WO2010059301A2 - Conception d'entrée intégrée - Google Patents

Conception d'entrée intégrée Download PDF

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Publication number
WO2010059301A2
WO2010059301A2 PCT/US2009/059996 US2009059996W WO2010059301A2 WO 2010059301 A2 WO2010059301 A2 WO 2010059301A2 US 2009059996 W US2009059996 W US 2009059996W WO 2010059301 A2 WO2010059301 A2 WO 2010059301A2
Authority
WO
WIPO (PCT)
Prior art keywords
outer structure
nacelle assembly
aft section
accordance
flange
Prior art date
Application number
PCT/US2009/059996
Other languages
English (en)
Other versions
WO2010059301A3 (fr
Inventor
Graham Howarth
David P. Calder
Original Assignee
General Electric Company
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 General Electric Company filed Critical General Electric Company
Priority to JP2011537450A priority Critical patent/JP2012509440A/ja
Priority to CA2742834A priority patent/CA2742834C/fr
Priority to EP09741092.2A priority patent/EP2346736B1/fr
Publication of WO2010059301A2 publication Critical patent/WO2010059301A2/fr
Publication of WO2010059301A3 publication Critical patent/WO2010059301A3/fr

Links

Classifications

    • 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
    • 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
    • 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
    • B64D2033/022—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising bird or foreign object protections
    • 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
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This invention relates generally to gas turbine engine nacelle assemblies and, more particularly, to methods and apparatus for an integrated inlet design for a nacelle assembly.
  • Some known nacelle assemblies used with turbine engines include a plurality of components that disrupt aerodynamic flow of the nacelle assembly with a plurality of circumferential and axial gaps and steps defined between the components.
  • at least one known nacelle assembly includes an inlet lip, an inlet outer barrel, and a fan cowl that define an outer flow surface of the nacelle assembly.
  • some known components include a plurality of segments, which define additional gaps and steps on the outer flow surface.
  • at least one known nacelle assembly used in a large high-bypass engine includes an inlet lip defined by a plurality of radial segments.
  • At least some of the components and at least some segments of the components used in the nacelle assembly are coupled in position within the nacelle assembly with a plurality of mechanical fasteners.
  • mechanical fasteners may secure a bulkhead that is positioned internal to the inlet lip.
  • the mechanical fasteners because of their orientation, also disrupt aerodynamic flow of the nacelle assembly.
  • heads of the mechanical fasteners are exposed on the outer surface of the nacelle assembly and are positioned directly in the outer flow path.
  • other gaps and/or steps in the nacelle assembly may inhibit laminar flow over the outer flow surface of the nacelle assembly, and may increase aerodynamic drag. Operating a turbine engine with increased aerodynamic drag may reduce fuel burn efficiency.
  • a method for assembling a nacelle assembly includes providing an outer structure that extends at least between a highlight defined by a forward end of the outer structure and a point defined by a maximum diameter of the nacelle assembly and coupling the outer structure to an inner barrel.
  • an outer structure of a nacelle assembly includes a highlight defined by a forward end of the outer structure and an outer aft section that includes a point defined by a maximum diameter of the nacelle assembly, wherein the nacelle assembly extends at least between the highlight and the point.
  • a nacelle assembly in yet another aspect, includes an inner barrel and an outer structure comprising a highlight and an outer aft section, wherein the highlight is defined by a forward end of the outer structure, wherein the outer aft section includes a point defined by a maximum diameter of the nacelle assembly, wherein the nacelle assembly extends at least between the highlight and the point.
  • Figure 1 is a perspective view of an exemplary aircraft
  • Figure 2 is a cross-sectional view of a portion of an exemplary turbine engine that may be used with the aircraft shown in Figure 1;
  • Figure 3 is a schematic illustration of a nacelle assembly used with the turbine engine shown in Figure 2;
  • Figure 4 is another schematic illustration of the nacelle assembly shown in Figure 3; and [0011] Figure S is a schematic illustration of an outer structure used with the nacelle assembly shown in Figure 3.
  • FIG. 1 is a schematic illustration of an exemplary aircraft ⁇ that includes at least one turbine engine 10 used to provide thrust for aircraft 8.
  • turbine engine 10 is coupled to a wing 11. More specifically, turbine engine 10 is coupled to a wing pylon (not shown) at wing 11. In an alternate embodiment, turbine engine 10 is coupled to a tail 13. More specifically, turbine engine 10 is coupled to a fuselage (not shown) at tail 13.
  • FIG. 2 is a cross-sectional view of a portion of turbine engine 10.
  • turbine engine 10 includes a fan assembly 16 that is rotatably coupled about a longitudinal centerline axis 32.
  • fan assembly 16 is positioned at a forward end 33 of turbine engine 10.
  • fan assembly 16 is positioned at an aft end 35 of turbine engine 10.
  • Fan assembly 16 includes a plurality of rows of fan blades 19 positioned within a nacelle assembly 12.
  • nacelle assembly 12 houses various operating components (not shown) of turbine engine 10.
  • turbine engine 10 also includes a core engine 17 that is positioned downstream from fan assembly 16.
  • Core engine 17 includes a compressor 18, a combustor 20, and a turbine 22 that is coupled to compressor 18 via a core rotor shaft 26.
