Gas turbine blade configuration
US9945232B2 · kind B2 · utility
1Cited by
6References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 12, 2014 |
| Grant date | Apr 17, 2018 |
| Priority date | — |
| Expiry date | May 20, 2035 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/202
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine blade (22), including an airfoil substrate (10) having an exterior surface, wherein: a base (14) of the airfoil substrate is located at a 0% radial on an inner platform surface (20) and a tip (16) of the airfoil substrate is located at a 100% radial; wherein at the 0% radial a cross-sectional profile of the exterior surface is substantially characterized by nominal X and Y coordinates present in Table 1; and wherein at a 50% radial location a cross-sectional profile of the exterior surface is characterized by nominal X and Y coordinates present in Table 6.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.