EP2742230A1 - Exhaust cone for aircraft turbojet engine - Google Patents

Exhaust cone for aircraft turbojet engine

Info

Publication number
EP2742230A1
EP2742230A1 EP12744051.9A EP12744051A EP2742230A1 EP 2742230 A1 EP2742230 A1 EP 2742230A1 EP 12744051 A EP12744051 A EP 12744051A EP 2742230 A1 EP2742230 A1 EP 2742230A1
Authority
EP
European Patent Office
Prior art keywords
flange
ejection cone
cone
outer skin
connecting flange
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP12744051.9A
Other languages
German (de)
French (fr)
Inventor
Hélène MALOT
Philippe Bienvenu
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Nacelles SAS
Original Assignee
Aircelle SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Aircelle SA filed Critical Aircelle SA
Publication of EP2742230A1 publication Critical patent/EP2742230A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/827—Sound absorbing structures or liners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/04—Mounting of an exhaust cone in the jet pipe
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/44—Nozzles having means, e.g. a shield, reducing sound radiation in a specified direction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/80—Couplings or connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to an ejection cone for an aircraft turbojet engine.
  • FIG. 1 Such a conventional ejection cone 1 is shown in Figure 1 appended hereto, in which the front and the rear of the structure along a motor axis are respectively located on the left and right of the figure.
  • This ejection cone is intended to be positioned downstream of the turbine of the turbojet, over which the primary nozzle is placed concentrically.
  • the ejection cone and the primary nozzle are both attached to a turbojet casing by a flange fastening system.
  • the ejection cone 1 comprises, strictly speaking, a front portion 5 (commonly referred to as “front plug”), of substantially cylindrical shape, and a rear portion 7 (commonly referred to as “rear”). plug "), of conical shape.
  • the front portion 5 may be especially acoustic or monolithic stiffened.
  • the front part 5 is acoustic, it means that it comprises at least one peripheral acoustic attenuation structure of the sandwich type comprising at least one resonator, in particular of honeycomb type, covered with a perforated outer skin and a full inner skin.
  • the outer skin also constitutes an outer surface (sheet) of the front portion 5 of the ejection cone.
  • the structure consists of a single sheet reinforced by stiffeners.
  • the rear portion 7 is monolithic stiffened by 9d stiffeners.
  • the front part 5 and the rear part 7 of the ejection cone may in particular be made from Inconel 625 type metal alloy sheets and be assembled by a flange connection system denoted 9b for the front flange part and 9c for the front flange part. rear flange part.
  • the front portion 5 further comprises an upstream connecting flange 9a to allow its attachment to the rear of the turbojet engine.
  • the flange 9b of the front portion 5 has on the one hand a portion 1 1 of diameter substantially equal to that of the outer skin of this front portion 5, and on the other hand a portion 13 of smaller diameter than that of the flange 9c of the rear portion 7 to which it is intended to be bonded, so that this portion 13 of the flange 9b can be inserted inside the flange 9c of the rear part 7.
  • Housing 15 formed in the thickness of the flange 9c can accommodate bolts 17 passing through the flange 9c and the flange 9b, fixed by means of nuts 18 attached by the interior of the ejection cone 1 thus assembled.
  • the housings 15 prevent the heads 19 of the bolts 17 are protruding outwardly of the cone 1, and thus cause aerodynamic losses.
  • an ejection cone of the prior art (FIG. 2) is a complex, multi-piece structure, and the cost of manufacturing is high and impacts the mass of the whole, which is undesirable.
  • the acoustic panel is closed at its front and rear ends respectively by peripheral flanges having a section C and commonly called closure C.
  • closure C's are bonded, in particular by brazing, with the corresponding front and rear flanges respectively providing the connection with the turbojet engine and the rear cone portion and ensures a large part of the maintenance of the acoustic attenuation structure.
  • These closing C are expensive parts made by machining and above all they represent a significant mass relative to the complete mass of the ejection cone.
  • the present invention aims to simplify the design of the acoustic attenuation structure and the ejection cone by overcoming these C closures.
  • an ejection cone for an aircraft turbojet engine comprising a front part having a front end equipped with a connecting flange at an output of a turbojet engine and / or a rear end equipped with a connecting flange at a rear portion of the ejection cone, said front portion being further provided with at least one acoustic attenuation structure comprising a corresponding outer skin, characterized in that the outer skin overlaps with at least one a part of the flange of the ia ison upstream or downstream corresponding and is assembled to the latter.
  • this type of direct connection between the acoustic attenuation structure and the front / rear flanges of the front part may concern only one or both closure Cs.
  • the outer skin and the front / rear flange are assembled by riveting.
  • the outer skin and the flange are assembled by brazing.
  • the rear link flange also constitutes a connecting flange before a rear portion of the ejection cone.
  • the outer skin is made from a metal alloy, such as Inconel 625.
  • FIG. 1 is a perspective view in axial section of an ejection cone of the prior art, mentioned in the preamble of the present description
  • FIG. 2 is a widened view of a junction zone between the acoustic panel and a rear flange connecting to a rear part of the ejection cone and showing the use of a closure C of the acoustic panel according to FIG. prior art
  • FIG. 3 is a widened view of a junction zone between the acoustic panel and a flange before binding to a rboreactor and showing the use of a closure C of the acoustic panel according to FIG. prior art
  • FIG. 4 is a view in longitudinal section of an ejection cone according to the invention.
  • FIGS. 5 and 6 are partial diagrammatic views in sections of the zones of attachment of the acoustic panel to an upstream flange according to two modes of assembly of the acoustic panel with the front flange,
  • FIG. 7 is a schematic partial sectional view of the rear zone of the acoustic panel attached to the rear flange of the front portion of the cone.
  • the front part 5 of the ejection cone 1 is equipped with an acoustic attenuation structure comprising a honeycomb core 51, for example a structure in honeycombs. covered with an outer skin 52 perforated and a full inner skin 53.
  • the cellular core is closed by a closing C 54, this closing C is also covered by the long run 55 of the pe r ex e 52, extension 55 not perforated, and by an extension of the inner skin 53.
  • connection between the acoustic attenuation structure and the rear link flange 9b is provided by the closing C 54, as previously explained, in particular by brazing between these elements.
  • the flange 9b has a thickness ensuring the absence of shift ("step", step) with the outer skin 52, and its extension 55 so as to best ensure the external aerodynamic continuity of the front portion 5 cone.
  • the junction shown in FIG. 3 between the acoustic attenuation structure and the flange 9a of the house is effected by means of a closing C by means of rows of rivets 56.
  • the present invention relates to an ejection cone 101 for an aircraft turbojet engine comprising a front portion of cone 105 of substantially cylindrical shape and equipped with at least one acoustic attenuation structure, said front portion 1 05 having, on the one hand, an upstream end eq ued with a flange lia ison 9a to an output of a turbojet, and secondly, a downstream end equipped with a connecting flange 9b to a rear portion of cone 7 substantially conical.
  • the front portion 105 of the cone is as previously described made from an acoustic attenuation structure comprising a cellular core 51 covered with an outer skin 52 perforated and a full inner skin 53.
  • the outer skin 52 is in extension of the cellular core (non-perforated extension) and overlaps with at least a portion of the corresponding connecting flange 9a and / or rear 9b and is assembled to the latter.
  • the outer skin 55 and the flange 9a are assembled at their connection zone by rivets 56.
  • the outer skin 55 and the flange 9a are joined together at the level of their bonding zone by welding.
  • the assembly by welding ensures an optimal continuity of the aerodynamic profile by avoiding any shifts ("step") between the front flange 9a and the outer skin 55.
  • the same principle is applicable to the rear end of the front part 105 with the flange of the section 9b, itself attached to the front flange 9c of the rear part 7.
  • the rear link flange 9b also constitutes a front connecting flange 9c of a rear portion 7 of the ejection cone 101.
  • the outer skin is made from a metal alloy such as Inconel 625. This same material can be used for all or part of the flanges.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Exhaust Silencers (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The present invention relates to an exhaust cone for an aircraft turbojet engine comprising a front part having a front end fitted with a connecting flange (9a) for connection to a turbojet engine outlet and/or a rear end fitted with a connecting flange (9b) for connection to a rear part of the exhaust cone, said front part also being equipped with at least one noise attenuation structure comprising a corresponding external skin (52), characterized in that the external skin straddles at least part of the corresponding upstream or downstream connecting flange and is assembled therewith.

