Invention Grant
US08635875B2 Gas turbine engine exhaust mixer including circumferentially spaced-apart radial rows of tabs extending downstream on the radial walls, crests and troughs
有权
燃气涡轮发动机排气混合器包括在径向壁上的下游延伸的周向间隔开的径向排的突出部分,波峰和槽
- Patent Title: Gas turbine engine exhaust mixer including circumferentially spaced-apart radial rows of tabs extending downstream on the radial walls, crests and troughs
- Patent Title (中): 燃气涡轮发动机排气混合器包括在径向壁上的下游延伸的周向间隔开的径向排的突出部分,波峰和槽
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Application No.: US12770117Application Date: 2010-04-29
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Publication No.: US08635875B2Publication Date: 2014-01-28
- Inventor: Mark Huzzard Cunningham
- Applicant: Mark Huzzard Cunningham
- Applicant Address: CA Longueuil, QC
- Assignee: Pratt & Whitney Canada Corp.
- Current Assignee: Pratt & Whitney Canada Corp.
- Current Assignee Address: CA Longueuil, QC
- Agency: Norton Rose Fulbright Canada LLP
- Main IPC: F02K9/97
- IPC: F02K9/97

Abstract:
A gas turbine engine exhaust mixer has a plurality of circumferentially distributed alternating inner and outer lobes. The outer lobes protrude into the annular bypass passage of the engine, whereas the inner lobes protrude into the main gas path passage of the engine. The inner and outer lobes respectively define alternating troughs and crest with radial interconnecting walls therebetween. The mixer has a jagged trailing edge including a plurality of tabs extending from each radial wall between the troughs and the crests.
Public/Granted literature
- US20110265447A1 GAS TURBINE ENGINE EXHAUST MIXER Public/Granted day:2011-11-03
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