US20140086678A1 - Assembly for an aircraft nacelle - Google Patents

Assembly for an aircraft nacelle Download PDF

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Publication number
US20140086678A1
US20140086678A1 US14/093,761 US201314093761A US2014086678A1 US 20140086678 A1 US20140086678 A1 US 20140086678A1 US 201314093761 A US201314093761 A US 201314093761A US 2014086678 A1 US2014086678 A1 US 2014086678A1
Authority
US
United States
Prior art keywords
flange
reinforcing plate
beveled
plate
assembly
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
US14/093,761
Other languages
English (en)
Inventor
Xavier Cazuc
Christophe Thorel
John Moutier
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
Assigned to AIRCELLE reassignment AIRCELLE ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: THOREL, CHRISTOPHE, MOUTIER, JOHN, CAZUC, XAVIER
Publication of US20140086678A1 publication Critical patent/US20140086678A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • 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
    • 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
    • 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
    • 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
    • F05D2300/70—Treatment or modification of materials
    • F05D2300/702—Reinforcement
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B2200/00—Constructional details of connections not covered for in other groups of this subclass
    • F16B2200/50—Flanged connections
    • 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

  • FIG. 1 Such a shroud is illustrated in FIG. 1 and designated by reference 10 .
  • This inner shroud 10 of the air inlet structure is traditionally treated to form a sound attenuation structure 11 for the sound wave.
  • the connecting flange 30 comprises a first part 31 extending in a radial direction and a second part 32 extending in the longitudinal direction of the turbojet engine, such that the longitudinal section of the flange 30 is L-shaped.
  • the second connecting part 32 of the flange 30 corresponding to the inner shroud 10 of the air inlet structure is intended to be fixed on said shroud 10 .
  • the flange 30 is generally made by draping pre-impregnated fabrics with autoclave curing, in dry fabrics or with a woven preform with injection of the Resin Transfer Molding type or by infusion.
  • a reinforcing plate 33 may be connected on one and/or the other of the flanges, here the flange 30 corresponding to the inner shroud 10 .
  • This reinforcing plate 33 makes it possible to meet the structural strength requirements of the connecting flange 30 .
  • This bead 320 forms an abrupt local thickness variation, typically 0.5 mm, which causes a variation in the fiber level and the orientation of those fibers of the composite material forming the flange 30 .
  • the stiffness variation between the flange part 30 and the shroud 10 may, in the case of a radial force applied on the flange 30 , create a weak spot at the shroud part at the flange 30 /shroud 10 transition.
  • the present disclosure provides an assembly for an aircraft nacelle, comprising:
  • a bead is prevented from being created on the second part of the flange, and the physical health of the composite is thereby improved.
  • this beveled shape allows a less abrupt stiffness transition between the flange and the shroud on which it rests and improves the mechanical strength of the shroud in the junction area with the flange under radial bias.
  • the assembly according to the present disclosure may comprise one or more of the following features, considered alone or in any technically possible combination:
  • FIG. 1 is a partial cross-sectional view of an assembly of an air inlet structure and fan casing according to the prior art
  • FIG. 2 is a partial cross-sectional view of the assembly of FIG. 1 at the interface between a flange of the assembly and a reinforcing plate of that flange;
  • FIG. 4 is a partial cross-sectional view of a flange according to a second form of the present disclosure, said flange being able to be used in an assembly as shown in FIG. 1 ;
  • FIG. 5 is a partial cross-sectional view of a flange according to a third form of the present disclosure, said flange being able to be used in an assembly as shown in FIG. 1 ;
  • the present disclosure relates to an assembly for an aircraft nacelle comprising:
  • a first form of the present disclosure is described with the help of FIG. 3 .
  • the reinforcing plate 330 comprises a beveled end part 331 , which is in direct contact with the second part 32 of the flange 30 .
  • the reinforcing plate 332 may be manufactured in the same way as the reinforcing plate 330 of the first form and comprise identical components.
  • the intermediate plate 36 typically has a thickness comprised between 0.1 and 3 mm.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Connection Of Plates (AREA)
  • Wind Motors (AREA)
  • Arc Welding In General (AREA)
US14/093,761 2011-05-30 2013-12-02 Assembly for an aircraft nacelle Abandoned US20140086678A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1154685A FR2975970B1 (fr) 2011-05-30 2011-05-30 Ensemble pour une nacelle d'aeronef
FR1154685 2011-05-30
PCT/FR2012/051123 WO2012164197A1 (fr) 2011-05-30 2012-05-21 Ensemble pour une nacelle d'aéronef

