Apparatus for injecting fuel into gas turbine engines
US6536216B2 · kind B2 · utility
27Cited by
8References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 8, 2000 |
| Grant date | Mar 25, 2003 |
| Priority date | — |
| Expiry date | Dec 8, 2020 |
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.