Burner of a gas turbine
US8938968B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 18, 2009 |
| Grant date | Jan 27, 2015 |
| Priority date | — |
| Expiry date | Oct 19, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23D2900/14021
- WIPO fieldThermal processes and apparatus
- WIPO sectorMechanical engineering
Abstract
An exemplary burner of a gas turbine includes a tubular body with an inlet for an entrance of an air flow, downstream of inlet vortex generators, and a lance projecting into the tubular body and having a terminal portion extending along a longitudinal axis of the burner which is provided with nozzle groups for injecting fuel into the tubular body. The nozzle groups can lay in an injection plane perpendicular to the axis of the terminal portion of the lance. Downstream of the lance, the burner has an outlet. A ratio x/L between an axial distance x between the side trailing edge of the vortex generator and the injection plane, and the length L of the tubular body can be less than approximately 0.1052.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.