Aircraft nacelle that incorporates a thrust reversal device
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-003/02
F02K-001/54
B63H-011/10
출원번호
US-0825393
(2010-06-29)
등록번호
US-8701386
(2014-04-22)
우선권정보
FR-09 54735 (2009-07-08)
발명자
/ 주소
Letay, Benoit
Saget, Benjamin
Lesieur, Franck
Flin, Stephane
출원인 / 주소
Airbus Operations SAS
대리인 / 주소
Young & Thompson
인용정보
피인용 횟수 :
1인용 특허 :
5
초록▼
An aircraft nacelle in which a power plant with an outside surface is arranged, whereby the nacelle has an inside wall that with the outside surface of the power plant delimits a secondary annular pipe, at least one moving part so as to create at least one lateral opening, and a thrust reversal devi
An aircraft nacelle in which a power plant with an outside surface is arranged, whereby the nacelle has an inside wall that with the outside surface of the power plant delimits a secondary annular pipe, at least one moving part so as to create at least one lateral opening, and a thrust reversal device that has at least one moving physical obstacle that can occupy a first retracted state in which it does not deflect the stream that circulates in the secondary pipe and another deployed state in which it at least partially deflects the stream that circulates in the secondary annular pipe toward the at least one side opening, characterized in that it includes a ring that is arranged in the secondary pipe, distant from the inside wall of the nacelle and the outside surface of the power plant that supports the at least one moving physical obstacle.
대표청구항▼
1. An aircraft nacelle in which a power plant with an outside surface is arranged, the aircraft nacelle comprising: an inside wall that, with the outside surface of the power plant, delimits a bypass duct;at least one moving part so as to create at least one lateral opening;and a thrust reversal dev
1. An aircraft nacelle in which a power plant with an outside surface is arranged, the aircraft nacelle comprising: an inside wall that, with the outside surface of the power plant, delimits a bypass duct;at least one moving part so as to create at least one lateral opening;and a thrust reversal device comprising at least one moving physical obstacle that can occupy a first retracted state in which said obstacle does not deflect the stream that circulates in the bypass duct and another deployed state in which said obstacle at least partially deflects the stream that circulates in the bypass duct toward said at least one lateral opening;wherein a ring is arranged in the bypass duct, radially spaced from the inside wall of the nacelle and the outside surface of the power plant, said ring comprising:on a first side, a series of outside flaps that can occupy a first retracted state in which the outside flaps do not project relative to the ring and a second deployed state in which the outside flaps do project relative to the ring in the direction of the inside wall of the nacelle so as to at least partially deflect the stream that circulates between the ring and the inside wall of the nacelle in the direction of said at least one lateral opening, andon a second side, a series of inside flaps that can occupy a first retracted state, in which the inside flaps do not project relative to the ring and a second deployed state in which the inside flaps do project relative to the ring in the direction of the outside surface of the power plant so as to at least partially deflect the stream that circulates between the ring and the outside surface of the power plant in the direction of said at least one lateral opening. 2. The aircraft nacelle according to claim 1, wherein the ring has a cross-section in the form of an aircraft wing with a leading edge that is rounded toward the front in the direction of flow of the streams in the bypass duct and a trailing edge that is tapered at the rear. 3. The aircraft nacelle according to claim 2, wherein the ring comprises: a chassis that may be connected directly to the nacelle and/or to the power plant,inside and outside flaps that are hinged relative to the chassis, andactuators for ensuring the change of state of said flaps. 4. The aircraft nacelle according to claim 3, wherein at a front, the chassis comprises a circular shape with a C-shaped cross-section that constitutes the leading edge of the ring, joints that connect a first end of the C of the circular shape to the outside flaps, joints that connect the second end of the C of the circular shape to the inside flaps, at a rear a circular shape with a V-shaped cross-section whose point forms the trailing edge of the ring, a first branch that comes into the extension of the outside flaps and the other branch into the extension of the inside flaps when the flaps are in the retracted state, as well as connecting means that connect the circular shapes. 5. The aircraft nacelle according to claim 4, wherein the connecting means comprise a first series of crosspieces that are arranged at the inside surface of the ring and that are arranged between the inside flaps and that have a V shape for filling in the space between the inside flaps when the inside flaps are in the retracted state. 6. The aircraft nacelle according to claim 4, wherein the connecting means comprise a second series of crosspieces that connect the leading edge to the trailing edge inside of the ring and that are arranged under the outside flaps. 7. The aircraft nacelle according to claim 3, wherein the ring comprises a plurality of pairs of flaps, whereby each pair comprises an outside flap and an inside flap that are arranged opposite, and for each pair, an actuator that is housed in the chassis, whereby a first end of the actuator is connected to said chassis, and whereby the second end of the actuator is connected by means of links respectively to the outside flap and to the inside flap. 8. The aircraft nacelle according to claim 3, wherein the surfaces of the flaps and/or the chassis in contact with the stream that circulates in the bypass duct comprise a coating for the acoustic treatment. 9. The aircraft nacelle according to claim 4, wherein the ring comprises a plurality of pairs of flaps, whereby each pair comprises an outside flap and an inside flap that are arranged opposite, and for each pair, an actuator that is housed in the chassis, whereby a first end of the actuator is connected to said chassis, and whereby the second end of the actuator is connected by means of links respectively to the outside flap and to the inside flap. 10. The aircraft nacelle according to claim 5, wherein the ring comprises a plurality of pairs of flaps, whereby each pair comprises an outside flap and an inside flap that are arranged opposite, and for each pair, an actuator that is housed in the chassis, whereby a first end of the actuator is connected to said chassis, and whereby the second end of the actuator is connected by means of links respectively to the outside flap and to the inside flap. 11. The aircraft nacelle according to claim 6, wherein the ring comprises a plurality of pairs of flaps, whereby each pair comprises an outside flap and an inside flap that are arranged opposite, and for each pair, an actuator that is housed in the chassis, whereby a first end of the actuator is connected to said chassis, and whereby the second end of the actuator is connected by means of links respectively to the outside flap and to the inside flap. 12. The aircraft nacelle according to claim 4, wherein the surfaces of the flaps and/or the chassis in contact with the stream that circulates in the secondary pipe comprise a coating for the acoustic treatment. 13. The aircraft nacelle according to claim 5, wherein the surfaces of the flaps and/or the chassis in contact with the stream that circulates in the secondary pipe comprise a coating for the acoustic treatment. 14. The aircraft nacelle according to claim 6, wherein the surfaces of the flaps and/or the chassis in contact with the stream that circulates in the bypass duct comprise a coating for the acoustic treatment. 15. The aircraft nacelle according to claim 7, wherein the surfaces of the flaps and/or the chassis in contact with the stream that circulates in the bypass duct comprise a coating for the acoustic treatment. 16. The aircraft nacelle according to claim 7, wherein there are more than ten pairs of flaps. 17. The aircraft nacelle according to claim 7, wherein there are more than twenty pairs of flaps.
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이 특허에 인용된 특허 (5)
Hapke ; Donald W., Combination primary and fan air thrust reversal control systems for long duct fan jet engines.
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