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, andguiding 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.
2 Assignments
0 Petitions
Accused Products
Abstract
The invention relates to a nacelle (100) for the turbojet of an aircraft that comprises a downstream structure including: an outer structure (106), a concentric inner structure (109) surrounding a downstream portion (111) of the turbojet and including an upstream section having a relatively small diameter (113) and a downstream section having a relatively large diameter (114), wherein said inner structure (109) defines together with the outer structure (106) an annular flow channel (108); and a guiding system (140) for connecting the inner structure (109) and the downstream portion (111) of the turbojet engine or a portion of a suspension mast; characterised in that the guiding system (140) includes a means for combining a translation and rotation movement of at least a portion of said inner structure (109) between a working position, in which the inner structure (109) is used as a cowling for the turbojet downstream portion (111), and a maintenance position in which the inner structure (109) exposes said turbojet downstream portion (111), thus enabling the movement of said portion if the inner structure (109) along the profile of the upstream section having a relatively small diameter (113), and then of the downstream section having a relatively large diameter (114).
18 Citations
15 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 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. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15)
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Specification