Integrated gas turbine compressor-rotary fuel injector
US6983606B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Sep 9, 2003 |
| Grant date | Jan 10, 2006 |
| Priority date | — |
| Expiry date | May 9, 2024 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C7/22
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An integrated gas turbine compressor and rotary fuel injector is provided which includes a rotary cup combustor having an atomizing element for dispersal and distribution of fuel throughout the combustor. The combustor is positioned in close proximity to the compressor impeller of a gas turbine engine having a centrifugal compressor. The rear face of the impeller, or the rear face of an attachment to the impeller, is contoured to receive the fuel supply. The contour terminates at a lip disposed at a larger radius from the centerline shaft than conventional shaft-mounted slingers. The larger radius of fuel release provides better fuel atomization due to larger rim speeds, thereby improving combustor performance.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.