Fire-sealing device comprising a flexible fire-break strip for a rear assembly of a nacelle of a jet engine

Abstract

The invention relates to a rear assembly (1) of a nacelle of a jet engine which comprises: a thrust reverser comprising a rear fixed structure; a combustion gas ejection nozzle (3) which extends the rear fixed structure; and a suspension pylon (4) to which the rear fixed structure is fixed. The rear assembly comprises a fire-sealing device which comprises a fire-break strip (6) made of a flexible and fire-resistant material, and which has a first longitudinal edge (61) and a second longitudinal edge (62) opposite one another. The first longitudinal edge of the fire-sealing device is fixed to at least one of the suspension pylon and the rear fixed structure, and the second longitudinal edge is fixed to the combustion gas ejection nozzle, with the fire-break strip then extending at least below the suspension pylon.

Description

[0001] DESCRIPTION

[0002] TITLE: Fire-sealing device comprising a flexible fire-resistant strip for a rear assembly of a turbojet engine nacelle

[0003] [Technical field]

[0004] The invention relates to a rear assembly of a nacelle of a turbojet engine comprising a fire-sealing device.

[0005] The invention also relates to a turbojet engine comprising a nacelle having such a rear assembly.

[0006] The invention finds a favorite, but not limiting, application in the fire sealing of an area between the suspension pylon and the combustion gas ejection nozzle of the rear assembly of the nacelle.

[0007] [State of the art]

[0008] As is known, an aircraft propulsion system can include a nacelle with a generally tubular shape surrounding a turbojet engine.

[0009] The nacelle generally comprises an upstream assembly designed to channel air towards the turbojet inlet; a middle assembly surrounding a turbojet fan; and a rear assembly which expels at high speed the air that has passed through the turbojet, thus generating the thrust necessary to propel the aircraft.

[0010] Turbojets are, for example, dual-flow turbojets capable of generating, by means of a rotation of blades which includes the fan, a flow of hot air from the combustion chamber of the turbojet and a flow of cold air which circulates outside the turbojet through an annular passage formed between a fairing of the turbojet and an internal wall of the nacelle.

[0011] The rear assembly of a nacelle includes a thrust reverser shaped to surround a downstream part of the turbojet and whose role is to improve the aircraft's braking capacity during landing, by redirecting at least some of the air ejected from the turbojet forward.

[0012] In general, a thrust reverser comprises a fixed rear structure including a cowl mounted to move longitudinally from front to back in a direction substantially parallel to the nacelle axis, between a closed position in which the cowl ensures the aerodynamic continuity of the nacelle, and an open position in which the cowl opens a passage in the nacelle. In another example, the fixed rear structure has two half-cowls arranged on either side of a median plane of the nacelle, and which are pivotally articulated by hinges fixed to the suspension pylon, about a longitudinal hinge axis, between a working position in which the half-cowls form part of the downstream fairing of the turbofan engine and define an annular stream of cold air with a thrust reverser cowl, and a maintenance position in which the half-cowls move away from the turbofan engine.

[0013] The rear fixed structure is attached to the suspension pylon and is extended in its downstream part by a combustion gas ejection nozzle surrounding an ejection cone, in order to optimize the flow of hot gases expelled by the core of the turbojet, and to absorb some of the noise generated by the interaction of these hot gases with the ambient air and the flow of cold air expelled by the turbojet fan.

[0014] It is known in the prior art to provide a fireproof seal between the suspension pylon and the combustion gas ejection nozzle to prevent any flame, originating from a fire in a compartment inside the rear fixed structure, from exiting towards the combustion gas ejection nozzle and outwards, whether the aircraft is on the ground or in flight.

[0015] It is also known that these fire-resistant seals are made in the form of two sets of overlapping metal strips, for example, made of a nickel-based superalloy. However, friction with the suspension tower and the flue gas nozzle, as well as the relative movements and vibrations of the suspension tower and the flue gas nozzle, cause these seals to wear, even if they have undergone a surface treatment process to limit wear. Therefore, they must be replaced once worn.

