APPARATUS FOR SUPPORTING A NACELLE OF AN AIRCRAFT ENGINE

Abstract

Apparatus for supporting a nacelle of an aircraft engine is provided by the present disclosure. In one form, the apparatus includes a frame, a supporting structure extending from the frame, and a structure for attaching a nacelle, which is rotatably mounted on the supporting structure and can be rotated about a substantially horizontal axis.

Claims

1. Tooling for supporting a nacelle of an aircraft turbojet engine comprising: a chassis; a support structure extending from the chassis; and a hooking structure of a nacelle, rotatably mounted on the support structure and movable in rotation about a horizontal axis.

2. The tooling according to claim 1, wherein the hooking structure is configured to allow fastening of all members constituting a nacelle on the tooling, in a manner similar to fastening of the members on an aircraft.

3. The tooling according to claim 1, wherein the hooking structure includes a device for fastening an air inlet of a nacelle.

4. The tooling according to claim 1, wherein the hooking structure includes a device for fastening a middle section of a nacelle.

5. The tooling according to claim 1, wherein the hooking structure includes a device for fastening a rear section of a nacelle.

6. The tooling according to claim 1 further comprising a first segment operable to support a rear section of a nacelle and a second segment operable to support a median section and an air inlet of a nacelle, wherein the second segment is movable in translation relative to the first section in a direction parallel to the horizontal axis of rotation of the hooking structure.

7. The tooling according claim 1, wherein the chassis further includes at least one device for displacement of the chassis.

8. The tooling according to claim 7, wherein the device for displacement of the chassis is one of retractable rollers and air bags.

9. The tooling according to claim 1 further comprising a device for rotatably driving the hooking structure.

10. The tooling according to claim 9, wherein the device for rotatably driving the hooking structure is an electric motor.

11. The tooling according to claim 1 further comprising a device for varying a height of the hooking structure.

12. The tooling according to claim 11, wherein the device for varying the height of the hooking structure is electrical.

13. An assembly comprising a nacelle and the tooling according to claim 1.

14. The assembly according to claim 13, wherein the nacelle includes a front section, a middle section, and a rear section.

Description

DRAWINGS

[0031] In order that the disclosure may be well understood, there will now be described various forms thereof, given by way of example, reference being made to the accompanying drawings, in which:

[0032] FIGS. 1 and 2 represent known tooling according to the prior art;

[0033] FIG. 3a is a perspective view of tooling in accordance with the present disclosure, on which a turbojet engine nacelle is assembled;

[0034] FIG. 3b is a side view of the tooling and nacelle of FIG. 3a;

[0035] FIG. 4a is a side view of the tooling of FIG. 3a in accordance with the present disclosure;

[0036] FIG. 4b is a perspective view of the tooling of FIG. 4a;

[0037] FIG. 5a is a front perspective view illustrating a variant of a hooking structure of the nacelle according to the present disclosure;

[0038] FIG. 5b is a rear perspective view of the hooking structure of FIG. 5a;

[0039] FIG. 6a is a side view illustrating a variant of the tooling of FIG. 3a; and

[0040] FIG. 6b is a top view illustrating the tooling of FIG. 6a.

[0041] The drawings described herein are for illustration purposes only and are not intended to limit the scope of the present disclosure in any way.

DETAILED DESCRIPTION

[0042] The following description is merely exemplary in nature and is not intended to limit the present disclosure, application, or uses. It should be understood that throughout the drawings, corresponding reference numerals indicate like or corresponding parts and features.

[0043] FIGS. 3a and 3b represent an example of one form of tooling 1 in accordance with the present disclosure, this tooling allowing supporting the entirety of a turbojet engine nacelle 2. In the example of FIGS. 3a and 3b, the nacelle 2 is a bypass turbojet engine nacelle. In the example, the nacelle 2 generally comprises three subassemblies: [0044] a front section 210, or air inlet; [0045] a middle section 220; and [0046] a rear section 230.

[0047] According to the present disclosure, the tooling 1 is shaped so as to allow the fastening of each of these three subassemblies on the tooling 1, in a manner identical to the fastening thereof on an aircraft under normal operating conditions, that is to say in a manner identical to the normal fastening thereof on the turbojet engine and/or on the motor pylon of an aircraft.

[0048] The tooling 1 includes a horizontal chassis 10 which supports a vertical structure 11. The vertical structure 11 carries at its upper end a hooking structure 12 of a turbojet engine nacelle 2. In the example, the chassis 10 has a general U-shape, elongated in a longitudinal direction. The chassis 10 includes, in the example, two longitudinal arms 110 and a cross-member 112. In order to facilitate the displacement thereof, the chassis 10 may include devices such as retractable rollers 114.

[0049] According to the present disclosure, the hooking structure 12 is pivotally mounted on the vertical structure 11, about a substantially horizontal axis of rotation, and substantially coincident with the longitudinal axis of the nacelle 2 when said nacelle is assembled on the tooling 1. The tooling 1 includes a device 120 for rotatably driving the hooking structure 12, comprising for example an electric motor. Thus, it is possible to control the rotation of the hooking structure 12, and therefore of the nacelle 2 it supports. The finishing operations of the nacelle, in particular the painting operations, are greatly facilitated since a ground operator may access to the entire nacelle, regardless of the dimensions of said nacelle. Similarly, quality control operations are simplified since they may be carried out by a ground operator.

