IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0673696
(2008-06-12)
|
등록번호 |
US-8783614
(2014-07-22)
|
우선권정보 |
FR-07 05921 (2007-08-20) |
국제출원번호 |
PCT/FR2008/000809
(2008-06-12)
|
§371/§102 date |
20100216
(20100216)
|
국제공개번호 |
WO2009/027587
(2009-03-05)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
5 |
초록
▼
The invention relates to a jet engine nacelle intended to equip an aircraft, comprising a forward air inlet section, a mid-section intended to surround a fan of the jet engine, and an aft section formed from at least first and second hath-shells rotatably mounted about an axis such that they can eac
The invention relates to a jet engine nacelle intended to equip an aircraft, comprising a forward air inlet section, a mid-section intended to surround a fan of the jet engine, and an aft section formed from at least first and second hath-shells rotatably mounted about an axis such that they can each be deployed between a working position in which the half-shells are drawn towards one another and a maintenance position in which the half-shells are spaced apart, at least the first half-shell (11) being equipped with a first follower element (19) in a region situated at a distance from the axis of rotation, the nacelle being equipped with a first fixed guide element (28), the first follower element (19) being designed to bear against a first guide element (28) which is fixed with respect to the jet engine during the rotation of the first half-shell (11). The first half-shell (11) is equipped with a second follower element (20), offset angularly from the first follower element (19) with respect to the axis of rotation of the first half-shell (11), designed to bear against a second guide element (29) during the rotation of the first half-shell (11).
대표청구항
▼
1. A nacelle of a turbojet engine, intended to be fitted to an aircraft, comprising: an air intake front section,a middle section intended to surround a fan of the turbojet engine, anda rear section formed of at least a first and a second half-shell mounted such that they are able to rotate about an
1. A nacelle of a turbojet engine, intended to be fitted to an aircraft, comprising: an air intake front section,a middle section intended to surround a fan of the turbojet engine, anda rear section formed of at least a first and a second half-shell mounted such that they are able to rotate about an axis so that each can be deployed between a work position in which the half-shells are close together and a maintenance position in which the half-shells are distanced from one another,the first half-shell comprising: a first follower element in a region situated some distance from an axis of rotation, the first follower element being designed to bear against a first guide element that is fixed with respect to the turbojet engine as the first half-shell rotates to a first phase of separation of the maintenance position; anda second follower element, angularly offset from the first follower element with respect to the axis of rotation of the first half-shell, the second follower element designed to bear against a second guide element that is fixed as the first half-shell rotates to a second phase of separation of the maintenance position,wherein the first follower element and the second follower progressively bear against the first and second guide elements during movement into the maintenance position and do not bear against the first and second guide elements in the work position. 2. The nacelle as claimed in claim 1, wherein the first and second follower elements respectively comprise a first and a second protruding lump, the first and second guide means comprising at least one bearing ramp against which the first and second lumps bear as the first half-shell rotates. 3. The nacelle as claimed in claim 2, wherein the bearing ramp is a single bearing ramp having a first and a second section, these being positioned in continuation of one another and defining a first and a second guide face respectively forming the first and the second guide elements, the first lump coming to bear against the first guide face at least, the second lump coming to bear against the second guide face at least. 4. The nacelle as claimed in claim 3, wherein the first and second guide faces make an angle with one another. 5. The nacelle as claimed in claim 1, wherein the first and/or the second follower elements are designed to bear against the first and/or the second guide elements over only part of the travel of the first half-shell. 6. The nacelle as claimed in claim 5, wherein, when the nacelle is in the work position, the first and second follower elements are distanced from the first and second guide elements. 7. The nacelle as claimed in claim 5, wherein the first half-shell can be rotated through an angular travel of between 40 and 60°, the first and the second follower elements collaborating with the first and the second guide elements over an angular travel of between 5 and 10°. 8. The nacelle as claimed in claim 7, wherein the work position is identified by an angular position at 0°, the maintenance position being identified by an angular position at between 40 and 60°, the follower elements and the guide elements being arranged in such a way that the first follower element bears against the first guide element in an angular position between about 0.3° and 4°, the second follower element bearing against the second guide element in an angular position of between about 4 and 7°. 9. The nacelle as claimed in claim 1, wherein the first and second guide elements are fixed to a frame that is fixed with respect to the turbojet engine, allowing the rear section to be attached to the middle section. 10. The nacelle as claimed in claim 3, wherein the bearing ramp has a first and a second end, the first and second lumps moving along the ramp in the direction from the first end toward the second end as the first half-shell moves from the work position toward the maintenance position, the second end being radially distanced outward with respect to the first end. 11. The nacelle as claimed in claim 10, wherein the second end is distanced away from the first end in the direction of the middle section.
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