Pipe cladding system for the mast connecting a reactor to the wing

Abstract

TITLE: Pipe covering system for the mast connecting a reactor to the wing structure Removable pipe covering system, comprising: - a bundle (F) of coplanar, parallel pipes (Ci), and - a module (100) forming a sealed and vibration-damping envelope of the pipes (Ci), comprising: an end device (1), fixed to the wing structure (AL) and crossed freely and in a sealed manner by the bundle (F), a base element (3) fixed to the reactor (R) and forming a sealed comb crossed in a fixed and sealed manner by the bundle (F), a fairing (2) for covering in a sealed and freely sliding manner the bundle (F) between the end device (1) and the base element (3), - the module (100) is divided into two parts (100a, 100b) according to the plane (PM) of the bundle (F) to cover the pipes on both sides of this plane. Figure 1

Description

Title of the invention: Pipe covering system for the mast connecting a reactor to the wing FIELD OF THE INVENTION

[0001] The present invention relates to a pipe covering system for the mast connecting a reactor to a wing. STATE OF THE ART

[0002] The reactor nacelle is connected to the wing by a connecting structure generally called a mast or pylon. The mast is fixed to the structure of the air intake of the reactor forming an aerodynamic fairing and covering the fluid lines connected to the wing. These are lines for fuel, fire extinguishing fluid, hydraulic fluid and very hot air under pressure taken from the reactor and which undergo significant variations in temperature and pressure.

[0003] These pipes pass through the mast. Although the reactor nacelle and the mast are removable equipment for maintenance work, access to the pipes is relatively difficult and these pipes as such are not protected against leaks. In addition, the pipes crossed by fluids under the operating conditions of the reactor, pressure surges and other variations in pressure and temperature of the fluids, constitute sources of vibrations contributing to the overall emission of operating noise.

[0004] PURPOSE OF THE INVENTION

[0005] The present invention aims to develop a system of pipes associated with the mast and which is particularly compact and nevertheless very accessible for interventions on the pipes while guaranteeing the sealing of the system in the event of leaks, taking up the mechanical deformations of the mast, the vibrations and the deformations of the pipes, resistant to the flame on the reactor side, and combining with the mast and remaining easily removable for maintenance.

[0006] DISCLOSURE AND ADVANTAGES OF THE INVENTION

[0007] To this end, the invention relates to a removable covering system for mast pipes connecting a reactor to the wing comprising:

[0008] - a bundle of coplanar, parallel conduits having longitudinal segments connected to transverse segments by elbows, to attach to the wing and the reactor, and

[0009] - a module forming a sealed envelope for the pipes, the module comprising:

[0010] A. an end device, fixed to the wing partition and crossed freely and in a sealed manner by the bundle of pipes, on the wing side,

[0011] B. a base element fixed to the reactor and forming a sealed comb crossed in a fixed and sealed manner by the bundle of pipes, on the reactor side,

[0012] C. a fairing for covering the bundle in a sealed and freely sliding manner between the end device and the base element, the end device providing a flexible connection with the fairing itself fixedly connected to the base element, the module being divided into two parts along the plane of the bundle to cover the pipes from both sides of the plane, closing over them in this plane or conversely opening to access the pipes.

[0013] The covering system according to the invention for the combination of the fixed bundle of pipes between the wing and the reactor and the removable module which covers them in a sealed manner while allowing free play of the pipes reacting differently according to the pressure and temperature to which they are exposed constitute an assembly with a module adapted to the bundle pipes and allowing very easy access to the bundle for checks and possible maintenance. The compact system can be integrated into the mast or be attached to it with the same advantages of compactness and accessibility and which, by its sealing, achieves an effective separation between the reactor enclosure and the wing.

[0014] Advantageously, the conduit bundle is formed of conduits organized in the direction of the diameters (increasing / decreasing)

[0015] According to another advantageous characteristic,

[0016] - the fairing comprises an end element and a running element receiving the longitudinal segments, terminated by an elbow element receiving the elbows of the pipes and assembled to the base element receiving the transverse segments of the bundle,

[0017] - the joining surface of the elbow element and the base element being inclined to follow the junction of straight transverse segments and pipe elbows.

[0018] This combination of simplified elements facilitates the manufacture of the fairing and its assembly to the base element, effective for holding the transverse segments according to their length.

[0019] According to another advantageous characteristic,

[0020] - the two parts of the fairing are symmetrical with respect to the plane, - each of the parts is composed of the end element and running elements, having identical profiles, ending with an elbow element, the inclined edge of which forms the junction surface connected to the inclined one above the base element.

[0021] The symmetry or quasi-symmetry of the two parts of the fairing facilitates and simplifies their manufacture and their adaptation to the different beams. It also facilitates the installation on the beam and conversely a rapid disassembly / reassembly for interventions and checks of the beam pipes.

