Gas turbine engine airfoil with large thickness properties
US10508549B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 2, 2015 |
| Grant date | Dec 17, 2019 |
| Priority date | — |
| Expiry date | Apr 6, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil for a gas turbine engine includes an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord is at least 0.4 between 50% and 95% span location.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.