Method of fabricating gas turbine fuel injection
US6604286B2 · kind B2 · utility
6Cited by
4References
4Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 21, 2002 |
| Grant date | Aug 12, 2003 |
| Priority date | — |
| Expiry date | Oct 21, 2022 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49348
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor for a gas turbine engine including a pilot fuel injection assembly that includes a replaceable heat shield is described. The pilot fuel injection assembly also includes a fuel stem and a mixer divider. The fuel stem includes a first end, a second end, and a body extending therebetween. An alignment slot is defined within a portion of the interface between the fuel stem body and the second end. The mixer divider is attached to the fuel stem second end and the heat shield is removably coupled to the mixer divider with a plurality of transfer tubes.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.