Turbine vane with non-uniform wall thickness
US10641114B2 · kind B2 · utility
1Cited by
11References
8Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 20, 2014 |
| Grant date | May 5, 2020 |
| Priority date | — |
| Expiry date | Aug 25, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A vane for use in a gas turbine engine has an airfoil extending between a leading edge and a trailing edge, and is generally hollow. The vane has a radially outer platform and a radially inner platform. At least one of the radially inner and radially outer platforms has thicker portions circumferentially located beyond one of the leading edge and the trailing edge, and thinner portions circumferentially beyond circumferential edges of the airfoil. A mid-turbine frame and a gas turbine engine are also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.