Rocket engine nozzle system
US8266887B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 4, 2008 |
| Grant date | Sep 18, 2012 |
| Priority date | — |
| Expiry date | Feb 23, 2031 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/71
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.