Shrouded turbine blades with locally increased contact faces
US7001152B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 9, 2003 |
| Grant date | Feb 21, 2006 |
| Priority date | — |
| Expiry date | Oct 9, 2023 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49336
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A one-piece blade for a turbine section of a gas turbine engine, the blade comprising a root, an airfoil and a shroud. The shroud extends generally perpendicularly from a tip of the airfoil and is defined by a pair of opposed bearing faces and a pair of opposed non-bearing faces. The bearing faces each have a contact portion adapted to contact a shroud of an adjacent blade. The shroud has a substantially constant nominal thickness and the bearing faces have a substantially constant face thickness across the contact portion, the face thickness being greater than the nominal thickness. The transition between the face thickness and the nominal thickness is substantially discontinuous.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.