Description

Cône d'éjection pour turboréacteur d'aéronef  Ejection cone for an aircraft turbojet engine
La présente invention se rapporte à un cône d'éjection pour turboréacteur d'aéronef. The present invention relates to an ejection cone for an aircraft turbojet engine.
Comme cela est connu en soi, il convient en général de prévoir un ensemble cône d'éjection / tuyère primaire à l'arrière d'un turboréacteur d'aéronef, afin d'une part d'optimiser l'écoulement des gaz chauds expulsés par le turboréacteur, et d'autre part d'absorber au moins une partie du bruit engendré par l'interaction de ces gaz chauds avec l'air ambiant et avec le flux d'air froid expulsé par la soufflante du turboréacteur.  As is known per se, it is generally necessary to provide a set of ejection cone / primary nozzle at the rear of an aircraft turbojet, in order firstly to optimize the flow of hot gases expelled by the turbojet, and secondly to absorb at least a portion of the noise generated by the interaction of these hot gases with the ambient air and with the flow of cold air expelled by the fan of the turbojet engine.
Ces éléments sont couramment désignés par les termes anglo- saxons « plug » pour le cône d'éjection et « nozzle » ou « primary nozzle » pour la tuyère.  These elements are commonly referred to by the Anglo-Saxon terms "plug" for the ejection cone and "nozzle" or "primary nozzle" for the nozzle.
Un tel cône d'éjection classique 1 est représenté à la figure 1 ci- annexée, sur laquelle l'avant et l'arrière de la structure suivant un axe moteur sont situés respectivement à gauche et à droite de la figure.  Such a conventional ejection cone 1 is shown in Figure 1 appended hereto, in which the front and the rear of the structure along a motor axis are respectively located on the left and right of the figure.
Ce cône d'éjection est destiné à être positionné en aval de la turbine du turboréacteur, par-dessus lequel la tuyère primaire est placée concentriquement. Le cône d'éjection et la tuyère primaire sont tous deux fixés sur un carter du turboréacteur par un système de fixation par brides.  This ejection cone is intended to be positioned downstream of the turbine of the turbojet, over which the primary nozzle is placed concentrically. The ejection cone and the primary nozzle are both attached to a turbojet casing by a flange fastening system.
Plus précisément, le cône d'éjection 1 comprend, à proprement parler, une partie avant 5 (couramment désignée sous le terme « front plug »), de forme sensiblement cyl indrique, et une partie arrière 7 (couramment désignée sous le terme « rear plug »), de forme conique.  More specifically, the ejection cone 1 comprises, strictly speaking, a front portion 5 (commonly referred to as "front plug"), of substantially cylindrical shape, and a rear portion 7 (commonly referred to as "rear"). plug "), of conical shape.
La partie avant 5 peut être notamment acoustique ou monolithique raidie.  The front portion 5 may be especially acoustic or monolithic stiffened.
Dans le cas où la partie avant 5 est acoustique, cela signifie qu'elle comprend au moins une structure d'atténuation acoustique périphérique de type sandwich comprenant au moins un résonateur, notamment de type nid d'abeille, recouvert d'une peau externe perforée et d'une peau interne pleine.  In the case where the front part 5 is acoustic, it means that it comprises at least one peripheral acoustic attenuation structure of the sandwich type comprising at least one resonator, in particular of honeycomb type, covered with a perforated outer skin and a full inner skin.
La peau externe constitue par ailleurs une surface externe (tôle) de la partie avant 5 du cône d'éjection.  The outer skin also constitutes an outer surface (sheet) of the front portion 5 of the ejection cone.
Dans le cas où la partie avant 5 est monolithique raidie, cela signifie que la structure est constituée d'une unique tôle renforcée par des raidisseurs.  In the case where the front portion 5 is monolithic stiffened, this means that the structure consists of a single sheet reinforced by stiffeners.
La partie arrière 7 est monolithique raidie par des raidisseurs 9d. La partie avant 5 et la partie arrière 7 du cône d'éjection pourront notamment être réalisées à partir de tôles en alliage métallique de type Inconel 625 et être assemblées par un système de jonction par bride notée 9b pour la partie bride avant et 9c pour la partie bride arrière. The rear portion 7 is monolithic stiffened by 9d stiffeners. The front part 5 and the rear part 7 of the ejection cone may in particular be made from Inconel 625 type metal alloy sheets and be assembled by a flange connection system denoted 9b for the front flange part and 9c for the front flange part. rear flange part.
La partie avant 5 comprend en outre une bride de liaison amont 9a destinée à permettre son rattachement à l'arrière du turboréacteur.  The front portion 5 further comprises an upstream connecting flange 9a to allow its attachment to the rear of the turbojet engine.
