Invention Grant
- Patent Title: Turbine engine component including an axially aligned skin core passage interrupted by a pedestal
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Application No.: US16669698Application Date: 2019-10-31
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Publication No.: US11143039B2Publication Date: 2021-10-12
- Inventor: Scott D. Lewis
- Applicant: Raytheon 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: F01D5/00
- IPC: F01D5/00 ; F01D5/18 ; F01D5/14 ; F01D9/04 ; F01D11/08 ; F01D25/12 ; F02C3/04 ; F02C7/18 ; F23R3/00
Abstract:
A component for a turbine engine includes a fore edge connected to an aft edge via a first surface and a second surface. Multiple cooling passages are defined within the turbine engine component. A skin core passage is defined immediately adjacent the first surface, and at least one pedestal interrupts a flow path through the skin core passage.
Public/Granted literature
- US20200149414A1 TURBINE ENGINE COMPONENT INCLUDING AN AXIALLY ALIGNED SKIN CORE PASSAGE INTERRUPTED BY A PEDESTAL Public/Granted day:2020-05-14
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