Gas turbine engine rotor including squealer tip pocket
US10801331B2 · kind B2 · utility
0Cited by
15References
15Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 7, 2016 |
| Grant date | Oct 13, 2020 |
| Priority date | — |
| Expiry date | Dec 23, 2037 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/202
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine blade includes a blade portion having a leading edge and a trailing edge. A first surface connects the leading edge to the trailing edge and a second surface connects the leading edge to the trailing edge. A tip section is located at a first end of the blade portion and includes a pocket protruding into the tip section from an outermost end of the tip section. The pocket has a first side wall adjacent the first surface and a second side wall adjacent the second surface. At least one of the first side wall and the second side wall have a curve distinct from a curve of the corresponding adjacent surface.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.