[0022] According to another advantageous characteristic,

[0023] the end device comprises:

[0024] - a sleeve-shaped bellows connected at one end to the wing and an element crossing forming the interface between the bellows and the fairing,

[0025] - the bellows having

[0026] * an outer edge fixed by a cup to the sail,

[0027] * an inner edge forming an inner seal intended to engage in the peri groove spherical of a support of the crossing element,

[0028] ** the inner edge being secured to the contour of the support by a strapping ring leaving free a peripheral support of the support for the assembly of the end device to the end element of the fairing,

[0029] - the sleeve-shaped bellows and its fixing cup being fitted onto the bundle of pipes and the crossing element divided into two parts being assembled on the pipes then joined to the inner edge of the bellows.

[0030] The end device installed at least partly on the bundle constitutes a fixed assembly point on the pipes in the wing while making it possible to absorb the expansion of the pipes connected to the other fixed connection point with the reactor, all the more so since, according to another advantageous characteristic, the crossing element is formed of two symmetrical parts assembled according to a junction plane, each comprising:

[0031] - a support formed from a transverse bottom perpendicular to the junction plane and a peripheral wall surrounding the partition, the support having cells for gaskets forming a free sealed passage for each pipe, the wall being provided with a groove for the O-ring of the bellows on which rests, after assembly of the crossing element in the inner edge of the bellows, the strapping ring secured to the crossing element.

[0032] According to another advantageous characteristic,

[0033] the fairing elements are formed of two shells,

[0034] - each hull having at least one member in the transverse plane perpen dicular at the junction plane with cells receiving the pipes,

[0035] - a veil of section equal to that of the module with transverse and longitudinal ribs tudinal, screw holes in the members to assemble the elements two by two and, assembly studs along the upper edge and the lower edge of the elements.

[0036] This shape of the fairing elements allows it to be adapted to the different beams required for the sites for which they are intended while providing effective mechanical protection.

[0037] According to another advantageous characteristic, the circular cells of the support receive a sealing gasket incorporating a sliding arch.

[0038] According to another advantageous characteristic, the sealing gaskets are connected by plates to cover the facets of the support and form a solid assembly connecting the gaskets and covering the front of the frame of the support.

[0039] According to another advantageous characteristic, the basic element is a comb formed by the assembly of two shells, meeting in the junction plane of the beam,

[0040] each shell having a top inclined along the line of the junctions between the straight segments and the curved segments and,

[0041] - a flat base, covered by the parts of a plate,

[0042] - the shells having cavities forming, by their assembly, tubular cells to receive the segments of the reactor-side pipes,

[0043] - the tubular cells having a section and a position corresponding to the segments, and extending through holes in the plate, which simplifies the manufacturing and possible repairs of the elements by replacing worn or damaged linings. Brief description of the drawings

[0044] The present invention will be described below in more detail using an embodiment of a removable pipe covering system for the mast connecting a reactor to a wing according to the invention shown schematically in the attached drawings in which:

[0045] [Fig-1] overview of the dressing system,

[0046] [Fig.lA] overall view of a bundle of pipes combined with the cladding module,

[0047] [Fig.lB] diagram of the axes of the pipes at the level of the pipe bends,

[0048] [Fig.2] perspective view of the end device,

[0049] [Fig.3] sectional view of the end device through the beam plane

[0050] [Fig.3A] sectional view of the end device, perpendicular to the plane of the beam,

[0051] [Fig.4] perspective view of a crossing element,

[0052] [Fig.4A] detailed, partial perspective view of the crossing device of [Fig.4],

[0053] [Fig.4B] exploded view of the crossing element of [Fig.4],

[0054] [Fig.5] perspective view of another crossing element,

[0055] [Fig.5A] sectional view perpendicular to the junction plane of the crossing element of [Fig.5],

[0056] [Fig.5B] exploded view of the crossing element of [Fig.5],

[0057] [Fig.6] perspective view of the fairing,

[0058] [Fig.6A] perspective view of one half of the fairing of [Fig.6],

[0059] [Fig.7] perspective view of a hull of the current element,

[0060] [Fig.8] perspective view of a shell of the elbow element,

[0061] [Fig.9] perspective view of the assembly of shells of common elements with damping sleeves,

[0062] [Fig. 10] partial perspective view of the assembled fairing,

[0063] [Fig. 11] perspective view of the base element,

[0064] [Fig. 12] side view of a shell of the base element,

[0065] [Fig. 12A] exploded sectional view of a part of the base element,

[0066] [Fig. 13] perspective view of a hull of the basic element of [Fig. 11],

[0067] [Fig. 13A] Perspective view of a shell of the base element.

[0068] DESCRIPTION OF AN EMBODIMENT

[0069] According to [Fig.l], the invention relates to a system for covering pipes ([Fig.lA]) connecting the reactor R to the wing AL of the aircraft. The covering system is composed of a bundle of pipes Ci and a covering module 100 associated with the mast (not shown), connecting the reactor R to the wing AL. The module 100 can be attached to the mast or integrated into the mast.

