EP2566757A1 - Unit for an aircraft thruster - Google Patents

Unit for an aircraft thruster

Info

Publication number
EP2566757A1
EP2566757A1 EP11725141A EP11725141A EP2566757A1 EP 2566757 A1 EP2566757 A1 EP 2566757A1 EP 11725141 A EP11725141 A EP 11725141A EP 11725141 A EP11725141 A EP 11725141A EP 2566757 A1 EP2566757 A1 EP 2566757A1
Authority
EP
European Patent Office
Prior art keywords
ferrule
flange
connecting flange
plane
connection
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Withdrawn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
EP11725141A
Other languages
German (de)
French (fr)
Inventor
Christophe Thorel
Bertrand Desjoyeaux
Florent Bouillon
John Moutier
Stéphane BARDIN
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 EP2566757A1 publication Critical patent/EP2566757A1/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Withdrawn legal-status Critical Current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
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • 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
    • 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
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/45—Flexibly connected rigid members

Definitions

  • the present invention relates to an assembly for an aircraft propulsion system and a method for manufacturing such an assembly.
  • a nacelle belonging to the propulsion system of the aircraft, generally has a structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a downstream section housing thrust reversal means and intended to surround the combustion chamber of the turbojet, and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine.
  • the air intake comprises, on the one hand, an inlet lip adapted to allow optimal capture to the turbojet of the air necessary to supply the blower and the internal compressors of the turbojet, and, of on the other hand, a downstream structure on which the lip is attached and intended to properly channel the air towards the blades of the fan.
  • This downstream structure comprises in particular an annular inner wall 1, illustrated in FIGS. 1 and 2, and an outer cover (not shown) radially spaced from the inner wall 1.
  • the inner wall 1 of the air intake structure is extended by a fan casing belonging to the median section of the nacelle in a direction parallel to the longitudinal axis of the turbojet engine.
  • downstream end of the inner wall 1 of the air inlet and the upstream end of the blower housing each carry peripheral connecting flanges 2,3 for assembling said air inlet together. and the fan casing, using fasteners such as screws 4 or bolts.
  • connection flange 2 of the air intake structure is respectively fixed downstream of the acoustic panel of the inner wall 1 or on the acoustic panel even by bolted elements 5.
  • Air intake structures are also known in which the external connection and the connection flange to the corresponding fan casing are integrated in a single piece of composite material.
  • the present invention aims to overcome these disadvantages.
  • the present invention proposes an assembly for an aircraft propulsion system comprising a first ferrule intended to be fixed to a second ferrule and a first connecting flange intended to be fixed to a second corresponding connecting flange integral with the second ferrule.
  • said first connecting flange comprising a plane portion extending in a radial direction with respect to the first ferrule characterized in that the connection between the first ferrule and the corresponding connecting flange is offset at a distance from the corresponding flange plane at a damping length of a moment generated by force flows through the first hole vi rol in predetermined condi tions of use of the set.
  • the present invention avoids the appearance of delamination between the first ferrule and the connecting flange, insofar as at this particular distance, it avoids stressing the connection between the ferrule and the corresponding flange connection.
  • the assembly according to the invention may comprise or more than one of the following characteristics, in particular: em ent or technically possible
  • the first shell is an inner shell of an air intake structure of a nacelle and / or a structure of the inverter of the nacelle and / or a turbojet fan casing;
  • the damping length I of said moment is defined on the following formula (1): wherein R and e respectively define the radius and thickness of the first ferrule and v, the fish coefficient of the material forming the first ferrule in line with the flange plane;
  • the first ferrule and the corresponding first connecting flange are made of a single piece of composite material
  • the first connecting flange is made of metallic material
  • the first ferrule further comprises a transition wedge intended to be placed in line with the plane of the first flange between the latter and the first ferrule;
  • the first ferrule further comprises a reinforcing plate attached to the connecting flange.
  • the invention also relates to a method of manufacturing an assembly as mentioned above comprising a step in which a connection is carried between the first ferrule and the corresponding connection flange at a distance from the flange plane corresponding to a length of damping of a moment generated by force flows passing through said first ferrule under predetermined conditions of use of the assembly.
  • FIG. 1 and 2 show partial sectional views of two assemblies of an air intake structure and a fan case of the state of the art
  • FIG. 3 is a partial sectional view of an embodiment of an assembly of an air intake structure and a fan casing according to an embodiment of the present invention
  • FIG. 4 is a detailed view of a method of manufacturing a flange for connecting a ferrule of the assembly of FIG. 3;
  • - Figure 5 is a partial perspective view of a ferrule of the assembly of Figure 3 on which it has highlighted the different force flows present on the shell.
  • An aircraft turbojet engine nacelle has a structure comprising an air inlet, a median section surrounding a turbojet fan, and a downstream section surrounding the turbojet and generally housing a thrust reversal system.
  • the air intake structure is divided into two zones, namely on the one hand, an annular inlet lip aerodynamic profile adapted to allow optimal capture to the turbojet of the air necessary for the supply of air.
  • the blower and internal compressors of the turbojet engine and, secondly, a downstream structure comprising an annular inner ring and an annular outer cover radially spaced from the inner shell, ferrule in te rn esurlaqu al is r pa rtée lal It is necessary to air the air to the blower.
  • Such a ferrule is designated by the general reference 10 in FIG.
  • This inner ferrule 10 of the air inlet structure is conventionally treated to form a sound attenuation structure 1 1 of the sound wave.
  • It may include an air permeable inner skin, an outer breathable skin and a honeycomb honeycomb core.
