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

Abstract

TITLE: Pipe Covering System for the Mast Connecting a Jet Engine to the Wing. Removable pipe covering system, comprising: - a bundle (F) of coplanar, parallel pipes (Ci), and - a module (100) forming a sealed enclosure and damping the vibrations of the pipes (Ci), comprising: an end device (1), fixed to the wing (AL) and freely and securely traversed by the bundle (F), a base element (3) fixed to the jet engine (R) and forming a sealed comb through which the bundle (F) is fixed and securely traversed, a fairing (2) to cover the bundle (F) between the end device (1) and the base element (3) in a sealed and freely sliding manner, - the module (100) is divided into two parts (100a, 100b) along 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 jet engine to the wing FIELD OF 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 engine nacelle is connected to the wing by a connecting structure generally called a mast or pylon. The mast is attached to the engine air intake structure, forming an aerodynamic fairing and covering the fluid lines connected to the wing. These lines carry fuel, fire-extinguishing fluid, hydraulic fluid, and very hot pressurized air drawn from the engine, which are subject to significant temperature and pressure variations.

[0003] These pipes pass through the mast. Although the reactor nacelle and the mast are removable for maintenance purposes, access to the pipes is relatively difficult, and the pipes themselves are not leak-proof. Furthermore, the pipes carrying fluids under reactor operating conditions, pressure surges, and other variations in fluid pressure and temperature, constitute sources of vibration that contribute to the overall operating noise.

[0004] PURPOSE OF THE INVENTION

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

[0006] DESCRIPTION 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 engine, and

[0009] - a module forming a watertight enclosure for the pipes, the module comprising:

[0010] A. an end device, fixed to the wing bulkhead and through which the bundle of pipes passes freely and in a sealed manner, on the wing side,

[0011] B. a basic element fixed to the reactor and forming a sealed comb through which the bundle of pipes passes in a fixed and sealed manner, on the reactor side,

[0012] C. a fairing to cover in a watertight and free sliding manner the bundle between the end device and the base element, the end device making a flexible connection with the fairing itself fixedly connected to the base element, the module being divided into two parts according to the plane of the bundle to cover the pipes on both sides of the plane, closing on them in this plane or conversely opening to access the pipes.

[0013] The enclosure system according to the invention, for combining the fixed duct bundle between the wing and the engine, and the removable module that covers them in a watertight manner while allowing free movement of the ducts, which react differently depending on the pressure and temperature to which they are exposed, constitutes an assembly with a module adapted to the ducts of the bundle and allowing very easy access to the bundle for inspections and any necessary maintenance. The compact system can be integrated into the mast or attached to it with the same advantages of compactness and accessibility, and its watertightness provides effective separation between the engine enclosure and the wing.

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

[0015] According to another advantageous feature,

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

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

[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 feature,

[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 current elements, having identical profiles, ending with an elbow element, whose inclined edge forms the junction surface connected to the inclined one above the base element.

[0021] The symmetry or near-symmetry of the two fairing parts facilitates and simplifies their manufacture and adaptation to different wiring harnesses. It also facilitates installation on the harness and, conversely, quick disassembly / reassembly for maintenance and inspection of the harness's wiring.

[0022] According to another advantageous feature,

[0023] The end device comprises:

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

[0025] - the bellows having

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

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

[0028] ** the inner edge being secured to the contour of the support by a strapping ring leaving a peripheral support free 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 and then joined to the inner edge of the bellows.

[0030] The end device, installed at least partially on the beam, constitutes a fixed assembly point on the pipes in the wing while allowing the expansion of the pipes connected to the other fixed connection point with the engine to be absorbed, especially since, according to another advantageous feature, the through-element is formed of two symmetrical parts assembled along a junction plane, each comprising:

[0031] - a support formed of a transverse base perpendicular to the joining plane and a peripheral wall surrounding the partition, the support having cells for fittings forming a free watertight passage for each pipe, the wall being provided with a groove for the bellows' O-ring on which, after assembly of the crossing element in the inner edge of the bellows, the strapping ring attached to the crossing element rests.

[0032] According to another advantageous feature,

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

[0034] - each hull having at least one member in the perpendicular transverse plane dicular at the junction plane with the alveoli receiving the ducts,

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

[0036] This shape of the fairing elements allows the adaptation of the fairing to the different beams required for the sites for which they are intended, while constituting effective mechanical protection.

