Seal assembly for a gas turbine engine
US12428969B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 7, 2024 |
| Grant date | Sep 30, 2025 |
| Priority date | — |
| Expiry date | Aug 7, 2044 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/55
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes a compressor section and a turbine section in axial flow arrangement defining an axially extending, longitudinal centerline, and arranged as a rotor and a stator. A seal assembly defines a primary seal at an interface of the rotor and the stator and separates an inlet plenum from an outlet plenum. The seal assembly includes one or more aspiration conduits fluidly connected to the primary seal. One or more flingers are positioned at least partially between the seal assembly and the inlet plenum that define one or more passageways fluidly connecting the inlet plenum to the one or more aspiration conduits. The flingers are positioned to direct at least a portion of an airflow within the inlet plenum away from the one or more passageways.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.