  • the middle section meanwhile, comprises on the one hand, an inner casing 20 surrounding the turbojet fan extending the inner shell 10 of the air intake structure and, on the other hand, an outer fairing structure of the casing extending the external hood of the air intake structure.
  • the inner ferrule 10 is intended to be fixed to the fan casing 20 in a joint plane designated by the letter A, thanks to peripheral annular connection flanges 30, 40 placed respectively on the downstream end of the inner ferrule 10. and on the upstream end of the fan casing 20.
  • Each connecting flange 30, 40 comprises a first connecting portion 31 forming a flange and extending in a radial direction and a second substantially cylindrical tubular connecting portion 32 extending in the longitudinal direction of the turbojet, so that the longitudinal section of the connection flange is L-shaped.
  • connection flanges can be proposed.
  • Each of the connecting flanges 30,40 protruding outwardly around the periphery of the inner shroud 10 of the air inlet and the blower housing 20 are pressed against each other by suitable fastening means. , parallel to the longitudinal axis of the turbojet and intended to pass through passages in each of the connecting flanges 30,40.
  • the connecting flange 30 of the inner ferrule 10 is thus connected by any known means (not shown in FIG. 3), such as bolts, to the connection flange 40 of the casing 20 at the junction plane A.
  • connection flanges 30, 40 may be associated with centering means making it possible to center the air intake structure with respect to the fan casing 20.
  • the second connecting portion 32 of the flange 30 corresponding to the inner ferrule 10 of the air intake structure is intended to be fixed on said ferrule 10.
  • this second connecting portion 32 forms a composite material part with the inner shell 10 of the air intake structure.
  • This embodiment has the advantage of eliminating any fastening such as bolts or screws, which could alter the acoustic quality of the inner shell 10.
  • connection between the inner ferrule 10 and the corresponding connection flange 30 is offset at a distance from the first portion 31 of the flange 30 corresponding to a characteristic quantity of a moment generated by the fluxes of through-forces said inner ferrule under predetermined conditions of use of the nacelle.
  • connection bonded between the flange 30 and the acoustic panel 1 1 of the inner shell 10 is biased by forces in the plane, namely tension, compression and shearing in the plane, which lead to a bending moment in the plane. of the aforementioned ison generator of interlaminar shear.
  • connection bonded between the flange 30 and the acoustic panel of the inner shell 10 is biased by force flows in the shell 10, namely axial tension and compression denoted by t, tension and circumferential compression denoted by f and shear plane designated by Ti 2 and the two associated arrows, shear in the wall of ferrule 10.
  • the tension and the axial compression lead to a bending moment at the level of the aforesaid interlaminar-shedding ionic bond at the interface between the flange 30 and the ferrule 10.
  • connection between the connecting flange 30 and the inner shroud 10 of the air intake structure is made substantially along the length of damping I at this time.
  • Such a damping length is defined by the following formula (1):
  • R is the radius of the ferrule
  • e is the thickness of the ferrule
  • v the fish coefficient of the material forming the ferrule at the first portion of the flange.
  • the damping length can be defined by the formula ( 2) next approach:
  • the connecting flange 30 is made of composite material.
  • the damping length of the aforementioned moment is the length at which the moment becomes negligible.
  • the acoustic panel of the inner shell 10 at this distance does not see the bending forces generated at the connection flange 30.
  • connection flange 30 with the acoustic panel 11 of the inner ferrule 10 by eliminating the acoustic junction zones which act as a sonic bridge.
  • connection allows the use of acoustic panel 11 comprising a low density honeycomb in the right of the connection flange 30, which has the advantage of promoting the reduction of mass of the panel 11 and of increase the acoustic surface of the latter.
  • an alternative embodiment may provide a connection flange 30 of metal material whose connection with the inner ferrule 10 will be performed at the aforementioned damping length.
  • a reinforcing plate 33 can be attached to the first connection portion 31 of the flange 30 corresponding to the inner ferrule 10 and fixed to the flange 30 by suitable means, if the requirements in terms of structural strength of the connection flange 30 require it.
  • an alternative embodiment of the present invention proposes to insert a transition wedge 34 between the inner ferrule 10 and the connection flange 30 to the right of the first connecting portion 31 of the flange 30.
  • this corner 34 is a profile having a section of generally triangular shape.
  • This profile is formed of folds of glass or carbon, as well as a filler resin.
  • this profile can be formed by pultrusion.
  • This transition wedge 34 offers the advantage of improving the material health in the flange 30 / ferrule transition zone 10, that is to say, it makes it possible to avoid the deformation of the tissues at the place where it is square.
  • connection flange 30 on the inner shroud 10 of the air intake structure a corresponding counter-form 35 is placed in place. that of the associated connection flange 30 that is desired to form and symmetrical to the latter.
  • this counter-form 35 is contiguous on a rear skin 36 of the connecting flange 30 which has been previously cooked.
  • connection flange 30 also comprises sacrificial pleats 37 placed behind the rear skin 36.
  • connection flange 30 is draped over the counter-shape assembly 35 / rear skin 36.
  • the invention is not limited to the embodiments of this nacelle, described above as examples, but it encompasses all variants.
  • connection flange any ferrule of an assembly for an aircraft propulsion system comprising a connection flange and, in particular, to a structure of the inverter of the nacelle and / or the casing surrounding the blower of the turbojet engine. comprising an acoustic attenuation structure and the corresponding connection flange.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Vibration Prevention Devices (AREA)
  • Details Of Aerials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to a unit for an aircraft thruster which includes a first ferrule (10) intended for being attached to a second ferrule (20) and a first connection flange (30) intended for being secured to a corresponding second connection flange (40) secured to the second ferrule (20), said first connection flange including a portion forming a plane (31) extending in a radial direction relative to the first ferrule (10) characterised in that the link between the first ferrule (10) and the corresponding connection flange (30) is offset to a distance from said plane that corresponds to a length for damping a bending moment generating shear, generated by fluxes of force passing through said first ferrule.

