Turbine blade for a gas turbine engine
US11879357B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 19, 2022 |
| Grant date | Jan 23, 2024 |
| Priority date | — |
| Expiry date | Dec 19, 2042 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine blade includes an aerofoil including a leading edge, a trailing edge, a first sidewall, a second sidewall, and an internal cooling circuit disposed within the aerofoil and configured to direct a cooling fluid within the aerofoil. The turbine blade includes at least one first recessed portion formed on the first sidewall proximal to a tip of the turbine blade. The first recessed portion is disposed proximal to and spaced apart from the trailing edge of the aerofoil. The first recessed portion includes a base surface, a first surface, and a second surface. The first recessed portion further includes at least one slot extending from the first surface to the internal cooling circuit. The slot is configured to allow a flow of the cooling fluid from the internal cooling circuit to the first recessed portion.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.