Gas turbine engine blade with variable density and wide chord tip
US10316671B2 · kind B2 · utility
0Cited by
3References
11Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 17, 2015 |
| Grant date | Jun 11, 2019 |
| Priority date | — |
| Expiry date | Oct 5, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil includes a first portion near the airfoil base with a first density and includes a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.