[0070] The pipes Ci (i =1.. .6 according to this example) are coplanar, parallel, of different diameters whose axes are located in the same median plane PM. These pipes are juxtaposed according to the increasing (or decreasing) direction of the diameters

[0071] The pipes Ci each consist of a longitudinal segment CLi connected by an elbow CCi to a transverse segment CTi. The longitudinal segment CLi is connected to the pipes of the wing AL and the transverse segment CTi is connected to the reactor R.

[0072] The bend in the pipes corresponds to an angle, preferably 90°, but which can also be another usual angle, for example, 120° or other angles imposed by the connection to be made between the reactor and the wing.

[0073] [Fig.lB] shows the organization of the pipes Ci by tracing their axes XCi, YCi for the segments CLi, CTi and in the part of the elbow segments CCi.

[0074] The extension of the axis XCI of the straight segment CLI of the pipe Cl and that of the axis YCI of its straight segment CTI intersect at point Mo.

[0075] The axis of the elbow DC1 connecting the axes XCI and YCI is a curve tangent to these axes. In the simplest case, it is an arc of a circle DC1 whose center Ml is on the bisector Lo of the angle of the axes XCI, YCI passing through the point Mo.

[0076] The radius of curvature RCi (RC1) is the minimum bending radius for the pipe Cl; this radius, depending on the diameter of the pipe, is chosen for minimum bulk.

[0077] The center of curvature Ml is at the distance RCI from the two axes XCi (XCI) and YCi (YCI) and on the bisector Lo.

[0078] The same applies to the other elbow axes DCi depending on the minimum possible radius of curvature for the pipes Ci represented by their axes XCi, YCi. The center of curvature Mi of the pipe Ci for its radius of curvature RCi is located on the bisector Lo at the distance RCi of the segment CLi (or what is the same, of the segment CTi). For this reason the "junction" points Jli,J2i which represent the origin and the end of the arc DCi of the bend of the pipe Ci are located on lines L1 and L2 which are very schematically slightly curved lines because there is no proportionality between the spacing of the axes XCi (or YCi) and the imposed radii of curvature RCi.

[0079] The above explanations apply to any elbow angle, in particular a usual angle of 90° or 120° or even 45° or any imposed angle.

[0080] The module 100 receiving and covering the bundle F is installed in a removable manner to allow the control and maintenance of the pipes Ci. It envelops, in a sealed manner, the bundle F between the wing and the reactor.

[0081] The module 100 consists of an end device 1 connected to the wing AL, a fairing 2 and a base element 3 connected to the reactor R; the fairing 2 makes the connection between the end device 1 and the base element 2.

[0082] The fairing 2 in combination with the end device 1 and the base element 3 constitutes a sealed enclosure nevertheless allowing the free translational movement of the Ti pipes subjected to expansions / contractions depending on the temperature variations of the pipes crossed by gases and liquids such as: fuel / extinguishing fluid / hydraulic liquid / high temperature compressed air.

[0083] Starting from the end device 1, the fairing 2 is composed of an assembly of elements 21, 22 of the same profile forming a longitudinal part and of an elbow element 23 connected to the base element 3 along a junction surface SJ whose shape substantially follows the line L2. The fairing 2 has a rectangular section, the large sides of which are parallel to the median plane PM connected by small rounded sides, preferably in an arc of a circle.

[0084] The fairing 2 is divided into two halves 2a, 2b by the median plane PM which is also the plane of symmetry of the bundle F and of the module 100. The fairing 2 is assembled by folding its two halves 2a, 2b onto the pipes Ci; the median plane PM thus constitutes the junction and assembly plane PJ, or even its plane of symmetry.

[0085] As will be detailed below, the end device 1 is at least partly engaged on the beam F on the wing side AL and the base element 3 is assembled on the beam F on the engine side M in a removable manner, but independently of the fairing 2.

[0086] According to figures 2, 3, 3A, 4, 4A, the end device 1 is composed of a bellows 10 and the crossing element 4. The bellows 10 of generally truncated cone shape, of rectangular section has small rounded sides, like the section of the fairing 2; the bellows 10 expands from its inner edge 101 of section close to that of the fairing to end with its outer edge 102 in the assembly plane to the wing AL.

[0087] Between its two edges 101, 102, the bellows 10 evolves according to a curved shape giving it transverse flexibility and extensibility in the longitudinal direction.

[0088] The bellows 10 is fixed to the wing by a cup 103 covering its outer edge 102. The inner edge 101 is fixed to the crossing element 4 which forms the interface between the end device 1 and the fairing 2 by constituting a sealed separation.

[0089] The crossing element 4 is formed by the assembly of two symmetrical halves 4a, 4b, assembled on the beam F at the junction between the end device 1 and the fairing 2, then joined to the end device 1 to then receive the fairing 2.

[0090] The end device 1 is partly fitted onto the bundle F before the bundle is assembled to the ducts of the wing since the bellows 10 is a one-piece sleeve; the same is true of its cup 103 which comes onto the outer edge 102 so that this subassembly (10, 101) will be fixed to the wing on standby, positioned exactly relative to the plane PM of the bundle F.

