US20130230390A1 - Leading edge structure, in particular for an air inlet of an aircraft engine nacelle - Google Patents

Leading edge structure, in particular for an air inlet of an aircraft engine nacelle Download PDF

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Publication number
US20130230390A1
US20130230390A1 US13/872,325 US201313872325A US2013230390A1 US 20130230390 A1 US20130230390 A1 US 20130230390A1 US 201313872325 A US201313872325 A US 201313872325A US 2013230390 A1 US2013230390 A1 US 2013230390A1
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US
United States
Prior art keywords
leading edge
air inlet
composite structure
structure according
reinforcing fibers
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
US13/872,325
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English (en)
Inventor
Florent Bouillon
Caroline Coat
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 US20130230390A1 publication Critical patent/US20130230390A1/en
Assigned to AIRCELLE reassignment AIRCELLE ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BOUILLON, FLORENT, COAT, CAROLINE
Assigned to AIRCELLE reassignment AIRCELLE ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BOUILLON, FLORENT, COAT, CAROLINE
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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/02—De-icing means for engines having icing phenomena
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/88—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2995/00—Properties of moulding materials, reinforcements, fillers, preformed parts or moulds
    • B29K2995/0012—Properties of moulding materials, reinforcements, fillers, preformed parts or moulds having particular thermal properties
    • B29K2995/0013—Conductive
    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
    • 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
    • Y02T50/40—Weight reduction

