IP Library Granted Patent US 8,266,887
Granted Patent B2
US 8,266,887 · App. 12/328,166 · Granted Sep 18, 2012

Rocket engine nozzle system

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Quick Facts
Patent No.
US 8,266,887
App. No.
12/328,166
Granted
Sep 18, 2012
Kind
B2
Abstract

The rocket engine nozzle system comprises a set of individual nozzles distributed in a ring around a central core of axially symmetrical shape that presents a central axis. Each individual nozzle placed at the periphery of the central core comprises a circular section throat for receiving gas from a combustion chamber, and a diverging portion that is tangential to the central core. The diverging portion has an outlet section that presents first and second lateral sides that converge radially towards the central axis of the central core, a curved outer side having its convex side facing outwards, and an inner side situated in the vicinity of the central core.

Claims (7)

1. A rocket engine nozzle system, comprising a set of individual nozzles of the rocket engine nozzle system distributed in a ring around a central core of axially symmetrical shape presenting a central axis, wherein each individual nozzle, which is placed at the periphery of the central core, comprises a circular section throat for receiving gas coming from a combustion chamber, and a diverging portion tangential to the central core, and wherein the diverging portion has an outlet section presenting first and second lateral sides that converge radially towards the central axis of the central core, an outer side that is curved with its convex side directed outwards, and an inner side situated in the vicinity of the central core.

2. A system according to claim 1 , wherein said inner side situated in the vicinity of the central core is curved with curvature close to that of the central core, and wherein said inner side presents continuity of slope with the central core, in a meridian plane comprising said central axis and a radius of said central core of axially symmetrical shape.

3. A system according to claim 1 , wherein said inner side situated in the vicinity of the central core is rectilinear.

4. A system according to claim 1 , wherein said outer side presents curvature that constitutes a portion of a circle concentric with the central core.

5. A system according to claim 1 , wherein said outer side presents curvature constituting a portion of an ellipse presenting radii smaller than the central core.

6. A system according to claim 1 , wherein said first and second lateral sides that converge radially towards said central axis are rectilinear.

7. A system according to claim 1 , wherein said first and second lateral sides that converge radially towards said central axis present curvature that is greater than that of the central core.

Assignments (3)
CHANGE OF NAME Recorded Nov 20, 2017
From: AIRBUS SAFRAN LAUNCHERS SAS
To: ARIANEGROUP SAS
Reel/Frame 044800/0080 →
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Nov 10, 2017
From: SNECMA
To: AIRBUS SAFRAN LAUNCHERS SAS
Reel/Frame 044787/0425 →
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Jan 28, 2009
From: VUILLAMY, DIDIER; GAZAVE, ROBERT
To: SNECMA
Reel/Frame 022168/0369 →