[0016] Furthermore, due to the arrangement and proximity of the suspension tower and the flue gas discharge nozzle, accessing the fire seal fasteners to remove and replace it from the suspension tower or flue gas discharge nozzle can be difficult. In some cases, removing a worn seal and installing a new one may require disassembling the flue gas discharge nozzle.

[0017] [Summary of the invention]

[0018] In order to address the problems of wear and assembly / disassembly of a sealing joint between the suspension pylon and the combustion gas ejection nozzle, the invention proposes a rear assembly of a nacelle of a turbojet engine, which rear assembly includes: a thrust reverser comprising a fixed rear structure;

[0019] - a combustion gas ejection nozzle that extends the fixed rear structure;

[0020] - a suspension pylon on which the rear fixed structure is fixed; the rear assembly comprising a fire-sealing device including a fire-stopping strip made of a flexible, fire-resistant material, and having a first longitudinal edge and a second longitudinal edge opposite each other, in which the first longitudinal edge is fixed to at least one of the suspension pylon and the rear fixed structure, and the second longitudinal edge is fixed to the combustion gas ejection nozzle, the fire-stopping strip then extending at least below the suspension pylon.

[0021] In the following description, a "soft material" is defined as a material whose hardness can be measured using the Shore hardness scale, as opposed to a rigid material, such as the material of the suspension pylon, nozzle, or rear fixed structure, whose hardness is measured using the Brinell, Vickers, or Rockwell hardness scales. Furthermore, the soft material preferably has a Young's modulus of less than 10 GPa.

[0022] In this case, this flexible material is adapted to deform reversibly so as to be able to absorb, by deforming, the movements, vibrations, contractions, expansions of other materials to which it is attached, that is to say the materials composing the combustion gas ejection nozzle and at least one of the suspension pylon and the rear fixed structure.

[0023] Furthermore, the fire resistance of this flexible material can be defined by its ability to withstand temperatures of 500 degrees Celsius or less.

[0024] In other words, because the firestop strip is made of a flexible material, it is deformable in bending and is not subject to the relative movements and vibrations of at least one of the suspension pylon and the rear fixed structure, and the combustion gas ejection nozzle. Consequently, the firestop strip exhibits reduced wear and its replacement is delayed or may not even be necessary.

[0025] The fire resistance of the material from which it is made allows the firestop tape to withstand temperatures of 500 degrees Celsius or less.

[0026] In two embodiments, the first longitudinal edge can, for example, be fixed either to the suspension pylon or to the rear fixed structure.

[0027] In another embodiment, the first longitudinal edge can be fixed to both the suspension pylon and the rear fixed structure. In one embodiment, the firestop strip is distributed symmetrically under the suspension pylon on either side of the nacelle's median plane within a given angular sector, in a so-called 12-hour zone. The angular sector can, for example, be 90 degrees, with the firestop strip then extending at a 45-degree angle on either side of the median plane.

[0028] In one embodiment, the firestop strip extends on either side of the nacelle's median plane beneath the suspension pylon, and also partially beneath the thrust reverser; more precisely, beneath the rear fixed structure comprising the thrust reverser. In one example, the firestop strip extends symmetrically with respect to the median plane and on either side of said median plane beneath a cowl comprising the rear fixed structure. In another example, the rear fixed structure comprises two cowls, or two half-cowls, arranged on either side of the nacelle's median plane and pivotally hinged at the suspension pylon; and the firestop strip extends symmetrically with respect to the median plane and on either side of said median plane beneath each of the two cowls, or half-cowls, comprising the rear fixed structure.

[0029] According to one feature of the invention, a first fastening means is integral with at least one of the suspension pylon and the rear fixed structure, and a second fastening means is integral with the combustion gas ejection nozzle, and in which the first longitudinal edge includes a first complementary fastening means which cooperates with the first fastening means for fixing the first longitudinal edge to at least one of the suspension pylon and the rear fixed structure, and the second longitudinal edge includes a second complementary fastening means which cooperates with the second fastening means for fixing the second longitudinal edge to the combustion gas ejection nozzle.

[0030] The first and second means of attachment and the first and second complementary means of attachment allow for easy assembly (in other words, attachment) and disassembly of the firestop strip between at least one of the suspension pylon and the rear fixed structure and the combustion gas ejection nozzle; with the operator being able to easily access the 12 o'clock zone between at least one of the suspension pylon and the rear fixed structure and the combustion gas ejection nozzle without the need, for example, to disassemble the combustion gas ejection nozzle from the rear assembly of the nacelle.