[0091] The crossing element 4 is first applied to the pipes Ci of the bundle F beyond the end device 1 to then be slid onto the pipes Ci and come into the opening formed by the inner edge 101 of the bellows 10 and receive in its outer groove, the seal 1011 of the inner edge 101 of the bellows 10.

[0092] The assembly thus produced is blocked after the fairing 2 has been joined by a ring 104, for example, U-shaped (open ring) which is placed on the inner edge 101 of the bellows and covers the edge of the fairing; it is screwed to the crossing element 4.

[0093] According to figures 4, 4A, 4B, as the crossing element 4 is composed of parts 4a, b symmetrical with respect to the junction plane PJ, to simplify its description it will be presented by the description of one (4a) of the parts 4a, 4b with, by convention, the only numerical references which are also those of the assembled element 4; the description of the other part 4b is deduced from this by simple symmetry; it is sufficient to add the suffix (b) to apply this description of the whole of the support 4 to only the part 4b (or 4a). This convention suffers from an exception if the same figure shows both an element of the part 4a and the same element of the part 4b.

[0094] According to figures 4, 4A, the support 41 of the part 4a (or 4b) is composed of a bottom 401 joined to a peripheral wall 402 having a contour in the shape of the section of the whole of the module 100 and in particular of its fairing 2.

[0095] The bottom 401 is provided with circular cells 411 aligned in the junction plane PJ with a section and a position corresponding to the conduits Ci of the bundle F. The cells 411 and the junction surfaces of the support 41 with the other support are covered by a sealing gasket 42 ([Fig.4B]) integrating hoops 421 forming a sliding surface of the gasket 42 ensuring sealing around each of the Ci pipes.

[0096] The lining 42 is composed of a succession of hoops 421 connected by a plate 422 at each end and intermediate plates 423 to come and fix themselves on the end facets 412 and the intermediate facets 413 of the support 41.

[0097] The hoops 421 are embedded in the cells 411 and the plates 422, 423 are retained against the facets 412, 413 by being held there by their fixing orifice 424 engaged on the stud 4141 of the chimneys 414 and the reliefs 4121 of the base 401.

[0098] The hoops 421 have grooves 425 receiving the half-rings 43a,b. The grooves also have pins 426 onto which the rings 43 are clipped via their orifice 431.

[0099] To receive the two beaks 432 at the two ends of the half-ring 43a or 43b, the groove 425 of the ring 421 has a recess ([Fig.4B]) so that the ring is perfectly blocked in the arch 421.

[0100] The end plates 422 have a contour identical to that of the bottom 401 and the peripheral wall 402 of the support 41 so as not to interrupt the groove 415, the rib 416, the peripheral support 417 and the groove 418.

[0101] Figures 5, 5A, 5B show another embodiment of an end device 1', composed of a bellows 10 and a crossing element 5. The bellows 10, similar to that of the crossing element 4, is of generally truncated cone shape with a rectangular section; it has small rounded sides like the section of the fairing 2; the bellows 10 expands from its inner edge 101 with a section close to that of the fairing to end with its outer edge 102 in the plane of assembly to the wing AL.

[0102] The bellows 10 evolves between its two edges 101, 102 according to a curved shape giving it transverse flexibility and extensibility in the longitudinal direction allowing it to absorb the variations imposed by the expansion or retraction of the pipes to which the fairing 2 and the base element 3 are fixed.

[0103] The bellows 10 is fixed to the wing by its cup 103 covering its outer edge 102. The inner edge 101 is fixed to the crossing element 5 between the end device 1' and the fairing 2, constituting a sealed and damped separation.

[0104] The crossing element 5 is formed by the assembly of two symmetrical halves (5a, 5b), assembled on the beam F at the junction between the end device 1' and the fairing 2.

[0105] The end device 1' is partly fitted onto the bundle F before the bundle itself is assembled to the wing ducts.

[0106] As for the embodiment already described, the crossing element 5 is first applied to the pipes Ci of the bundle F beyond the end device 1' to then be slid onto the pipes and come into the opening formed by the inner edge 101 of the bellows 10 and receive in its outer groove, the seal 101 1 of the edge interior 101 of bellows 10.

[0107] The assembly thus produced is blocked after the joining of the fairing 2 by a ring ring such as the ring 104.

[0108] The crossing element 5 is composed of parts 5a, 5b symmetrical with respect to the junction plane PJ; each of the parts is composed of a support 51 and sealing and damping gaskets 52.

[0109] To simplify the description of element 5, it is presented by the description of part 5a with the same convention relating to references as those applied to the first embodiment. As in the previous case, this convention suffers from an exception, for the parts of the figures showing both an element of part 5a and the same element of part 5b. For reasons of simplification, figures 5 and 5B have references designating the half-elements of the part 5a shown which are not all completed with the suffix (a) or (b).

[0110] The support 51 of the part 5a (or 5b) is composed of a bottom 501 joined to a peripheral wall 502 whose outline has the shape of the section of the module 100.