  • core engine 17 During operation, core engine 17 generates combustion gases that are channeled downstream to a turbine 24 which extracts energy from the gases for powering fan assembly 16 through a shaft 28.
  • FIGs 3 and 4 are schematic illustrations of nacelle assembly 12.
  • nacelle assembly 12 is generally annular and defines an opening 32 sized and configured to channel air through nacelle assembly 12.
  • Nacelle assembly 12 has a diameter 34 at forward end 33 measured with respect to an inner surface 43 that is smaller than a maximum diameter 36 of an outer surface of nacelle assembly 12.
  • Nacelle assembly 12 includes an inner barrel 38 and an outer structure 40.
  • outer structure 40 is fabricated from a continuous fiber reinforced thermoplastic material.
  • outer structure 40 may be fabricated from a continuous fiber reinforced thermoset material.
  • outer structure 40 incorporates an integral surfacing film to facilitate protecting nacelle assembly 12 from lighting strikes.
  • Outer structure 40 includes a highlight 42 that is defined by forward end 33 of outer structure 40, an outer aft section 44 that is defined by highlight 42, and an inner aft section 46 that is defined by highlight 42.
  • Outer aft section 44 includes a point 45 on an outer surface 47 defined by the maximum diameter 36 of nacelle assembly 12.
  • outer structure 40 is coupled to a hoop frame (not shown) at an aft end 35 of outer aft section 44 proximate to a fan cowl 54, such that the hoop frame facilitates coupling outer structure 40 to fan cowl 54.
  • inner aft section 46 includes a first flange 48 that is used to couple outer structure 40 to inner barrel 38.
  • outer structure 40 includes a second flange 50 that is used to couple outer structure 40 to a fan case 53.
  • nacelle assembly 12 includes a plurality of bulkheads 57, 58, and 59 that facilitate structurally supporting nacelle assembly 12.
  • Bulkheads 57, 58, and 59 also facilitate absorbing any aftward forces induced to outer surface 47 of outer structure 40, such as may be created during a bird-strike for example.
  • bulkhead 57 is coupled to outer aft section 44 and inner aft section 46
  • bulkhead 58 is coupled to outer aft section 44 and inner barrel 38
  • bulkhead 59 is coupled to outer aft section 44 and fan case 53.
  • bulkhead 59 is coupled to an aft end 35 of outer aft section 44 such that bulkhead 59 facilitates coupling outer structure 40 to fan cowl 54.
  • Bulkheads 57, 58, and 59 may be coupled through a plurality of coupling processes such as through a mechanical fastening process, a thermoplastic welding process, and an adhesive bonding process.
  • FIG. 5 is a schematic illustration of outer structure 40.
  • outer structure 40 includes at least one stiffener 56 that is oriented either circumferentially and/or longitudinally to facilitate structurally supporting outer aft section 44.
  • stiffener 56 is an independent component that is coupled to inner surface 43 of outer structure 40 via, for example, thermoplastic welding and/or an adhesive bonding.
  • stiffener 56 may be formed integrally with outer structure 40.
  • nacelle assembly 12 includes a structural foam 60 that is oriented and positioned to facilitate absorbing any aftward forces induced to outer surface 47 of outer structure 40, such as may be created during a bird-strike for example.
  • structural foam 60 is coupled downstream 35 from highlight 42, against inner surface 43 of outer structure 40 using at least one of a thermoplastic welding process and an adhesive bonding process.
  • Outer structure 40 defines an aerodynamic surface over outer surface 47 and facilitates maintaining laminar flow over outer surface 47 from highlight 42 to point 45 defined by maximum diameter 36. Outer surface 47 facilitates reducing drag and improving aerodynamics and fuel efficiency.
  • outer structure 40 facilitates reducing assembly time and a number of components of nacelle assembly 12 as compared to known nacelle assemblies, thereby facilitating reducing manufacturing costs and improving manufacturing cycle time.
  • the part count reduction and the use of advanced materials, such as thermoplastic or graphite, facilitate a weight reduction for nacelle assembly 12 as compared to known nacelle assemblies.
  • the methods, apparatus, and systems described herein for an integrated inlet design are not limited to the specific embodiments described herein.
  • the integrated inlet design described herein provides a more aerodynamic design that facilitates reducing drag and increasing fuel efficiency.
  • Practice of the methods, apparatus, or systems described or illustrated herein is not limited to nacelle assemblies. Rather, the methods, apparatus, and systems described or illustrated herein may be utilized independently and separately from other components and/or steps described herein.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Wind Motors (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention est relative à un ensemble de nacelle et à un procédé d'assemblage de celui-ci. L'ensemble de nacelle comprend un cylindre intérieur et une structure extérieure comprenant un point culminant et une section arrière extérieure, dans lequel le point culminant est défini par une extrémité avant de la structure extérieure, dans lequel la section arrière extérieure comprend un point défini par un diamètre maximum de l'ensemble de nacelle, dans lequel l'ensemble de nacelle s'étend au moins entre le point culminant et le point.
PCT/US2009/059996 2008-11-19 2009-10-08 Conception d'entrée intégrée WO2010059301A2 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
JP2011537450A JP2012509440A (ja) 2008-11-19 2009-10-08 一体型吸気口設計
CA2742834A CA2742834C (fr) 2008-11-19 2009-10-08 Conception d'entree integree
EP09741092.2A EP2346736B1 (fr) 2008-11-19 2009-10-08 Conception d'entrée intégrée