[0031] According to one embodiment of the invention, one of the first fastening means and the first complementary fastening means comprises a first slide and the other of the first fastening means and the first complementary fastening means comprises a first male rail engaged inside the first slide.

[0032] The first slide and the first male rail advantageously prevent the firestop strip from wearing down by rubbing against at least one of the suspension pylon and the rear fixed structure, while allowing easy assembly and disassembly between the firestop strip and at least one of the suspension pylon and the rear fixed structure, giving, for example, the operator free access to the 12 o'clock zone above the combustion gas ejection nozzle.

[0033] Alternatively or additionally, one of the second fastening means and the second complementary fastening means includes a second slide and the other of the second fastening means and the second complementary fastening means includes a second male rail engaged inside the second slide.

[0034] The second slide and the second male rail advantageously prevent the firestop strip from wearing down by rubbing against the combustion gas ejection nozzle, while allowing easy assembly and disassembly between the firestop strip and the combustion gas ejection nozzle, avoiding, for example, disassembly of the combustion gas ejection nozzle from the rear assembly of the nacelle.

[0035] In one example, the first and / or second slide might have a cylindrical cross-section. In another example, the first and / or second slide might have a dovetail cross-section.

[0036] According to one embodiment of the invention, the first male rail and / or the second male rail comprise a first metal insert and / or a second metal insert respectively.

[0037] The first metal insert (respectively the second metal insert) facilitates the engagement and sliding of the first male rail (respectively the second male rail) in the first slide (respectively the second slide).

[0038] According to one embodiment of the invention, the first fastening means comprises a series of first fastening holes associated with first fastening members, and the first complementary fastening means comprises a series of first holes allowing the passage of the first fastening members through the first holes to fix themselves onto the first fastening holes.

[0039] Alternatively or additionally, the second fastening means includes a series of second fastening holes associated with second fastening members, and the second complementary fastening means includes a series of second holes allowing the passage of the second fastening members through the second holes to attach to the second fastening holes.

[0040] Advantageously, the first fixing orifices, the first holes, and the first fixing devices allow easy assembly and disassembly between the firestop strip and at least one of the suspension pylon and the rear fixed structure, giving, for example, the operator free access to the 12 o'clock zone above the combustion gas ejection nozzle.

[0041] The second fixing orifices, the second holes, and the second fixing devices allow for easy assembly and disassembly between the firestop strip and the combustion gas ejection nozzle, avoiding, for example, disassembly of the combustion gas ejection nozzle from the rear assembly of the nacelle.

[0042] In one embodiment, the first fixing members and / or the second fixing members may correspond to screws, the threaded rods of which are provided to be housed and then fixed inside the first fixing holes and / or the second fixing members respectively.

[0043] According to one embodiment of the invention, the first holes and / or the second holes are made in the firestop strip and reinforced by means of eyelets, or are made in a first metal strip fixedly attached to the first longitudinal edge and / or in a second metal strip fixedly attached to the second longitudinal edge, respectively.

[0044] In one embodiment, the initial series of holes is formed in the first longitudinal edge of the firestop strip. The first longitudinal edge of the firestop strip is thus fixed to at least one of the suspension pylon and the rear fixed structure. Advantageously, most of the surface of the firestop strip does not experience friction with at least one of the suspension pylon and the rear fixed structure; friction occurs at the first longitudinal edge. Consequently, wear across most of the surface of the firestop strip is significantly reduced, postponing, or even eliminating, the need for its replacement.

[0045] In another embodiment, the second longitudinal edge of the firestop strip is directly attached to the flue gas discharge nozzle. Advantageously, most of the surface of the firestop strip does not rub against the flue gas discharge nozzle; friction occurs at the second longitudinal edge. Consequently, wear on most of the surface of the firestop strip is significantly reduced, postponing or even eliminating the need for replacement.

