Core arrangement for turbine engine component
US10406596B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 1, 2015 |
| Grant date | Sep 10, 2019 |
| Priority date | — |
| Expiry date | May 17, 2036 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/202
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
A casting core for an airfoil according to an example of the present disclosure includes, among other things, a first portion extending in a first direction and corresponding to a first cavity of an airfoil. The first portion defines a reference plane along a parting line formed by a casting die. The first portion defines a plurality of grooves corresponding to a plurality of trip strips of the airfoil. Each of the plurality of grooves defines a respective groove axis, and the plurality of grooves are distributed in the first direction along a first side of the reference plane such that one or more of the groove axes are oriented with respect to a pull direction of the casting die. A method for fabricating a gas turbine engine component is also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.