Turbine blade platform trailing edge undercut
US6761536B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 31, 2003 |
| Grant date | Jul 13, 2004 |
| Priority date | — |
| Expiry date | Jan 31, 2023 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/30
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine blade having an airfoil to platform interface configured to minimize thermal and vibratory stresses is disclosed. This configuration minimizes exposure to the conditions that are known to cause high cycle fatigue and low cycle fatigue cracks. The turbine blade incorporates a channel in the platform trailing edge that extends from the platform concave face to the platform convex face and has a portion having a constant radius. The channel extends a sufficient distance into a stress field created by the aerodynamic loading of the turbine blade airfoil in order to redirect the mechanical stresses away from the blade trailing edge while allowing the platform trailing edge region to be more responsive to thermal fluctuations.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.