Description

Ensemble pour système propulsif d'aéronef  Aircraft Propulsion System Package
La présente invention concerne un ensemble pour système propulsif d'aéronef et un procédé de fabrication d'un tel ensemble. The present invention relates to an assembly for an aircraft propulsion system and a method for manufacturing such an assembly.
Une nacelle, appartenant au système propulsif de l'aéronef, présente généralement une structure comprenant une entrée d'air en amont du turboréacteur, une section médiane destinée à entourer une soufflante du turboréacteur, une section aval abritant des moyens d'inversion de poussée et destinée à entourer la chambre de combustion du turboréacteur, et est généralement terminée par une tuyère d'éjection dont la sortie est située en aval du turboréacteur.  A nacelle, belonging to the propulsion system of the aircraft, generally has a structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a downstream section housing thrust reversal means and intended to surround the combustion chamber of the turbojet, and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine.
L'entrée d'air comprend, d'une part, une lèvre d'entrée adaptée pour permettre la captation optimale vers le turboréacteur de l'air nécessaire à l'alimentation de la soufflante et des compresseurs internes du turboréacteur, et, d'autre part, une structure aval sur laquelle est rapportée la lèvre et destinée à canaliser convenablement l'air vers les aubes de la soufflante.  The air intake comprises, on the one hand, an inlet lip adapted to allow optimal capture to the turbojet of the air necessary to supply the blower and the internal compressors of the turbojet, and, of on the other hand, a downstream structure on which the lip is attached and intended to properly channel the air towards the blades of the fan.
Cette structure aval comprend notamment une paroi interne 1 annulaire, illustrée sur les figures 1 et 2, et un capot externe (non illustré) radialement espacé de la paroi interne 1 .  This downstream structure comprises in particular an annular inner wall 1, illustrated in FIGS. 1 and 2, and an outer cover (not shown) radially spaced from the inner wall 1.
La paroi interne 1 de la structure d'entrée d'air est prolongée par un carter de soufflante appartenant à la section médiane de la nacelle dans une direction parallèle à l'axe longitudinal du turboréacteur.  The inner wall 1 of the air intake structure is extended by a fan casing belonging to the median section of the nacelle in a direction parallel to the longitudinal axis of the turbojet engine.
Plus particul ièrement, l'extrémité aval de la paroi interne 1 de l'entrée d'air et l'extrémité amont du carter de la soufflante portent, chacun, des brides de raccordement 2,3 périphériques pour assembler ensemble ladite entrée d'air et le carter de soufflante, à l'aide d'éléments de fixation tels que des vis 4 ou des boulons.  More particularly, the downstream end of the inner wall 1 of the air inlet and the upstream end of the blower housing each carry peripheral connecting flanges 2,3 for assembling said air inlet together. and the fan casing, using fasteners such as screws 4 or bolts.
Dans les structures d'entrée d'air actuelles, telles qu'illustrées sur les figures 1 et 2, la bride de raccordement 2 de la structure d'entrée d'air est respectivement fixée en aval du panneau acoustique de la paroi interne 1 ou sur le panneau acoustique même par des éléments boulonnés 5.  In the current air inlet structures, as illustrated in FIGS. 1 and 2, the connection flange 2 of the air intake structure is respectively fixed downstream of the acoustic panel of the inner wall 1 or on the acoustic panel even by bolted elements 5.
La présence des éléments boulonnés 5 nécessite alors des renforts locaux dans le plan de bride qui ont une incidence sur la masse de la structure d'entrée d'air.  The presence of the bolted members 5 then necessitates local reinforcements in the flange plane which affect the mass of the air intake structure.
De plus, de tels agencements limitent les dimensions du panneau acoustique de la paroi interne 1 de la structure d'entrée d'air, si on ne souhaite pas le détériorer par l'aménagement des éléments boulonnés 5, comme illustré sur la figure 1 . In addition, such arrangements limit the dimensions of the acoustic panel of the inner wall 1 of the air intake structure, if it is not desired not damage by the arrangement of the bolted elements 5, as shown in Figure 1.
On connaît également des structures d'entrée d'air dans lesquelles l a pa ro i i ntern e et l a brid e d e raccordement au carter de soufflante correspondante sont intégrées dans une pièce unique en matériau composite.  Air intake structures are also known in which the external connection and the connection flange to the corresponding fan casing are integrated in a single piece of composite material.
Or, dans une telle pièce, on constate un cisaillement interlaminaire au niveau de la liaison collée entre la bride et le panneau acoustique de la paroi interne  However, in such a room, there is an interlaminar shear at the bonded bond between the flange and the acoustic panel of the inner wall
Il existe alors un risque de délaminage dans la pièce composite qui entraîne une baisse importante de la résistance mécanique de la paroi interne de la structure d'entrée d'air, et même la rupture de cette dernière.  There is then a risk of delamination in the composite part which causes a significant drop in the mechanical strength of the inner wall of the air inlet structure, and even the rupture of the latter.
La présente invention a pour objet de remédier à ces inconvénients.  The present invention aims to overcome these disadvantages.
