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WO2011157962A1 - Airflow-straightening structure for the nacelle of an aircraft engine - Google Patents

Airflow-straightening structure for the nacelle of an aircraft engine Download PDF

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Publication number
WO2011157962A1
WO2011157962A1 PCT/FR2011/051379 FR2011051379W WO2011157962A1 WO 2011157962 A1 WO2011157962 A1 WO 2011157962A1 FR 2011051379 W FR2011051379 W FR 2011051379W WO 2011157962 A1 WO2011157962 A1 WO 2011157962A1
Authority
WO
WIPO (PCT)
Prior art keywords
strapping
hub
nacelle
aircraft engine
vanes
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.)
Ceased
Application number
PCT/FR2011/051379
Other languages
French (fr)
Inventor
Bertrand Desjoyeaux
Nicolas Dezeustre
Wouter Balk
François Gallet
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 Aircraft Engines SAS
Safran Nacelles SAS
Original Assignee
Aircelle SA
SNECMA SAS
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, SNECMA SAS filed Critical Aircelle SA
Priority to CA2802590A priority Critical patent/CA2802590A1/en
Priority to CN2011800290615A priority patent/CN102971217A/en
Priority to RU2013101809/11A priority patent/RU2013101809A/en
Priority to EP11735896.0A priority patent/EP2582580A1/en
Priority to BR112012030323A priority patent/BR112012030323A2/en
Publication of WO2011157962A1 publication Critical patent/WO2011157962A1/en
Priority to US13/718,562 priority patent/US20130108432A1/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • 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
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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 airflow rectifying structure for an aircraft engine.
  • a nacelle of axis A for moteu r (turbofan) with double flow conventionally comprises an external structure 1 comprising an upstream part 3 forming an air inlet, a intermediate portion 5, the inner skin 6 forms a casing for the blower 7 of the engine, and a downstream portion 9 can incorporate thrust reversal means.
  • This nacel carries it by means of an internal structure 11 comprising a fairing 13 of the engine 15.
  • the outer structure 1 defines, with the internal structure 1 1, a vein of a ann ann laire 1 7, often designated by "vein of cold air", as opposed to the hot air generated by the engine 15 .
  • the fan 7 consists essentially of a propeller provided with blades 19, rotatably mounted on a fixed hub 21 connected to the fan casing 6 by a plurality of fixed arms 25, which can be distributed at 120 degrees for example.
  • flow straightening vanes 23 also called OGV ("Outlet Guide Vanes"), for straightening the flow of cold air generated by the fan 7.
  • the present invention aims to simplify this conventional arrangement, in particular to obtain a weight gain.
  • an airflow rectifying structure for an aircraft engine comprising:
  • a strapping within which are arranged a plurality of flow rectification vanes supporting a fan hub, and
  • this structure being remarkable in that at least two of the elements selected from the group comprising said strapping, said plurality of vanes, said hub and said cap, are formed in one piece, that is to say without any assembly operation, and in that at least one of the elements selected from the group comprising said strapping, said plurality of vanes, said hub and said tread is formed at least in part of a composite material.
  • Providing that at least two of the aforementioned elements (strapping, blades, hub, yoke) are manufactured in one piece limits the number of assembly operations to be performed during assembly of the nacelle, and the Providing that at least one of these four elements is formed of composite material makes it possible to obtain a weight gain.
  • said strapping incorporates the casing of said blower; said strapping incorporates an air inlet shell of the nacelle;
  • said strapping incorporates a thrust reverser deflection edge: these different arrangements make it possible to reduce even more the number of parts.
  • the present invention also relates to a nacelle for an aircraft engine, which is remarkable in that it includes a structure for rectifying the air flow in accordance with the foregoing.
  • FIG. 1 is a longitudinal, half-sectional view of a nacelle and engine assembly of the prior art, commented in the preamble of the present description,
  • FIG. 2 is a perspective view of a straightening structure for the air flow according to the invention.
  • FIG. 3 is a detailed sectional view of the upstream portion of an engine with an air flow rectification structure in accordance with a particular embodiment of the present invention, and FIG. part of nacelle associated.
  • identical or similar references designate identical or similar organs or sets of members. Note also that we have taken care to represent in these figures a reference to three axes X, Y, Z, these three axes being respectively representative of the longitudinal, transverse and vertical directions of the engine when it is installed on an aircraft .
  • the airflow rectifying structure according to the invention may comprise a plurality of flow rectifying vanes 23 extending between a wheel radially. inner 27 and a radially outer wheel 29, these vanes and wheels thus forming a flow rectifying grid.
  • the larger diameter wheel 29 is intended to be fixed or integrated inside a band 31 forming part of the inner skin of the intermediate portion 5 of the external structure 1 of the engine.
  • the smaller diameter wheel 27 supports the fixed hub 21 on which the fan 7 is rotatably mounted.
  • a yoke 33 for suspending the nacelle to a support mast sol idaire of the structure of an aircraft: this yoke makes it possible to connect the nacelle and its associated engine 15 to the aircraft.
  • the airflow rectifying vanes 23 and the wheels 27, 29 are formed in one piece.
  • the hub 21 from one side and the assembly formed by the strapping 31 and the yoke 33 on the other hand are also formed in one piece.
  • At least some of its members are formed of composite material, for example by weaving.
  • the assembly of the abovementioned bodies that is, the hub 21, the blades 23, the wheels 27, 29, the strapping 31 and the yoke 33, are formed integrally and in composite material.
  • FIG. 3 shows in detail the upstream part of a nacelle and part of the engine equipped with a structure for rectifying the flow of air on the invention
  • the strapping 31 may incorporate the fan casing 6 and the air intake ferrule 35.
  • the air inlet shell 35 is a substantially cylindrical piece forming the inner skin of the air inlet 3, on which are reported sound absorption panels 37 that can typically have a structure u n id of abeil le, so as to constitute resonators of Helmholtz.
  • Strapping 31 may further incorporate, in its downstream part, an extension 37 forming a deflection edge, that is to say defining one of the walls of the channel for guiding the flow of cold air to the outside of the nacelle during the implementation of the thrust reversal means (not shown).
  • the additional integration of the fan casing 6, the shell 35 and the deflection edge 37 to the flow straightening structure according to the invention makes it possible to gain even more in structural simplicity, as well as in weight when the set of parts is made in one piece and composite material.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Ceramic Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

