Tangential rotor blade slot spacer for a gas turbine engine
US11242761B2 · kind B2 · utility
0Cited by
13References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 18, 2020 |
| Grant date | Feb 8, 2022 |
| Priority date | — |
| Expiry date | Feb 18, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor disk assembly for a gas turbine engine includes a rotor disk that defines an axis, the rotor disk comprising a slot within a rim of the disk and a spacer within the slot, the spacer having a clearance feature sized to permit rotation of a rotor blade from an insertion position to an installed position.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.