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

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

[0039] According to another advantageous feature, 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 an upper surface inclined along the line of the junctions between the straight segments and the curved segments and,

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

[0042] - the shells having cavities which, when assembled, form tubular alveoli to receive the reactor-side pipe segments,

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

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

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

[0046] [Fig.1A] Overview of a bundle of conduits combined with the cladding module,

[0047] [Fig.1B] Diagram of the pipe axes at the pipe bends,

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

[0049] [Fig.3] Cross-sectional view of the end device by the beam plane

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

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

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

[0053] [Fig.4B] Exploded view of the through-element of the [Fig.4],

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

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

[0056] [Fig.5B] Exploded view of the through-element of the [Fig.5],

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

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

[0059] [Fig.7] Perspective view of a shell 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 shock-absorbing sleeves,

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

[0063] [Fig. 11] Perspective view of the basic element,

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

[0065] [Fig. 12A] exploded cross-sectional view of part of the basic element,

[0066] [Fig. 13] Perspective view of a shell of the basic element of the [Fig. 11],

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

[0068] DESCRIPTION OF AN IMPLEMENTATION METHOD

[0069] According to [Fig. 1], the invention relates to a pipe covering system ([Fig. 1A]) connecting the engine R to the wing AL of the aircraft. The covering system consists of a bundle of pipes Ci and a covering module 100 associated with the mast (not shown), connecting the engine 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 lie in the same median plane PM. These pipes are juxtaposed in the increasing (or decreasing) direction of diameters

[0071] The Ci pipes 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 AL wing pipes and the transverse segment CTi is connected to the R reactor.

[0072] The bend in the pipes corresponds to an angle, preferably of 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. 1B shows the organization of the Ci conduits 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 XCI axis of the straight segment CLI of the pipe Cl and that of the YCI axis 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 between 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 a minimum footprint.

[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 bend 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 from segment CLi (or, equivalently, from segment CTi). For this reason, the "junction" points Jli, J2i, which represent the origin and end of the arc DCi of the bend in 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, including a usual angle of 90° or 120° or even 45° or any imposed angle.

[0080] The module 100 receiving and covering the beam F is installed in a removable manner to allow control and maintenance of the Ci lines. It hermetically seals the beam F between the wing and the engine.

[0081] 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 links 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 allowing the free translational movement of the Ti pipes subjected to expansions / contractions according to the temperature variations of the pipes through which gases and liquids such as: fuel / fire extinguishing fluid / hydraulic fluid / high temperature compressed air pass.

[0083] Starting from the end device 1, the fairing 2 consists of an assembly of elements 21, 22 of the same profile forming a longitudinal part and an elbow element 23 connected to the base element 3 by a joining surface SJ whose shape substantially follows the line L2. The fairing 2 has a rectangular cross-section, the long sides of which are parallel to the median plane PM connected by short rounded sides, preferably in the form of 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 beam F and the module 100. The fairing 2 is assembled by folding its two halves 2a, 2b onto the conduits Ci; the median plane PM thus constitutes the junction and assembly plane PJ, or even its plane of symmetry.

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

[0086] According to figures 2, 3, 3A, 4, 4A, the end device 1 consists of a bellows 10 and the through element 4. The bellows 10, which is generally frustoconical in shape and has a rectangular cross-section, has small rounded sides, like the cross-section of the fairing 2; the bellows 10 widens from its inner edge 101, which has a cross-section close to that of the fairing, to terminate at its outer edge 102 in the plane of assembly 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 through element 4 which forms the interface between the end device 1 and the fairing 2 by constituting a watertight 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 subsequently receive the fairing 2.

[0090] The end device 1 is partially fitted onto the beam F before the beam is assembled to the wing lines 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 sub-assembly (10, 101) will be fixed to the wing in preparation, positioned exactly with respect to the plane PM of the beam F.

[0091] The crossing element 4 is first applied to the conduits Ci of the bundle F beyond the end device 1 and then slid onto the conduits 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 made is locked after the fairing 2 is joined by a U-shaped (open ring) strapping ring 104 which is placed on the inner edge 101 of the bellows and covers the edge of the fairing; it is screwed to the through element 4.

[0093] According to Figures 4, 4A, 4B, since the through-element 4 is composed of parts 4a, b that are 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, using, by convention, only the numerical references that are also those of the assembled element 4; the description of the other part 4b follows from this by simple symmetry; it suffices to add the suffix (b) to apply this description of the entire support 4 to only part 4b (or 4a). This convention has an exception if the same figure shows both an element of part 4a and the same element of part 4b.

