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특허 상세정보

Turbine engine nacelle laminar flow control arrangement

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-021/06   
미국특허분류(USC) 244/209 ; 244/208 ; 244/130
출원번호 US-0970058 (1992-11-02)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 44  인용 특허 : 0
초록

A laminar flow control arrangement for use in a nacelle for an aircraft turbine engine. The nacelle has a microporous outer skin in the area where air flow over the skin is to be maintained in laminar flow. A honeycomb core is bonded to the inner surface of the nacelle skin. A perforated back skin is bonded to the inner surface of the core. Several closely spaced circumferential flutes open to the back skin are fastened to the back skin. At least one collector duct is connected to the flutes and a suction pump. In operation, the suction pump pulls air th...

대표
청구항

A laminar flow control aircraft turbine engine nacelle arrangement which comprises: a microporous nacelle outer skin; a honeycomb core bonded to the inner surface of said nacelle skin; a perforated back skin bonded to said core; a plurality of closely spaced circumferential flutes open to said back skin and fastened thereto; at least one longitudinal collector duct operatively connected to said flutes; and suction pump means for drawing air from said collector duct; whereby air is drawn through said microporous skin, core, skin, flutes and collector duct...

이 특허를 인용한 특허 피인용횟수: 44

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