Fabrication of a rocket engine with a transition structure between the combustion chamber and the injector
US6249967A · kind A · utility
4Cited by
6References
13Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 31, 1998 |
| Grant date | Jun 26, 2001 |
| Priority date | — |
| Expiry date | Aug 31, 2018 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49826
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rocket engine is fabricated by a multistep brazing and welding technique. An annular step collar is fns brazed to a trnnsition joint. This first subassembly is second brazed to the combustion chamber. This second subassembly is third brezed to an annular adaptor to form a third subassembly. The succeeding brazing steps are performed at successively lower temperatures. The third subassembly is welded to an injector.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.