Rotor for gas turbine engine
US11060406B2 · kind B2 · utility
2Cited by
6References
14Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 11, 2019 |
| Grant date | Jul 13, 2021 |
| Priority date | — |
| Expiry date | Oct 11, 2039 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor for an aircraft engine includes a hub having a rotation axis, a circumferential array of structural members extending radially outward from the hub to an annular ring, the structural members having cross-sections that increase in length as the structural members extend from the hub to the annular ring, the length of each cross-section of the cross-sections defined by opposite edges of a structural member of the structural members that corresponds to that cross-section, and a circumferential array of airfoils extending radially outward from the annular ring.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.