[0046] The eyelets advantageously protect the firestop strip by preventing part of the first and / or second fixing elements, for example screw heads, from rubbing against the firestop strip at the first and / or second holes, for example in the event of relative movement of at least one of the suspension pylon and the rear fixed structure and / or the combustion gas ejection nozzle, at the risk of damaging, or even tearing, the firestop strip at the first and / or second holes.

[0047] In another embodiment, the first holes are made in a first metal strip fixed to the first longitudinal edge. In other words, the firestop strip is attached to at least one of the suspension pylon and the rear fixed structure by means of this first metal strip. Since the firestop strip is not in direct contact with at least one of the suspension pylon and the rear fixed structure, no friction can occur between them. Consequently, and advantageously, wear on the firestop strip is significantly reduced, postponing, or even eliminating, its replacement.

[0048] In another embodiment, the second holes are provided in a second metal strip fixed to the second longitudinal edge. In other words, the firestop strip is attached to the combustion gas discharge nozzle by means of this second metal strip. Since the firestop strip is not in direct contact with the combustion gas discharge nozzle, no friction can occur between them. Consequently, and advantageously, wear on the firestop strip is significantly reduced, postponing, or even eliminating, its replacement.

[0049] In another embodiment, the first holes and the second holes are respectively made in a first metal strip and a second metal strip attached fixedly to the first longitudinal edge and the second longitudinal edge of the firestop strip.

[0050] In several embodiments, and as previously indicated, the first fastening means and the first supplementary fastening means may be of the same nature as the second fastening means and the second supplementary fastening means, respectively. For example:

[0051] - one of the first fastening means and of the first complementary fastening means may include a first slide and the other of the first fastening means and of the first complementary fastening means may include a first male rail engaged inside the first slide, and one of the second fastening means and of the second complementary fastening means may include a second slide and the other of the second fastening means and of the second complementary fastening means may include a second male rail engaged inside the second slide;or - the first fastening means may include a series of first fastening holes associated with first fastening members, the first complementary fastening means may include a series of first holes allowing the passage of the first fastening members through the first holes to fasten onto the first fastening holes, the second fastening means may include a series of second fastening holes associated with second fastening members, and the second complementary fastening means may include a series of second holes allowing the passage of the second fastening members through the second holes to fasten onto the second fastening holes.

[0052] In several other embodiments, the first fastening means and the first supplementary fastening means may not be of the same nature as the second fastening means and the second supplementary fastening means. For example, one of the first fastening means and the first supplementary fastening means may comprise a first slide, and the other of the first fastening means and the first supplementary fastening means may comprise a first male rail engaged inside the first slide; and the second fastening means may comprise a series of second fastening holes associated with second fastening members, and the second supplementary fastening means may comprise a series of second holes allowing the second fastening members to pass through the second holes to fasten onto the second fastening holes.

[0053] These different examples should be considered in an illustrative rather than a restrictive sense.

[0054] According to one embodiment of the invention, the firestop strip is in a loose state when it is fixed between the combustion gas ejection nozzle and at least one of the suspension pylon and the rear fixed structure.

[0055] Being in a loose state between the combustion gas ejection nozzle and at least one of the suspension pylon and the rear fixed structure, the firestop strip can advantageously tighten or loosen according to any forces induced by relative movements or vibrations of the combustion gas ejection nozzle and / or at least one of the suspension pylon and the rear fixed structure. Consequently, these forces do not damage the firestop strip. According to one embodiment of the invention, the fire-sealing device comprises a metal reinforcement integral with the firestop strip.

[0056] In other words, in one embodiment of the invention, the firestop strip can be reinforced by being attached to the metal frame.

[0057] According to one embodiment of the invention, the metal frame comprises metal ribs.

[0058] According to one embodiment of the invention, the metal reinforcement extends transversely between the first longitudinal edge and the second longitudinal edge.

[0059] According to one feature of the invention, the flexible and fire-resistant material is a flexible non-woven and fibrous material, containing for example carbon, silica, ceramic or metal fibers, or a woven metallic material.

[0060] The invention also relates to a turbojet engine comprising a nacelle having a rear assembly as described above.

