CA2802590A1 - 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
CA2802590A1
CA2802590A1 CA2802590A CA2802590A CA2802590A1 CA 2802590 A1 CA2802590 A1 CA 2802590A1 CA 2802590 A CA2802590 A CA 2802590A CA 2802590 A CA2802590 A CA 2802590A CA 2802590 A1 CA2802590 A1 CA 2802590A1
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CA
Canada
Prior art keywords
strapping
hub
nacelle
vanes
aircraft engine
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.)
Abandoned
Application number
CA2802590A
Other languages
French (fr)
Inventor
Bertrand Desjoyeaux
Nicolas Dezeustre
Wouter Balk
Francois 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
Publication of CA2802590A1 publication Critical patent/CA2802590A1/en
Abandoned legal-status Critical Current

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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

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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

Cette structure de redressement de flux d'air pour moteur (15) d'aéronef, comprend; 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 une chape (33) de liaison à un mât de suspension, fixée sur ledit cerclage (31). Cette structure est remarquable 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, 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.This air flow straightening structure for an aircraft engine (15) comprises; a hoop (31) inside which are arranged a plurality of flow straightening vanes (23) supporting a hub (21) of the fan (19), and a yoke (33) for connection to a suspension mast, fixed on said strapping (31). This structure is remarkable in that at least two of the elements chosen from the group comprising said strapping (31), said plurality of vanes (23), said hub (21) and said yoke (33), are formed of a one piece, that is to say without any assembly operation, and in that at least one of the elements chosen from the group comprising said strapping (31), said plurality of blades (23), said hub (21) and said yoke (33) is formed at least in part from a composite material.

Description

WO 2011/15796 WO 2011/15796

2 PCT/FR2011/051379 Structure de redressement de flux d'air pour nacelle de moteur d'aéronef La présente invention se rapporte à une structure de redressement de flux d'air pour moteur d'aéronef.
Comme cela est connu en soi, et représenté à la figure 1 ci-jointe, une nacelle d'axe A pour moteur (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.
Cette nacelle comporte par ailleurs une structure interne 11 comportant un carénage 13 du moteur 15.
La structure externe 1 définit, avec la structure interne 11, une veine d'air annulaire 17, souvent désignée par veine d'air froid , par opposition à l'air chaud engendré par le moteur 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 pluralité de bras fixes 25, pouvant être répartis à 120 degrés par exemple.
En amont de ces bras fixes se trouvent des aubes de redressement de flux 23, appelées aussi OGV ( Outlet Guide Vanes ), permettant de redresser le flux d'air froid engendré par la soufflante 7.
La présente invention a pour but de simplifier cet agencement classique, dans le but notamment d'obtenir un gain de poids.
On atteint ce but de l'invention avec une structure de redressement de flux d'air pour moteur d'aéronef, comprenant :
- un cerclage à l'intérieur duquel sont disposées une pluralité
d'aubes de redressement de flux supportant un moyeu de soufflante, et - une chape de liaison à un mât de suspension, fixée sur ledit cerclage, 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.
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.
Suivant d'autres caractéristiques optionnelles de cette structure selon l'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, - ledit cerclage incorpore le carter de ladite soufflante ;
- ledit cerclage incorpore une virole d'entrée d'air de la nacelle ;
- ledit cerclage incorpore un bord de déviation d'inverseur de poussée : ces différentes dispositions permettent de réduire encore plus le nombre de pièces.
La présente invention se rapporte également à une nacelle pour moteur d'aéronef, remarquable en ce qu'elle comprend une structure de redressement du flux d'air conforme à ce qui précède.
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 :
- la figure 1 est une vue en demi-coupe longitudinale d'un ensemble de nacelle et de moteur de l'art antérieur, commenté en préambule de la présente description, - la figure 2 est une vue en perspective d'une structure de redressement du flux d'air selon l'invention, et - la figure 3 est une vue de détail en coupe de la partie amont d'un moteur équipé d'une structure de redressement du flux d'air conforme à un mode de réalisation particulier de la présente invention, et de la partie de nacelle associée.
Sur l'ensemble de ces figures, des références identiques ou analogues désignent des organes ou ensembles d'organes identiques ou analogues. 2 PCT / FR2011 / 051379 Airflow rectifying structure for aircraft engine nacelle The present invention relates to a straightening structure airflow for an aircraft engine.
As is known per se, and shown in Figure 1 attached, an A-axis nacelle for a turbofan engine (turbojet engine) comprises conventionally an external structure 1 comprising an upstream portion 3 forming air inlet, an intermediate portion 5 whose inner skin 6 form casing for the blower 7 of the engine, and a downstream part 9 which can incorporate means reverse thrust.
This nacelle also has an internal structure 11 having a fairing 13 of the engine 15.
The external structure 1 defines, with the internal structure 11, a annular air vein 17, often referred to as cold air vein, by opposition to 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 by example.
Upstream of these fixed arms are recovery vanes 23, also called OGV (Outlet Guide Vanes), allowing straighten the flow of cold air generated by the fan 7.
The present invention aims to simplify this arrangement classic, especially for the purpose of gaining weight.
This object of the invention is achieved with a straightening structure air flow system for an aircraft engine, comprising:
- a strapping within which are arranged a plurality of flow straightening vanes supporting a hub of blower, and - a clevis for connection to a suspension mast, attached to the said strapping, this structure being remarkable in that at least two of the selected from the group comprising said strapping, said plurality blades, said hub and said clevis are formed integrally, that is, 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 screed is formed at least partly of composite material.
Providing at least two of the foregoing (strapping, blades, hub, clevis) are made in one piece allows to limit the number of assembly operations to be performed when mounting the nacelle, and providing that at least one of these four elements is formed of composite material makes it possible to obtain a weight gain.
According to other optional features of this structure according to the invention:
- all said elements are integrally formed and made of material composite: this optimizes the simplicity of assembly and the reduction of weight, said strapping incorporates the casing of said blower;
said strapping incorporates an air inlet shell of the nacelle;
said strapping incorporates an inverter deflection edge of These different provisions make it possible to reduce the Number of pieces.
The present invention also relates to a nacelle for aircraft engine, remarkable in that it includes a structure of rectification of the airflow in accordance with the above.
Other features and advantages of the present invention will appear in the light of the following description and the examination of figures appended hereto, in which:
FIG. 1 is a longitudinal half-sectional view of a set of nacelle and engine of the prior art, commented in preamble of this description, FIG. 2 is a perspective view of a structure of straightening of the air flow according to the invention, and FIG. 3 is a detail view in section of the upstream portion of a engine equipped with a structure for rectifying the flow of air according to a particular embodiment of this invention, and the associated nacelle part.
On all these figures, identical references or analogues designate organs or groups of identical or like.

