Invention Grant
- Patent Title: Cooling hole for a gas turbine engine component
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Application No.: US16283279Application Date: 2019-02-22
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Publication No.: US10822971B2Publication Date: 2020-11-03
- Inventor: Brandon W. Spangler , Dominic J. Mongillo
- Applicant: UNITED TECHNOLOGIES CORPORATION
- Applicant Address: US CT Farmington
- Assignee: Raytheon Technologies Corporation
- Current Assignee: Raytheon Technologies Corporation
- Current Assignee Address: US CT Farmington
- Agency: Carlson, Gaskey & Olds, P.C.
- Main IPC: F01D9/02
- IPC: F01D9/02 ; F01D5/18 ; F01D9/06 ; F23R3/00 ; F01D11/20 ; F01D5/28

Abstract:
A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall having an internal surface and an outer skin, a cooling hole having an inlet extending from the internal surface and merging into a metering section, and a diffusion section downstream of the metering section that extends to an outlet located at the outer skin. The diffusion section of the cooling hole includes a first side diffusion angle, a second side diffusion angle and a downstream diffusion angle at a downstream surface of the diffusion section, the downstream diffusion angle being less than the first side diffusion angle and the second side diffusion angle.
Public/Granted literature
- US20190186277A1 COOLING HOLE FOR A GAS TURBINE ENGINE COMPONENT Public/Granted day:2019-06-20
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