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

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

[0096] The trim 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 arches 421 are embedded in the alveoli 411 and the plates 422, 423 are held against the facets 412, 413 by being held there by their fixing hole 424 engaged on the stud 4141 of the chimneys 414 and the reliefs 4121 of the bottom 401.

[0098] The hoops 421 have grooves 425 receiving the half-rings 43a,b. The grooves also have nipples 426 onto which the rings 43 are clipped by 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 notch ([Fig.4B]) so that the ring is perfectly locked in the hoop 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 through element 5. The bellows 10, similar to that of the through element 4, is generally frustoconical in shape with a rectangular cross-section; it has small rounded sides like the cross-section of the fairing 2; the bellows 10 widens from its inner edge 101, which has a cross-section close to that of the fairing, to terminate 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 contraction 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 watertight 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 partially fitted onto the beam F before the beam itself is assembled to the wing ducts.

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

[0107] The assembly thus formed is locked after the fairing 2 is joined by a strapping ring such as ring 104.

[0108] The through 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 in part 5a with the same reference convention as that applied to the first embodiment. As in the previous case, this convention has one exception, for parts of the figures showing both an element of part 5a and the same element of part 5b. For the sake of simplification, figures 5 and 5B have references designating the half-elements of the represented part 5a, not all of which are completed with the suffix (a) or (b).

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

[0111] The base 501 is provided with circular recesses 511, or at least semi-circular recesses 511a, which form the circular recesses 511 when the two parts 5a,b are joined. The recesses are aligned in the junction plane PJ and have a cross-section and position corresponding to the conduits Ci of the bundle. The recesses 511 receive a sealing and damping gasket 52 forming a sliding surface that ensures a seal around the conduits Ci and dampens their vibrations.

[0112] The recesses 511, of the same structure but with dimensions adapted to the conduits to be received, have a crenellated surface with recessed cylindrical segments 5111 of a certain radius of curvature and raised cylindrical segments 5112 of a smaller radius of curvature, forming peripheral housings to receive the lining 52 composed of shock-absorbing links 522 connecting raised wedges 521, located peripherally relative to the links. The wedges 521 fit, by their adapted shape, into the cylindrical segments 5111, and the shock-absorbing links 522 come against the cylindrical segments 5112. For fairing assembly reasons, each part 5a, 5b has only half-recesses, and the linings 52 are composed of two halves assembled 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-shims 52a,b each having a wedge 521 and two half-shims 521 separated by two shock-absorbing links 522.

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

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

[0116] The half-rings 53a,b are preferably overmolded onto the half-trims 52a,b so that the assemblies thus formed are united and remain attached to the half-cells 5 lia,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] The [Fig.6] is a view of the fairing 2 composed of an end element 21, common 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 beam F covered by the fairing 2.

[0119] Figure 6A shows half 2a of the fairing. The end element 21 (21a,b) is assembled to two running elements 22 (22a,b) and then to an elbow element 23a,b. The shells of the elements bear the same reference number followed only by the suffix (a) or (b). For the same reasons of simplification as those already stated above, the description of the shells will, except where otherwise noted, be given using only the numerical reference numbers without the suffixes (a) and (b) that are added to obtain the description of the part with the suffix (a) or that with the suffix (b).

[0120] Fig. 7 shows a hull 22a of a common element 22. The hull 22a has a web 221 with a cross-section equal to half the cross-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 hulls 22a,b.

[0121] The members 222 have alveoli 225 in positions and sections corresponding to the conduits Ci to be capped.

[0122] The cells 225 have external grooves 2251 or recesses so as to form, with the cell of the adjacent hull member, 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 main element 22 in that it has only one member 212, its other side remaining free to engage with the peripheral support 417 of the through element 4 and be locked there by screwing the ring of strapping 104. The screws pass through the holes 2111 in the web 211 to fit into the screw blocks 403 of the cross 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 member 22. The upper edge 233 and the lower edge 234 each have a straight section near the member 232 and then a curved section joining the other side of the elbow element 23 is terminated by a slanted edge 238 which forms the joining surface SJ.

[0126] The assembly of the hulls (21a, 22a, 23a) and (21b, 22b, 23b) is done by screwing the adjacent members together to make 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 segments 21, 22, 23 are provided with assembly studs 228 applied against each other are held assembled by a sliding ladder 7 ([Fig. 10]) and screw studs 229 are assembled by screws.