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US12/274,038 US8152461B2 (en) 2008-11-19 2008-11-19 Integrated inlet design
US12/274,038 2008-11-19

Publications (2)

Publication Number Publication Date
WO2010059301A2 true WO2010059301A2 (fr) 2010-05-27
WO2010059301A3 WO2010059301A3 (fr) 2010-07-22

Family

ID=42172193

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2009/059996 WO2010059301A2 (fr) 2008-11-19 2009-10-08 Conception d'entrée intégrée

Country Status (5)

Country Link
US (1) US8152461B2 (fr)
EP (1) EP2346736B1 (fr)
JP (1) JP2012509440A (fr)
CA (1) CA2742834C (fr)
WO (1) WO2010059301A2 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014133636A3 (fr) * 2012-12-27 2014-11-20 General Electric Company Structure composite hybride de type fibre continue/fibre coupée/polymère
US9243647B2 (en) 2012-02-20 2016-01-26 Rolls-Royce Plc Aircraft propulsion system nacelle

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8197191B2 (en) * 2009-04-14 2012-06-12 Rohr, Inc. Inlet section of an aircraft engine nacelle
US8382039B2 (en) * 2009-12-30 2013-02-26 MRA Systems Inc. Turbomachine nacelle and anti-icing system and method therefor
US9168716B2 (en) * 2012-09-14 2015-10-27 The Boeing Company Metallic sandwich structure having small bend radius
FR2987601A1 (fr) * 2012-09-20 2013-09-06 Aircelle Sa Nacelle laminaire
ITFI20130100A1 (it) * 2013-05-03 2014-11-04 Nuovo Pignone Srl "composite material inlet plenum and gas turbine engine system comprising said plenum"
US9664113B2 (en) * 2014-03-15 2017-05-30 The Boeing Company One piece inlet lip skin design
US9725190B2 (en) * 2015-02-13 2017-08-08 The Boeing Company Aircraft engine inlet assembly apparatus
US10160552B2 (en) 2016-02-12 2018-12-25 Rohr, Inc. Inlet assembly for a turbofan engine
US11125157B2 (en) * 2017-09-22 2021-09-21 The Boeing Company Advanced inlet design
FR3075761A1 (fr) * 2017-12-21 2019-06-28 Airbus Operations Partie anterieure de nacelle d'un ensemble propulsif comportant un cadre de rigidification incline
US11946413B2 (en) * 2019-07-29 2024-04-02 The Boeing Company Inlet bulkheads for large diameter aircraft engines
FR3099915A1 (fr) * 2019-08-13 2021-02-19 Airbus Operations Partie antérieure de nacelle d’un ensemble propulsif d’aéronef dont la lèvre d’entrée d’air est liée au panneau extérieur par emboitement
EP3945033B1 (fr) * 2020-07-27 2022-09-07 Airbus Operations (S.A.S.) Ensemble propulsif pour aéronef
FR3115223B1 (fr) * 2020-10-21 2023-05-12 Safran Nacelles Fabrication d’une lèvre d’entrée d’air ou d’un secteur annulaire de lèvre d’entrée d’air intégrant des ouvertures à bord rentré
BR102022003769A2 (pt) 2021-05-04 2022-11-16 The Boeing Company Estrutura de entrada de nacele de um conjunto de motor