En se reportant à la figure 2, on peut voir que, classiquement, la bride 9b de la partie avant 5 présente d'une part une partie 1 1 de diamètre sensiblement égal à celui de la peau externe de cette partie avant 5, et d'autre part une partie 13 de diamètre inférieur à celui de la bride 9c de la partie arrière 7 à laquelle elle est destinée à être liée, de sorte que cette partie 13 de la bride 9b peut s'insérer à l'intérieur de la bride 9c de la partie arrière 7.  Referring to FIG. 2, it can be seen that, conventionally, the flange 9b of the front portion 5 has on the one hand a portion 1 1 of diameter substantially equal to that of the outer skin of this front portion 5, and on the other hand a portion 13 of smaller diameter than that of the flange 9c of the rear portion 7 to which it is intended to be bonded, so that this portion 13 of the flange 9b can be inserted inside the flange 9c of the rear part 7.
Des logements 15 formés dans l'épaisseur de la bride 9c permettent d'accueillir des boulons 17 traversant cette bride 9c et la bride 9b, fixés au moyen d'écrous 18 rapportés par l'intérieur du cône d'éjection 1 ainsi assemblé.  Housing 15 formed in the thickness of the flange 9c can accommodate bolts 17 passing through the flange 9c and the flange 9b, fixed by means of nuts 18 attached by the interior of the ejection cone 1 thus assembled.
Les logements 15 permettent d'éviter que les têtes 19 des boulons 17 ne soient protubérantes vers l'extérieur du cône 1 , et ne provoquent ainsi des pertes aérodynamiques.  The housings 15 prevent the heads 19 of the bolts 17 are protruding outwardly of the cone 1, and thus cause aerodynamic losses.
Comme on peut le comprendre à la lumière de ce qui précède, un cône d'éjection de la tech n iq ue antérieure (fig u re 2) est u ne structu re complexe, faisant intervenir de nombreuses pièces, et dont le coût de fabrication est élevé et impacte la masse de l'ensemble, ce qui n'est pas souhaitable.  As can be understood in the light of the foregoing, an ejection cone of the prior art (FIG. 2) is a complex, multi-piece structure, and the cost of manufacturing is high and impacts the mass of the whole, which is undesirable.
II existe donc un besoin permanent de simplifier la structure de montage d'un tel cône d'éjection, afin d'en abaisser tant la masse que le coût de fabrication.  There is therefore a permanent need to simplify the mounting structure of such an ejection cone, in order to lower both the mass and the cost of manufacture.
Notamment, selon la technique antérieure, dans le cas où la partie avant est de type acoustique, le panneau acoustique est fermé à ses extrémités avant et arrière respectivement par des brides périphériques présentant une section en C et couramment appelées C de fermeture.  In particular, according to the prior art, in the case where the front part is acoustic type, the acoustic panel is closed at its front and rear ends respectively by peripheral flanges having a section C and commonly called closure C.
Ces C de fermeture sont liées, notamment par brasage, avec les brides avant et arrière correspondantes assurant respectivement la liaison avec le turboréacteur et la partie arrière de cône et assure une grande partie du maintien de la structure d'atténuation acoustique. Ces C d e fermeture sont des pièces coûteuses réalisées par usinage et surtout elles représentent une masse non négligeable par rapport à la masse complète du cône d'éjection. These closure C's are bonded, in particular by brazing, with the corresponding front and rear flanges respectively providing the connection with the turbojet engine and the rear cone portion and ensures a large part of the maintenance of the acoustic attenuation structure. These closing C are expensive parts made by machining and above all they represent a significant mass relative to the complete mass of the ejection cone.
La présente invention vise à simplifier la conception de la structure d'atténuation acoustique et du cône d'éjection en s'affranchissant de ces C de fermetures.  The present invention aims to simplify the design of the acoustic attenuation structure and the ejection cone by overcoming these C closures.
On atteint ce but de l'invention avec un cône d'éjection pour turboréacteur d'aéronef comportant une partie avant présentant une extrémité avant équipée d'une bride de liaison à une sortie d'un turboréacteur et/ou une extrémité arrière équipée d'une bride de liaison à une partie arrière du cône d'éjection, ladite partie avant étant en outre équipée d'au moins une structure d'atténuation acoustique comprenant une peau externe correspondante, caractérisée en ce que la peau externe vient en chevauchement avec au moins une partie de la bride de l ia ison amont ou aval correspondante et est assemblée à cette dernière.  This object of the invention is achieved with an ejection cone for an aircraft turbojet engine comprising a front part having a front end equipped with a connecting flange at an output of a turbojet engine and / or a rear end equipped with a connecting flange at a rear portion of the ejection cone, said front portion being further provided with at least one acoustic attenuation structure comprising a corresponding outer skin, characterized in that the outer skin overlaps with at least one a part of the flange of the ia ison upstream or downstream corresponding and is assembled to the latter.
Ainsi, en prévoyant une liaison directe entre la peau externe de la partie avant et respectivement la bride avant et/ou arrière de liaison correspondante, il n'est plus nécessaire de recourir à un C de fermeture du panneau acoustique et servant d'interface entre le panneau sandwich et la bride avant et/ou arrière de la partie avant du cône d'éjection.  Thus, by providing a direct connection between the outer skin of the front part and respectively the corresponding front and / or back flange, it is no longer necessary to resort to a closing C of the acoustic panel and serving as an interface between the sandwich panel and the front and / or rear flange of the front part of the ejection cone.