[0128] The common elements 22 are dimensioned 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 shells 22a assembled and whose cavities 225 are lined with damping sleeves 6 having a toothed profile, elastic to hold the pipes and dampen vibrations.

[0130] The sleeves 6 are adapted to the diameter of the pipes Ci and the cavities 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 common elements 22. The same applies to the junction of a common 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 blocks 228 by the sliding ladder 7 allowing the shells 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 angled 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 basic element 3 is a hollow piece composed of a comb 31 and a plate 32; the assembly is divided into two symmetrical parts, by the joining 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 with the other elements of module 100, the description is based on one (31a) of the shells 31a, 31b and is valid both for the other shell 31b by the substitution of the suffix (a) by the suffix (b) and for the base element 31 by the deletion of the suffix (a) from the description of the shell 31a. The plate 32 is divided into two parts 32a,b along the joining plane and covering the open underside (301, 30la,b) of the base element 3.

[0137] The shell 31a comprises parallel tubular cavities (311a) with cross-sections and positions 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 cavities 311a, which substantially follows the line L2 of the junctions J2i ([Fig. IB]). The cavities 311a open into the top 302a through elliptical openings, bordered by a continuous seal 315a, integrated into a groove in the top 302a. The cavities 311a are connected by intermediate, planar strips 313a in the junction plane PJ.

[0138] At the opening of the alveoli 311a in the bottom 301a, open, the edge forms a half-section of the groove 312a ([Fig.12A]).

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

[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 basic element 3. These parts are assembled on the transverse segments CTi attached to the reactor so that their assembly on the olives 33 ensures the locking of the basic element 3 with respect to the reactor.

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

[0142] In more detail, [Fig. 12] shows the shape of the tubular alveoli 311 (311a) terminated at the bottom by grooves (312-322) receiving the olives 33 and at the top by an elliptical orifice 3111, of reduced section, close to the section of the CTi pipe and bordered by the elliptical part of the joint 315. The remainder of the alveoli 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. 12A shows the shell 31a and the plate 32a, separated, highlighting the conical surfaces 312a bordering the opening of the alveoli 31a and forming the "top" gorges receiving the olives 33.

[0145] In parallel, it shows the plate 32a whose orifices 321a open into the top through 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 part 3a of the basic element 3 with examples of olives 33 engaged in some grooves (311a-322a) of this part 3a.

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

[0148] Fig. 13A shows the shell 31a forming the beak 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 fairing system is carried out by installing the end device 1 and the base element 3; then after assembly of the two halves 2a, 2b of the fairing and installation of the latter fixed to the device 1 and the base element 3.

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

[0151] NOMENCLATURE OF PRINCIPAL 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] Inner seal

[0158] 102 Outer edge

[0159] 103 Basin

[0160] 104 Strapping ring

[0161] 1041 Screw drilling

[0162] 2 Fairing

[0163] 2a, 2b Fairing halves

[0164] 21 End element

[0165] 2la,b Shells

[0166] 211 Sail

[0167] 2111 Drilling

[0168] 212 Member

[0169] 213 Upper edge

[0170] 214B lower order

[0171] 215 Alveolus

[0172] 216 Transverse 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 External groove

