Invention Grant
- Patent Title: Gas turbine engine turbine blade tip cooling
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Application No.: US15032736Application Date: 2014-10-10
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Publication No.: US10436039B2Publication Date: 2019-10-08
- Inventor: Brooks E. Snyder , Thomas N. Slavens
- 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.
- International Application: PCT/US2014/060072 WO 20141010
- International Announcement: WO2015/069411 WO 20150514
- Main IPC: F01D5/18
- IPC: F01D5/18 ; F01D5/20 ; B22F3/105 ; B22F5/04 ; B22F7/08 ; B23K26/342 ; B22D25/02 ; B23K15/00 ; B33Y10/00 ; B33Y80/00
Abstract:
A gas turbine engine component includes a structure having a surface configured to be exposed to a hot working fluid. The surface includes a recessed pocket that is circumscribed by an overhang. At least one cooling groove is provided by the overhang.
Public/Granted literature
- US20160265366A1 GAS TURBINE ENGINE TURBINE BLADE TIP COOLING Public/Granted day:2016-09-15
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