 |
| Application number | US-201715609104-A |
| Country | US |
| Kind code | B2 |
| Filing date | May 31, 2017 |
| Priority date | Jun 2, 2016 |
| Publication date | Sep 7, 2021 |
| Grant date | Sep 7, 2021 |
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Abstract
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An injection apparatus for a rocket engine comprises an injection plate which delimits a combustion chamber upstream. The injection apparatus further comprises a plurality of coaxial injection elements distributed in the injection plate, each of which injection elements forms an inner outlet opening, delimited by a central sleeve body, for a first propellant component and an outer outlet opening for a second propellant component. The outer outlet opening is formed between the central sleeve body and a wall section which surrounds the central sleeve body in an annular manner. At least in a partial number of the injection elements, the central sleeve body projects from the wall section in the direction towards the combustion chamber. In particular, the central sleeve body projects relative to the injection plate into the combustion chamber.
First claim
Opening claim text (preview).
The invention claimed is: 1. An injection apparatus for a rocket engine, comprising: an injection plate delimiting a combustion chamber upstream, a plurality of coaxial injection elements distributed in the injection plate, each coaxial injection element forming an inner outlet opening, delimited by a central sleeve body, for a first propellant component and an outer outlet opening for a second propellant component, wherein the outer outlet opening is formed between the central sleeve body and a wall section which surrounds the central sleeve body in an annular manner, wherein in a partial number of the coaxial injection elements, the central sleeve body projects from the wall section in a direction towards the combustion chamber, wherein the central sleeve body comprises a plurality of tangential holes distributed in a peripheral direction, through which the first propellant component enters the central sleeve body, wherein the injection plate is flat on a plate side that faces the combustion chamber, at least in a region of the coaxial injection elements, in which the wall section is flush with the injection plate, and, in the partial number of the coaxial injection elements, the central sleeve body protrudes from the injection plate on the plate side that faces the combustion chamber, and wherein in a remaining partial number of the coaxial injection elements, an axial end face of the central sleeve body that faces the combustion chamber is flush with the plate side of the injection plate that faces the combustion chamber, so that the central sleeve body does not protrude relative to the plate side of the injection plate. 2. The injection apparatus according to claim 1 , wherein in at least the partial number of the coaxial injection elements with the protruding central sleeve body, the wall section in each case does not protrude relative to the plate side of the injection plate that faces the combustion chamber. 3. The injection apparatus according to claim 1 , wherein the coaxial injection elements with the protruding central sleeve body are distributed, when the injection plate is seen from above, on at least one of at least one circle or at least one radial spoke.
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- What does patent US11111882B2 cover?
- An injection apparatus for a rocket engine comprises an injection plate which delimits a combustion chamber upstream. The injection apparatus further comprises a plurality of coaxial injection elements distributed in the injection plate, each of which injection elements forms an inner outlet opening, delimited by a central sleeve body, for a first propellant component and an outer outlet openin…
- Who is the assignee on this patent?
- Airbus Ds Gmbh, Arianegroup Gmbh
- What technology area does this patent fall under?
- Primary CPC classification F02K9/52. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Sep 07 2021 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).