This airflow-straightening structure for an aircraft engine (15) comprises: a hoop (31) inside which there are arranged a plurality of flow-straightening vanes (23) bearing a hub (21) of a fan (19), and a clevis (33) for connecting to a suspension strut, said clevis being fixed to said hoop (31). This structure is notable for the fact that at least two of the elements chosen from the group consisting of said hoop (31), said plurality of vanes (23), said hub (21) and said clevis (33) are formed in one piece, that is to say without any assembly operation, and for the fact that at least one of the elements chosen from the group consisting of said hoop (31), said plurality of vanes (23), said hub (21) and said clevis (33) is at least partially formed of composite material.

Description

Structure de redressement de flux d'air pour nacelle de moteur d'aéronef  Airflow rectifying structure for aircraft engine nacelle

La présente invention se rapporte à une structure de redressement de flux d'air pour moteur d'aéronef. The present invention relates to an airflow rectifying structure for an aircraft engine.

Comme cela est connu en soi, et représenté à la figure 1 ci-jointe, une nacelle d'axe A pour moteu r (turboréacteur) à double flux comprend classiquement une structure externe 1 comportant une partie amont 3 formant entrée d'air, une partie intermédiaire 5 dont la peau interne 6 forme carter pour la soufflante 7 du moteur, et une partie aval 9 pouvant incorporer des moyens d'inversion de poussée.  As is known per se, and represented in FIG. 1 attached, a nacelle of axis A for moteu r (turbofan) with double flow conventionally comprises an external structure 1 comprising an upstream part 3 forming an air inlet, a intermediate portion 5, the inner skin 6 forms a casing for the blower 7 of the engine, and a downstream portion 9 can incorporate thrust reversal means.

Cette nacel le com porte par a il leu rs u ne structu re interne 1 1 comportant un carénage 13 du moteur 15.  This nacel carries it by means of an internal structure 11 comprising a fairing 13 of the engine 15.

La structure externe 1 définit, avec la structure interne 1 1 , une veine d 'a ir ann u la ire 1 7, souvent désig née par « veine d 'air froid », par opposition à l'air chaud engendré par le moteur 15.  The outer structure 1 defines, with the internal structure 1 1, a vein of a ann ann la laire 1 7, often designated by "vein of cold air", as opposed to the hot air generated by the engine 15 .