A cet effet, la présente invention propose un ensemble pour système propulsif d'aéronef comprenant une première virole destinée à être fixée à une seconde virole et une première bride de raccordement destinée à être fixée à une seconde bride de raccordement correspondante solidaire de la seconde virole, ladite première bride de raccordement comprenant une portion formant plan s'étendant suivant une direction radiale par rapport à la première virole remarquable en ce que la liaison entre la première virole et la bride de raccordement correspondante est déportée à une distance du plan de bride correspondant à une longueur d'amortissement d'un moment généré par des flux d'efforts traversa nt l ad ite prem ière vi rol e dan s des cond itions prédéterminées d'utilisation de l'ensemble.  For this purpose, the present invention proposes an assembly for an aircraft propulsion system comprising a first ferrule intended to be fixed to a second ferrule and a first connecting flange intended to be fixed to a second corresponding connecting flange integral with the second ferrule. said first connecting flange comprising a plane portion extending in a radial direction with respect to the first ferrule characterized in that the connection between the first ferrule and the corresponding connecting flange is offset at a distance from the corresponding flange plane at a damping length of a moment generated by force flows through the first hole vi rol in predetermined condi tions of use of the set.
Grâce à la présente invention, on évite l'apparition du délaminage entre la première virole et la bride de raccordement, dans la mesure où à cette distance particulière, on évite de solliciter la liaison entre cette virole et la bride de raccordement correspondante.  Thanks to the present invention, it avoids the appearance of delamination between the first ferrule and the connecting flange, insofar as at this particular distance, it avoids stressing the connection between the ferrule and the corresponding flange connection.
Selon des modes particu l iers de réal isation de l'invention, l'ensemble selon l ' i nvention peut com prend re u ne ou pl u sieu rs d es ca ractéristiq u es su iva ntes , pri se(s ) i sol ém ent ou en com b i n a ison techniquement possible :  According to particular embodiments of the invention, the assembly according to the invention may comprise or more than one of the following characteristics, in particular: em ent or technically possible
- la première virole est une virole interne d'une structure d'entrée d'air d'une nacelle et/ou d'une structure de l'inverseur de la nacelle et/ou d'un carter de soufflante de turboréacteur ; - la longueur d'amortissement I dudit moment est définie sur la formule (1 ) suivante : dans laquelle R et e définissent, respectivement, le rayon et l'épaisseur de la première virole et v, le coefficient de poisson du matériau formant la première virole au droit du plan de bride ; the first shell is an inner shell of an air intake structure of a nacelle and / or a structure of the inverter of the nacelle and / or a turbojet fan casing; the damping length I of said moment is defined on the following formula (1): wherein R and e respectively define the radius and thickness of the first ferrule and v, the fish coefficient of the material forming the first ferrule in line with the flange plane;
- la première virole et l a première bride de raccordement correspondante sont réalisées en une pièce unique en matériau composite ;  - The first ferrule and the corresponding first connecting flange are made of a single piece of composite material;
- la première bride de raccordement est en matériau métallique ; the first connecting flange is made of metallic material;
- la première virole comprend , en outre, un coin de transition destiné à être mis en place au droit du plan de la première bride entre cette dernière et la première virole ; - The first ferrule further comprises a transition wedge intended to be placed in line with the plane of the first flange between the latter and the first ferrule;
- la première virole comprend, en outre, une plaque de renfort rapportée sur la bride de raccordement.  - The first ferrule further comprises a reinforcing plate attached to the connecting flange.
L'invention concerne, également, un procédé de fabrication d'un ensemble tel que précité comprenant une étape dans laquelle on déporte une liaison entre la première virole et la bride de raccordement correspondante à une distance du plan de bride correspondant à une longueur d'amortissement d'un moment généré par des flux d'efforts traversant ladite première virole dans des conditions prédéterminées d'utilisation de l'ensemble.  The invention also relates to a method of manufacturing an assembly as mentioned above comprising a step in which a connection is carried between the first ferrule and the corresponding connection flange at a distance from the flange plane corresponding to a length of damping of a moment generated by force flows passing through said first ferrule under predetermined conditions of use of the assembly.
D'autres caractéristiques et avantages de la présente invention, apparaîtront à la lecture de la description détaillée qui va suivre, selon des modes de réalisation donnés à titre d'exemples non limitatifs et en référence aux dessins annexés sur lesquels :  Other characteristics and advantages of the present invention will appear on reading the detailed description which follows, according to embodiments given by way of non-limiting examples and with reference to the appended drawings in which:
- les figures 1 et 2 représentent des vues partielles en coupe de deux assemblages d'une structure d'entrée d'air et d'un carter de soufflante de l'état de l'art ;  - Figures 1 and 2 show partial sectional views of two assemblies of an air intake structure and a fan case of the state of the art;
- la figure 3 est une vue partielle en coupe d'un mode de réalisation d'un assemblage d'une structure d'entrée d'air et d'un carter de soufflante selon un mode de réalisation de la présente invention ;  FIG. 3 is a partial sectional view of an embodiment of an assembly of an air intake structure and a fan casing according to an embodiment of the present invention;
- La fig u re 4 est u ne vue en cou pe détaillée d'un mode de fabrication d'une bride de raccordement d'une virole de l'assemblage de la figure 3 ; - La figure 5 est une vue en perspective partielle d'une virole de l'assemblage de la figure 3 sur laquelle on a mis en évidence les différents flux d'efforts présents sur la virole. Une nacelle de turboréacteur d'aéronef possède une structure comprenant une entrée d'air, une section médiane entourant une soufflante de turboréacteur, et u ne section aval entourant le turboréacteur et abritant généralement un système d'inversion de poussée. FIG. 4 is a detailed view of a method of manufacturing a flange for connecting a ferrule of the assembly of FIG. 3; - Figure 5 is a partial perspective view of a ferrule of the assembly of Figure 3 on which it has highlighted the different force flows present on the shell. An aircraft turbojet engine nacelle has a structure comprising an air inlet, a median section surrounding a turbojet fan, and a downstream section surrounding the turbojet and generally housing a thrust reversal system.