Bien évidemment, ce type de liaison directe entre la structure d'atténuation acoustique et les brides avant/arrière de la partie avant peut concerner un seul ou les deux C de fermeture.  Of course, this type of direct connection between the acoustic attenuation structure and the front / rear flanges of the front part may concern only one or both closure Cs.
Selon une première variante de réalisation, la peau externe et la bride avant / arrière sont assemblées par rivetage.  According to a first variant embodiment, the outer skin and the front / rear flange are assembled by riveting.
Selon une deuxième variante de réalisation la peau externe et la bride sont assemblées par brasage.  According to a second embodiment, the outer skin and the flange are assembled by brazing.
Préférentiellement, la bride de liaison arrière constitue également une bride de liaison avant d'une partie arrière du cône d'éjection.  Preferably, the rear link flange also constitutes a connecting flange before a rear portion of the ejection cone.
Avantageusement, la peau externe est réalisée à partir d'un alliage métallique, tel que l'Inconel 625.  Advantageously, the outer skin is made from a metal alloy, such as Inconel 625.
La présente invention sera mieux comprise à la lecture de la description détaillée qui suit en regard du dessin annexé dans lequel :  The present invention will be better understood on reading the detailed description which follows with reference to the appended drawing in which:
- la figure 1 est une vue en perspective et en coupe axiale d'un cône d'éjection de la technique antérieure, mentionnée dans le préambule de la présente description, - la figure 2 est une vue élarg ie d'une zone de jonction entre le panneau acoustique et une bride arrière de liaison à une partie arrière du cône d'éjection et montrant l'utilisation d'un C de fermeture du panneau acoustique selon l'art antérieur, FIG. 1 is a perspective view in axial section of an ejection cone of the prior art, mentioned in the preamble of the present description, FIG. 2 is a widened view of a junction zone between the acoustic panel and a rear flange connecting to a rear part of the ejection cone and showing the use of a closure C of the acoustic panel according to FIG. prior art,
- la figure 3 est une vue élarg ie d'une zone de jonction entre le pan neau acoustique et u ne bride avant de l iaison à un tu rboréacteu r et montrant l'utilisation d'un C de fermeture du panneau acoustique selon l'art antérieur,  FIG. 3 is a widened view of a junction zone between the acoustic panel and a flange before binding to a rboreactor and showing the use of a closure C of the acoustic panel according to FIG. prior art,
- la figure 4 est une vue en coupe longitudinale d'un cône d'éjection selon l'invention,  FIG. 4 is a view in longitudinal section of an ejection cone according to the invention,
- les figures 5 et 6 sont des vues partielles schématiques en coupes des zones de rattachement du panneau acoustique à une bride amont selon deux modes d'assemblage du panneau acoustique avec la bride avant,  FIGS. 5 and 6 are partial diagrammatic views in sections of the zones of attachment of the acoustic panel to an upstream flange according to two modes of assembly of the acoustic panel with the front flange,
- la figure 7 est une vue partielle schématique en coupe de la zone arrière du panneau acoustique rattachée à la bride arrière de la partie avant du cône.  - Figure 7 is a schematic partial sectional view of the rear zone of the acoustic panel attached to the rear flange of the front portion of the cone.
Sur l'ensemble de ces figures, des références identiques désignent des organes ou ensembles d'organe identiques ou analogues.  In all of these figures, identical references denote identical or similar organs or groups of members.
Comme visible plus précisément sur la figure 2, la partie avant 5 du cône d'éjection 1 est équipée d'une structure d'atténuation acoustique com prenant u n e âme alvéol a ire 51 , par exemple u ne structu re en n ids d'abeille, recouvert d'une peau externe 52 perforée et d'une peau interne 53 pleine.  As can be seen more precisely in FIG. 2, the front part 5 of the ejection cone 1 is equipped with an acoustic attenuation structure comprising a honeycomb core 51, for example a structure in honeycombs. covered with an outer skin 52 perforated and a full inner skin 53.
Comme décrit précédemment et conformément à l'art antérieur, l'âme alvéolaire est fermée par un C de fermeture 54, ce C de fermeture étant ég a l em ent recouvert pa r u n pro long em ent 55 d e l a pe u exte rn e 52 , prolongement 55 non perforé, et par un prolongement de la peau interne 53.  As previously described and in accordance with the prior art, the cellular core is closed by a closing C 54, this closing C is also covered by the long run 55 of the pe r ex e 52, extension 55 not perforated, and by an extension of the inner skin 53.
La liaison entre la structure d'atténuation acoustique et la bride de liaison arrière 9b est assurée par le C de fermeture 54, comme précédemment expliqué, notamment par brasage entre ces éléments.  The connection between the acoustic attenuation structure and the rear link flange 9b is provided by the closing C 54, as previously explained, in particular by brazing between these elements.
