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특허 상세정보

Gas turbine engine exhaust mixer including circumferentially spaced-apart radial rows of tabs extending downstream on the radial walls, crests and troughs

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-009/97   
미국특허분류(USC) 060/770; 060/262; 181/213
출원번호 US-0770117 (2010-04-29)
등록번호 US-8635875 (2014-01-28)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Norton Rose Fulbright Canada LLP
인용정보 피인용 횟수 : 3  인용 특허 : 59

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.


1. An exhaust mixer assembly for a gas turbine engine of the type having an outer annular passage coaxially surrounding a core passage, the exhaust mixer assembly comprising a duct surrounding the outer annular passage and extending to a duct exit, the outer and core passages coaxially communicating with a lobed exhaust mixer, the lobed exhaust mixer having and upstream end, a downstream end and a lobed annular wall extending therebetween, the lobed annular wall defining a plurality of circumferentially distributed alternating inner and outer lobes, the ...

이 특허에 인용된 특허 (59)

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