La structure d'entrée d'air se divise en deux zones, à savoir d'une part, u ne lèvre d'entrée annulaire à profil aérodynamique adaptée pour permettre la captation optimale vers le turboréacteur de l'air nécessaire à l'alimentation de la soufflante et des compresseurs internes du turboréacteur, et, d'autre part, une structure aval comprenant une virole interne annulaire et un capot externe annulaire rad ialement espacé de la virole interne, virole i n te rn e s u r l a q u el l e est ra p po rtée l a l èvre et d est i n ée à ca n a l i se r convenablement l'air vers la soufflante.  The air intake structure is divided into two zones, namely on the one hand, an annular inlet lip aerodynamic profile adapted to allow optimal capture to the turbojet of the air necessary for the supply of air. the blower and internal compressors of the turbojet engine, and, secondly, a downstream structure comprising an annular inner ring and an annular outer cover radially spaced from the inner shell, ferrule in te rn esurlaqu al is r pa rtée lal It is necessary to air the air to the blower.
Une telle virole est désignée par la référence générale 10 sur la figure 3.  Such a ferrule is designated by the general reference 10 in FIG.
Cette virole interne 10 de la structure d'entrée d'air est traitée de façon classique pour former u ne structure 1 1 acoustique d'atténuation de l'onde sonore.  This inner ferrule 10 of the air inlet structure is conventionally treated to form a sound attenuation structure 1 1 of the sound wave.
Elle peut comporter une peau interne perméable à l'air, une peau externe perméable à l'air et une âme alvéolaire en nid d'abeille.  It may include an air permeable inner skin, an outer breathable skin and a honeycomb honeycomb core.
D'autres variantes de réalisation sont envisageables, comme le rem pl acement de l 'â m e alvéol a i re pa r de l a mou sse poreu se ou d es microsphères.  Other alternative embodiments are conceivable, such as the replacment of the alveol to the pores of the pores or microspheres.
La section médiane, quant à elle, comprend d'une part, un carter interne 20 entourant la soufflante du turboréacteur prolongeant la virole interne 10 de la structure d'entrée d'air et, d'autre part, une structure externe de carénage du carter prolongeant le capot externe de la structure d'entrée d'air.  The middle section, meanwhile, comprises on the one hand, an inner casing 20 surrounding the turbojet fan extending the inner shell 10 of the air intake structure and, on the other hand, an outer fairing structure of the casing extending the external hood of the air intake structure.
La virole interne 10 est destinée à être fixée au carter de soufflante 20 dans un plan de jonction désigné par la lettre A, grâce à des brides de raccordement annulaires périphériques 30,40 placées, respectivement, sur l'extrémité aval de la virole interne 10 et sur l'extrémité amont du carter de soufflante 20. Chaque bride de raccordement 30, 40 comprend une première portion de raccordement 31 formant bride et s'étendant suivant une direction radiale et une deuxième portion de raccordement 32 tubulaire de forme sensiblement cylindrique s'étendant selon la direction longitudinale du turboréacteur, de sorte que la section longitudinale de la bride de raccordement est en forme de L. The inner ferrule 10 is intended to be fixed to the fan casing 20 in a joint plane designated by the letter A, thanks to peripheral annular connection flanges 30, 40 placed respectively on the downstream end of the inner ferrule 10. and on the upstream end of the fan casing 20. Each connecting flange 30, 40 comprises a first connecting portion 31 forming a flange and extending in a radial direction and a second substantially cylindrical tubular connecting portion 32 extending in the longitudinal direction of the turbojet, so that the longitudinal section of the connection flange is L-shaped.
Toutefois, d'autres formes de réalisation des brides de raccordement peuvent être proposées.  However, other embodiments of the connection flanges can be proposed.
Chacune des brides de raccordement 30,40 faisant saillie vers l'extérieur à la périphérie de la virole interne 10 de l'entrée d'air et du carter de soufflante 20 sont pressées l'une contre l'autre par des moyens de fixation adaptés, parallèles à l'axe longitudinal du turboréacteur et destinés à traverser des passages en regard dans chacune des brides de raccordement 30,40.  Each of the connecting flanges 30,40 protruding outwardly around the periphery of the inner shroud 10 of the air inlet and the blower housing 20 are pressed against each other by suitable fastening means. , parallel to the longitudinal axis of the turbojet and intended to pass through passages in each of the connecting flanges 30,40.
La bride de raccordement 30 de la virole interne 10 est ainsi reliée par tous moyens connus (non illustrés sur la figure 3), tel que des boulons, à la bride de raccordement 40 du carter 20 au niveau du plan de jonction A.  The connecting flange 30 of the inner ferrule 10 is thus connected by any known means (not shown in FIG. 3), such as bolts, to the connection flange 40 of the casing 20 at the junction plane A.
Par ailleurs, quelque soit le mode de réalisation, les différentes brides de raccordement 30,40 peuvent être associées à des moyens de centrage permettant d'assurer le centrage de la structure d'entrée d'air par rapport au carter de soufflante 20.  Moreover, whatever the embodiment, the various connection flanges 30, 40 may be associated with centering means making it possible to center the air intake structure with respect to the fan casing 20.
Selon le mode de réalisation illustré sur la figure 3, la deuxième portion de raccordement 32 de la bride 30 correspondant à la virole interne 10 de la structure d'entrée d'air est destinée à être fixée sur ladite virole 10.  According to the embodiment illustrated in FIG. 3, the second connecting portion 32 of the flange 30 corresponding to the inner ferrule 10 of the air intake structure is intended to be fixed on said ferrule 10.
