Invention Grant
- Patent Title: Gas turbine engine vane end devices
-
Application No.: US14132738Application Date: 2013-12-18
-
Publication No.: US09938845B2Publication Date: 2018-04-10
- Inventor: Linnea Taketa , John Munson , Ted J. Freeman
- Applicant: Rolls-Royce North American Technologies, Inc. , Rolls-Royce Corporation
- Applicant Address: US IN Indianapolis US IN Indianapolis
- Assignee: Rolls-Royce Corporation,Rolls-Royce North American Technologies Inc.
- Current Assignee: Rolls-Royce Corporation,Rolls-Royce North American Technologies Inc.
- Current Assignee Address: US IN Indianapolis US IN Indianapolis
- Agency: Barnes & Thornburg LLP
- Main IPC: F01D11/00
- IPC: F01D11/00 ; F01D17/16 ; F04D27/02 ; F04D19/02 ; F04D29/16 ; F01D5/28 ; F01D9/04 ; F01D11/02 ; F01D17/14 ; F16J15/3288 ; F04D29/08 ; F04D27/00 ; F01D11/12

Abstract:
A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.
Public/Granted literature
- US20150003963A1 GAS TURBINE ENGINE VANE END DEVICES Public/Granted day:2015-01-01
Information query