[0050] FIG. 4a shows the tooling 1 in accordance with the present disclosure, without a nacelle assembled on the hooking structure. The hooking structure comprises two main segments, a rear segment 121 and a front segment 122. The rear segment 121 is secured to the vertical structure 11 via a pivot connection. In the example of FIGS. 4a and 4b, the rear segment carries at its rear end a toothed ring 123 allowing rotatably driving the hooking structure 12. The front 122 and rear 121 segments carry the set of the devices serving to the fastening of a nacelle on the tooling 1. These fastening devices include an air inlet fastening support 124, a median section fastening support 125, and two rear section fastening supports 126, 127. The set of the devices for fastening the different portions correspond to the different fastening points provided on the turbojet engine and/or the motor pylon corresponding to the nacelle. Thus, the fastening devices 124, 125, 126, 127 are configured such that the nacelle 2 is fastened on the tooling 1 in exactly the same manner as on an aircraft in an operating condition. In particular, manipulations and movements of portions of the nacelle which are possible in real conditions may be reproduced when the nacelle is mounted on the tooling. This includes in particular the displacement and/or the opening of the different cowls of the nacelle in the maintenance position, or the opening, if necessary, of the thrust reversers.

[0051] FIG. 4b represents the hooking structure 12 of the tooling of FIG. 4a and shows the fastening devices 124, 125, 126, 127 in more detail.

[0052] The air inlet fastening support 124 forms a support for fastening the air inlet flange of the nacelle 2, this flange being located in the front section 210 of the nacelle 2. The air inlet fastening support 124 includes for this purpose fastening plates 1240, in the example six fastening plates 1240 which are each disposed at the end of an arm 1242.

[0053] The middle section fastening support 125 includes a beam 1250 on which three attachment devices 1252 are fastened, allowing the fastening, via hinges, of the members forming the median section 220 of the nacelle 2.

[0054] The first rear section fastening support 126 includes a beam 1260 on which four attachment devices 1262 are fastened allowing the fastening, via hinges, of the members forming the rear section 230 of the nacelle 2. The second rear section fastening support 127 is formed by a star-shaped structure including branches 1270 and peripheral ends 1272. The peripheral ends 1272 partially reproduce the groove of the blade/groove-type flanging system (also called “V-blade/V-groove”).

[0055] The example of FIGS. 4a and 4b shows a hooking structure 12 including front 122 and rear 121 segments mainly constituted by an assembly of tubular beams.

[0056] The example shown in FIGS. 5a and 5b shows that the hooking structure may be made in different manners, as long as the different hooking points of the nacelle are present and correctly positioned. In this example, it is can be seen that the front 122 and rear 121 segments form a single tubular structure 128. This tubular structure 128 carries the different fastening devices 124, 125, 126, 127.

[0057] In the example shown in FIGS. 5a and 5b, additional members are further represented, which are of course compatible with the various forms of the present disclosure. These members are drainage systems 129 (also called “drain masts”), one or several damping and stopping devices 130 (also called “bumpers”). Furthermore, FIG. 5a shows that the rear segment 121 is provided at its top end with panels 131 corresponding to access hatches of a nacelle called “hinge access panels.” These panels 131 are detachable and may also equip the front segment 122.

[0058] FIGS. 6a and 6b show a variant of the tooling of FIG. 3a, including a device allowing varying the height of the hooking structure 12 relative to the chassis (see arrow H in FIG. 6a), in particular in order to facilitate the work of the operators during the different painting or quality control operations. Furthermore, the support structure 12 includes clearances 132 in order to allow the passage of the ends of the fairings called beaver-tailed fairings (also called “beavertails”) during the rotation of the nacelle, in case where one of the thrust reverser cowls is in the retracted position, as shown in FIG. 6b.

[0059] In the various forms of the present disclosure, it can be provided that the front segment 122 may slide (forward) relative the rear segment 121. This disposition allows releasing the space necessary for detaching (or conversely mounting) the rear section 230 of the nacelle 2 without having to previously detach the middle section 220.

[0060] Moreover, the chassis is shaped so as to provide the stability necessary for the tooling, taking into account the total mass of a nacelle. Furthermore, the chassis, and in particular the size thereof, will be advantageously provided so that the tooling may carry a half-nacelle while having sufficient lateral stability.

[0061] Although the present disclosure has been described in connection with a particular example of various forms, it is quite obvious that it is in no way limited thereto and that it comprises all the technical equivalents of the described means as well as the combinations thereof if said technical equivalents are included within the scope of the present disclosure.

[0062] The description of the disclosure is merely exemplary in nature and, thus, variations that do not depart from the substance of the disclosure are intended to be within the scope of the disclosure. Such variations are not to be regarded as a departure from the spirit and scope of the disclosure.