Plus précisément, cette deuxième portion de raccordement 32 forme une pièce en matériau composite avec la virole interne 10 de la structure d'entrée d'air.  More specifically, this second connecting portion 32 forms a composite material part with the inner shell 10 of the air intake structure.
Ce mode de réalisation a pour avantage de supprimer toute fixation telle que des boulons ou des vis, qui pourrait altérer la qualité acoustique de la virole interne 10.  This embodiment has the advantage of eliminating any fastening such as bolts or screws, which could alter the acoustic quality of the inner shell 10.
Selon la présente invention, la liaison entre la virole interne 10 et la bride de raccordement 30 correspondante est déportée à une distance de la première portion 31 de la bride 30 correspondant à une grandeur caractéristique d'un moment généré par les flux d'efforts traversant ladite virole interne dans des conditions prédéterminées d'utilisation de la nacelle.  According to the present invention, the connection between the inner ferrule 10 and the corresponding connection flange 30 is offset at a distance from the first portion 31 of the flange 30 corresponding to a characteristic quantity of a moment generated by the fluxes of through-forces said inner ferrule under predetermined conditions of use of the nacelle.
Ces conditions s'entendent comme étant les conditions dans lesquelles le turboréacteur est en fonctionnement et notamment, lorsque l'aéronef est en service lors des phases de décollage, de vol et d'atterrissage mais aussi au sol. These conditions are understood as being the conditions under which the turbojet engine is operating and in particular when the aircraft is in service during take-off, flight and landing but also on the ground.
En effet, la liaison collée entre la bride 30 et le panneau acoustique 1 1 de la virole interne 10 est sollicitée par des efforts dans le plan, à savoir tension, compression et cisaillement dans le plan, qui conduisent à un moment de flexion au n iveau de l a l ia ison précitée générateur de cisaillement interlaminaire.  Indeed, the connection bonded between the flange 30 and the acoustic panel 1 1 of the inner shell 10 is biased by forces in the plane, namely tension, compression and shearing in the plane, which lead to a bending moment in the plane. of the aforementioned ison generator of interlaminar shear.
Plus précisément, en référence à la figure 5, la liaison collée entre la bride 30 et le panneau acoustique de la virole interne 10 est sollicitée par des flux d'efforts dans la virole 10, à savoir tension et compression axiale désignée par t, tension et compression circonférentielle désignée par f et cisaillement plan désignée par Ti2 et les deux flèches associées, cisaillement dans la paroi de la virole 10. More specifically, with reference to FIG. 5, the connection bonded between the flange 30 and the acoustic panel of the inner shell 10 is biased by force flows in the shell 10, namely axial tension and compression denoted by t, tension and circumferential compression denoted by f and shear plane designated by Ti 2 and the two associated arrows, shear in the wall of ferrule 10.
La tension et la compression axiale conduisent à un moment de flexion au n iveau de l a l ia ison précitée g én érateu r d e cisa i l l ement interlaminaire, à l'interface entre la bride 30 et la virole 10.  The tension and the axial compression lead to a bending moment at the level of the aforesaid interlaminar-shedding ionic bond at the interface between the flange 30 and the ferrule 10.
La liaison entre la bride de raccordement 30 et la virole interne 10 de la structure d'entrée d'air est réalisée sensiblement à la long ueu r d'amortissement I de ce moment.  The connection between the connecting flange 30 and the inner shroud 10 of the air intake structure is made substantially along the length of damping I at this time.
Une telle longueur d'amortissement est définie par la formule (1 ) suivante : Such a damping length is defined by the following formula (1):
dans laquelle : in which :
R est le rayon de la virole,  R is the radius of the ferrule,
e est l'épaisseur de la virole,  e is the thickness of the ferrule,
v = le coefficient de poisson du matériau formant la virole au niveau de la première portion de la bride.  v = the fish coefficient of the material forming the ferrule at the first portion of the flange.
Dans un exemple non limitatif de la présente invention pour une structure quasi isotrope c'est à dire pour laquelle le nombre de plis à 45° est égale au nombre de plis à 0°, la longueur d'amortissement peut être définie par la formule (2) approchée suivante :  In a non-limiting example of the present invention for a quasi-isotropic structure, ie for which the number of folds at 45 ° is equal to the number of folds at 0 °, the damping length can be defined by the formula ( 2) next approach:
(2) / = 0.8 x V ? x e Dans un exemple non limitatif de la présente invention, pour un matériel à l'échelle d'un futur monocouloir la longueur d'amortissement I est de l'ordre de 50 mm. (2) / = 0.8 x V? xe In a non-limiting example of the present invention, for a material at the scale of a future single-aisle the damping length I is of the order of 50 mm.
Dans le mode de réalisation de la figure 3, la bride de raccordement 30 est en matériau composite.  In the embodiment of Figure 3, the connecting flange 30 is made of composite material.
Il est à noter que la longueur d'amortissement du moment précité est la longueur à laquelle le moment devient négligeable.  It should be noted that the damping length of the aforementioned moment is the length at which the moment becomes negligible.
Par conséquent, à cette distance particulière, on évite de solliciter la liaison entre la virole interne 10 et la bride de raccordement 30 correspondante en flexion, ce qui permet de diminuer les risques de délaminage, notamment lorsque les pièces sont en matériau composite.  Therefore, at this particular distance, it avoids stressing the connection between the inner ring 10 and the corresponding connection flange 30 bending, which reduces the risk of delamination, especially when the parts are composite material.
En effet, le panneau acoustique de la virole interne 10 à cette distance ne voit pas les efforts de flexion générés au niveau de la bride de raccordement 30.  Indeed, the acoustic panel of the inner shell 10 at this distance does not see the bending forces generated at the connection flange 30.
