Guiding system for aircraft nacelle maintenance
First Claim
1. A nacelle for turbojet of an aircraft, including a downstream structure comprising:
- an outer structure,a concentric inner structure surrounding a downstream portion of the turbojet and including an upstream section having a relatively small diameter and a downstream section having a relatively large diameter, wherein said inner structure defines together with the outer structure an annular flow channel, anda guiding system for connecting the inner structure and the downstream portion of the turbojet engine or a portion of a suspension mast,wherein the guiding system includes a means for combining a translation and rotation movement of at least a portion of said inner structure between a working position, in which the inner structure is used as a cowling for the turbojet downstream portion, and a maintenance position in which the inner structure exposes said turbojet downstream portion, thus enabling movement of said portion of the inner structure along the profile of the upstream section having a relatively small diameter, and then of the downstream section having a relatively large diameter,wherein the inner structure rotates about an axis transverse to a longitudinal axis of the nacelle.
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Accused Products
Abstract
A nacelle includes a downstream structure having an outer structure, a concentric inner structure surrounding a downstream portion and an upstream section having a relatively small diameter and a downstream section having a relatively large diameter, the inner and outer structures define an annular flow channel. The nacelle includes a guiding system for connecting the inner structure and downstream portion or a portion of a suspension mast, the system combines a translation and rotation movement of at least a portion of the inner structure between a working position, where the inner structure is used as a cowling for the turbojet downstream portion, and a maintenance position where the inner structure exposes the turbojet downstream portion and enable movement of the portion of the inner structure along the profile of the upstream section having a relatively small diameter, and the downstream section having a relatively large diameter.
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Citations
17 Claims
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1. A nacelle for turbojet of an aircraft, including a downstream structure comprising:
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an outer structure, a concentric inner structure surrounding a downstream portion of the turbojet and including an upstream section having a relatively small diameter and a downstream section having a relatively large diameter, wherein said inner structure defines together with the outer structure an annular flow channel, and a guiding system for connecting the inner structure and the downstream portion of the turbojet engine or a portion of a suspension mast, wherein the guiding system includes a means for combining a translation and rotation movement of at least a portion of said inner structure between a working position, in which the inner structure is used as a cowling for the turbojet downstream portion, and a maintenance position in which the inner structure exposes said turbojet downstream portion, thus enabling movement of said portion of the inner structure along the profile of the upstream section having a relatively small diameter, and then of the downstream section having a relatively large diameter, wherein the inner structure rotates about an axis transverse to a longitudinal axis of the nacelle. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17)
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Specification