Device for discharging hot air for a jet engine air inlet cowl, with a deicing circuit
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/047
출원번호
US-0739640
(2000-12-20)
우선권정보
FR-0016155 (1999-12-21)
발명자
/ 주소
Alain Porte FR
Stephane Viala FR
출원인 / 주소
Aerospatiale Matra Airbus FR
대리인 / 주소
Stevens, Davis, Miller & Mosher, LLP
인용정보
피인용 횟수 :
13인용 특허 :
5
초록▼
A device for discharging hot air for a jet engine air inlet cowl, with a deicing circuit. The air inlet cowl for a jet engine, the leading edge of which is hollow and swept with a flow of deicing hot air, includes orifices for discharging the hot air flow to the outside of the leading edge, which fo
A device for discharging hot air for a jet engine air inlet cowl, with a deicing circuit. The air inlet cowl for a jet engine, the leading edge of which is hollow and swept with a flow of deicing hot air, includes orifices for discharging the hot air flow to the outside of the leading edge, which form an arrangement such that at least two pressurized hot air jets passing through two adjacent orifices have, downstream of a calibration piece in which the orifices are made, different inclinations with respect to the calibration piece.
대표청구항▼
1. An air inlet cowl for a jet engine, particularly for an aircraft, said air inlet cowl being equipped, at the front, with means for deicing its leading edge and for this purpose comprising:a hollow leading edge delimiting an internal peripheral chamber which is closed by an internal partition, sai
1. An air inlet cowl for a jet engine, particularly for an aircraft, said air inlet cowl being equipped, at the front, with means for deicing its leading edge and for this purpose comprising:a hollow leading edge delimiting an internal peripheral chamber which is closed by an internal partition, said internal partition being equipped with a trough-shaped duct directed toward the rear of said leading edge and open toward the periphery of said air inlet cowl; a pipe which can be connected, at its rear end which is the opposite end to said leading edge, to a pressurized hot air circuit and, at its front end toward said leading edge, to an injector injecting said pressurized hot air into said internal chamber; and a calibration piece made of a material resistant to high temperatures and forming part of the external surface of said cowl, to the rear of said leading edge, said piece closing off said trough-shaped duct and being pierced with at least two orifices to place said internal chamber in communication with the outside, said orifices being distributed at least roughly parallel to said leading edge and serving to calibrate the flow of pressurized hot air ejected by said trough-shaped duct, while deflecting away from said cowl the pressurized hot air jets resulting from the passage of said flow of hot air through said orifices, said orifices having an oblong shape and being oriented at least approximately longitudinally with respect to said cowl, wherein said orifices form an arrangement in which an area of each orifice depends on its position in said arrangement, the area varying according to an extent of lateral positioning of said orifice, wherein at least two pressurized hot air jets passing through two adjacent orifices have, downstream of said calibration piece, different inclinations with respect to said calibration piece, and wherein said piece extends longitudinally in said external surface of said cowl, toward the rear thereof, to act as thermal protection for said cowl with respect to said hot air jets passing through said orifices.
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이 특허에 인용된 특허 (5)
Cook Leonard J. (Canoga Park CA) Rosenthal Herman A. (San Diego CA), Aircraft anti-icing plenum.
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