Une telle liaison permet également d'intégrer la bride de raccordement 30 au panneau acoustique 11 de la virole interne 10 en supprimant les zones de jonction acoustique qui jouent le rôle de pont sonique.  Such a connection also makes it possible to integrate the connection flange 30 with the acoustic panel 11 of the inner ferrule 10 by eliminating the acoustic junction zones which act as a sonic bridge.
On améliore ainsi la qualité acoustique de la virole interne 10.  This improves the acoustic quality of the inner shell 10.
De plus, une telle liaison permet l'utilisation de panneau acoustique 11 comprenant un nid d'abeille de faible densité au droit de la bride de raccordement 30, ce qui offre l'avantage de favoriser la diminution de masse du panneau 11 et d'augmenter la surface acoustique de ce dernier.  In addition, such a connection allows the use of acoustic panel 11 comprising a low density honeycomb in the right of the connection flange 30, which has the advantage of promoting the reduction of mass of the panel 11 and of increase the acoustic surface of the latter.
Toutefois, une variante de réalisation peut proposer une bride de raccordement 30 en matériau métallique dont la liaison avec la virole interne 10 sera réalisée à la longueur d'amortissement précitée.  However, an alternative embodiment may provide a connection flange 30 of metal material whose connection with the inner ferrule 10 will be performed at the aforementioned damping length.
Par ailleurs, en référence aux figures 3 et 4, une plaque de renfort 33 peut être rapportée sur la première portion de raccordement 31 de la bride 30 correspondant à la virole interne 10 et fixée à la bride 30 par des moyens adaptés, si les exigences en terme de résistance structurale de la bride de raccordement 30 l'exigent.  Moreover, with reference to FIGS. 3 and 4, a reinforcing plate 33 can be attached to the first connection portion 31 of the flange 30 corresponding to the inner ferrule 10 and fixed to the flange 30 by suitable means, if the requirements in terms of structural strength of the connection flange 30 require it.
De plus, une variante de réalisation de la présente invention propose d'insérer un coin de transition 34 entre la virole interne 10 et la bride de raccordement 30 au droit de la première portion de raccordement 31 de la bride 30.  In addition, an alternative embodiment of the present invention proposes to insert a transition wedge 34 between the inner ferrule 10 and the connection flange 30 to the right of the first connecting portion 31 of the flange 30.
Ce coin est placé dans la zone de transition entre la viole interne This corner is placed in the transition zone between the internal viol
10 et la deuxième portion de raccordement 32 de la bride 30. Dans un exemple non limitatif de la présente invention, ce coin 34 est un profilé présentant une section de forme générale triangulaire. 10 and the second connecting portion 32 of the flange 30. In a non-limiting example of the present invention, this corner 34 is a profile having a section of generally triangular shape.
Ce profilé est formé de plis de verre ou de carbone, ainsi que d'une résine de remplissage.  This profile is formed of folds of glass or carbon, as well as a filler resin.
Dans une variante de réalisation, ce profilé peut être formé par pultrusion.  In an alternative embodiment, this profile can be formed by pultrusion.
Ce coin de transition 34 offre l'avantage d'améliorer la santé matière dans la zone de transition bride 30 / virole 10 c'est-à-dire qu'il permet d'éviter la déformation des tissus à l'endroit où il est placé.  This transition wedge 34 offers the advantage of improving the material health in the flange 30 / ferrule transition zone 10, that is to say, it makes it possible to avoid the deformation of the tissues at the place where it is square.
En outre, sa présence évite une zone de concentration de contraintes dans la zone de transition précitée.  In addition, its presence avoids a stress concentration zone in the aforementioned transition zone.
Par ailleurs, tel qu'illustré sur la figure 4, lors de la fabrication de la bride de raccordement 30 sur la virole interne 10 de la structure d'entrée d'air, on met en place une contre-forme 35 de forme correspondante à celle de la bride de raccordement 30 associée que l'on souhaite former et symétrique à cette dernière.  Furthermore, as illustrated in FIG. 4, during the manufacture of the connection flange 30 on the inner shroud 10 of the air intake structure, a corresponding counter-form 35 is placed in place. that of the associated connection flange 30 that is desired to form and symmetrical to the latter.
Plus précisément, cette contre-forme 35 est accolée sur une peau arrière 36 de la bride de raccordement 30 qui a été cuite préalablement.  More specifically, this counter-form 35 is contiguous on a rear skin 36 of the connecting flange 30 which has been previously cooked.
Pour cela, on utilise un outillage de positionnement de contre- forme connu de l'homme du métier qui ne sera pas décrit plus en détails par la suite.  For this purpose, a counter positioning tool known to those skilled in the art will be used which will not be described in more detail later.
Tel qu ' il l ustré su r la fig ure 4 , la bride de raccordement 30 comprend également des plis sacrificiels 37, placés en arrière de la peau arrière 36.  As shown in FIG. 4, the connection flange 30 also comprises sacrificial pleats 37 placed behind the rear skin 36.
On vient ensuite draper la bride de raccordement 30 sur l'ensemble contre-forme 35/ peau arrière 36.  Next, the connection flange 30 is draped over the counter-shape assembly 35 / rear skin 36.
Comme il va de soi, l'invention ne se limite pas aux seules formes de réalisation de cette nacelle, décrites ci-dessus à titre d'exemples, mais elle embrasse au contraire toutes les variantes.  As goes without saying, the invention is not limited to the embodiments of this nacelle, described above as examples, but it encompasses all variants.