La bride 9b présente une épaisseur assurant l'absence de décalage (« step », marche) avec la peau externe 52, et son prolongement 55 de manière à assurer au mieux la continuité aérodynamique externe de la partie avant 5 de cône.  The flange 9b has a thickness ensuring the absence of shift ("step", step) with the outer skin 52, and its extension 55 so as to best ensure the external aerodynamic continuity of the front portion 5 cone.
De manière similaire en partie avant, la jonction représentée sur la figure 3 entre la structure d'atténuation acoustique et la bride 9a de l iaison s'effectue par l'intermédiaire d'un C de fermeture au moyen de rangées de rivets 56. Similarly in the front part, the junction shown in FIG. 3 between the acoustic attenuation structure and the flange 9a of the house is effected by means of a closing C by means of rows of rivets 56.
Conformément à l'invention et tel que représenté plus en détail sur les figures 4 à 7 dans laquelle la structure d'atténuation acoustique n'est pas supportée à l'aide de C de fermeture 54.  According to the invention and as shown in more detail in FIGS. 4 to 7 in which the acoustic attenuation structure is not supported by means of closure C 54.
Pour ce faire, la présente invention se rapporte à un cône d'éjection 101 pour turboréacteur d'aéronef comprenant une partie avant de cône 105 de forme sensiblement cyl indrique et é q u i p é e d ' a u m o i n s u n e structure d'atténuation acoustique ladite partie avant 1 05 présentant, d'une part, une extrém ité amont éq u ipée d ' u ne bride de l ia ison 9a à une sortie d'un turboréacteur, et d'autre part, une extrémité aval équipée d'une bride de liaison 9b à une partie arrière de cône 7 sensiblement conique.  For this purpose, the present invention relates to an ejection cone 101 for an aircraft turbojet engine comprising a front portion of cone 105 of substantially cylindrical shape and equipped with at least one acoustic attenuation structure, said front portion 1 05 having, on the one hand, an upstream end eq ued with a flange lia ison 9a to an output of a turbojet, and secondly, a downstream end equipped with a connecting flange 9b to a rear portion of cone 7 substantially conical.
La partie avant 105 du cône est comme décrit précédemment réalisée à partir d'une structure d'atténuation acoustique comprenant une âme alvéolaire 51 recouverte d'une peau externe 52 perforée et d'une peau interne 53 pleine.  The front portion 105 of the cone is as previously described made from an acoustic attenuation structure comprising a cellular core 51 covered with an outer skin 52 perforated and a full inner skin 53.
Conformément à l'invention, la peau externe 52 vient en prolongement de l'âme alvéolaire (prolongement non perforé) et chevauche avec au moins une partie de la bride de liaison avant 9a et/ou arrière 9b correspondante et est assemblée à cette dernière.  According to the invention, the outer skin 52 is in extension of the cellular core (non-perforated extension) and overlaps with at least a portion of the corresponding connecting flange 9a and / or rear 9b and is assembled to the latter.
Comme représenté schématiquement sur la figure 5 la peau externe 55 et la bride 9a sont assemblées au niveau de leur zone de liaison par des rivets 56.  As shown diagrammatically in FIG. 5, the outer skin 55 and the flange 9a are assembled at their connection zone by rivets 56.
Alternativement, comme représenté sur la figure 6, la peau externe 55 et la bride 9a sont assemblées au n iveau de leur zone de liaison par soudage.  Alternatively, as shown in FIG. 6, the outer skin 55 and the flange 9a are joined together at the level of their bonding zone by welding.
L'assemblage par soudage permet d'assurer une continuité optimale du profil aérodynamique en s'affranchissant des éventuels décalages (« step ») entre la bride avant 9a et la peau externe 55.  The assembly by welding ensures an optimal continuity of the aerodynamic profile by avoiding any shifts ("step") between the front flange 9a and the outer skin 55.
Comme représenté sur la figure 7, le même principe est applicable à l'extrém ité arrière de la partie avant 1 05 avec la bride de l iaison 9b, elle- même rattachée à la bride avant 9c de la partie arrière 7.  As shown in FIG. 7, the same principle is applicable to the rear end of the front part 105 with the flange of the section 9b, itself attached to the front flange 9c of the rear part 7.
Selon un mode particulier de réalisation non représenté, la bride de liaison arrière 9b constitue également une bride de liaison avant 9c d'une partie arrière 7 du cône d'éjection 101 . Avantageusement la peau externe est réalisée à partir d'un alliage métallique tel que l'Inconel 625. Ce même matériau peut être utilisé pour les brides en tout ou partie. According to a particular embodiment not shown, the rear link flange 9b also constitutes a front connecting flange 9c of a rear portion 7 of the ejection cone 101. Advantageously, the outer skin is made from a metal alloy such as Inconel 625. This same material can be used for all or part of the flanges.
Bien entendu, la présente invention n'est nullement limitée aux modes de réalisation décrits et représentés.  Of course, the present invention is not limited to the embodiments described and shown.

