Method and apparatus for non-parallel turbine dovetail-faces
US6592330B2 · kind B2 · utility
8Cited by
9References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 30, 2001 |
| Grant date | Jul 15, 2003 |
| Priority date | — |
| Expiry date | Dec 2, 2021 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49321
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A dovetail assembly including non-parallel relief faces that facilitates reduced pressure face brinelling in turbine engines. The assembly includes a plurality of rotor blades, each including a dovetail. Each dovetail includes at least a pair of blade tangs including blade relief faces. The dovetail assembly also includes a rotor disk including a plurality of dovetail slots, each sized to receive a dovetail. Each dovetail slot is defined by at least one pair of opposing disk tangs including disk relief faces. The disk relief faces are non-parallel to the blade relief faces when the dovetail is mounted in the dovetail slot.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.