Gas turbine engine airfoil
US10774650B2 · kind B2 · utility
0Cited by
5References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 12, 2017 |
| Grant date | Sep 15, 2020 |
| Priority date | — |
| Expiry date | May 10, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A curvature inflection point is located between 30% and 70% of an axial chord length of the airfoil.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.