Claims

REVENDICATIONS
1 . Cône d'éjection (101 ) pour turboréacteur d'aéronef comportant une partie avant (105) présentant une extrémité avant équipée d'une bride de liaison (9a) à une sortie d'un turboréacteur et/ou une extrémité arrière équipée d'une bride de liaison (9b) à une partie arrière du cône d'éjection, lad ite partie avant étant en outre équ ipée d'au moins une structure d ' attén u at ion aco u sti q u e com pren a nt u n e pea u exte rn e (52) correspondante, caractérisée en ce que la peau externe vient en chevauchement avec au moins une partie de la bride de liaison amont ou aval correspondante et est assemblée à cette dernière. 1. Ejection cone (101) for an aircraft turbojet having a front portion (105) having a front end equipped with a connecting flange (9a) at an output of a turbojet engine and / or a rear end equipped with a connecting flange (9b) at a rear part of the ejection cone, the said front part being furthermore equipped with at least one attenuating structure aco ust that includes a pea u ex rt e (52), characterized in that the outer skin overlaps with and is connected to at least a portion of the corresponding upstream or downstream connecting flange.
2. Cône d'éjection (101 ) selon la revendication 1 , caractérisé en ce que la peau externe (52) et la bride avant (9a) / arrière (9b) sont assemblées par rivetage (56). 2. Ejection cone (101) according to claim 1, characterized in that the outer skin (52) and the front flange (9a) / rear (9b) are assembled by riveting (56).
3. Cône d'éjection (101 ) selon la revendication 1 , caractérisé en ce que la peau externe (52) et la bride (9a, 9b) sont assemblées par soudage. 3. Ejection cone (101) according to claim 1, characterized in that the outer skin (52) and the flange (9a, 9b) are assembled by welding.
4. Cône d'éjection (101 ) selon l'une quelconque des revendications 1 à4. Ejection cone (101) according to any one of claims 1 to
3, caractérisé en ce que la bride de liaison arrière (9b) constitue également une bride de liaison avant (9c) d'une partie arrière (7) du cône d'éjection. 3, characterized in that the rear connecting flange (9b) also constitutes a front connecting flange (9c) of a rear portion (7) of the ejection cone.
5. Cône d'éjection (101 ) selon l'une quelconque des revendications 1 à 4, caractérisé en ce que la peau externe (52) est réalisée à partir d'un alliage métallique tel que l'Inconel 625. 5. Ejection cone (101) according to any one of claims 1 to 4, characterized in that the outer skin (52) is made from a metal alloy such as Inconel 625.
EP12744051.9A 2011-08-12 2012-07-05 Exhaust cone for aircraft turbojet engine Withdrawn EP2742230A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1157321A FR2978989B1 (en) 2011-08-12 2011-08-12 EJECTION CONE FOR AIRCRAFT TURBOJET ENGINE
PCT/FR2012/051583 WO2013024218A1 (en) 2011-08-12 2012-07-05 Exhaust cone for aircraft turbojet engine

