Invention Grant
- Patent Title: Hybrid cooling schemes for airfoils of gas turbine engines
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Application No.: US15875500Application Date: 2018-01-19
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Publication No.: US10697307B2Publication Date: 2020-06-30
- Inventor: Nicholas M. LoRicco , Ricardo Trindade , Dominic J. Mongillo, Jr.
- 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: Cantor Colburn LLP
- Main IPC: F01D5/18
- IPC: F01D5/18 ; F01D9/06

Abstract:
Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between a first platform and a second platform, a first platform feed cavity defined by the first platform, a second platform exit cavity defined by the second platform, a first hybrid skin core cooling cavity passage formed within the airfoil body and fluidly connecting the first platform feed cavity to the second platform exit cavity, and at least one purge aperture formed in the second platform and fluidly connecting the second platform exit cavity to an exterior of the second platform. The airfoil body does not include any apertures fluidly connecting the first hybrid skin core cooling cavity passage to an exterior of the airfoil body.
Public/Granted literature
- US20190226344A1 HYBRID COOLING SCHEMES FOR AIRFOILS OF GAS TURBINE ENGINES Public/Granted day:2019-07-25
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