Combustion device of a gas turbine including a plurality of passages and chambers defining helmholtz resonators
US8839624B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 30, 2010 |
| Grant date | Sep 23, 2014 |
| Priority date | — |
| Expiry date | Nov 29, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00014
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustion device for a gas turbine that includes a portion having first and second walls that defines an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device. A plurality of first passages connect the inside of the combustion device to the zone between the first and second walls and a plurality of second passages connect the zone between the first and second walls to the outside of the combustion device. A plurality of chambers are defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage. Each chamber defining a Helmholtz damper.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.