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6179249B1 (en) * 1996-12-26 2001-01-30 Aerospatiale Societe Nationale Industrielle Turbojet pod with laminar flow
EP1084951A2 (fr) * 1999-09-17 2001-03-21 Rolls-Royce Plc Ensemble nacelle pour turbo-moteur à combustion
EP1845018A2 (fr) * 2006-04-14 2007-10-17 Rohr, Inc. Lèvre d'entrée de nacelle acoustique de construction composite et chauffage électrique intégral pour la protection contre le givre disposé dedans
FR2906568A1 (fr) * 2006-10-02 2008-04-04 Aircelle Sa Structure d'entree d'air deposable pour nacelle de turboreacteur.

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3871844A (en) * 1973-09-28 1975-03-18 Sr Frank F Calvin Screen apparatus for air inlet
US5259724A (en) * 1992-05-01 1993-11-09 General Electric Company Inlet fan blade fragment containment shield
US5931422A (en) * 1997-06-09 1999-08-03 Mcdonnell Douglas Active reinforced elastomer system
US6089505A (en) * 1997-07-22 2000-07-18 Mcdonnell Douglas Corporation Mission adaptive inlet
US7588212B2 (en) * 2003-07-08 2009-09-15 Rohr Inc. Method and apparatus for noise abatement and ice protection of an aircraft engine nacelle inlet lip
JP2007500298A (ja) * 2003-07-29 2007-01-11 プラット　アンド　ホイットニー　カナダ　コーポレイション ターボファンケースと製造方法
US7370467B2 (en) * 2003-07-29 2008-05-13 Pratt & Whitney Canada Corp. Turbofan case and method of making
FR2868123B1 (fr) * 2004-03-29 2006-06-23 Airbus France Sas Structure d'entree d'air pour moteur d'aeronef
US20060032983A1 (en) * 2004-07-19 2006-02-16 Brand Joseph H Foreign object damage tolerant nacelle anti-icing system
US8092169B2 (en) * 2008-09-16 2012-01-10 United Technologies Corporation Integrated inlet fan case

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6179249B1 (en) * 1996-12-26 2001-01-30 Aerospatiale Societe Nationale Industrielle Turbojet pod with laminar flow
EP1084951A2 (fr) * 1999-09-17 2001-03-21 Rolls-Royce Plc Ensemble nacelle pour turbo-moteur à combustion
EP1845018A2 (fr) * 2006-04-14 2007-10-17 Rohr, Inc. Lèvre d'entrée de nacelle acoustique de construction composite et chauffage électrique intégral pour la protection contre le givre disposé dedans
FR2906568A1 (fr) * 2006-10-02 2008-04-04 Aircelle Sa Structure d'entree d'air deposable pour nacelle de turboreacteur.

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9243647B2 (en) 2012-02-20 2016-01-26 Rolls-Royce Plc Aircraft propulsion system nacelle
WO2014133636A3 (fr) * 2012-12-27 2014-11-20 General Electric Company Structure composite hybride de type fibre continue/fibre coupée/polymère

Also Published As

Publication number Publication date
US20100124494A1 (en) 2010-05-20
CA2742834A1 (fr) 2010-05-27
JP2012509440A (ja) 2012-04-19
EP2346736B1 (fr) 2020-11-25
CA2742834C (fr) 2017-03-28
US8152461B2 (en) 2012-04-10
WO2010059301A3 (fr) 2010-07-22
EP2346736A2 (fr) 2011-07-27

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