Turbine assembly for a gas turbine engine and method of manufacturing the same
US7758306B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 22, 2006 |
| Grant date | Jul 20, 2010 |
| Priority date | — |
| Expiry date | Oct 25, 2028 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49236
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine assembly for a gas turbine engine. The turbine assembly includes at least one stator assembly including a radially inner band and at least one stator vane that extends radially outward from the inner band. The stator vane includes an airfoil having a root portion adjacent to the inner band and a tip portion. The airfoil also includes at least one lean directional change that is defined between the root portion and the tip portion. The turbine assembly also includes at least one turbine blade assembly that includes at least one rotor blade. The blade assembly is coupled in flow communication with the stator assembly such that an axial spacing is defined therebetween. The axial spacing defined adjacent to the at least one lean directional change is wider than the axial spacing defined adjacent to the root portion.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.