Gas turbine combustor
US10443845B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 4, 2015 |
| Grant date | Oct 15, 2019 |
| Priority date | — |
| Expiry date | Apr 23, 2037 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03045
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine combustor includes a combustor liner, a flow sleeve in which the combustor liner is provided and an annular flow passage formed between the combustor liner and the flow sleeve, through which compressed air flows. The flow sleeve includes an internal-diameter changing portion diagonally connected to the flow sleeve and an internal-diameter reducing portion connected to the internal-diameter changing portion and extending along the flow direction of the compressed air. The combustor liner includes an annular protruding portion annularly formed on an outer wall of the combustor liner and protruding toward the flow sleeve. The annular protruding portion is located at a position on the outer wall of the combustion liner, the position facing a connection position between the flow sleeve and the internal-diameter changing portion or being at an upstream side of the position facing the connection position in the flow direction of the compressed air.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.