[0111] The bottom 501 is provided with circular cells 511 or at least semi-circular cells 511a forming the circular cells 511 when the two parts 5a,b are joined. The cells are aligned in the junction plane PJ and have a section and a position corresponding to the pipes Ci of the bundle. The cells 511 receive a sealing and damping gasket 52 forming a sliding surface ensuring sealing around the pipes Ci and damping their vibrations.

[0112] The cells 511 of the same structure, but of dimensions adapted to the pipes to be received, have a crenellated surface with hollow cylindrical segments 5111, of a certain radius of curvature and raised cylindrical segments 5112 of a smaller radius of curvature, forming peripheral housings for receiving the lining 52 composed of damping links 522 connecting wedges 521 in relief, on the periphery relative to the links. The wedges 521 are housed by their adapted shape in the cylindrical segments 5111 and the damping links 5222 come against the cylindrical segments 5112. For reasons of assembly of the fairing, each part 5a, 5b has only half-cells and the linings 52 are composed of two halves assembling in the junction plane PJ. For this reason, each cell 511 has a complete cylindrical segment 5111 and two halves of such a segment 5111 at each end of the half-cell, straddling the junction plane PJ.

[0113] This same reason requires half-fittings 52a,b each having a shim 521 and two half-shims 521 separated by two damping links 522.

[0114] The inner surface of the lining 52 is cylindrical, smooth with the same radius of curvature, nevertheless with axial grooves 523 at the junction of the inner side of the damping link 522 and a shim 521.

[0115] The inner surface of the lining 52 receives a ring 53 also in two parts with a smooth inner surface, but with an outer surface provided with ribs 531 which fit into the grooves 523 and thus block the half-rings 53a,b also divided by the junction plane PJ.

[0116] The half-rings 53a,b are preferably overmolded onto the half-linings 52a,b so that the sets thus formed are united and remain attached to the half-cells 5 11a,b.

[0117] As a note, the variant of the support 51 shown in the exploded view shows the peripheral wall 502 with screw blocks 503 which are not shown in [Fig.5].

[0118] [Fig.6] is a view of the fairing 2 composed of an end element 21, running elements 22 and an elbow element 23, of the same profile; they are each formed of two symmetrical parts 2la,b, 22a,b, 23a,b with respect to the junction plane PJ which is also the median plane PM of the bundle F covered by the fairing 2.

[0119] [Fig.6A] shows a half 2a of the fairing. The end element 21 (21a,b) is assembled to two standard elements 22 (22a,b) then to an elbow element 23a,b. The shells of the elements bear the same reference only followed by the suffix (a) or (b). For the same reasons of simplification as those already stated above, the description of the shells will be made, except exception, with only the numerical references without the suffixes (a), (b) which are added to obtain the description of the part with the suffix (a) or that with the suffix (b).

[0120] [Fig.7] shows a shell 22a of a current element 22. The shell 22a comprises a web 221 of section equal to half the section of the fairing; it is bordered laterally by two members 222 in the assembly plane of the elements as well as by an upper edge 223 and a lower edge 224. The members 222 and the edges 223, 224 arrive in the junction plane of the two shells 22a,b.

[0121] The members 222 have cells 225 in positions and sections corresponding to the pipes Ci to be covered.

[0122] The cells 225 have external grooves 2251 or recesses so as to form, with the cell of the frame of the neighboring hull, a housing for a shock-absorbing sleeve not shown here.

[0123] The web 221 is reinforced by transverse ribs 226 and longitudinal ribs 227. For the passage of large diameter pipes, the transverse ribs 226 have clearances 2261. The upper edge 223 is provided with assembly studs 228; the lower edge 224 is provided with assembly studs 229.

[0124] The end element 21 ([Fig.6A]) differs from the current element 22 in that it has only one member 212, its other side remaining free to engage on the peripheral support 417 of the crossing element 4 and be blocked there by the screwing of the ring of strapping 104. The screws pass through the holes 2111 of the web 211 to be housed in the screw blocks 403 of the crossing element 4 ([Fig.3A]).

[0125] According to [Fig.8], the shell 23a,b of the elbow element 23 comprises a curved web 231, bordered by a single member 232 and reinforced by transverse ribs 236 and longitudinal ribs 237 aligned with those of the current element 22. The upper edge 233 and the lower edge 234 each have a straight section near the member 232 then a curved section joining the other side of the elbow element 23 is terminated by a slanted edge 238 which forms the junction surface SJ.

[0126] The assembly of the shells (21a, 22a, 23a) and (21b, 22b, 23b) is done by screwing the adjacent members to produce the two halves 2a,b of the fairing 2.

[0127] The edges 213, 223, 233 of the shells 21a,b, 22a,b, 23a,b of all the segments 21, 22, 23 are provided with assembly studs 228 applied against each other and held together by a sliding ladder 7 ([Fig. 10]) and screw studs 229 are assembled by screws.

[0128] The common elements 22 are sized to adapt by their combination to different beam lengths F, for example, two or more typical lengths.

