Gas turbine blade with corrugated tip wall
US10260352B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 27, 2016 |
| Grant date | Apr 16, 2019 |
| Priority date | — |
| Expiry date | Jun 9, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02P10/25
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
A gas turbine engine blade (10), including a base portion (12) having a cast wall, and a tip portion (14) attached to the base portion and having a wall (60) formed by an additive manufacturing process. The tip portion wall may be formed to be solid and less than 2 mm in thickness, or it may be corrugated and be greater than 2 mm in thickness. Openings (80) defining the wall corrugations may be semi-circular, rectangular, trapezoidal, or elliptical in cross-sectional shape. The resulting blade has lower tip mass while retaining adequate mechanical properties. The tip portion may be formed to have a directionally solidified grain structure on a base portion having an equiaxed grain structure.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.