Belted toroid pressure vessel and method for making the same
US-9541235-B2 · Jan 10, 2017 · US
Thrust nozzle with double contour and smooth transition
US10590888B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10590888-B2 |
| Application number | US-201615268737-A |
| Country | US |
| Kind code | B2 |
| Filing date | Sep 19, 2016 |
| Priority date | Sep 18, 2015 |
| Publication date | Mar 17, 2020 |
| Grant date | Mar 17, 2020 |
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Abstract
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A thrust nozzle, in particular thrust nozzle for a rocket engine, with a convergent wall section, a throat section and a divergent wall section. The divergent wall section has a first region adjacent to the throat section, the wall contour of which region corresponds to a truncated ideal nozzle, and the divergent wall section has a second region facing away from the throat section, which region has a wall contour deviating from the first region.
First claim
Opening claim text (preview).
The invention claimed is: 1. A thrust nozzle comprising: a convergent wall section downstream of a combustion chamber of a rocket engine, a throat section and a divergent wall section, wherein the divergent wall section has a first region adjacent to the throat section, wherein the wall contour of the first region corresponds to a truncated ideal nozzle, and the divergent wall section has a second region facing away from the throat section, wherein the second region has a wall contour deviating from the wall contour of first region, wherein a transition from the wall contour of the first region to the wall contour of the second region is continuous, wherein a contour angle corresponding to a tangential angle to the wall, at a last point of the wall contour of the first region, corresponds to the contour angle at a first point of the wall contour of the second region, wherein the contour angle of the divergent wall section, seen in longitudinal section through the thrust nozzle, runs continuously on the transition from the first region to the second region such that the contour angle at a last point of the wall contour in the first region and the contour angle at a first point of the wall contour in the second region are the same, and wherein the second region of the divergent wall section is paraboloid-shaped. 2. A rocket engine with a thrust nozzle comprising: a convergent wall section downstream of a combustion chamber of the rocket engine, a throat section and a divergent wall section, wherein the divergent wall section has a first region adjacent to the throat section, wherein the wall contour of the first region corresponds to a truncated ideal nozzle, and the divergent wall section has a second region facing away from the throat section, wherein the second region has a wall contour deviating from the wall contour of first region, wherein a transition from the wall contour of the first region to the wall contour of the second region is continuous, wherein a contour angle corresponding to a tangential angle to the wall, at a last point of the wall contour of the first region, corresponds to the contour angle at a first point of the wall contour of the second region, wherein the contour angle of the divergent wall section, seen in longitudinal section through the thrust nozzle, runs continuously on the transition from the first region to the second region such that the contour angle at a last point of the wall contour in the first region and the contour angle at a first point of the wall contour in the second region are the same, and wherein the second region of the divergent wall section is paraboloid-shaped.
Assignees
Inventors
Classifications
- F02K9/97Primary
Rocket nozzles (thrust or thrust vector control F02K9/80) · CPC title
parabolic · CPC title
characterised by thrust or thrust vector control (burning control of solid propellants F02K9/26; feeding control of liquid or gaseous propellants F02K9/56; re-ignitable, restartable or intermittently operated rocket-engine plants F02K9/94) · CPC title
paraboloid · CPC title
Constructional parts; Details not otherwise provided for · CPC title
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Frequently asked questions
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- What does patent US10590888B2 cover?
- A thrust nozzle, in particular thrust nozzle for a rocket engine, with a convergent wall section, a throat section and a divergent wall section. The divergent wall section has a first region adjacent to the throat section, the wall contour of which region corresponds to a truncated ideal nozzle, and the divergent wall section has a second region facing away from the throat section, which region…
- Who is the assignee on this patent?
- Airbus Ds Gmbh
- What technology area does this patent fall under?
- Primary CPC classification F02K9/97. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Mar 17 2020 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).