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
PCT/FR2012/051123 Continuation WO2012164197A1 (fr) 2011-05-30 2012-05-21 Ensemble pour une nacelle d'aéronef

Publications (1)

Publication Number Publication Date
US20140086678A1 true US20140086678A1 (en) 2014-03-27

Family

ID=46321144

Family Applications (1)

Application Number Title Priority Date Filing Date
US14/093,761 Abandoned US20140086678A1 (en) 2011-05-30 2013-12-02 Assembly for an aircraft nacelle

Country Status (8)

Country Link
US (1) US20140086678A1 (ru)
EP (1) EP2714517B1 (ru)
CN (1) CN103582597A (ru)
BR (1) BR112013027790A2 (ru)
CA (1) CA2837439A1 (ru)
FR (1) FR2975970B1 (ru)
RU (1) RU2013157084A (ru)
WO (1) WO2012164197A1 (ru)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150007905A1 (en) * 2012-03-22 2015-01-08 Aircelle Method for manufacturing a one-piece preform for a composite structure
EP3434597A1 (en) * 2017-07-26 2019-01-30 United Technologies Corporation Nacelle
US10767596B2 (en) 2017-07-26 2020-09-08 Raytheon Technologies Corporation Nacelle

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110821583B (zh) * 2019-12-05 2022-06-17 中国航发四川燃气涡轮研究院 机匣筒体的边缘连接结构和机匣

Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6123170A (en) * 1997-08-19 2000-09-26 Aerospatiale Societe Nationale Industrielle Noise reducing connection assembly for aircraft turbine housings
US6415496B1 (en) * 1998-12-18 2002-07-09 Construcciones Aeronauticas, S.A. Process for making a dismountable and/or fixed traction-compression coupling to be applied to composite materials
US6672833B2 (en) * 2001-12-18 2004-01-06 General Electric Company Gas turbine engine frame flowpath liner support
US20100000227A1 (en) * 2006-07-12 2010-01-07 Airbus France Air intake for an aircraft turbine engine
US7682682B2 (en) * 2004-02-20 2010-03-23 Airbus France Stiffener stop with staggered slopes and panel fitted with such a stop
US7712488B2 (en) * 2008-03-31 2010-05-11 Albany Engineered Composites, Inc. Fiber architecture for Pi-preforms
US7967248B2 (en) * 2007-03-12 2011-06-28 Patria Aerostructures Oy Rib element and composite flange for aircraft
US8079773B2 (en) * 2005-10-18 2011-12-20 General Electric Company Methods and apparatus for assembling composite structures
US8646723B2 (en) * 2008-09-23 2014-02-11 Airbus Operations Sas Device for connecting an air inlet with an aircraft nacelle actuator assembly
EP2703148A1 (en) * 2011-04-26 2014-03-05 IHI Corporation Moulded article
US8851416B2 (en) * 2010-10-15 2014-10-07 Airbus Operations (S.A.S.) Aircraft nacelle including at least one radial partition between two conducts
US9109509B2 (en) * 2010-05-07 2015-08-18 Aircelle Unit for an aircraft thruster
US20160023431A1 (en) * 2014-07-25 2016-01-28 The Boeing Company Fabric jacketed unidirectional noodle
US9315275B2 (en) * 2011-08-05 2016-04-19 Airbus Operations Sas Fastening device particularly suitable for the fastening between an air intake and an engine of an aircraft nacelle

