Combustor arrangement for a gas turbine
US10352568B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 28, 2015 |
| Grant date | Jul 16, 2019 |
| Priority date | — |
| Expiry date | Dec 29, 2036 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03341
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor arrangement for a gas turbine includes a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. These elements of the combustor arrangement are arranged in a row to form a flow path extending between the first combustion chamber and the second burner. The arrangement includes a central lance body in the flow path, extending from the first burner into the second burner, which lance body includes at least one air duct for providing air for the mixer, wherein the air is injected into the combustor through air supply elements.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.