Blade/disk dovetail backcut for blade/disk stress reduction (6FA+E, stage2)
US7476085B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 28, 2006 |
| Grant date | Jan 13, 2009 |
| Priority date | — |
| Expiry date | Jul 2, 2026 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/94
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.