Definitions

  • the present disclosure relates to a leading edge structure, in particular for an air inlet of an aircraft engine nacelle.
  • an aircraft engine nacelle forms the fairing of that engine and performs multiple functions: this nacelle in particular has, in its upstream portion, a part commonly called “air inlet,” which has a generally cylindrical shape, and the role of which is in particular to channel the outside air toward the engine.
  • this nacelle portion includes, in its upstream area, a leading edge structure 1 comprising a leading edge 2 strictly speaking, commonly called “air inlet lip,” on the one hand, and a first inner partition 3 defining a compartment 5 in which ice protection means 6 are arranged, i.e., any means making it possible to perform anti-icing and/or deicing of the lip, on the other hand.
  • the air inlet lip 2 is fixed by riveting to the downstream portion 7 of the air inlet, that downstream portion having a protective cowl 9 on its outer surface, and on its inner surface, acoustic absorption means 11 commonly called “acoustic shroud”; this downstream portion 7 of the air inlet defines a kind of box closed by a second partition 13 .
  • all of these pieces are made from metal alloys, typically aluminum-based alloys for the air inlet lip 2 and the protective cowl 9 , and titanium-based alloys for the two partitions 3 and 13 .
  • the cowl 9 can also be made from a composite material.
  • Such a traditional air inlet has a certain number of drawbacks: its weight is relatively high, its construction requires many assembly operations, and the presence of a large number of rivets affects its aerodynamic qualities.
  • the thermal conduction of the composite materials is lower than that of metal materials, and in particular aluminum.
  • Modifying the dimensions of the composite material, and more particularly reducing the thickness of the composite material, does not make it possible to reduce this problem.
  • such a modification also causes a decrease in the strength of the air inlet lip relative to the mechanical stresses, and the static strength and/or impact strength with respect to tools, birds or hail.
  • the present disclosure provides improved composite materials for aircraft leading edge structures, in particular for nacelles, that does not have the drawbacks of the prior art.
  • One aspect of the present disclosure is to propose a composite leading edge structure that offers effective anti-icing or deicing, in particular in the case of electric ice protection means.
  • Another aspect of the present disclosure is to propose a leading edge structure with optimized thermal conduction in the thickness of the structure making it possible to reduce the temperature differences between the inner and outer skins of the leading edge, increase the thermal efficacy of the lip—ice protection means system, and reduce the temperature increase response time.
  • leading edge structure in particular for an aircraft nacelle air inlet, comprising a leading edge and an inner partition defining a longitudinal compartment inside said leading edge accommodating deicing and/or anti-icing means, remarkable in that said leading edge is formed from at least one multiaxial composite structure placed on top of a heating element designed for deicing and/or anti-icing.
  • a multiaxial composite structure refers to a composite comprising fibers in all three spatial directions, having reinforcing fibers passing through its thickness, making it possible to connect the composite layers to each other.
  • transverse reinforcing fibers creates a progressive thermal conductivity in the thickness of the composite structure, making it possible to be able to reach a suitable temperature for effective deicing and/or anti-icing on the outer skin of the leading edge while keeping the resin of the composite structure below its vitreous transition temperature at all points and all times.
  • transverse reinforcing fibers creates an improvement in the time necessary for the structure to reach the required temperatures for proper operation of the anti-icing and/or deicing system.
  • leading edge structure According to other optional features of the leading edge structure according to the present disclosure:
  • the present disclosure also relates to an air inlet comprising a leading edge structure according to the above.
  • the present disclosure also relates to a nacelle for an aircraft engine comprising an air inlet according to the above.
  • FIG. 1 diagrammatically illustrates an air inlet section of a prior art in longitudinal cross-section (see preamble of the present description);
  • FIG. 2 is a transverse cross-sectional view of an air inlet leading edge structure according to one form of the present disclosure
  • FIGS. 3 and 4 are diagrams, in transverse cross-section, of two different embodiments of a structure made from a composite material with a weaving frame of the angle interlock type of the leading edge structure of FIG. 2 ;
  • FIG. 5 is a diagram, in transverse cross-section, of one form of a tufted composite material structure of the leading edge structure of FIG. 2 .
  • a leading edge structure designed in particular to be incorporated into an air inlet of an aircraft engine nacelle traditionally comprises, as previously described in the prior art, a leading edge 2 (visible in FIG. 1 ) and an inner longitudinal partition defining a compartment designed to accommodate, in particular, ice protection means of the deicing and/or anti-icing type.
  • FIG. 2 shows one form of a leading edge 2 or air inlet lip according to the present disclosure.
  • this leading edge 2 may be structural.
  • leading edge 2 has a structural function, in addition to an aerodynamic function.
  • the forces are additionally also reacted by the inner partition 3 , which is sized appropriately.
  • leading edge 2 has a variable thickness along its profile, and in particular, for example, a greater thickness at significant curves and lesser at its ends.
  • leading edge 2 is made up of a stack of particular layers.
  • the leading edge 2 comprises a layer of thermally insulating material 20 on top of which a deicing mat is placed that is formed, in one non-limiting example of the present disclosure, by a core 21 sandwiched between two layers of elastomer material 22 .
  • the core 21 integrated into the air inlet lip 2 is designed as a heating element intended to ensure the electrical conduction to allow deicing of the lip 2 and/or anti-icing protection of the latter part.