[0129] [Fig.9] shows an example of common elements represented by two assembled shells 22a and whose cells 225 are lined with damping sleeves 6 having a toothed, elastic profile to hold the pipes and dampen vibrations.

[0130] The sleeves 6 are adapted to the diameter of the pipes Ci and the cells 225. The sleeves 6 are divided into two parts 6a, 6b each fixed in the groove 2251 formed by the assembly of the members 222 / 222 of two shells 22a, b of successive current elements 22. The same applies to the junction of a current element 22 with the end element 21 or with the elbow element 23.

[0131] [Fig.9] also shows the screw holes 2221 for assembling the shells 22a. The same applies to the assembly of the shell 21a of the end element 21 to a running element 22 and of the shell 23a of the elbow element 23 to the shell 22a of the running element 22.

[0132] [Fig. 10] shows the assembly of the pads 228 by the sliding ladder 7 allowing the hulls to be held together along their entire length.

[0133] The elbow is assembled in the same way with a circular arc ladder with a radius of curvature equal to that of the upper edge 233. The slanted side 238 is provided with screw blocks 2381 for assembly to the base element 3.

[0134] According to figures 11, 12, 12A, 13, 13A the base element 3 is a hollow part composed of a comb 31 and a plate 32; the assembly is divided into two symmetrical parts, by the junction and assembly plane PJ of the module 100.

[0135] The comb 31 is formed of two shells 3la,b symmetrical with respect to the plane PJ.

[0136] As for the other elements of the module 100, the description is made from one (31a) of the shells 31a, 31b and applies both to the other shell 31b by substituting the suffix (a) with the suffix (b) and to the base element 31 by deleting the suffix (a) from the description of the shell 31a. The plate 32 is divided into two parts 32a,b along the junction plane and covering the open underside (301, 30la,b) of the base element 3.

[0137] The shell 31a comprises parallel tubular cells (311a), of section and position corresponding to the transverse segments CTi to be received. The height of the top 302a of the element 3 forming the junction surface SJ is also the height of the tubular cells 311a which substantially follows the line L2 of the junctions J2i ([Fig. 1B]). The cells 311a open into the top 302a by elliptical openings, bordered by a joint 315a, continuous, integrated in a groove of the top 302a. The cells 311a are connected by intermediate, flat strips 313a in the junction plane PJ.

[0138] At the opening of the cells 311a in the open bottom 301a, the edge forms a half-section of groove 312a ([Fig.l2A]).

[0139] Each part 32a of the plate 32 comprises orifices 321a corresponding to the passage of the CTi pipe segments. The orifices 321a,b form in the top of the plate 32, a half-section of groove 322 to complete the homologous half-section 312 of the cells 311 of the assembly of the shells 31a,b and to form, for each cell 311, a groove (312, 322) receiving an olive (ring) 33 welded to each CTi pipe.

[0140] In practice, the shells 3la,b are assembled by their platinum part 32a to form each part (31a, 32a) and (31b, 32b) of the base element 3. These parts are assembled on the transverse segments CTi secured to the reactor so that their assembly on the olives 33 ensures the blocking of the base element 3 relative to the reactor.

[0141] The olives 33 will be tightened in the grooves (312, 322) by the installation of the two shells 31a, b of the comb 31 screwed transversely to each other. The sealing by the olives 33 is completed by the seal 315.

[0142] In more detail, [Fig. 12] shows the shape of the tubular cells 311 (311a) terminated in the lower part by grooves (312-322) receiving the olives 33 and in the upper part by an orifice 3111, elliptical, of reduced section, close to the section of the CTi pipe and bordered by the elliptical part of the seal 315. The remainder of the cell 311a has a section greater than that of the CTi pipe.

[0143] The ends of the shell 31a have assembly holes and connecting elements 316, not detailed, to join the two parts 3a,b of the base element 3.

[0144] [Fig.l2A] shows the shell 31a and the plate 32a, separated, highlighting the conical surfaces 312a bordering the outlet of the cells 311a and forming the “top” gorges receiving olives 33.

[0145] In parallel, it shows the plate 32a whose orifices 321a open into the top via conical surfaces 322a forming the underside of the grooves (312-322) obtained by the assembly of the shell 31a and the plate 32a.

[0146] [Fig. 13] shows in isometric view the part 3a of the base element 3 with examples of olives 33 engaged in some grooves (311a-322a) of this part 3a.

[0147] As already indicated, the olives are in reality welded onto the CTi pipes, aligned in the plane of the grooves 312-322 of the base element 3.

[0148] [Fig.l3A] shows the shell 31a forming the spout 31 without the plate 32a, but with some olives 33 highlighting how the olives 33 engage in the conical surfaces 312 at the outlet of the alveoli 311.

[0149] The installation of the covering system is done by installing the end device 1 and the base element 3; then after assembling the two halves 2a, 2b of the fairing and installing the latter fixed to the device 1 and to the base element 3.

[0150] Disassembly is carried out in the reverse order; it can, depending on requirements, be limited to fairing 2.