[0061] [Brief description of the figures]

[0062] Other features and advantages of the present invention will become apparent from the detailed description below, along with non-limiting examples of implementation, made with reference to the accompanying figures in which:

[0063] [Fig 1] is a schematic perspective view of a rear assembly of a turbojet engine;

[0064] [Fig 2] is a schematic cross-sectional view of part of the rear assembly of the nacelle, in which a firestop strip, included in a fire-sealing device, is fixed between a suspension pylon and a combustion gas ejection nozzle of the rear assembly;

[0065] [Fig 3] is a schematic longitudinal section view of the rear assembly illustrating a fixing of the firestop strip between the suspension pylon and the combustion gas ejection nozzle according to a first embodiment;

[0066] [Fig 4] is a schematic longitudinal section view of the rear assembly illustrating a fixing of the firestop strip between the suspension pylon and the combustion gas ejection nozzle according to a second embodiment;

[0067] [Fig 5] illustrates schematic perspective and partial views of two variant embodiments of the firestop strip (respectively Figure 5-a and Figure 5-b), when it is fixed between the suspension pylon and the combustion gas ejection nozzle according to the second embodiment shown in Figure 4;

[0068] [Fig. 6] illustrates a schematic longitudinal section view of the rear assembly, according to one embodiment in which the fire-resistant strip is integral with a metal frame. [Detailed description of one or more embodiments of the invention]

[0069] A rear assembly 1 of a nacelle 10 of a turbojet 11 is schematically illustrated in Figure 1 and Figure 2. This rear assembly 1 is given in an illustrative and non-restrictive manner.

[0070] The rear assembly 1 of the nacelle 10 includes a thrust reverser 20 shaped to surround a downstream portion of the turbofan engine 11. The thrust reverser 20 includes a rear fixed structure 2 comprising, for example, two half-hoods 21, 22 which have a symmetrical design along a plane of symmetry corresponding to the median plane MP of the nacelle. The two half-hoods are, for example, pivotally articulated about a longitudinal hinge axis by hinges fixed to the suspension pylon 4, which provides suspension for the nacelle and the turbofan engine, and to which the rear fixed structure 2 is attached. The rear fixed structure 2 is extended in its downstream portion by a combustion gas ejection nozzle 3 surrounding an ejection cone 5.

[0071] The rear assembly 1 of the nacelle 10 includes a fire-sealing device comprising a fire-stopping strip 6 made of a flexible, fire-resistant material, which material may, for example, be a flexible non-woven, fibrous material containing, for example, carbon, silica, ceramic or metal fibers, or a woven metallic material.

[0072] The firestop strip 6 is attached to the flue gas ejection nozzle 3, and to at least one of the suspension pylon 4 and the rear fixed structure 2. In one example, the firestop strip 6 is attached to the flue gas ejection nozzle 3 and the suspension pylon 4. In another example, the firestop strip 6 is attached to the flue gas ejection nozzle 3 and the rear fixed structure 2. In yet another example, the firestop strip 6 is attached to the flue gas ejection nozzle 3, the suspension pylon 4 and the rear fixed structure 2.

[0073] The firebreak strip 6 is designed to fill a given angular sector and extend at least below the suspension pylon 4 on either side and symmetrically with respect to the median plane MP, in an area designated as the 12-hour zone. The angular sector may, for example, be equal to 90 degrees, with the firebreak strip 6 then extending at an angle of 45 degrees on either side of the median plane MP.

[0074] In another embodiment, the firestop strip 6 extends on either side of the median plane MP of the nacelle 10 under the suspension pylon 4, but also partly under the rear fixed structure 2. According to the example illustrated in Figure 2, the firestop strip 6 can, for example, extend under the suspension pylon 4 and partly under each half-hood 21, 22 that comprise the rear fixed structure 2.

[0075] With reference to Figures 3 to 6, the firestop strip comprises a first longitudinal edge 61 and a second longitudinal edge 62.

[0076] To secure the firestop strip 6 between the combustion gas ejection nozzle 3 and at least one of the suspension pylon 4 and the rear fixed structure 2, a first fastening means 71 is rigidly mounted on at least one of the suspension pylon 4 and the rear fixed structure 2, and a second fastening means 72 is rigidly mounted on the combustion gas ejection nozzle 3; and the first longitudinal edge 61 includes a first complementary fastening means 81 and the second longitudinal edge 62 includes a second complementary fastening means 82. The interaction between the first fastening means 71 and the first complementary fastening means 81 enables the first longitudinal edge 61 to be secured to at least one of the suspension pylon 4 and the rear fixed structure 2.Similarly, the cooperation between the second fastening means 72 and the second complementary fastening means 82 allows the second longitudinal edge 62 to be fixed to the combustion gas ejection nozzle 3.

