Turbine engine tip clearance control system with thrust bearing
US12421863B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 21, 2023 |
| Grant date | Sep 23, 2025 |
| Priority date | — |
| Expiry date | Jul 21, 2043 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/52
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An assembly is provided for an aircraft powerplant. This assembly includes a rotating assembly, a first structure, a second structure and a thrust bearing. The rotating assembly includes a first bladed rotor and a second bladed rotor. The first bladed rotor includes a plurality of first rotor blades. The second bladed rotor includes a plurality of second rotor blades. The first structure is configured as or otherwise includes a first shroud. The first shroud circumscribes the first bladed rotor. The first shroud is adjacent first tips of the first rotor blades. The second structure is configured as or otherwise includes a second shroud. The second shroud circumscribes the second bladed rotor. The second shroud is adjacent second tips of the second rotor blades. The second shroud is configured to move along an axis relative to the first shroud. The thrust bearing couples the rotating assembly to the second structure.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.