Ainsi, l'invention s'applique à toute virole d'un ensemble pour système propulsif d'aéronef comprenant une bride de raccordement et, notamment, à une structure de l'inverseur de la nacelle et/ou au carter entourant la soufflante du turboréacteur comprenant une structure d'atténuation acoustique et à la bride de raccordement correspondante.  Thus, the invention applies to any ferrule of an assembly for an aircraft propulsion system comprising a connection flange and, in particular, to a structure of the inverter of the nacelle and / or the casing surrounding the blower of the turbojet engine. comprising an acoustic attenuation structure and the corresponding connection flange.

Claims

REVENDICATIONS
1 . Ensemble pour système propulsif d'aéronef comprenant une première virole (10) destinée à être fixée à une seconde virole (20) et une première bride de raccordement (30) destinée à être solidarisée à une seconde bride de raccordement (40) correspondante solidaire de la seconde virole (20), ladite première bride de raccordement comprenant une portion formant plan (31 ) s'étendant suivant une direction radiale par rapport à la première virole (10) caractérisé en ce que la liaison entre la première virole (10) et la bride de raccordement (30) correspondante est déportée à une distance dudit plan correspondant à une longueur d'amortissement d'un moment de flexion générateur de cisaillement, généré par des flux d'efforts traversant ladite première virole. 1. Assembly for an aircraft propulsion system comprising a first ferrule (10) intended to be fixed to a second ferrule (20) and a first connecting flange (30) intended to be secured to a second connecting flange (40) correspondingly secured to the second ferrule (20), said first connecting flange comprising a plane portion (31) extending in a radial direction relative to the first ferrule (10), characterized in that the connection between the first ferrule (10) and the corresponding connecting flange (30) is offset at a distance from said plane corresponding to a damping length of a shear-generating bending moment generated by force flows passing through said first ferrule.
2. Ensemble selon la revendication 1 caractérisé en ce que la première virole (10) est une virole interne d'une structure d'entrée d'air de la nacelle et/ou d'une structure de l'inverseur de la nacelle et/ou d'un carter de soufflante de turboréacteur. 2. An assembly according to claim 1 characterized in that the first ferrule (10) is an inner shell of an air inlet structure of the nacelle and / or a structure of the inverter of the nacelle and / or a turbojet fan casing.
3. Ensemble selon la revendication 1 caractérisé en ce que la longueur d'amortissement I dud it moment est défin ie sur la formule (1 ) suivante : 3. The assembly of claim 1 characterized in that the damping length I dud it moment is defin ie on the following formula (1):
dans laquelle R et e définissent, respectivement, le rayon et l'épaisseur de la première virole (10) et v, le coefficient de poisson du matériau formant la première virole (10) au droit du plan de bride.  wherein R and e respectively define the radius and thickness of the first ferrule (10) and v, the fish coefficient of the material forming the first ferrule (10) in line with the flange plane.
4. Ensemble selon l'une des revendications 1 à 3 caractérisé en ce que la première virole (10) et la première bride de raccordement (30) correspondante sont réalisées en une pièce unique en matériau composite. 4. Assembly according to one of claims 1 to 3 characterized in that the first ferrule (10) and the corresponding first connecting flange (30) are made of a single piece of composite material.
5. Nacelle selon l'une des revendications 1 à 3 caractérisée en ce que la première bride de raccordement (30) est en matériau métallique. 5. Nacelle according to one of claims 1 to 3 characterized in that the first connecting flange (30) is made of metallic material.
6. Ensemble selon l'une des revendications 1 à 5 caractérisé en ce que la première virole (10) comprend, en outre, un coin de transition (34) destiné à être mis en place au droit du plan de bride entre cette dernière et la première virole (10). 6. An assembly according to one of claims 1 to 5 characterized in that the first ferrule (10) further comprises a transition wedge (34) intended to be placed in line with the flange plane between the latter and the first ferrule (10).
7. Ensemble selon l'une des revendications 1 à 6, caractérisé en ce que la première virole (10) comprend, en outre, une plaque de renfort (33) rapportée sur la première bride de raccordement (30). 7. An assembly according to one of claims 1 to 6, characterized in that the first ferrule (10) further comprises a reinforcing plate (33) attached to the first connecting flange (30).
8. Procédé de fabrication d'un ensemble selon l'une des revendications 1 à 7 comprenant une étape dans laquelle on déporte une liaison entre la première virole (10) et la première bride de raccordement (30) correspondante à une distance dudit plan correspondant à une longueur d'amortissement d'un moment de flexion générateur de cisaillement, généré par des flux d'efforts traversant ladite première virole. 8. A method of manufacturing an assembly according to one of claims 1 to 7 comprising a step in which is deported a connection between the first ferrule (10) and the corresponding first connecting flange (30) at a distance from said corresponding plane at a damping length of a shear generating bending moment, generated by force flows passing through said first shell.
EP11725141A 2010-05-07 2011-05-09 Unit for an aircraft thruster Withdrawn EP2566757A1 (en)

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FR1053578A FR2959726B1 (en) 2010-05-07 2010-05-07 ASSEMBLY FOR PROPULSIVE AIRCRAFT SYSTEM
PCT/FR2011/051042 WO2011138571A1 (en) 2010-05-07 2011-05-09 Unit for an aircraft thruster

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US20130315657A1 (en) 2013-11-28
RU2570181C2 (en) 2015-12-10
FR2959726B1 (en) 2013-05-31
BR112012026825A2 (en) 2016-07-12
WO2011138571A1 (en) 2011-11-10
CA2798005A1 (en) 2011-11-10
US9109509B2 (en) 2015-08-18
FR2959726A1 (en) 2011-11-11

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