[0077] The fastening means 71, 72 and the additional fastening means 81, 82 allow easy assembly and disassembly of the firestop strip 6 between at least one of the suspension pylon 4 and the rear fixed structure 2 and the combustion gas ejection nozzle 3; with the operator being able to easily access the 12 o'clock zone between at least one of the suspension pylon 4 and the rear fixed structure 2 and the combustion gas ejection nozzle 3, without the operator needing, for example, to disassemble the combustion gas ejection nozzle 3 from the rear assembly 1 of the gondola.

[0078] Subsequently, and unless otherwise indicated, it is assumed that the first longitudinal edge 61 is fixed to the suspension pylon 4.

[0079] In an embodiment illustrated in Figure 3, the first fastening means 71 and the second fastening means 72 comprise, respectively, a first slide 91 and a second slide 94, which first slide 91 and second slide 94 may, for example, have a cylindrical cross-section. The first supplementary fastening means 81 and the second supplementary fastening means 82 comprise, respectively, a first male rail 92 and a second male rail 95 intended to be engaged inside the first slide 91 and the second slide 94; the first male rail 92 and the second male rail 95 may, for example, comprise, respectively, a first metal insert 93 and a second metal insert 96 to facilitate the engagement and sliding of the male rails 92, 95 inside the slides 91, 94.

[0080] In another embodiment illustrated in Figure 4, the first fastening means 71 comprises a series of first fastening holes 101 associated with first fastening members 102, and the first complementary fastening means 81 comprises a series of first holes 103 allowing the first fastening members 102 to pass through the first holes 103 so that they may be fixed onto the first fastening holes 101. Similarly, the second fastening means 72 comprises a series of second fastening holes 104 associated with second fastening members 105, and the second complementary fastening means 82 comprises a series of second holes 106 allowing the second fastening members 105 to pass through the second holes 106 so that they may be fixed onto the second fastening holes 104.

[0081] The fasteners 102, 105 can correspond to screws, whose threaded rods are designed to be housed and then fixed inside the fastener holes 102, 104.

[0082] Referring to Figure 5-a, in one embodiment, the first holes 103 and the second holes 106 are provided respectively at the first longitudinal edge 61 and the second longitudinal edge 62 directly in the fire-resistant strip 6 itself. The holes 103, 106 are preferably reinforced by means of eyelets 107 which prevent any part of the fasteners 102, 105, for example screw heads, from rubbing against the fire-resistant strip 6 at the holes 103, 106, for example in the event of movement of the pylon 4 and the combustion gas ejection nozzle 3, at the risk of damaging, or even tearing, the fire-resistant strip 6 at the holes 103, 106.

[0083] With reference to Figure 5-b, in another embodiment, the first holes 103 and the second holes 106 are provided respectively in a first metal strip 108 and a second metal strip 109 attached fixedly to the first longitudinal edge 61 and the second longitudinal edge 62. The metal strips 108, 109 can be fixed to the longitudinal edges 61, 62 of the firestop strip 6 by means, for example, of a seam 110 or a weld.

[0084] As an example, the firestop strip 6 is in a loose state when fixed between the flue gas discharge nozzle 3 and at least one of the suspension pylon 4 and the rear fixed structure 2, as illustrated in Figures 3 and 4. Being in a loose state between the flue gas discharge nozzle 3 and the suspension pylon 4, the firestop strip 6 can advantageously tighten or loosen depending on any forces induced by relative movements and / or vibrations of the flue gas discharge nozzle 3 or the suspension pylon 4. Consequently, these potential forces do not damage the firestop strip 6.

[0085] In another example, the fire-sealing device includes a metal reinforcement 64 attached to and strengthening the firestop strip 6. The metal reinforcement 64 may, for example, include metal struts. Referring to Figure 6, the metal reinforcement may extend transversely between the first longitudinal edge 61 and the second longitudinal edge 62.