Publications (1)

Publication Number Publication Date
EP2742230A1 true EP2742230A1 (en) 2014-06-18

Family

ID=46639577

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12744051.9A Withdrawn EP2742230A1 (en) 2011-08-12 2012-07-05 Exhaust cone for aircraft turbojet engine

Country Status (8)

Country Link
US (1) US9051899B2 (en)
EP (1) EP2742230A1 (en)
CN (1) CN103717870A (en)
BR (1) BR112014001679A2 (en)
CA (1) CA2842874A1 (en)
FR (1) FR2978989B1 (en)
RU (1) RU2014108721A (en)
WO (1) WO2013024218A1 (en)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3026786B1 (en) * 2014-10-07 2019-07-26 Safran Aircraft Engines FLANGE OF CLOSURE OF AN EXHAUST CASING
US10337453B2 (en) * 2015-04-21 2019-07-02 Rohr, Inc. Attachment feature for a core panel
FR3037358B1 (en) * 2015-06-11 2017-05-19 Snecma EXHAUST CASE ASSEMBLY AND END OF REVOLUTION PIECE
CN105298684B (en) * 2015-09-18 2017-11-03 中国航空工业集团公司沈阳发动机设计研究所 A kind of aero-engine tail bone attachment structure
FR3043138B1 (en) * 2015-11-04 2019-09-13 Safran Aircraft Engines DEGASSING TUBE AND EJECTION CONE FOR A TURBOMACHINE, AND THEIR ASSEMBLY TOOLS
US10907508B2 (en) * 2015-11-12 2021-02-02 Rohr, Inc. Turbine engine and exhaust system connection
FR3082238A1 (en) * 2018-06-11 2019-12-13 Airbus Operations PRIMARY NOZZLE OF A PRIMARY EJECTION DUCT OF A TURBOMACHINE
FR3084917B1 (en) * 2018-08-09 2021-04-16 Safran Ceram SET FOR A TURBOMACHINE EJECTION TUBE
FR3084916B1 (en) * 2018-08-10 2020-07-17 Safran Ceramics FLEXIBLE FIXING EJECTION CONE
CN109372653A (en) * 2018-12-13 2019-02-22 中国航发沈阳发动机研究所 A kind of fanjet noise-reducing exhaust component
FR3098552B1 (en) * 2019-07-08 2022-07-15 Airbus Operations Sas TURBOMACHINE COMPRISING A STRUCTURE AND AN INTERNAL STRUCTURE OF A PRIMARY EXHAUST DUCT FIXED TO THE SAID STRUCTURE
FR3100575B1 (en) * 2019-09-05 2022-04-08 Safran Ceram AERODYNAMIC FLEXIBLE ATTACHMENT CONE
FR3100845B1 (en) * 2019-09-13 2022-07-08 Safran Nacelles Outer nozzle member for turbomachine
FR3115830B1 (en) * 2020-11-05 2022-09-30 Safran Nacelles Set for a turbomachine
US11867077B2 (en) 2021-06-07 2024-01-09 Rohr, Inc. Acoustic structure with floating interior skin
US11976597B2 (en) 2021-09-13 2024-05-07 Rohr, Inc. Low-frequency acoustic center body

