Rocket engine with combustion chamber step structure insert, and its fabrication
US6138451A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | May 11, 1998 |
| Grant date | Oct 31, 2000 |
| Priority date | — |
| Expiry date | May 11, 2018 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49346
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rocket engine has a combustion chamber formed of an annular wall made of an annular wall material, and an annular insert made of an annular insert material that is of substantially the same thermal expansion coefficient as the annular wall material. The annular insert has an insert outer surface sized to fit within and contact the wall inner surface along less than the wall length. The annular wall and the annular insert are welded together. There is further an attachment between the combustion chamber and an injector. The attachment includes an annular metallic deposit bonded to the combustion chamber, an annular adaptor ring, a weld joint between the adaptor ring and the metallic deposit, and a joint between the adaptor ring and the injector.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.