[특허]Engine nacelle of an aircraft comprising a vortex generator arrangement

Airbus Operations GmbH

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Engine nacelle of an aircraft comprising a vortex generator arrangement

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-023/06 B64C-007/02 B64D-029/02
미국특허분류(USC)	244/199.1;
출원번호	US-0663094 (2008-06-16)
등록번호	US-8827210 (2014-09-09)
우선권정보	DE-10 2007 027 697 (2007-06-15); DE-10 2008 025 152 (2008-05-26)
국제출원번호	PCT/EP2008/004841 (2008-06-16)
§371/§102 date	20091204 (20091204)
국제공개번호	WO2008/151843 (2008-12-18)
발명자 / 주소	Schwetzler, Detlev
출원인 / 주소	Airbus Operations GmbH
대리인 / 주소	Ingrassia Fisher & Lorenz, P.C.
인용정보	피인용 횟수 : 1 인용 특허 : 7

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An engine nacelle of an aircraft, which engine nacelle on one side comprises several fin-shaped vortex generators so that with an increase in the angle of attack, to improve maximum lift, the field of vorticity generated by said vortex generators overall extends over an increasing region of the wing in the direction of the wingspan, with the first vortex generator being located within a positioning corridor situated between two boundary lines, wherein: the starting point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=35 degrees and the engine-nacelle longitudinal coordinate X=L/4; the end point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=25 degrees and the engine-nacelle longitudinal coordinate X=L·⅔; the starting point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=90 degrees and the engine-nacelle longitudinal coordinate X=L/4; the end point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=55 degrees and the engine-nacelle longitudinal coordinate X=L·⅔.

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1. An engine nacelle of an aircraft, comprising: a nacelle housing having an outer flow surface, a front end, a first side and a second side, and a longitudinal axis that is coaxial with a rotational axis of an engine to be mounted within the nacelle housing; anda plurality of vortex generators, wherein each vortex generator is formed as a fin-shaped vortex generator having a connection region laying completely on the outer flow surface of the nacelle housing, and wherein the plurality of vortex generators are arranged at least on one of the first and second sides of the nacelle housing to generate turbulent airflow,wherein a first of the plurality of vortex generators is positioned closest to the front end of the nacelle housing and at an engine-nacelle longitudinal coordinate of X≧L/4, where L is a length of the nacelle housing, X is a position along a longitudinal coordinate extending parallel to the longitudinal axis, and a starting point of the engine-nacelle longitudinal coordinate is a point at which an entry plane of the nacelle housing intersects the longitudinal axis, and the plurality of vortex generators are arranged in such a way that the overall vorticity field generated by the plurality of vortex generators extends over an increasing wing area in the wingspan direction of a wing of the aircraft as the angle of attack increases in order to improve maximum lift. 2. The engine nacelle according to claim 1, wherein: the nacelle housing includes: (i) a vertical axis that is perpendicular to the longitudinal axis and running through a middle axis of a pylon running parallel to the longitudinal axis, and (ii) an engine-nacelle circumferential angle, phi, which is measured from the vertical axis and circumferentially along the outer flow surface;the first vortex generator is located at a smallest engine-nacelle circumferential angle, phi, as compared with the other vortex generators;a frontmost point of the first vortex generator is located within a positioning corridor situated between first and second boundary lines;a starting point of the first boundary line is a circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=35 degrees and the engine-nacellelongitudinal coordinate X=L/4;an end point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi =25 degrees and the engine-nacelle longitudinal coordinate X=L·⅔;a starting point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=90 degrees and the engine-nacelle longitudinal coordinate X=L/4;an end point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=55 degrees and the engine-nacelle longitudinal coordinate X=L·⅔; andin each case the boundary line is the line that extends over the external circumference of the engine nacelle and is a shortest line between the starting point of said external circumference and the end point of said external circumference. 3. The engine nacelle according to claim 1, wherein the vortex generators are arranged on a side of the nacelle housing, which side faces towards a fuselage. 4. The engine nacelle according to claim 1, wherein at least one of the vortex generators is arranged on the second side, an outboard side, of the nacelle housing. 5. The engine nacelle according to claim 4, wherein: on each of the first and second sides of the nacelle housing, a respective plurality of the vortex generators are arranged;the nacelle housing includes: (i) a vertical axis that is perpendicular to the longitudinal axis and running through a middle axis of a pylon running parallel to the longitudinal axis, and (ii) an engine-nacelle circumferential angle, phi, which is measured from the vertical axis and circumferentially along the outer flow surface;in each of the respective plurality of vortex generators, a frontmost point of a first of the plurality of vortex generators is located within a positioning corridor situated between first and second boundary lines;a starting point of the first boundary line is a circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=35 degrees and the engine-nacelle longitudinal coordinate X=L/4;the end point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=25 degrees and the engine-nacelle longitudinal coordinate X=L·⅔;the starting point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=90 degrees and the engine-nacelle longitudinal coordinate X=L/4;the end point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=55 degrees and the engine-nacelle longitudinal coordinate X=L·⅔; andin each case the boundary line is the line that extends over the external circumference of the engine nacelle and is the shortest line between the starting point of said external circumference and the end point of said external circumference. 6. The engine nacelle according to claim 2, wherein a second vortex generator is situated on the engine-nacelle circumferential angle of phi=10 to 30 degrees below the first vortex generator. 7. The engine nacelle according to claim 1, wherein respective longitudinal directions of the vortex generators are inclined by delta-theta=0 to 10 degrees in relation to the longitudinal axis of the engine nacelle. 8. The engine nacelle according to claim 1, wherein each vortex generator includes an external contour that protrudes from the outer flow surface and extends, gradually rising, from the connection region at the outer flow surface of the nacelle housing to a maximum height at a rear end of the respective vortex generator. 9. The engine nacelle according to claim 8, wherein the external contour of at least one vortex generator is a straight line. 10. The engine nacelle according to claim 8, wherein a ratio of the overall length to the maximum height of the vortex generator is between 1.4 and 3.6. 11. The engine nacelle according to claim 8, wherein the overall length of the vortex generator relative to a length of the engine nacelle is between 0.10 and 0.15. 12. The engine nacelle of an aircraft, according to claim 8, wherein a distance of the external contour of at least one vortex generator from the outer flow surface, defined by a gradient of the connection region in the longitudinal direction of the vortex generator is defined by the function Y=HG·[1−(LG−X)2 /LG2], with: X being a longitudinal coordinate of the vortex generator with an overall length LG of the vortex generator;Y being a height coordinate of the vortex generator with a maximum height HG of the vortex generator in relation to the outer flow surface on the longitudinal coordinate X=LG; andwherein the external contour protruding from the outer flow surface is within the range of ±10% of the Y-value resulting from the function. 13. The engine nacelle according to claim 1, wherein the plurality of vortex generators are arranged to overlap in the longitudinal direction.

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이 특허를 인용한 특허 피인용횟수: 1

Bacon, Andrew. Fuel efficiency of road vehicles. USP20180910081397.

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Engine nacelle of an aircraft comprising a vortex generator arrangement

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Engine nacelle of an aircraft comprising a vortex generator arrangement

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이 특허에 인용된 특허 (7)

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