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1543312A (en) * 1976-07-21 1979-04-04 Rolls Royce Honeycomb linings
FR2623249A1 (en) * 1987-11-12 1989-05-19 Snecma ASSEMBLY CONSISTING OF TWO PIECES OF MATERIALS HAVING DIFFERENT EXPANSION COEFFICIENTS, CONNECTED THEREBY AND METHOD OF ASSEMBLY
GB9120658D0 (en) * 1991-09-27 1991-11-06 Short Brothers Plc Ducted fan turbine engine
US5251435A (en) * 1991-10-30 1993-10-12 General Electric Company Reverser inner cowl with integral bifurcation walls and core cowl
GB9613615D0 (en) * 1996-06-28 1996-08-28 Short Brothers Plc Method of manufacturing a noise attenuation panel
FR2869874B1 (en) * 2004-05-04 2006-06-23 Snecma Moteurs Sa AIRCRAFT ENGINE WITH MEANS OF SUSPENSION TO THE STRUCTURE OF AN AIRCRAFT
US7870722B2 (en) * 2006-12-06 2011-01-18 The Boeing Company Systems and methods for passively directing aircraft engine nozzle flows
FR2920146B1 (en) * 2007-08-20 2009-10-30 Aircelle Sa NACELLE WITH ADAPTABLE OUTPUT SECTION
FR2935753B1 (en) * 2008-09-08 2011-07-01 Snecma Propulsion Solide FASTENING, FASTENING CONNECTIONS FOR MOUNTING CMC PIECES
DE102008051241B4 (en) * 2008-10-10 2011-06-16 Airbus Operations Gmbh Muffler for an auxiliary engine of an aircraft
FR2949820B1 (en) * 2009-09-04 2011-10-14 Aircelle Sa STRUCTURING ASSEMBLY FOR AN EJECTION TUBE.
US8579584B2 (en) * 2010-10-06 2013-11-12 Dewain Ray Brown Turbofan jet engine
US9279386B2 (en) * 2012-03-09 2016-03-08 Hamilton Sundstrand Corporation Jet noise reduction using eduction effect
FR2988777B1 (en) * 2012-03-29 2014-04-25 Snecma Propulsion Solide INTEGRATION OF REAR BODY PARTS OF AERONAUTICAL MOTOR
US8985942B2 (en) * 2012-07-02 2015-03-24 United Technologies Corporation Turbine exhaust case duct

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2013024218A1 *

Also Published As

Publication number Publication date
US20140158458A1 (en) 2014-06-12
RU2014108721A (en) 2015-09-20
US9051899B2 (en) 2015-06-09
WO2013024218A1 (en) 2013-02-21
CA2842874A1 (en) 2013-02-21
FR2978989A1 (en) 2013-02-15
FR2978989B1 (en) 2013-07-26
BR112014001679A2 (en) 2017-03-07
CN103717870A (en) 2014-04-09

Similar Documents

Publication Publication Date Title
EP2742230A1 (en) Exhaust cone for aircraft turbojet engine
EP2250357B1 (en) Air intake structure for an aircraft nacelle
FR2949820A1 (en) STRUCTURING ASSEMBLY FOR AN EJECTION TUBE.
WO2010012899A2 (en) Assembly of components connected by a device that maintains the integrity of the surface of one of the components
EP2742227A1 (en) Exhaust plug for an aircraft turbojet engine
EP0284466B1 (en) Exhaust pipes connecting device and internal combustion engine equipped with this device
EP3673163B1 (en) Cell structure and acoustic attenuation device for a nacelle of an aircraft propulsion assembly
WO2020174162A1 (en) Expandable cellular system for a sandwich panel
FR3044960A1 (en) PANEL FOR AIRCRAFT TURBO BURNER BOAT COMPRISING THERMAL PROTECTION AND ANTI-FIRE PROTECTION
EP2879955B1 (en) Air inlet for helicopter engine with increased circumferential intake lips
FR2940377A1 (en) Inner partition and outer panel assembly for air inlet structure of nacelle of turbojet engine of aircraft, has connecting element comprising structural skin fixed to partition and porous material attached to skin and fixed to outer panel
FR3027630B1 (en) ASSEMBLY OF INTERNAL FIXED STRUCTURE OF TURBOJET NACELLE AND THERMAL PROTECTION
EP4240954A1 (en) Fastening of an exhaust cone in a turbomachine nozzle
FR3120352A1 (en) NACELLE AIR INTAKE EQUIPPED WITH A MIXED ICE PROTECTION SYSTEM
EP3959137A1 (en) Nacelle air intake and nacelle comprising such an air intake
WO2017220931A1 (en) Assembly of a fixed internal structure of a turbojet engine nacelle and thermal protection panels
FR2936776A1 (en) Air inlet structure for use in jet engine nacelle of airplane, has rear frame connecting external cowl and inner wall, and heat insulation unit arranged on inner wall, where frame and heat insulation unit form rear structural element
WO2008152311A2 (en) Device for insulating an exhaust manifold
WO2023166266A1 (en) Ejection cone for an aircraft turbine engine
EP4028656A1 (en) Structural and/or acoustic panel comprising a u-shaped sealing flange directed toward the inside of the panel, and method for manufacturing such a panel
FR3082238A1 (en) PRIMARY NOZZLE OF A PRIMARY EJECTION DUCT OF A TURBOMACHINE

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20140226

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

DAX Request for extension of the european patent (deleted)
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN WITHDRAWN

18W Application withdrawn

Effective date: 20160805