Invention Grant
- Patent Title: Core arrangement for turbine engine component
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Application No.: US16520911Application Date: 2019-07-24
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Publication No.: US11148191B2Publication Date: 2021-10-19
- Inventor: Matthew S. Gleiner , Bret M. Teller , James T. Auxier
- Applicant: United Technologies Corporation
- Applicant Address: US CT Farmington
- Assignee: United Technologies Corporation
- Current Assignee: United Technologies Corporation
- Current Assignee Address: US CT Farmington
- Agency: Carlson, Gaskey & Olds, P.C.
- Main IPC: B22D25/02
- IPC: B22D25/02 ; F01D5/14 ; F01D5/18 ; F01D9/04 ; F01D25/12 ; B22C9/10 ; B22C9/06 ; B22D15/00 ; B22D17/00

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.
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