La soufflante 7 consiste essentiellement en une hélice munie de pales 19, montée rotative sur un moyeu fixe 21 relié au carter de soufflante 6 par une plural ité de bras fixes 25, pouvant être répartis à 120 degrés par exemple.  The fan 7 consists essentially of a propeller provided with blades 19, rotatably mounted on a fixed hub 21 connected to the fan casing 6 by a plurality of fixed arms 25, which can be distributed at 120 degrees for example.

En amont de ces bras fixes se trouvent des aubes de redressement de fl ux 23, appelées aussi OGV (« Outlet Guide Vanes »), permettant de redresser le flux d'air froid engendré par la soufflante 7.  Upstream of these fixed arms are flow straightening vanes 23, also called OGV ("Outlet Guide Vanes"), for straightening the flow of cold air generated by the fan 7.

La présente invention a pour but de simplifier cet agencement classique, dans le but notamment d'obtenir un gain de poids.  The present invention aims to simplify this conventional arrangement, in particular to obtain a weight gain.

On atteint ce but de l'invention avec une structure de redressement de flux d'air pour moteur d'aéronef, comprenant :  This object of the invention is achieved with an airflow rectifying structure for an aircraft engine, comprising:

- un cerclage à l'intérieur duquel sont disposées une pluralité d'aubes de redressement de flux supportant un moyeu de soufflante, et  a strapping within which are arranged a plurality of flow rectification vanes supporting a fan hub, and

- une chape de l iaison à un mât de suspension, fixée sur ledit cerclage,  - a fork clevis to a suspension pole, fixed on said strapping,

cette structure étant remarquable en ce qu'au moins deux des éléments choisis dans le groupe comprenant ledit cerclage, ladite pluralité d'aubes, ledit moyeu et ladite chape, sont formés d'un seul tenant, c'est- à-dire sans aucune opération d'assemblage, et en ce qu'au moins l 'un des éléments choisis dans le groupe comprenant ledit cerclage, ladite pluralité d'aubes, ledit moyeu et ladite chape est formé au moins en partie en matériau composite. this structure being remarkable in that at least two of the elements selected from the group comprising said strapping, said plurality of vanes, said hub and said cap, are formed in one piece, that is to say without any assembly operation, and in that at least one of the elements selected from the group comprising said strapping, said plurality of vanes, said hub and said tread is formed at least in part of a composite material.

Le fait de prévoir qu'au moins deux des éléments susmentionnés (cerclage, aubes, moyeu, chape) soient fabriqués d'un seul tenant permet de limiter le nombre d'opérations d'assemblage à réaliser lors du montage de la nacelle, et le fait de prévoir que l'un au moins de ces quatre éléments soit formé en matériau composite permet d'obtenir un gain de poids.  Providing that at least two of the aforementioned elements (strapping, blades, hub, yoke) are manufactured in one piece limits the number of assembly operations to be performed during assembly of the nacelle, and the Providing that at least one of these four elements is formed of composite material makes it possible to obtain a weight gain.

Suivant d'autres caractéristiques optionnelles de cette structure selon l'invention :  According to other optional features of this structure according to the invention:

- tous lesdits éléments sont formés d'un seul tenant et en matériau composite : on optimise de la sorte la simplicité de montage et la réduction de poids ;  - All said elements are formed integrally and composite material: in this way optimizes the simplicity of assembly and weight reduction;

- ledit cerclage incorpore le carter de ladite soufflante ; - ledit cerclage incorpore une virole d'entrée d'air de la nacelle ; said strapping incorporates the casing of said blower; said strapping incorporates an air inlet shell of the nacelle;

- ledit cerclage incorpore un bord de déviation d 'inverseur de poussée : ces d ifférentes dispositions permettent de rédu ire encore plus le nombre de pièces. said strapping incorporates a thrust reverser deflection edge: these different arrangements make it possible to reduce even more the number of parts.

La présente invention se rapporte également à une nacelle pour moteur d'aéronef, remarquable en ce q u 'el le com prend u ne structure de redressement du flux d'air conforme à ce qui précède.  The present invention also relates to a nacelle for an aircraft engine, which is remarkable in that it includes a structure for rectifying the air flow in accordance with the foregoing.

