• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a tool (1) for supporting a nacelle (2) of an aircraft turbojet, comprising: - a chassis (10); a support structure (11) rising from the chassis; - An attachment structure (12) of a nacelle, rotatably mounted on the support structure (11) and rotatable about a substantially horizontal axis.
    公开号:FR3031084A1
    申请号:FR1463396
    申请日:2014-12-29
    公开日:2016-07-01
    发明作者:Thierry Drieu；Patrice Chantal；Anthony Damour；Stephane Labazee
    申请人:Aircelle SA；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a handling assembly of an aircraft engine nacelle, such as a turbojet engine. An aircraft is driven by one or more propulsion units, each comprising a turbojet engine housed in a nacelle.
    [0002] Modern nacelles are intended to house a turbojet engine, capable of generating a hot gas flow (also called primary flow), from the combustion chamber of the turbojet, and a cold air flow (also called secondary flow), generated by the fan blades of the turbojet engine and circulating outside the turbojet engine through an annular passage (also called a vein) formed between a shroud of the turbojet engine (or an internal structure the nacelle surrounding the turbojet engine) and an inner wall of the nacelle. The primary and secondary flows are ejected from the turbojet engine from the rear of the nacelle. A nacelle has a tubular structure usually comprising an air inlet in front of the turbojet engine, a median section intended to surround the fan of the turbojet engine, and a rear section, the rear section generally housing thrust reverser means and being intended for surround the combustion chamber of the turbojet engine. In addition, the nacelle is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine. The rear section of the nacelle is usually formed of first and second half-shells of substantially hemi-cylindrical shape, disposed on either side of a longitudinal vertical plane of symmetry of the nacelle. The median and rear sections are, in a conventional manner, connected to one another by a frame, the first and second half-shells being generally equipped with positioning means cooperating in the working position with complementary positioning means arranged on the framework. Due to the size, weight and relative fragility of the nacelle components, the finishing, final assembly and handling operations are complex, time consuming and require expensive equipment. Finishing operations include painting operations, which are crucial to the final quality of the exterior appearance. For as much these operations do not seem currently optimized in terms of quality and speed of execution. In conventional manner, the painting operations of a nacelle are carried out by means of support trolleys dedicated to the various subassemblies of a nacelle, namely the air inlet, the two half-parts forming the section. median and the two half-parts forming the rear section. Each of these elements is thus fixed on a corresponding support carriage to be painted by an operator. Examples of these known devices are shown in Figures 1 and 2. Figure 1 shows a painting tool 100 for a nacelle air inlet 101. Figure 2 shows a painting tool 201 for a rear half-section 210 of nacelle. This conventional method has several disadvantages. In the first place, it requires a large number of specific equipment, including no less than five different support carriages for a single nacelle. In addition, for the largest elements, the operators are forced, to access all the areas to be painted, to use platforms of different heights, which implies for operators a very degraded ergonomics. Different operations subsequent to painting operations are also impacted by poor ergonomics and efficiency. Indeed, once the painting operations are complete, the nacelle 20 must be equipped and mounted on a motor, called "slave motor", to perform the latest quality control (including including dimensional control). This implies to have to handle each subset of the nacelle to mount them on the slave engine, with the risks and difficulties that entails. Then, the nacelle is presented to the client mounted on the slave engine, so that the customer can perform the checks and decide whether or not to accept the delivery of this nacelle. Finally, the nacelle is dismantled and the subassemblies are installed on specific transport trolleys to be delivered to the customer. Handling operations are therefore performed several times.
    [0003] At each stage of this process, the handling of the elements constituting the nacelle is a critical operation because the nacelles are very heavy parts and very large dimensions, but relatively fragile. In general, the precautions necessary to handle the elements of a nacelle are time-consuming and risk-generating.