3 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.
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 pluralité d'aubes de redressement de flux 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.
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.
La roue de plus petit diamètre 27 supporte le moyeu fixe 21 sur lequel est montée rotative la soufflante 7.
Sur la partie supérieure du cerclage 31 est fixée une chape 33 de suspension de la nacelle à un mât de support solidaire de la structure d'un aéronef: cette chape permet de relier la nacelle et son moteur associé 15 à
l'aéronef.
De manière préférée, les aubes de redressement de flux d'air 23 et les roues 27, 29 sont formées d'un seul tenant.
De manière préférée également, le moyeu 21 d'une part et l'ensemble formé par le cerclage 31 et la chape 33 d'autre part sont également formés d'un seul tenant.
De manière préférée, certains au moins desdits organes sont formés en matériau composite, par tissage par exemple.
De manière encore plus préférée, l'ensemble des organes susmentionnés, c'est-à-dire le moyeu 21, les aubes 23, les roues 27, 29, le cerclage 31 et la chape 33, sont formés d'un seul tenant, et en matériau composite.
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.
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 3 Note also that we took care to represent on these figures a reference to three axes X, Y, Z, these three axes being representative longitudinal, transverse and vertical directions respectively engine when installed on an aircraft.
We now turn to Figure 2, where we can see that the airflow straightening structure according to the invention can comprise a plurality of flow rectification vanes 23 extending between a wheel radially inner 27 and a radially outer wheel 29, these blades and these wheels thus forming a flux recovery grid.
The larger diameter wheel 29 is intended to be fixed or integrated within a strapping 31 forming part of the inner skin of the intermediate part 5 of the external structure 1 of the engine.
The smaller diameter wheel 27 supports the fixed hub 21 on which is rotatably mounted the blower 7.
On the upper part of the strapping 31 is fixed a clevis 33 of suspension of the nacelle to a support mast integral with the structure of a aircraft: this yoke connects the nacelle and its associated engine 15 to the aircraft.
Preferably, the airflow rectifying blades 23 and the wheels 27, 29 are formed in one piece.
Also preferably, the hub 21 on the one hand and the assembly formed by the strapping 31 and the yoke 33 on the other hand are also formed in one piece.
Preferably, at least some of said organs are formed of composite material, for example by weaving.
Even more preferably, all the organs aforementioned, that is to say the hub 21, the blades 23, the wheels 27, 29, the strapping 31 and the yoke 33, are formed in one piece, and in material composite.
This makes it possible to obtain a multifunctional piece of very high overall weight less than all the parts it replaces, and not requiring any assembly operation.
As can be understood from the foregoing, the the hub 21 of the fan 7 is directly supported by the vanes rectifying flow 23, eliminates the support arms of this

