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US 10,590,888 B2Granted
Thrust nozzle with double contour and smooth transition
AssigneeAirbus DS GmbH
InventorsManuel Frey, Thomas Aichner, Philip Martin
Life of this patent
Estimating the term…
Abstract
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.
Claims2
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.
5 more elements
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.
5 more elements
Dependencies are inferred from the claim text.