Invention Application
- 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.: US20200149414A1Publication Date: 2020-05-14
- Inventor: Scott D. Lewis
- Applicant: United Technologies Corporation
- Main IPC: F01D5/18
- IPC: F01D5/18 ; F23R3/00 ; F02C7/18 ; F02C3/04 ; F01D25/12 ; F01D11/08 ; F01D9/04 ; F01D5/14
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
- US11143039B2 Turbine engine component including an axially aligned skin core passage interrupted by a pedestal Public/Granted day:2021-10-12
Information query
