Low radius ratio fan for a gas turbine engine
US9239062B2 · kind B2 · utility
5Cited by
4References
13Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 10, 2012 |
| Grant date | Jan 19, 2016 |
| Priority date | — |
| Expiry date | Oct 9, 2034 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A fan blade for a gas turbine engine includes: a straight axial dovetail, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure and suction sides, and further including at least one shoulder protruding from a nominal surface of a selected one of the pressure and suction sides, wherein the at least one shoulder includes a boss defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the selected side.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.