Gas turbine engine blade with variable density and wide chord tip
US10954799B2 · kind B2 · utility
0Cited by
5References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 29, 2019 |
| Grant date | Mar 23, 2021 |
| Priority date | — |
| Expiry date | Apr 29, 2039 |
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 has a leading edge and a trailing edge that define the true chord length. The airfoil includes a first portion near the airfoil base with a first density and 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. The second portion is in the range of 90% span to 100% span.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.