Method and apparatus for reducing rotor assembly circumferential rim stress
US6471474B1 · kind B1 · utility
94Cited by
40References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 20, 2000 |
| Grant date | Oct 29, 2002 |
| Priority date | — |
| Expiry date | Oct 21, 2020 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49321
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor assembly for a gas turbine engine operates with reduced circumferential rim stress. The rotor assembly includes a rotor including a plurality of rotor blades extending radially outward from an annular rim. A root fillet extends circumferentially around each blade between the blades and rim. The rim includes an outer surface including a plurality of concave indentations extending between adjacent rotor blades and forming a compound radius. Each indentation extends from a leading edge of the rotor blades towards a trailing edge of the rotor blades.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.