System and apparatus for gas turbine combustor inner cap and resonating tubes
US10228138B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 2, 2016 |
| Grant date | Mar 12, 2019 |
| Priority date | — |
| Expiry date | Feb 23, 2037 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00014
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A damping system and apparatus are disclosed for dampening acoustic pressure oscillations of a gas flow in a combustor of a gas turbine engine having at least one combustor with a combustor liner. A second inner cap portion is disposed on the at least one combustor inner liner. The second inner cap portion can have a hot surface, a cold surface, at least one burner opening protruding from the cold surface, and at least one neck ring having an internal opening and protruding from the cold surface. At least one resonating tube having a resonating tube neck is integrated with and protruding from the at least one neck ring. The at least one resonating tube is disposed between adjacent burner openings, and is configured such that the radial dimension is greater than or equal to the axial dimension.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.