    [0004] In view of the foregoing, there is therefore a need to improve both the painting operations of a nacelle, the quality control operations of the nacelle as well as the transport operations of the nacelle. The present invention proposes to respond to these constraints with the aid of a single tool. To this end, the invention relates to a support tool for a nacelle of an aircraft turbojet, comprising: - a chassis; a support structure rising from the chassis; - An attachment structure of a nacelle, rotatably mounted on the support structure and movable in rotation about a substantially horizontal axis. Thus, by providing a single tool for fixing the entirety of the elements of a nacelle, in their normal operating position, the entire nacelle can be painted in a single painting operation, which represents a great saving of time and quality, especially for the painting of type logos said through. In addition, thanks to the rotational nature of the tool, all parts of the nacelle can be easily reached by a ground operator. In addition, each element of the nacelle being fixed to the tool in the same way that it would, in real condition, be attached to a turbojet engine, the tooling makes it possible to carry out all the final assembly operations and finishing operations. the nacelle on the engine, as for example the qualitative control. Finally, the displacement of the mounted nacelle can be ensured directly, without having to carry out additional handling operations. In one embodiment, the attachment structure of the nacelle comprises a nacelle air inlet fixing device. In one embodiment, the hooking structure of the nacelle comprises a support for fixing the middle section of a nacelle.
    [0005] In one embodiment, the attachment structure of the nacelle comprises a device for fixing the rear section of a nacelle. In one embodiment, the tooling comprises a first section, intended to carry the rear section of a nacelle, and a second section, intended to carry the middle section and the air inlet of a nacelle, the second section. being mobile in translation relative to the first section, in a direction parallel to the axis of rotation of the attachment structure.
    [0006] In one embodiment, the chassis is equipped with devices allowing its displacement, such as retractable wheels or air cushions. In one embodiment, the tooling comprises a device 5 for rotating the attachment structure, such as an electric motor. In one embodiment, the tooling comprises a device, in particular an electrical device, for varying the height of the attachment structure.
    [0007] The invention will be better understood on reading the detailed description which follows, given with reference to the appended drawings, in which: FIGS. 1 and 2 represent known tools; - Figures 3a and 3b show views of a tool according to the invention, on which is assembled a turbojet engine nacelle; - Figures 4a and 4b show views of a tool according to the invention; - Figures 5a and 5b show an alternative embodiment of the attachment structure of the nacelle; FIGS. 6a and 6b show a variant of the tool of FIG. 3a. FIGS. 3a and 3b show an exemplary embodiment of a tool 1 according to the invention, this tooling making it possible to support the entirety of a nacelle 2 of a turbojet engine. In the example of FIGS. 3a and 3b, the nacelle 2 is a nacelle of a turbojet engine. The tool 1 comprises a horizontal frame 10 which supports a vertical structure 11. The vertical structure 11 carries at its upper end a fastening structure 12 of a nacelle 2 of a turbojet engine. In the example, the frame 10 has a generally U-shaped shape elongate in a longitudinal direction. The frame 10 comprises in the example two longitudinal arms 110 and a cross member 112. In order to facilitate its movement, the frame 10 may comprise devices such as retractable casters 114. In accordance with the invention, the attachment structure 12 is 35 pivotally mounted on the vertical structure 11, about a substantially horizontal axis of rotation, and substantially coincides with the longitudinal axis of the nacelle 2. The tool 1 comprises a driving device 120 in rotation of the structure fastening 12, comprising for example an electric motor. Thus, it is possible to control the rotation of the attachment structure 12, and therefore of the platform 2 that it supports. The finishing operations of the nacelle, in particular the painting operations, are greatly facilitated since an operator on the ground can access the whole of the nacelle, whatever the dimensions thereof. Similarly, the quality control operations are simplified since they can be performed by a ground operator. Figure 4a shows a tool according to the invention, without nacelle assembly on the attachment structure. The attachment structure comprises two main sections, a rear section 121 and a front section 122. The rear section 121 is integral with the vertical structure 11 via a pivot connection. In the example of FIGS. 4a and 4b, the rear section carries at its rear end a ring gear 123 15 for rotating the attachment structure 12. The front 122 and rear 121 sections carry the set of devices. for attaching a platform to the tooling 1. These fastening devices include an air inlet fixing bracket 124, a middle section mounting bracket 125, and two rear section mounting brackets 126, 127.
