- Patent Title: Gas turbine engine with dovetail connection having contoured root
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Application No.: US15365498Application Date: 2016-11-30
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Publication No.: US10577951B2Publication Date: 2020-03-03
- Inventor: Daniel K. Vetters , Ted J. Freeman , Andrew J. Lazur , Robert J. Shinavski , Wayne S. Steffier
- Applicant: Rolls-Royce North American Technologies, Inc. , Rolls-Royce High Temperature Composites Inc.
- Applicant Address: US IN Indianapolis US CA Cypress
- Assignee: Rolls-Royce North American Technologies Inc.,Rolls-Royce High Temperature Composites Inc.
- Current Assignee: Rolls-Royce North American Technologies Inc.,Rolls-Royce High Temperature Composites Inc.
- Current Assignee Address: US IN Indianapolis US CA Cypress
- Agency: Barnes & Thornburg LLP
- Main IPC: F01D5/30
- IPC: F01D5/30 ; F01D25/24 ; F01D5/28 ; F02C3/04
Abstract:
A gas turbine engine includes a turbine having turbine blades and a shroud having a blade track for positioning radially outside of the blades. At least one of the blades and the blade track are secured in place using a dovetail connection between a dovetail receiver and a dovetail assembly formed to include a contoured root.
Public/Granted literature
- US20180149026A1 Gas Turbine Engine with Dovetail Connection Having Contoured Root Public/Granted day:2018-05-31
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