4 moyeu, présents dans les nacelles de la technique antérieure : on gagne de la sorte en simplicité structurelle et en poids.
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.
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 une structure en nid d'abeille, de manière à constituer des résonateurs de 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).
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.
Bien entendu, la présente invention n'est nullement limitée aux modes de réalisation décrits et représentés, fournis à titre de simples exemples. 4 hub, present in the nacelles of the prior art: we win the so in structural simplicity and weight.
Referring now to Figure 3, where there is shown detailed way the upstream part of a nacelle and a part of the engine equipped of a straightening structure of the air flow on the invention, we can see that the strapping 31 may incorporate the fan casing 6 and the inlet ferrule air 35.
For the record, the air intake ferrule 35 is a piece of shape substantially cylindrical forming the inner skin of the air inlet 3, on which are reported sound absorption panels 37 that can typically have a honeycomb structure so as to constitute Helmholtz resonators.
The strapping 31 may further incorporate, in its downstream part, a extension 37 forming a deflection edge, that is to say defining one of the walls channel to guide the flow of cold air to the outside of the nacelle during implementation of the thrust reversal means (not shown).
As can be understood, the additional integration of the fan casing 6, ferrule 35 and deflection edge 37 at the structure flux recovery according to the invention, makes it possible to gain even more structural simplicity, as well as in weight when the set of pieces is made in one piece and made of composite material.
Of course, the present invention is not limited to described and illustrated embodiments provided as simple examples.

Claims (6)

1. Structure de redressement de flux d'air pour moteur (15) d'aéronef, comprenant :
- 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 - une chape (33) de liaison à un mât de suspension, fixée sur ledit cerclage (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, 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. 1. Airflow rectifying structure for an aircraft engine (15), comprising:
- a strapping (31) inside which are disposed a plurality of flux rectifying vanes (23) supporting a blower hub (21) (19), and - a clevis (33) connecting to a suspension pole, fixed on said strapping (31), this structure being characterized in that at least two of the selected from the group comprising said strapping (31), said plurality of vanes (23), said hub (21) and said cap (33) 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 (31), said plurality of vanes (23), said hub (21) and said yoke (33) is formed at least partly of material composite. 2. 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. 2. Structure according to claim 1, characterized in that all said elements (21, 23, 31, 33) are integrally formed of material composite. 3. Structure selon l'une quelconque des revendications précédentes, caractérisée en ce que ledit cerclage (31) incorpore le carter (6) de ladite soufflante (19). 3. Structure according to any one of the preceding claims, characterized in that said strapping (31) incorporates the casing (6) of said blower (19). 4. Structure selon l'une quelconque des revendications précédentes, caractérisée en ce que ledit cerclage (31) incorpore une virole d'entrée d'air (35). 4. Structure according to any one of the preceding claims, characterized in that said strapping (31) incorporates an inlet ferrule air (35). 5. 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. 5. Structure according to any one of the preceding claims, characterized in that said strapping (31) incorporates a deflection edge (37) thrust reverser. 6 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 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.
CA2802590A 2010-06-18 2011-06-16 Airflow-straightening structure for the nacelle of an aircraft engine Abandoned CA2802590A1 (en)

Applications Claiming Priority (3)

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
PCT/FR2011/051379 WO2011157962A1 (en) 2010-06-18 2011-06-16 Airflow-straightening structure for the nacelle of an aircraft engine

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CA2802590A1 true CA2802590A1 (en) 2011-12-22

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

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Effective date: 20170616