Reducing noise from a combustor of a gas turbine engine
US12359814B2 · kind B2 · utility
0Cited by
3References
14Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 3, 2023 |
| Grant date | Jul 15, 2025 |
| Priority date | — |
| Expiry date | Feb 3, 2043 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method of reducing noise from a combustor of a gas turbine engine includes the steps of establishing a maximum noise limit that may be for a particular frequency range. A primary fuel flow percentage, which may be emitted from a fuel nozzle arrangement having various groupings of simplex and duplex nozzles, is then established. An immersion depth measured between an aft rim of a swirler and a distal tip of the fuel nozzles may then be reduced thereby reducing the noise amplitude.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.