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4509616A (en) * 1983-05-02 1985-04-09 United Technologies Corporation Acoustical liners
FR2898870B1 (fr) * 2006-03-24 2008-05-23 Aircelle Sa Structure de virole d'entree d'air
FR2926789B1 (fr) * 2008-01-29 2010-05-28 Aircelle Sa Nacelle pour turboreacteur

Patent Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6123170A (en) * 1997-08-19 2000-09-26 Aerospatiale Societe Nationale Industrielle Noise reducing connection assembly for aircraft turbine housings
US6415496B1 (en) * 1998-12-18 2002-07-09 Construcciones Aeronauticas, S.A. Process for making a dismountable and/or fixed traction-compression coupling to be applied to composite materials
US6672833B2 (en) * 2001-12-18 2004-01-06 General Electric Company Gas turbine engine frame flowpath liner support
US7682682B2 (en) * 2004-02-20 2010-03-23 Airbus France Stiffener stop with staggered slopes and panel fitted with such a stop
US8079773B2 (en) * 2005-10-18 2011-12-20 General Electric Company Methods and apparatus for assembling composite structures
US20100000227A1 (en) * 2006-07-12 2010-01-07 Airbus France Air intake for an aircraft turbine engine
US7967248B2 (en) * 2007-03-12 2011-06-28 Patria Aerostructures Oy Rib element and composite flange for aircraft
US7712488B2 (en) * 2008-03-31 2010-05-11 Albany Engineered Composites, Inc. Fiber architecture for Pi-preforms
US8646723B2 (en) * 2008-09-23 2014-02-11 Airbus Operations Sas Device for connecting an air inlet with an aircraft nacelle actuator assembly
US9109509B2 (en) * 2010-05-07 2015-08-18 Aircelle Unit for an aircraft thruster
US8851416B2 (en) * 2010-10-15 2014-10-07 Airbus Operations (S.A.S.) Aircraft nacelle including at least one radial partition between two conducts
EP2703148A1 (en) * 2011-04-26 2014-03-05 IHI Corporation Moulded article
US9315275B2 (en) * 2011-08-05 2016-04-19 Airbus Operations Sas Fastening device particularly suitable for the fastening between an air intake and an engine of an aircraft nacelle
US20160023431A1 (en) * 2014-07-25 2016-01-28 The Boeing Company Fabric jacketed unidirectional noodle

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150007905A1 (en) * 2012-03-22 2015-01-08 Aircelle Method for manufacturing a one-piece preform for a composite structure
EP3434597A1 (en) * 2017-07-26 2019-01-30 United Technologies Corporation Nacelle
US10767596B2 (en) 2017-07-26 2020-09-08 Raytheon Technologies Corporation Nacelle
US11046445B2 (en) 2017-07-26 2021-06-29 Raytheon Technologies Corporation Nacelle
US11408369B2 (en) 2017-07-26 2022-08-09 Raytheon Technologies Corporation Nacelle
US11548652B2 (en) 2017-07-26 2023-01-10 Raytheon Technologies Corporation Nacelle

Also Published As

Publication number Publication date
EP2714517B1 (fr) 2017-08-02
BR112013027790A2 (pt) 2017-01-10
FR2975970B1 (fr) 2013-05-17
CN103582597A (zh) 2014-02-12
FR2975970A1 (fr) 2012-12-07
RU2013157084A (ru) 2015-07-10
WO2012164197A1 (fr) 2012-12-06
EP2714517A1 (fr) 2014-04-09
CA2837439A1 (fr) 2012-12-06

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Legal Events

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AS Assignment

Owner name: AIRCELLE, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:CAZUC, XAVIER;THOREL, CHRISTOPHE;MOUTIER, JOHN;SIGNING DATES FROM 20131105 TO 20131107;REEL/FRAME:031898/0641

STCB Information on status: application discontinuation

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