D'autres caractéristiques et avantages de la présente invention apparaîtront à la lumière de la description qui va suivre, et à l'examen des figures ci-annexées, dans lesquelles :  Other characteristics and advantages of the present invention will emerge in the light of the description which follows, and on examining the appended figures, in which:

- la figure 1 est une vue en demi-coupe long itud inale d'un ensemble de nacelle et de moteur de l'art antérieur, commenté en préambule de la présente description,  FIG. 1 is a longitudinal, half-sectional view of a nacelle and engine assembly of the prior art, commented in the preamble of the present description,

- l a fig u re 2 est u n e vu e en perspective d ' u n e stru ctu re d e redressement du flux d'air selon l'invention, et  FIG. 2 is a perspective view of a straightening structure for the air flow according to the invention, and

- la figure 3 est une vue de détail en coupe de la partie amont d'un moteur équ ipé d'u ne structure de redressement du flux d'air conforme à un mode de réal isation particul ier de la présente invention, et de la partie de nacelle associée.  FIG. 3 is a detailed sectional view of the upstream portion of an engine with an air flow rectification structure in accordance with a particular embodiment of the present invention, and FIG. part of nacelle associated.

Su r l 'ensemble de ces fig u res, des références identiq ues ou analogues désignent des organes ou ensembles d'organes identiques ou analogues. On notera par ailleurs que l'on a pris soin de représenter sur ces figures un repère à trois axes X, Y, Z, ces trois axes étant représentatifs respectivement des directions longitudinale, transversale et verticale du moteur lorsqu'il est installé sur un aéronef. According to all these figures, identical or similar references designate identical or similar organs or sets of members. Note also that we have taken care to represent in these figures a reference to three axes X, Y, Z, these three axes being respectively representative of the longitudinal, transverse and vertical directions of the engine when it is installed on an aircraft .

On se reporte à présent à la figure 2, sur laquelle on peut voir que la structure de redressement de flux d'air selon l'invention peut comprendre une plural ité d'aubes de redressement de fl ux 23 s'étendant entre une roue radialement intérieure 27 et une roue radialement extérieure 29, ces aubes et ces roues formant ainsi une grille de redressement de flux.  Referring now to FIG. 2, it can be seen that the airflow rectifying structure according to the invention may comprise a plurality of flow rectifying vanes 23 extending between a wheel radially. inner 27 and a radially outer wheel 29, these vanes and wheels thus forming a flow rectifying grid.

La roue de plus grand diamètre 29 est destinée à être fixée ou intégrée à l 'intérieur d'un cerclage 31 faisant partie de la peau interne de la partie intermédiaire 5 de la structure externe 1 du moteur.  The larger diameter wheel 29 is intended to be fixed or integrated inside a band 31 forming part of the inner skin of the intermediate portion 5 of the external structure 1 of the engine.

La roue de plus petit diamètre 27 supporte le moyeu fixe 21 sur lequel est montée rotative la soufflante 7.  The smaller diameter wheel 27 supports the fixed hub 21 on which the fan 7 is rotatably mounted.

Sur la partie supérieure du cerclage 31 est fixée une chape 33 de suspension de la nacelle à un mât de support sol idaire de la structure d'un aéronef : cette chape permet de relier la nacelle et son moteur associé 15 à l'aéronef.  On the upper part of the rim 31 is fixed a yoke 33 for suspending the nacelle to a support mast sol idaire of the structure of an aircraft: this yoke makes it possible to connect the nacelle and its associated engine 15 to the aircraft.

De manière préférée, les aubes de redressement de flux d'air 23 et les roues 27, 29 sont formées d'un seul tenant.  Preferably, the airflow rectifying vanes 23 and the wheels 27, 29 are formed in one piece.

De man ière préférée éga lement, l e moyeu 21 d ' u n e part et l'ensemble formé par le cerclage 31 et la chape 33 d'autre part sont également formés d'un seul tenant.  Also preferably, the hub 21 from one side and the assembly formed by the strapping 31 and the yoke 33 on the other hand are also formed in one piece.

De man ière préférée, certains au moins desd its organes sont formés en matériau composite, par tissage par exemple.  In a preferred manner, at least some of its members are formed of composite material, for example by weaving.