    [0008] The set of fasteners of the different parts correspond to the different attachment points provided on the turbojet corresponding to the nacelle. Thus, the fasteners 124, 125, 126, 127 are configured such that the platform 2 is fixed on the tool 1 exactly in the same way as on a motor in operating condition. In particular, all manipulations and movements of parts of the nacelle that are possible under real conditions can be reproduced when the nacelle is mounted on the tool. This includes in particular the displacement and / or opening of the various covers of the nacelle in the maintenance position, or the opening, if necessary, of the thrust reversers.
    [0009] FIG. 4b shows the attachment structure 12 of the tool of FIG. 4a and shows in more detail the fixing devices 124, 125, 126, 127. The air inlet fixing support 124 forms a support for the attachment of the air intake flange of the nacelle 2. The air intake fixing bracket comprises for this purpose six fixing plates 1240, which are in the example each disposed at the end of an arm 1242.
    [0010] The medial-section attachment support 125 comprises a beam 1250 on which three fastening devices 1252 are fixed for fixing, by means of hinges, the elements forming the central section of the nacelle 2.
    [0011] The first rear section fastening support 126 comprises a beam 1260 on which four fastening devices 1262 are fastened for fixing, by means of hinges, the elements forming the rear section of the nacelle 2. The second support of FIG. Rear section attachment 127 is formed by a star structure having branches 1270 and peripheral ends 1272. The peripheral ends 1272 partially duplicate the groove of the knife / groove clamping system (also referred to as "V-blade / V"). groove "). The embodiment of FIGS. 4a and 4b shows an attachment structure 12 comprising front 122 and rear 121 sections consisting mainly of an assembly of tubular beams. The exemplary embodiment shown in FIGS. 5a and 5b shows that the hooking structure can be made in different ways, as long as the various hooking points of the basket are present and correctly positioned. In this example, it can be seen that the front 122 and rear 121 sections 121 form a single tubular structure 128. This tubular structure 128 carries the various fixing devices 124, 125, 126, 127. In the embodiment of FIGS. 5a and 5b, additional elements have also been represented, which are of course compatible with all the embodiments. of the present invention. These elements are drainage systems 129 (also referred to as "drain masts"), one or more damping and stopping devices 130 (also referred to as "bumpers"). In addition, Figure 5a shows that the rear section 121 is provided at its upper end with panels 131 corresponding to access hatches of a nacelle called "hinge access panels". These panels 131 are removable and can also equip the front section 122. Figures 6a and 6b show a variant of the tool of Figure 3a, comprising a device for varying the height of the attachment structure 12 relative to to the chassis (see arrow H in Figure 6a), in particular to facilitate the work of operators in different painting operations or quality control. In addition, the support structure 12 includes clearances 132 to allow the passage of the ends of the fairings said beaverail tail (also called "beavertails") during the rotation of the nacelle, in the case where one thrust reverser covers are in the retracted position, as shown in Figure 6b. In all the embodiments, provision can be made for the front section 122 to slide (towards the front) with respect to the rear section 121. This arrangement makes it possible to free up the space required for disassembly (or conversely assembly) of the rear section of the nacelle 2 without having to disassemble the middle section beforehand. Furthermore, the frame is shaped to provide the stability necessary for the tooling, taking into account the total mass of a nacelle. In addition, the frame will be provided that the tool can carry a half nacelle while having sufficient lateral stability. Although the invention has been described in connection with a particular embodiment, it is obvious that it is in no way limited and that it includes all the technical equivalents of the means described and their combinations if these These are within the scope of the invention.
    权利要求:
    Claims (8)
    [0001]
    REVENDICATIONS1. Tool (1) for supporting a nacelle (2) of an aircraft turbojet, comprising: - a chassis (10); a support structure (11) rising from the chassis; - An attachment structure (12) of a nacelle, rotatably mounted on the support structure (11) and rotatable about a substantially horizontal axis.
    [0002]
    2. Tooling (1) according to claim 1, wherein the attachment structure (12) of the nacelle comprises a nacelle air inlet fixing device (124).
    [0003]
    3. Tooling (1) according to claim 1 or 2, wherein the attachment structure (12) of the nacelle comprises a middle section of attachment support (125) of a nacelle.
