Stator assembly for compressor mid-plane rotor balancing and sealing in gas turbine engine
US11236615B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 1, 2020 |
| Grant date | Feb 1, 2022 |
| Priority date | — |
| Expiry date | Sep 1, 2040 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/15
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A stator assembly, at a compressor mid-plane in a gas turbine engine, to be mounted around a rotor disc, enables access to the rotor disc (e.g., for trim balancing), without requiring disassembly of the stator assembly and/or a compressor case in which the stator assembly is housed, via a removable stator vane. The stator assembly may comprise vane apertures, aligned along a radial axis, that hold the removable stator vane when inserted into the stator assembly, and provide a radial pathway to the rotor disc, when the removable stator vane is removed from the stator assembly. In addition, a case access assembly may seal the removable stator vane in place within a compressor case when engaged, and provide access to the removable stator vane and radial pathway through the compressor case when disengaged. This enables trim balancing of a mid-plane compressor rotor assembly through the stator assembly and compressor case.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.