Stress relief feature for aerated gas turbine fuel injector
US6823677B2 · kind B2 · utility
15Cited by
11References
13Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 3, 2002 |
| Grant date | Nov 30, 2004 |
| Priority date | — |
| Expiry date | Dec 24, 2022 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00005
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Thermal stress relief in a nozzle head of a gas turbine fuel nozzle is provided by forming a slit through each selected air passages of the nozzle head. The strategic location of stress-relief slits contributes to extend the fatigue life of the nozzle with minimal cost and impact on the nozzle aerodynamics.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.