Gas turbine engine turbine blade airfoil profile
US9115588B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Jul 2, 2012 |
| Grant date | Aug 25, 2015 |
| Priority date | — |
| Expiry date | Apr 19, 2034 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface that extends from a platform in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by a local axial chord, and a span location, wherein the local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.