De m a n ière en core pl u s préférée , l 'ensem bl e des orga n es susmentionnés, c'est-à-d ire le moyeu 21 , les aubes 23, les roues 27, 29, le cerclage 31 et la chape 33, sont formés d'un seu l tenant, et en matériau composite.  In a most preferred manner, the assembly of the abovementioned bodies, that is, the hub 21, the blades 23, the wheels 27, 29, the strapping 31 and the yoke 33, are formed integrally and in composite material.

Ceci permet d'obtenir une pièce multifonction de poids global très inférieur à l'ensemble des pièces qu'elle remplace, et ne nécessitant aucune opération d'assemblage.  This makes it possible to obtain a multifunctional part of overall weight that is much lower than all the parts it replaces, and does not require any assembly operation.

Comme on peut le comprendre à la lumière de ce qui précède, le fait que le moyeu 21 de la soufflante 7 soit supporté directement par les aubes de redressement de flux 23, permet de s'affranchir des bras de support de ce moyeu, présents dans les nacelles de la technique antérieure : on gagne de la sorte en simplicité structurelle et en poids. As can be understood in the light of the foregoing, the fact that the hub 21 of the fan 7 is directly supported by the flux-straightening vanes 23 makes it possible to omit the support arms of this fan. hub, present in the nacelles of the prior art: we gain in this way in structural simplicity and weight.

En se reportant à présent à la figure 3, où l'on a représenté de manière détaillée la partie amont d'une nacelle et une partie du moteur équipés d'une structure de redressement du flux d'air sur l'invention, on peut voir que le cerclage 31 peut incorporer le carter de soufflante 6 et la virole d'entrée d'air 35.  Referring now to FIG. 3, which shows in detail the upstream part of a nacelle and part of the engine equipped with a structure for rectifying the flow of air on the invention, it is possible to see that the strapping 31 may incorporate the fan casing 6 and the air intake ferrule 35.

Pour mémoire, la virole d'entrée d'air 35 est une pièce de forme sensiblement cylindrique formant la peau interne de l'entrée d'air 3, sur laquelle sont rapportés des panneaux d'absorption acoustique 37 pouvant typiquement présenter u ne structure en n id d'abeil le, de man ière à constituer des résonateurs de Helmholtz.  For the record, the air inlet shell 35 is a substantially cylindrical piece forming the inner skin of the air inlet 3, on which are reported sound absorption panels 37 that can typically have a structure u n id of abeil le, so as to constitute resonators of Helmholtz.

Le cerclage 31 peut en outre incorporer, dans sa partie aval, une extension 37 formant bord de déviation, c'est-à-dire définissant l'une des parois du canal permettant de guider le flux d'air froid vers l'extérieur de la nacelle lors de la mise en oeuvre des moyens d'inversion de poussée (non représentés).  Strapping 31 may further incorporate, in its downstream part, an extension 37 forming a deflection edge, that is to say defining one of the walls of the channel for guiding the flow of cold air to the outside of the nacelle during the implementation of the thrust reversal means (not shown).

Comme on peut le comprendre, l'intégration supplémentaire du carter de soufflante 6, de la virole 35 et du bord de déviation 37 à la structure de redressement de flux selon l'invention , permet de gagner encore en simplicité structurelle, ainsi qu'en poids lorsque l'ensemble de pièces est réalisé d'un seul tenant et en matériau composite.  As can be understood, the additional integration of the fan casing 6, the shell 35 and the deflection edge 37 to the flow straightening structure according to the invention makes it possible to gain even more in structural simplicity, as well as in weight when the set of parts is made in one piece and composite material.

Bien entendu, la présente invention n'est nullement limitée aux modes de réal isation décrits et représentés, fourn is à titre de simples exemples.  Of course, the present invention is not limited to the embodiments described and shown, provided as simple examples.

