Disrupting flow vortices to attenuate resonant tones within a gas turbine engine
US12385417B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 28, 2023 |
| Grant date | Aug 12, 2025 |
| Priority date | — |
| Expiry date | Jul 28, 2043 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/98
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An assembly is provided for a gas turbine engine. This assembly includes a rotating structure of the gas turbine engine, a stationary structure of the gas turbine engine and a volume formed by and extending between the rotating structure and the stationary structure. The rotating structure is rotatable about an axis. The rotating structure includes a seal land and a fluid nozzle. The stationary structure includes a seal element. The seal element is arranged with the seal land to form a seal assembly that seals an annular gap between the stationary structure and the rotating structure. The volume is adjacent the seal element and the seal land. The fluid nozzle is configured to direct a fluid jet out from the rotating structure and into the volume.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.