Non-circular stress reducing crossover
US12012866B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 12, 2023 |
| Grant date | Jun 18, 2024 |
| Priority date | — |
| Expiry date | Jun 12, 2043 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil for a gas turbine engine is configured to extend in a radial direction relative to an engine axis from an inner diameter to an outer diameter. The airfoil comprises a body having a base disposed at the inner diameter, a tip disposed at the outer diameter, a leading edge, a trailing edge, and pressure and suction side walls extending between the leading edge and the trailing edge and between the base and the tip. The body defines an interior cavity. A first wall is disposed in the interior cavity, extends radially, and adjoins the pressure side wall and the suction side wall to form a first cooling channel. A first hole through the first wall connects the first cooling channel to a second cooling channel. The first hole has a profile that tapers inward toward the base.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.