Core arrangement for turbine engine component
US11148191B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 24, 2019 |
| Grant date | Oct 19, 2021 |
| Priority date | — |
| Expiry date | Jun 27, 2040 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/202
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
A gas turbine engine according to an example of the present disclosure includes, among other things, a rotor and a vane spaced axially from the rotor, and a blade outer air seal spaced radially from the rotor. At least one of the rotor and the vane includes an airfoil section extending from a platform. At least one of the airfoil section, the platform and the blade outer air seal includes a first cavity extending in a first direction, the first cavity defining a reference plane along a parting line formed by a casting die, and a plurality of trip strips including a first set of trip strips distributed in the first direction along a surface of the first cavity and on a first side of the reference plane, each of the plurality of trip strips defining a respective groove axis extending longitudinally between a first end and an opposed, second end of a respective one the plurality of trip strips, and the groove axes being oriented with respect to a pull direction of the casting die. A casting core and method for fabricating a gas turbine engine component is also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.