Combustion gas discharge nozzle for a rocket engine provided with a sealing device between a stationary part and a moving part of the nozzle
US10316796B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Jul 23, 2014 |
| Grant date | Jun 11, 2019 |
| Priority date | — |
| Expiry date | Aug 29, 2036 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/55
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The invention relates to a combustion gas discharge nozzle for a rocket engine including a stationary part and a moving part extending from the stationary part, the moving part made using flaps positioned downstream from the stationary part and forming an extension of the nozzle, the nozzle including a sealing device extending between the fixed part and the moving part in the form of a flexible membrane withstanding a local temperature of the combustion gases at the nozzle outlet and connecting the end of the stationary part to a border of the flaps or petals forming the moving part, the flexible membrane forming an annular tubing, the sealing device being provided with a duct for injecting gas at the flexible membrane between the stationary part and the moving part extending the nozzle.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.