Claims

REVENDICATIONS Structure de redressement de flux d'air pour moteur (15) d'aéronef, comprenant : An airflow rectifying structure for an aircraft engine (15), comprising: - un cerclage (31 ) à l'intérieur duquel sont disposées une pluralité d'aubes de redressement de flux (23) supportant un moyeu (21 ) de soufflante (19), et  a strapping (31) inside which are arranged a plurality of flow rectification vanes (23) supporting a fan hub (21), and - une chape (33) de liaison à un mât de suspension, fixée sur ledit cerclage (31 ),  - a yoke (33) for connection to a suspension pylon, fixed on said strapping (31), cette structure étant caractérisée en ce qu'au moins deux des éléments choisis dans le groupe comprenant ledit cerclage (31 ), ladite pluralité d'aubes (23), ledit moyeu (21 ) et ladite chape (33), sont formés d'un seul tenant, c'est-à-dire sans aucune opération d'assemblage,  this structure being characterized in that at least two of the elements selected from the group comprising said strapping (31), said plurality of blades (23), said hub (21) and said yoke (33), are formed of a only holding, that is to say without any assembly operation, et en ce qu'au moins l'un des éléments choisis dans le groupe comprenant ledit cerclage (31 ), ladite pluralité d'aubes (23), ledit moyeu (21 ) et ladite chape (33) est formé au moins en partie en matériau composite.  and in that at least one of the elements selected from the group comprising said strapping (31), said plurality of blades (23), said hub (21) and said yoke (33) are formed at least in part by composite material. Structure selon la revendication 1 , caractérisée en ce que tous lesdits éléments (21 , 23, 31 , 33) sont formés d'un seul tenant et en matériau composite. Structure according to claim 1, characterized in that all said elements (21, 23, 31, 33) are formed integrally and composite material. Structure selon l'une quelconque des revend ications précédentes, caractérisée en ce que ledit cerclage (31 ) incorpore le carter (6) de ladite soufflante (19). Structure according to any one of the preceding claims, characterized in that said strapping (31) incorporates the housing (6) of said fan (19). Structure selon l'une quelconque des revendications précédentes, caractérisée en ce que ledit cerclage (31 ) incorpore une virole d'entrée d'air (35). Structure according to any one of the preceding claims, characterized in that said strapping (31) incorporates an air inlet shell (35). Structure selon l'une quelconque des revendications précédentes, caractérisée en ce que ledit cerclage (31 ) incorpore un bord de déviation (37) d'inverseur de poussée. Structure according to any one of the preceding claims, characterized in that said strapping (31) incorporates a deflection edge (37) of thrust reverser. 6. Nacelle (1 ) pour moteur d'aéronef, caractérisée en ce qu'elle comprend une structure de redressement de flux d'air conforme à l'une quelconque des revendications précédentes. 6. Nacelle (1) for an aircraft engine, characterized in that it comprises an air flow rectification structure according to any one of the preceding claims.
PCT/FR2011/051379 2010-06-18 2011-06-16 Airflow-straightening structure for the nacelle of an aircraft engine Ceased WO2011157962A1 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
CA2802590A CA2802590A1 (en) 2010-06-18 2011-06-16 Airflow-straightening structure for the nacelle of an aircraft engine
CN2011800290615A CN102971217A (en) 2010-06-18 2011-06-16 Airflow-straightening structure for the nacelle of an aircraft engine
RU2013101809/11A RU2013101809A (en) 2010-06-18 2011-06-16 AIR FLOW DIRECTION SYSTEM FOR AIRCRAFT ENGINE GONDOLA
EP11735896.0A EP2582580A1 (en) 2010-06-18 2011-06-16 Airflow-straightening structure for the nacelle of an aircraft engine
BR112012030323A BR112012030323A2 (en) 2010-06-18 2011-06-16 airflow targeting structure for an aircraft engine and aircraft engine nacelle
US13/718,562 US20130108432A1 (en) 2010-06-18 2012-12-18 Airflow-straightening structure for the nacelle of an aircraft engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR10/54852 2010-06-18
FR1054852A FR2961555B1 (en) 2010-06-18 2010-06-18 AIR FLOW RECTIFYING STRUCTURE FOR AN AIRCRAFT ENGINE NACELLE

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US13/718,562 Continuation US20130108432A1 (en) 2010-06-18 2012-12-18 Airflow-straightening structure for the nacelle of an aircraft engine

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EP (1) EP2582580A1 (en)
CN (1) CN102971217A (en)
BR (1) BR112012030323A2 (en)
CA (1) CA2802590A1 (en)
FR (1) FR2961555B1 (en)
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FR2961555B1 (en) 2014-04-18
CN102971217A (en) 2013-03-13
BR112012030323A2 (en) 2016-08-09
RU2013101809A (en) 2014-07-27
CA2802590A1 (en) 2011-12-22
EP2582580A1 (en) 2013-04-24
US20130108432A1 (en) 2013-05-02
FR2961555A1 (en) 2011-12-23

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