The present disclosure relates to a propulsion unit for an aircraft including a nacelle which surrounds a turbojet engine. The nacelle has an inner structure surrounding a downstream compartment of the turbojet engine, and the inner structure includes two annular half-portions. The propulsion unit a
The present disclosure relates to a propulsion unit for an aircraft including a nacelle which surrounds a turbojet engine. The nacelle has an inner structure surrounding a downstream compartment of the turbojet engine, and the inner structure includes two annular half-portions. The propulsion unit also includes a rail/guide unit and to move the annular half-portions between a working position and a maintenance position. In particular, the rail/guide unit radially moves away the annular half-portions relative to a longitudinal axis of the nacelle, during a translation movement of the annular half-portions. The nacelle is provided with a connecting rod which is connected to the annular half-portions and to the turbojet engine and so that the connecting rod contributes to rotate the annular half-portions about the rail.
대표청구항▼
1. A propulsion unit for an aircraft comprising: a bypass-type turbojet engine;a nacelle surrounding the turbojet engine, the nacelle comprising a downstream structure comprising an outer structure which defines, with a concentric inner structure surrounding a downstream compartment of the turbojet
1. A propulsion unit for an aircraft comprising: a bypass-type turbojet engine;a nacelle surrounding the turbojet engine, the nacelle comprising a downstream structure comprising an outer structure which defines, with a concentric inner structure surrounding a downstream compartment of the turbojet engine, an annular flow channel, the concentric inner structure being realized in a form of two annular half-portions; andmeans for displacing and for guiding at least one of the two annular half-portions, the displacing and guiding means being configured to displace and to guide said at least one of the two half-portion alternately between a working position wherein the two annular half-portions form a shell around the downstream compartment of the turbojet engine, and a maintenance position wherein said at least one annular half-portion uncovers at least partially the downstream compartment, the displacing and guiding means comprising at least one rail/slide system providing translational guiding of said at least one annular half-portion, alternately between an upstream and a downstream of the nacelle, and at least one connecting rod connected, on the one hand to said at least one annular half-portion and on the other hand to the turbojet engine, said at least one annular half-portion being pivotally mounted onto said at least one rail/slide system,wherein the rail/slide system is configured to radially move away with respect to a longitudinal axis of the nacelle at least an upstream upper portion of the at least one annular half-portion through which said half-portion is pivotably mounted on the rail/slide system, during a displacement of said at least one annular half-portion from the upstream toward the downstream of the nacelle, andwherein said connecting rod is configured to drive the at least one annular half-portion in rotation about an axis along which at least one guide rail of the rail/slide system extends, simultaneously with the displacement of the at least one annular half-portion along said guide rail. 2. The propulsion unit according to claim 1, wherein said at least one connecting rod comprises a first end mounted in a ball-joint connection on a lower portion of said at least one annular half-portion and a second end pivotally mounted on a fixed attachment point of the turbojet engine. 3. The propulsion unit according to claim 1, wherein said at least one connecting rod supports said at least one annular half-portion in the maintenance position. 4. The propulsion unit according to claim 1, wherein said at least one guide rail of the rail/slide system is secured to the downstream compartment of the turbojet engine. 5. The propulsion unit according to claim 4, wherein the axis along which said at least one guide rail extends is substantially non-collinear with a longitudinal axis of the nacelle. 6. The propulsion unit according to claim 4, wherein one of ends of said at least one guide rail is located close to an engine pylon supporting the propulsion unit. 7. The propulsion unit according to claim 4, wherein said at least one guide rail is supported by an engine pylon supporting the propulsion unit. 8. The propulsion unit according to claim 4, wherein the rail/slide system comprises at least one slide supported by said upstream portion of at least one annular half-portion, said at least one slide configured to slide along said at least one guide rail. 9. The propulsion unit according to claim 8, wherein said upstream portion of the at least one annular half-portion is located in an upstream upper area of said at least one annular half-portion. 10. The propulsion unit according to claim 1, wherein an angle of rotation of said at least one annular half-portion about said at least one rail is between 0° and 30°. 11. The propulsion unit according to claim 1, wherein the means for displacing and for guiding at least one of the two half-portions comprise a second rail/slide system comprising: a rail secured to the downstream compartment of the turbojet engine, substantially diametrically opposite to an engine pylon supporting the propulsion unit; anda slide movable in translation along the rail when activating actuating means,wherein the slide further supports the displacing means when activating the actuating means of the slide. 12. The propulsion unit according to claim 11, wherein the displacing means comprise at least one counter connecting rod, one end of which is pivotally mounted on the slide and other end of which is pivotally mounted on said at least one connecting rod. 13. The propulsion unit according to claim 1, wherein the downstream compartment of the turbojet engine is equipped with an accessory gearbox. 14. The propulsion unit according to claim 13, wherein the accessary gearbox comprises at least two arms forming V-shape. 15. The propulsion unit according to claim 1, wherein the guide rail of the rail/slide system is shaped so that the axis along which the guide rail extends is substantially non-collinear with the longitudinal axis of the nacelle and is shaped to radially move away from said longitudinal axis when progressing to downstream area of said propulsion unit.
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이 특허에 인용된 특허 (5)
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