    [0004]
    4. Tooling (1) according to one of the preceding claims, wherein the attachment structure (12) of the nacelle comprises a rear section fixing device (126) of a nacelle.
    [0005]
    5. Tooling (1) according to one of the preceding claims, comprising a first section (121) intended to carry the rear section of a nacelle and a second section (122) intended to carry the median section and the air intake of a nacelle, the second section (122) being movable in translation relative to the first section (131), in a direction parallel to the axis of rotation of the attachment structure (12). 30
    [0006]
    6. Tooling (1) according to one of the preceding claims, wherein the frame is equipped with devices (114) for its displacement, such as retractable rollers or air cushions.
    [0007]
    7. Tooling (1) according to one of the preceding claims, 35 comprising a device for rotating the attachment structure (12), such as an electric motor. 3031084 9
    [0008]
    8. Tooling (1) according to one of the preceding claims, comprising a device, including an electrical device for varying the height of the attachment structure (12). 5
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    同族专利:
    公开号 | 公开日
    FR3031084B1|2018-04-27|
    US10589876B2|2020-03-17|
    EP3240729B1|2020-07-15|
    WO2016108015A1|2016-07-07|
    EP3240729A1|2017-11-08|
    US20170297744A1|2017-10-19|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    BE560669A|
    JP2002193195A|2000-12-28|2002-07-10|Ishikawajima Harima Heavy Ind Co Ltd|Method and device for mounting nacelle|
    FR2848200A1|2002-12-04|2004-06-11|Air Nacelle Services|Load e.g. air inlet, handling device for airplane, has tool of modification rotating around horizontal axis parallel to another horizontal axis, and tool of translation moving in horizontal direction parallel to both axes|
    FR2992292A1|2012-06-25|2013-12-27|Aircelle Sa|DEVICE AND METHOD FOR ASSEMBLING A FIXED PUSH-INVERTER STRUCTURE OF AN AIRCRAFT PROPULSION ASSEMBLY|
    US2848200A|1954-11-26|1958-08-19|Gen Motors Corp|Heat exchanger|
    US2849124A|1956-05-07|1958-08-26|William H Warner|Engine auxiliary equipment handling jack assembly|
    US8939434B2|2011-06-14|2015-01-27|Timothy Selby|Method and device for removal of vertical manway cover|
    US9091384B2|2012-11-08|2015-07-28|Joseph R. Helmin|Pipe jack|US10539053B2|2017-07-06|2020-01-21|General Electric Company|Engine transportation apparatus|
    FR3092824A1|2019-02-20|2020-08-21|Airbus Operations|system comprising an air inlet for an aircraft engine and an inflatable protection for said air inlet|
    FR3098746B1|2019-07-17|2021-07-30|Safran Aircraft Engines|TOOLS AND METHOD FOR DISMANTLING AND MOVING A TURBINE CASE OF THE TRV TYPE FROM AN AIRCRAFT TURBOMACHINE|
    法律状态:
    2015-12-15| PLFP| Fee payment|Year of fee payment: 2 |
    2016-07-01| PLSC| Publication of the preliminary search report|Effective date: 20160701 |
    2016-10-20| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-23| PLFP| Fee payment|Year of fee payment: 4 |
    2018-03-02| CD| Change of name or company name|Owner name: SAFRAN NACELLES, FR Effective date: 20180125 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-11-17| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1463396|2014-12-29|
    FR1463396A|FR3031084B1|2014-12-29|2014-12-29|SUPPORT TOOLING OF AN AIRCRAFT ENGINE NACELLE|FR1463396A| FR3031084B1|2014-12-29|2014-12-29|SUPPORT TOOLING OF AN AIRCRAFT ENGINE NACELLE|
    PCT/FR2015/053729| WO2016108015A1|2014-12-29|2015-12-22|Apparatus for supporting a nacelle of an aircraft engine|
    EP15823366.8A| EP3240729B1|2014-12-29|2015-12-22|Engine nacelle support device|
    US15/635,515| US10589876B2|2014-12-29|2017-06-28|Apparatus for supporting a nacelle of an aircraft engine|
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