Rocket engine with integral combustion chamber step structure and its fabrication
US6138450A · 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 F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K9/62
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rocket engine is prepared by fabricating a combustion chamber having an annular wall as a single piece of material. The wall has a first axial region with a first inner diameter, a second axial region with a second inner diameter greater than the first inner diameter, and an inner wall step transition between the first axial region and the second axial region. The combustion chamber is attached to an injector by bonding an annular metallic deposit to the first axial region of the combustion chamber, providing an annular adaptor ring, first welding the adaptor ring to the metallic deposit, and second welding the adaptor ring to the injector.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.