Stress relieving slots for turbine vane ring
US8888442B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 30, 2012 |
| Grant date | Nov 18, 2014 |
| Priority date | — |
| Expiry date | Jan 26, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49995
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine vane ring has radially outer and inner annular shrouds defining therebetween an annular gaspath. Circumferentially spaced-apart airfoil vanes extend radially across the gaspath between the outer and the inner shrouds. The radially outer shroud has a circumferentially continuous cylindrical wall extending axially from a leading edge to a trailing edge. A set of circumferentially distributed stress relieving slots is defined in the leading edge of the cylindrical wall at locations adjacent to the leading edge of at least some of said airfoil vanes. The stress relieving slots extend radially through the cylindrical wall from the radially inner surface to the opposed radially outer surface thereof.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.