[0151] NOMENCLATURE OF MAIN ELEMENTS

[0152] 100 Dressing module

[0153] 100a, 100b Parts of the module

[0154] 1, 1' End devices

[0155] 10 Bellows

[0156] 101 Inner edge

[0157] lOUInner joint

[0158] 102 B ord exterior

[0159] 103 Bowl

[0160] 104 Strapping ring

[0161] 1041 Screw drilling

[0162] 2 Fairing

[0163] 2a, 2b Halves of the fairing

[0164] 21 End element

[0165] 2la,b Shells

[0166] 211 Sail

[0167] 2111 Drilling

[0168] 212 Frame

[0169] 213 Upper edge

[0170] 214B lower order

[0171] 215 Alveolus

[0172] 216 Cross rib

[0173] 217 Longitudinal rib

[0174] 22 Current element

[0175] 22a,b Shells

[0176] 221 Sail

[0177] 222 Member in the assembly plane

[0178] 2221 Screw hole

[0179] 223 Upper edge

[0180] 224 Lower edge

[0181] 225 Alveolus of the frame

[0182] 2251 Outer groove

[0183] 226 Cross rib

[0184] 2261 Clearance

[0185] 227 Longitudinal rib

[0186] 228 Assembly plot

[0187] 229 Screwing pad

[0188] 23 Elbow element

[0189] 23a,b Shells

[0190] 231 Sail

[0191] 232 Frame

[0192] 233 Upper edge

[0193] 234 Lower edge

[0194] 235 Alveolus

[0195] 236 Cross rib

[0196] 237 Longitudinal rib

[0197] 238 Slanted edge

[0198] 2381 Screw block

[0199] 3 Basic element

[0200] 3a,b Parts forming the basic element 3

[0201] 31 Comb

[0202] 31 a,b Shells

[0203] 301 Below

[0204] 302 Above

[0205] 311 Tubular alveolus

[0206] 312 Half-section of throat

[0207] 313 Flat intermediate strip

[0208] 314 Back

[0209] 315 Joint

[0210] 32 Platinum

[0211] 32a,b Parts of the plate

[0212] 321 Orifice

[0213] 322 Half-section of throat

[0214] 33 Olive

[0215] 4 Crossing element

[0216] 4a,b Parts

[0217] 41 Support

[0218] 4la,b Parts

[0219] 401 Background

[0220] 402 Peripheral wall

[0221] 403 Screw block

[0222] 411 Alveolus

[0223] 412 End facet

[0224] 4121 Relief

[0225] 413 Inner facet

[0226] 414 Chimney

[0227] 4141 Plot

[0228] 415 Seal groove 1011

[0229] 416 Separating rib

[0230] 417 Peripheral support of the fairing

[0231] 418 Groove for the fairing seal

[0232] 419 Fairing gasket

[0233] 42 Sealing gasket

[0234] 421 Arch

[0235] 422 Outer plate

[0236] 423 Inner plate

[0237] 424 Orifice

[0238] 43 Ring

[0239] 5 Other crossing element

[0240] 5A,B Symmetrical halves of the crossing element 5

[0241] 501 Background

[0242] 502 Peripheral wall

[0243] 503 Screw block

[0244] 511 Alveolus

[0245] Sealing and damping gasket

[0246] 521 Cale

[0247] 522 Shock absorber link

[0248] 53 Ring

[0249]

[0250]

[0251]

[0252]

[0253]

[0254]

[0255]

[0256]

[0257]

[0258]

[0259]

[0260]

[0261]

[0262]

[0263]

[0264]

[0265]

[0266]

[0267]

[0268]

[0269] 6 Damping sleeve 6a,b Parts of the sleeve 7 Scale AL Wing F Bundle of pipes R Reactor Ci Pipe CLi Longitudinal segment CCi Elbow CTi Transverse segment XCi Axis of pipe Ci on segment CLi YCi Axis of pipe Ci on segment CTi DCi Arc of the bending circle of the axis of pipe Ci PM Median plane of the bundle PJ Junction plane SJ Junction surface Jli Origin of the bending arc YCi J2i End of the bending arc YCi L1 Line of junctions Ji L2 Line of junctions Jli forming the origins of the bending arc Lo Bisector of the angle of the axes (XCi, XC2i) of the pipe Ci

Claims

Claims

1. Removable covering system for mast pipes connecting a reactor to the wing comprising: - a bundle (F) of coplanar (PM) pipes (Ci), parallel, having longitudinal segments (CLi) connected to transverse segments (CTi) by elbows (CCi), to be fixed to the wing (AL) and to the reactor (R), and - a module (100) forming a sealed envelope of the pipes (Ci), the module comprising: A. an end device (1), fixed to the partition of the wing (AL) and crossed freely and in a sealed manner by the bundle (F) of pipes, on the wing (AL) side, B. a base element (3) fixed to the reactor (R) and forming a sealed comb (31) crossed in a fixed and sealed manner by the bundle (F) of pipes, on the reactor (R) side, C.a fairing (2) for covering the bundle (F) in a sealed and freely sliding manner between the end device (1) and the base element (3), - the end device (1) providing a flexible connection with the fairing (2) itself fixedly connected to the base element (3), - the module (100) being divided into two parts (100a, 100b) along the plane (PM) of the bundle (F) to cover the pipes (Ci) on both sides of the plane (PM), closing over them in this plane or conversely opening to access the pipes (Ci).

