Invention Grant
- Patent Title: Gas turbine engine exhaust nozzle
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Application No.: US11014232Application Date: 2004-12-17
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Publication No.: US07578132B2Publication Date: 2009-08-25
- Inventor: John R Webster
- Applicant: John R Webster
- Applicant Address: GB London
- Assignee: Rolls-Royce plc
- Current Assignee: Rolls-Royce plc
- Current Assignee Address: GB London
- Agency: Manelli Dension & Selter PLLC
- Agent Jeffrey S. Melcher
- Main IPC: F02K1/00
- IPC: F02K1/00

Abstract:
A gas turbine engine exhaust nozzle arrangement for the flow of exhaust gases therethrough between an upstream end and a downstream end thereof comprising a nozzle and a plurality of tabs which extend in a generally axial direction from a downstream portion of the nozzle wherein the nozzle further comprises an actuation mechanism capable of moving the tabs between a first deployed position, where the tabs interact with a gas stream to reduce exhaust noise thereof, and a second non-deployed position, where the tabs are substantially aerodynamically unobtrusive.
Public/Granted literature
- US20050229585A1 Gas turbine engine exhaust nozzle Public/Granted day:2005-10-20
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