Gas turbine engine airfoil squealer pocket cooling hole configuration
US10053992B2 · kind B2 · utility
1Cited by
17References
14Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 2, 2015 |
| Grant date | Aug 21, 2018 |
| Priority date | — |
| Expiry date | Apr 20, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine airfoil includes a body that provides an exterior airfoil surface that extends in a radial direction to a tip. The exterior surface has a leading edge in a forward direction and a trailing edge in an aft direction. The tip includes a squealer pocket that has a recess surface. A cooling passage is arranged in the body. Each of the cooling holes extends from an inlet at the cooling passage to an outlet at the recessed surface. The inlet and outlet are arranged at an angle in an angular direction relative to the recessed surface. The angular direction is toward at least one of the forward and aft directions.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.