[0183] 226 Transverse rib

[0184] 2261 Clearance

[0185] 227 Longitudinal rib

[0186] 228 Assembly stud

[0187] 229 Screw stud

[0188] 23 Elbow element

[0189] 23a,b Shells

[0190] 231 Sail

[0191] 232 Member

[0192] 233 Upper edge

[0193] 234 Lower edge

[0194] 235 Alveolus

[0195] 236 Transverse 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 Top

[0205] 311 Tubular alveolus

[0206] 312 Throat half-section

[0207] 313 Plane intermediate strip

[0208] 314 Back

[0209] 315 Joint

[0210] 32 Platinum

[0211] 32a,b Parts of the plate

[0212] 321 Orifice

[0213] 322 Throat half-section

[0214] 33 Olive

[0215] 4 Crossing element

[0216] 4a,b Parts

[0217] 41 Support

[0218] 4la,b Parts

[0219] 401 Fund

[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 Joint groove 1011

[0229] 416 Separating rib

[0230] 417 Peripheral fairing support

[0231] 418 Groove for fairing seal

[0232] 419 Fairing seal

[0233] 42 Sealing gasket

[0234] 421 Arch

[0235] 422 Exterior plate

[0236] 423 Interior plate

[0237] 424 Orifice

[0238] 43 Ring

[0239] 5 Other crossing element

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

[0241] 501 Fund

[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 Sleeve parts 7 Scale AL Wing F Pipe bundle R Reactor Ci Pipe CLi Longitudinal segment CCi Elbow CTi Transverse segment XCi Pipe axis Ci on segment CLi YCi Pipe axis Ci on segment CTi DCi Arc of the bending circle of the pipe axis Ci PM Median plane of the bundle PJ Junction plane SJ Junction surface Jli Origin of the arc YCi J2i bending curve End of the YCi bending arc L1 Line of junctions Ji L2 Line of junctions Jli forming the origins of the Lo bending arc Bisector of the angle between the axes (XCi, XC2i) of the pipe Ci

Claims

Demands

1. A removable cladding system for mast pipes connecting a jet engine to the wing comprising: - a bundle (F) of coplanar (PM) parallel pipes (Ci) having longitudinal segments (CLi) connected to transverse segments (CTi) by bends (CCi), for attachment to the wing (AL) and the jet engine (R), and - a module (100) forming a watertight enclosure for the pipes (Ci), the module comprising: A. an end device (1), fixed to the wing bulkhead (AL) and freely and watertight through which the bundle (F) of pipes passes, wing side (AL), B. a base element (3) fixed to the jet engine (R) and forming a watertight comb (31) through which the bundle (F) of pipes passes in a fixed and watertight manner, jet engine side (R), C.a fairing (2) to cover in a watertight and free sliding manner the bundle (F) between the end device (1) and the base element (3), - the end device (1) making 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) according to the plane (PM) of the bundle (F) to cover the pipes (Ci) by the two sides of the plane (PM), closing on them in this plane or conversely opening to access the pipes (Ci).

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

3. A removable cladding system according to claim 1, characterized in that: - the fairing (2) comprises an end element (21) and a main 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 beam (F), - the junction surface (SJ) of the elbow element (22) and the element base (3) being inclined to follow the junction (J2i) of the straight transverse segments (CTi) and the bends (CCi) of the pipes (Ci).

4. A fairing 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 common elements (22), having identical profiles, ending with an elbow element (23), the inclined edge (238) of which forms the joining surface (SJ) connected to the inclined one above (302) of the base element (3).

5. A fairing system according to claims 1 to 4, characterized in that the end device (1) comprises: - a sleeve-shaped bellows (10) connected at one end to the wing (AL) and a through-element (4) forming the interface between the bellows (10) and the fairing (2), - the bellows (10) having * an outer edge (102) fixed by means of 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 through-element (4), ** the inner edge (101) being secured to the contour of the support (41) by a retaining ring (104) leaving a peripheral support (417) of the support (41) free for the assembly of the end device (1) to the element end (21) of the fairing (2),- the bellows (10) in the shape of a sleeve and its fixing cup (103) being fitted onto the bundle of pipes (F) and the through element (4) divided into two parts (4a, 4b) being assembled onto 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 through 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 base (401) perpendicular to the junction plane (PJ) and a peripheral wall (402) surrounding the partition (401), the support (41) having alveoli (411) for fittings (42) forming a free, sealed passage for each conduit (Ci), the wall (402) being provided with a groove (415) for the O-ring (1011) of the bellows (10) on which, after assembly of the through element (4) in the inner edge (101) of the bellows, the strapping ring (104) attached to the through element (4) rests.

7. A fairing 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 recesses (215, 225, 235) receiving the conduits (Ci), - a web (211, 221, 231) of cross-section equal to that of the module with transverse (216, 226, 236) and longitudinal (217, 227, 237) ribs, - screw holes in the members for assembling the elements in pairs, and - assembly studs (228, 229) along the upper edge (213, 223, 233) and the lower edge (214, 224, 234) of the elements (21, 22, 23).

8. Dressing 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 arch (421).

9. Dressing 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. A covering system according to claim 1, characterized in that the basic element (3) is a comb (31) formed by the assembly of two shells (3a,b), meeting in the junction plane (PJ) of the beam (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 which, by their assembly, form tubular alveoli (311) to receive the segments (CTi) of the pipes (Ci) on the reactor side (R), - the tubular alveoli (311) having a section and a position corresponding to the segments (CTi), and extending through orifices (321) into the plate (32).

11. Dressing system according to claim 10, characterized in that the top (302) has a two-part (315a,b) seal (315), each integrated into the outlets of the alveoli (311) and a groove formed at the entrance of the alveoli (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 conduit (Ci).

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