- Patent Title: Gas turbine engine blade with ceramic tip and cooling arrangement
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Application No.: US15102890Application Date: 2014-12-02
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Publication No.: US10415394B2Publication Date: 2019-09-17
- Inventor: Thomas N. Slavens , Mosheshe Camara-Khary Blake , Timothy J. Jennings , Nicholas M. LoRicco , Sasha M. Moore , Clifford J. Musto
- 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/US2014/068072 WO 20141202
- International Announcement: WO2015/094636 WO 20150625
- Main IPC: F01D5/14
- IPC: F01D5/14 ; F01D5/18 ; F01D5/20 ; F01D5/28
Abstract:
A blade for a gas turbine engine includes an airfoil that extends a span from a root to a tip. The airfoil is provided by a first portion near the root and has a metallic alloy. A third portion near the tip has a refractory material. A second portion joins the first and third portions and has a functional graded material.
Public/Granted literature
- US20160312617A1 GAS TURBINE ENGINE BLADE WITH CERAMIC TIP AND COOLING ARRANGEMENT Public/Granted day:2016-10-27
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