  • the insulation-heating mat assembly forms the outer skin of the air inlet lip 2 .
  • the leading edge 2 also comprises a composite structure 23 placed on top of the assembly made up of the heating mat and the insulation 20 .
  • an anti-erosion layer is or is not also provided placed on top of the composite structure 23 .
  • this multiaxial composite structure 23 is a monolithic structure.
  • “Monolithic” means that the different plies (i.e., the layers each comprising fibers embedded in resin) forming the composite material are alongside one another, without any core being inserted between those plies.
  • Another form may provide composite structures 23 of the sandwich type.
  • a sandwich structure is a composite structure made up of two skins that may be multiaxial and that are separated by a core that can, in one non-limiting example, be made using a honeycomb structure.
  • this composite structure 23 is a multiaxial composite structure in the areas sensitive to ice.
  • It may thus be formed by a superposition of one-dimensional (UD) and/or two-dimensional (2D) plies oriented forming a preform, connected to each other by reinforcing fibers passing through them at least in their thickness.
  • UD one-dimensional
  • 2D two-dimensional
  • the plies may be formed, in non-limiting examples, from an epoxy carbon or bismaleimide carbon (BMI) material.
  • BMI bismaleimide carbon
  • a method for manufacturing such a multiaxial monolithic composite may consist of the dry assembly of dry fiber layers forming a preform with reinforcing fibers in the thickness to dope the thermal behavior, using a sewing or needling method.
  • a sewing or needling method One example will be described later relative to FIG. 5 .
  • pre-polymerized or metal composite needles are inserted.
  • composite structures are proposed with reinforcing fibers in the thickness to dope the thermal behavior that are obtained by weaving, braiding or knitting, as illustrated in reference to FIGS. 3 and 4 .
  • leading edge structure 2 it is also possible to provide a second multiaxial composite structure, that structure being inserted between the deicing mat and the layer of thermally insulating material 20 .
  • FIGS. 3 and 4 Two forms of a multiaxial composite structure are illustrated in FIGS. 3 and 4 . These two forms are not limiting.
  • a composite structure 23 is shown with a weaving frame of the angle interlock type, and more particularly, of the three-dimensional angle interlock type.
  • This frame is woven by three types of fibers, i.e., fibers 231 in the warp direction, fibers 232 in the weft direction, and reinforcing fibers 233 passing through the thickness of the structure 23 .
  • the first series 231 of fibers interlaced two by two extends toward the normal to the plane of the structure 23 and the second series 232 of fibers extends in the plane of the structure 23 .
  • This structure 23 being multiaxial, it also comprises the reinforcing fibers 233 that crimp through all of the stacking layers of the fibers in the weft direction.
  • the orientation of the reinforcing fibers 233 is inclined relative to the normal to the plane of the structure 23 .
  • the incline angle is 30° and 60°.
  • FIG. 4 a composite structure 23 with a weaving frame of the angle interlock type, and more particularly the orthogonal interlock type, is shown.
  • This frame is woven by at least three types of fibers, including two types of fibers 234 , 235 oriented in the weft and warp direction of the weaving, i.e., the plane of the structure 23 and arranged in a stack or interlacing, and fibers oriented vertically to reinforce the direction in the thickness of the structure 23 passing through the other two types of fibers 234 , 235 to form a Cartesian reference.
  • Reinforcing fibers 236 are also added. They are arranged substantially parallel to the normal to the plane of the structure 23 to intercept the so-called Cartesian fibers.
  • FIG. 5 Another form of a multiaxial composite structure 23 is proposed in FIG. 5 .
  • a multiaxial composite structure 23 is made using a sewing method by tufting, in which the reinforcing fibers 237 have been tufted in the thickness of said structure 23 .
  • thermally conducting and can be made from carbon, copper or aluminum, these materials being cited as examples.
  • the thermal conduction characteristics of the reinforcing fibers 233 , 236 of the monolithic composite structure are used, combined with those of the heating core 231 , so as to meet deicing requirements, in particular electric, and/or anti-icing requirements, and reduce the temperature difference between the inner and outer skins of the lip.
  • the reinforcing fibers 233 , 236 pass through the thickness of the composite structure 23 and form a grid of elements having an electrical conductivity that will participate in conducting heat between the inner skin and the outer skin of the lip 2 .
  • the thermal properties of the leading edge structure 2 are significantly reinforced by the physical properties of the reinforcing fibers 233 , 236 in the thickness of the composite structure 23 .
  • the necessary temperature to perform deicing and/or anti-icing is obtained without locally exceeding the vitreous transition temperature of the composite structure 23 , while remaining compatible with the thicknesses necessary for the structural issue of an air inlet lip 2 .
  • a leading edge structure 2 according to the disclosure is thus capable of withstanding high thermal stresses as well as high mechanical stresses.
  • the density of the reinforcing fibers 233 , 236 varies depending on the heat needs.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Composite Materials (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Textile Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Laminated Bodies (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Moulding By Coating Moulds (AREA)
  • Woven Fabrics (AREA)
  • Resistance Heating (AREA)
US13/872,325 2010-10-29 2013-04-29 Leading edge structure, in particular for an air inlet of an aircraft engine nacelle Abandoned US20130230390A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR10/58931 2010-10-29
FR1058931A FR2966801B1 (fr) 2010-10-29 2010-10-29 Structure de bord d'attaque notamment pour entree d'air de nacelle de moteur d'aeronef
PCT/FR2011/052475 WO2012056155A2 (fr) 2010-10-29 2011-10-24 Structure de bord d'attaque notamment pour entrée d'air de nacelle de moteur d'aéronef