[0086] The various embodiments proposed by the invention advantageously allow for a significant limitation of the wear of the firestop strip 6, postponing its replacement over time, which replacement may even be unnecessary.

[0087] Although the present invention has been described with reference to specific embodiments, it is evident that modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. In particular, individual features of the various embodiments illustrated / mentioned can be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.

Claims

DEMANDS 1. Rear assembly (1) of a nacelle (10) of a turbojet engine (11), which rear assembly (1) comprises: - a thrust reverser (20) comprising a fixed rear structure (2); - a combustion gas ejection nozzle (3) which extends the rear fixed structure (2); - a suspension pylon (4) on which the rear fixed structure (2) is fixed; the rear assembly (1) comprising a fire-sealing device including a fire-stopping strip (6) made of a flexible, fire-resistant material, and having a first longitudinal edge (61) and a second longitudinal edge (62) opposite each other, in which the first longitudinal edge (61) is fixed on at least one of the suspension pylon (4) and the rear fixed structure (2), and the second longitudinal edge (62) is fixed on the combustion gas ejection nozzle (3), the fire-stopping strip (6) then extending at least below the suspension pylon (4).

2. Rear assembly (1) according to claim 1, wherein a first fastening means (71) is integral with at least one of the suspension pylon (4) and the rear fixed structure (2), and a second fastening means (72) is integral with the combustion gas ejection nozzle (3), and wherein the first longitudinal edge (61) comprises a first complementary fastening means (81) which cooperates with the first fastening means (71) for fixing the first longitudinal edge (61) to at least one of the suspension pylon (4) and the rear fixed structure (2), and the second longitudinal edge (62) comprises a second complementary fastening means (82) which cooperates with the second fastening means (8) for fixing the second longitudinal edge (72) to the combustion gas ejection nozzle (3).

3. Rear assembly (1) according to claim 2, wherein one of the first fastening means (71) and the first complementary fastening means (81) comprises a first slide (91) and the other of the first fastening means (71) and the first complementary fastening means (81) comprises a first male rail (92) engaged inside the first slide (91) and / or wherein one of the second fastening means (72) and the second complementary fastening means (82) comprises a second slide (94) and the other of the second fastening means (72) and the second complementary fastening means (82) comprises a second male rail engaged (95) inside the second slide (94).

4. Rear assembly (1) according to claim 3, wherein the first male rail (92) and / or the second male rail (95) comprises a first metal insert (93) and / or a second metal insert (96) respectively.

5. Rear assembly (1) according to claim 2, wherein the first fastening means (71) comprises a series of first fastening holes (101) associated with first fastening members (102), and the first complementary fastening means (81) comprises a series of first holes (103) allowing the passage of the first fastening members (102) through the first holes (103) to fix onto the first fastening holes (101) and / or wherein the second fastening means (72) comprises a series of second fastening holes (104) associated with second fastening members (105), and the second complementary fastening means (82) comprises a series of second holes (106) allowing the passage of the second fastening members (105) through the second holes (106) to fix onto the second fastening holes (104).

6. Rear assembly (1) according to claim 5, wherein the first holes (103) and / or the second holes (106) are made in the firestop strip (6) and reinforced by means of eyelets (107), or are made in a first metal strip (108) attached fixedly to the first longitudinal edge (61) and / or in a second metal strip (109) attached fixedly to the second longitudinal edge (62), respectively.

7. Rear assembly (1) according to any one of the preceding claims, wherein the firestop strip (6) is in a loose state when fixed between the combustion gas ejection nozzle (3) and at least one of the suspension pylon (4) and the rear fixed structure (2).

8. Rear assembly (1) according to any one of the preceding claims, wherein the fire sealing device comprises a metal frame (64) integral with the firestop strip (6).

9. Rear assembly (1) according to any one of the preceding claims, wherein the flexible, fire-resistant material is a flexible, non-woven, fibrous material, containing, for example, carbon, silica, ceramic or metal fibers, or a metallic woven material.

10. Turbojet (11) comprising a nacelle (10) having a rear assembly (1) according to any one of the preceding claims.

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