2. Removable cladding system according to claim 1, characterized in that the conduit bundle (Cl) is formed of parallel coplanar conduits (PM) organized in the direction of diameter (increasing / decreasing).

3. Removable cladding system according to claim 1, characterized in that - the fairing (2) comprises an end element (21) and a running element (22) receiving the longitudinal segments (CLi), terminated by an elbow element (22) receiving the elbows (CCi) of the pipes and assembled to the base element (3) receiving the transverse segments (CTi) of the bundle (F), - the junction surface (SJ) of the elbow element (22) and of the element base (3) being inclined to follow the junction (J2i) of the straight transverse segments (CTi) and the elbows (CCi) of the pipes (Ci).

4. Cladding system according to claim 3, characterized in that - the two parts (2a, b) of the fairing (2) are symmetrical with respect to the plane (PM), - each of the parts (2a, b) is composed of the end element (21) and of current elements (22), having identical profiles, ending in an elbow element (23), the inclined edge (238) of which forms the junction surface (SJ) connected to the inclined one above (302) of the base element (3).

5. A covering system according to claims 1 to 4, characterized in that the end device (1) comprises: - a sleeve-shaped bellows (10) connected by one end to the wing (AL) and a crossing element (4) forming the interface between the bellows (10) and the fairing (2), - the bellows (10) having * an outer edge (102) fixed by a cup (103) to the wing (AL), * an inner edge (101) forming an inner seal (1011) intended to engage in the peripheral groove (415) of a support (41) of the crossing element (4), ** the inner edge (101) being secured to the contour of the support (41) by a ring (104) leaving free a peripheral support (417) of the support (41) for the assembly of the end device (1) to the end element (21) of the fairing (2),- the sleeve-shaped bellows (10) and its fixing cup (103) being fitted onto the bundle of pipes (F) and the crossing element (4) divided into two parts (4a, 4b) being assembled on the pipes (Ci) then joined to the inner edge (102) of the bellows (10).,

6. Cladding system according to claim 5, characterized in that the crossing element (4) is formed of two symmetrical parts (4a, b) assembled along a junction plane (PJ), each comprising: - a support (41) formed of a transverse bottom (401) perpendicular to the junction plane (PJ) and a peripheral wall (402) surrounding the partition (401), the support (41) having cells (411) for gaskets (42) forming a free sealed passage for each pipe (Ci), the wall (402) being provided with a groove (415) for the O-ring (1011) of the bellows (10) on which rests, after assembly of the crossing element (4) in the inner edge (101) of the bellows, the strapping ring (104) secured to the crossing element (4).

7. Cladding system according to claim 4, characterized in that the elements (21, 22, 23) of the fairing (2) are formed of two shells (21a, b; 22a, b; 23a, b), - each shell having at least one member (211, 222, 232) in the transverse plane perpendicular to the junction plane (PJ) with cells (215, 225, 235) receiving the pipes (Ci), - a web (211, 221, 231) of section equal to that of the module with transverse ribs (216, 226, 236) and longitudinal ribs (217, 227, 237), - screw holes in the members for assembling the elements two by two and, - assembly pads (228, 229) along the upper edge (213, 223, 233) and the lower edge (214, 224, 234) of the elements (21, 22, 23).

8. Cladding system according to claims 6 and 7, characterized in that the circular cells (411) of the support (41) receive a sealing gasket (42) incorporating a sliding hoop (421).

9. Cladding system according to claim 8, characterized in that the sealing gaskets (42) are connected by plates (422, 423) to cover the facets (412, 413) of the support (41) and form a solid assembly connecting the gaskets and covering the front of the member (212) of the support (41).

10. Dressing system according to claim 1, characterized in that the base element (3) is a comb (31) formed by the assembly of two shells (3 la, b), meeting in the junction plane (PJ) of the bundle (F), each shell having a top (302) inclined along the line (L2) of the junctions (J2i) between the straight segments (CTi) and the curved segments (CCi) and, - a flat bottom (301), covered by the parts (32a, b) of a plate (32), - the shells having cavities forming, by their assembly, tubular cells (311) to receive the segments (CTi) of the pipes (Ci) on the reactor (R) side, - the tubular cells (311) having a section and a position corresponding to the segments (CTi), and extending through orifices (321) in the plate (32).

11. Dressing system according to claim 10, characterized in that the top (302) comprises a seal (315) in two parts (315a, b), each integrated into the outlets of the cells (311) and a groove formed at the entrance of the cells (311) at the junction with the orifices (321) of the plate (32), the grooves each receiving an olive (33) integral with the segment (TCi) of each pipe (Ci).

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