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
PCT/FR2011/052475 Continuation WO2012056155A2 (fr) 2010-10-29 2011-10-24 Structure de bord d'attaque notamment pour entrée d'air de nacelle de moteur d'aéronef

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US20130230390A1 true US20130230390A1 (en) 2013-09-05

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US13/872,325 Abandoned US20130230390A1 (en) 2010-10-29 2013-04-29 Leading edge structure, in particular for an air inlet of an aircraft engine nacelle

Country Status (8)

Country Link
US (1) US20130230390A1 (de)
EP (1) EP2632797B1 (de)
CN (1) CN103648909A (de)
BR (1) BR112013009247A2 (de)
CA (1) CA2813925A1 (de)
FR (1) FR2966801B1 (de)
RU (1) RU2577975C2 (de)
WO (1) WO2012056155A2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170127477A1 (en) * 2015-10-30 2017-05-04 Itt Manufacturing Enterprises Llc Metal and composite leading edge assemblies

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20200173363A1 (en) * 2018-12-04 2020-06-04 Rohr, Inc. Nacelle inlet structure

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4877689A (en) * 1988-09-30 1989-10-31 United States Of America As Represented By The Administrator, National Aeronautics And Space Administration High temperature insulation barrier composite
US5115962A (en) * 1988-12-20 1992-05-26 United Technologies Corporation Method of attaching ceramic fiber arrays to metallic substrates
US5654060A (en) * 1995-06-16 1997-08-05 The Boeing Company High temperature insulation system
US20080179448A1 (en) * 2006-02-24 2008-07-31 Rohr, Inc. Acoustic nacelle inlet lip having composite construction and an integral electric ice protection heater disposed therein
WO2010049164A2 (en) * 2008-10-31 2010-05-06 Rockwool International A/S Insulating product
US20100155538A1 (en) * 2008-12-24 2010-06-24 Calder David P Anti-icing system and method for preventing ice accumulation
US20110036950A1 (en) * 2008-04-21 2011-02-17 Aircelle De-icing and/or anti-icing system for the leading edge of an aircraft wing
US20110168843A1 (en) * 2009-12-30 2011-07-14 Mra Systems, Inc. Turbomachine nacelle and anti-icing system and method therefor
US20110167781A1 (en) * 2009-12-30 2011-07-14 Mra Systems, Inc. Turbomachine nacelle and anti-icing system and method therefor

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FR2886674B1 (fr) * 2005-06-07 2007-08-03 Airbus France Sas Systeme pour le degivrage du bord d'attaque d'un capot d'entree d'air pour turbomoteur
DE102006031330B4 (de) * 2005-07-14 2014-03-20 Goodrich Corp. Für Eis empfänglicher Abschnitt eines Flugzeugs, insbesondere Flugtriebwerk- Zelleneinlasslippe, umfassend ein Eisschutzsystem, Flugtriebwerk mit einer solchen Einlasslippe sowie ein Verfahren zum Schutz einer solchen Einlasslippe vor Vereisung
FR2898867B1 (fr) * 2006-03-27 2008-12-19 Airbus France Sas Systeme pour le degivrage d'un capot d'entree d'air pour turbomoteur.
FR2912780B1 (fr) * 2007-02-20 2012-03-02 Airbus France Revetement pour le traitement acoustique incorporant une structure alveolaire avec une forme complexe
DE102008063545C5 (de) * 2008-12-09 2015-04-30 Deutsches Zentrum für Luft- und Raumfahrt e.V. Multiaxialgelege, Verfahren zur Herstellung eines Faserverbundkunststoffs und Faserverbundkunststoff
JP5336225B2 (ja) * 2009-02-21 2013-11-06 東邦テナックス株式会社 多軸ステッチ基材とそれを用いたプリフォーム

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4877689A (en) * 1988-09-30 1989-10-31 United States Of America As Represented By The Administrator, National Aeronautics And Space Administration High temperature insulation barrier composite
US5115962A (en) * 1988-12-20 1992-05-26 United Technologies Corporation Method of attaching ceramic fiber arrays to metallic substrates
US5654060A (en) * 1995-06-16 1997-08-05 The Boeing Company High temperature insulation system
US20080179448A1 (en) * 2006-02-24 2008-07-31 Rohr, Inc. Acoustic nacelle inlet lip having composite construction and an integral electric ice protection heater disposed therein
US20110036950A1 (en) * 2008-04-21 2011-02-17 Aircelle De-icing and/or anti-icing system for the leading edge of an aircraft wing
WO2010049164A2 (en) * 2008-10-31 2010-05-06 Rockwool International A/S Insulating product
US20100155538A1 (en) * 2008-12-24 2010-06-24 Calder David P Anti-icing system and method for preventing ice accumulation
US20110168843A1 (en) * 2009-12-30 2011-07-14 Mra Systems, Inc. Turbomachine nacelle and anti-icing system and method therefor
US20110167781A1 (en) * 2009-12-30 2011-07-14 Mra Systems, Inc. Turbomachine nacelle and anti-icing system and method therefor

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170127477A1 (en) * 2015-10-30 2017-05-04 Itt Manufacturing Enterprises Llc Metal and composite leading edge assemblies
US10321519B2 (en) * 2015-10-30 2019-06-11 Itt Manufacturing Enterprises Llc Metal and composite leading edge assemblies
US11310872B2 (en) 2015-10-30 2022-04-19 Itt Manufacturing Enterprises Llc Metal and composite leading edge assemblies

Also Published As

Publication number Publication date
WO2012056155A3 (fr) 2014-01-09
BR112013009247A2 (pt) 2016-07-26
WO2012056155A2 (fr) 2012-05-03
CA2813925A1 (fr) 2012-05-03
CN103648909A (zh) 2014-03-19
RU2013123486A (ru) 2014-12-10
EP2632797B1 (de) 2016-04-20
EP2632797A2 (de) 2013-09-04
FR2966801B1 (fr) 2012-11-02
FR2966801A1 (fr) 2012-05-04
RU2577975C2 (ru) 2016-03-20

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Owner name: AIRCELLE, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BOUILLON, FLORENT;COAT, CAROLINE;REEL/FRAME:039628/0664

Effective date: 20130408

AS Assignment

Owner name: AIRCELLE, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BOUILLON, FLORENT;COAT, CAROLINE;REEL/FRAME:039775/0181

Effective date: 20130408

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION