WO2008085542A3 - Aircraft engine inlet having zone of deformation - Google Patents

Aircraft engine inlet having zone of deformation Download PDF

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Publication number
WO2008085542A3
WO2008085542A3 PCT/US2007/072710 US2007072710W WO2008085542A3 WO 2008085542 A3 WO2008085542 A3 WO 2008085542A3 US 2007072710 W US2007072710 W US 2007072710W WO 2008085542 A3 WO2008085542 A3 WO 2008085542A3
Authority
WO
WIPO (PCT)
Prior art keywords
deformation
zone
rear support
aircraft engine
inner barrel
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/US2007/072710
Other languages
French (fr)
Other versions
WO2008085542A2 (en
Inventor
Jeffrey D Shutrump
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.)
Rohr Inc
Original Assignee
Rohr Inc
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 Rohr Inc filed Critical Rohr Inc
Priority to EP20070872235 priority Critical patent/EP2041399B1/en
Publication of WO2008085542A2 publication Critical patent/WO2008085542A2/en
Publication of WO2008085542A3 publication Critical patent/WO2008085542A3/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • 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
    • 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
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B64D27/402—Arrangements for mounting power plants in aircraft comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant
    • 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
    • B64D29/02—Power-plant nacelles, fairings or cowlings associated with wings
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • 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
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining

Landscapes

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

Abstract

The present invention relates to an inlet assembly for a turbofan engine nacelle and to a method of manufacturing an inlet assembly for an aircraft engine nacelle. An inlet assembly (17) for an aircraft engine nacelle (1) includes an inner barrel (39), an outer barrel (41) radially spaced from the inner barrel, and a rear support (35) for supporting the outer barrel relative to the inner barrel. The rear support (35) includes at least one radially extending stiff ener (63) and at least one energy absorber (67) defining a zone of deformation (71) adjacent the inner barrel (39). The rear support (35) is deformable in the zone of deformation (71) in response to forces applied during a fan blade-out event to prevent fracture of the rear support.
PCT/US2007/072710 2006-07-19 2007-07-03 Aircraft engine inlet having zone of deformation Ceased WO2008085542A2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20070872235 EP2041399B1 (en) 2006-07-19 2007-07-03 Aircraft engine inlet having zone of deformation

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US11/488,980 US7721525B2 (en) 2006-07-19 2006-07-19 Aircraft engine inlet having zone of deformation
US11/488,980 2006-07-19

Publications (2)

Publication Number Publication Date
WO2008085542A2 WO2008085542A2 (en) 2008-07-17
WO2008085542A3 true WO2008085542A3 (en) 2008-10-02

Family

ID=38970117

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2007/072710 Ceased WO2008085542A2 (en) 2006-07-19 2007-07-03 Aircraft engine inlet having zone of deformation

Country Status (3)

Country Link
US (2) US7721525B2 (en)
EP (2) EP2336500B1 (en)
WO (1) WO2008085542A2 (en)

Families Citing this family (29)

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Publication number Priority date Publication date Assignee Title
FR2904604B1 (en) * 2006-08-04 2009-02-27 Airbus France Sas STRUCTURE ELEMENT OF AN AIRCRAFT
FR2920137B1 (en) * 2007-08-20 2009-09-18 Aircelle Sa FIXING A STRUCTURE OF A TURBOJET NACELLE BY A REINFORCED KNIFE / GRIP BRIDGE
FR2936776A1 (en) * 2008-10-08 2010-04-09 Aircelle Sa Air inlet structure for use in jet engine nacelle of airplane, has rear frame connecting external cowl and inner wall, and heat insulation unit arranged on inner wall, where frame and heat insulation unit form rear structural element
US8197191B2 (en) * 2009-04-14 2012-06-12 Rohr, Inc. Inlet section of an aircraft engine nacelle
GB0907580D0 (en) * 2009-05-05 2009-06-10 Rolls Royce Plc A duct wall for a fan or a gas turbine engine
FR2966126B1 (en) * 2010-10-15 2013-06-28 Airbus Operations Sas AIRCRAFT NACELLE INCORPORATING A REAR FRAME INCLINE TOWARDS THE REAR
US9371138B2 (en) * 2012-06-07 2016-06-21 Rohr, Inc. Nacelle
US9567089B2 (en) * 2012-07-24 2017-02-14 Rohr, Inc. Hybrid hinge and latch beam
EP2690273B1 (en) 2012-07-24 2022-03-09 Rohr, Inc. Panel for a nacelle strucure
US9279342B2 (en) 2012-11-21 2016-03-08 General Electric Company Turbine casing with service wedge
FR2998548B1 (en) * 2012-11-23 2015-01-30 Airbus Operations Sas AIRCRAFT NACELLE COMPRISING A REINFORCED CONNECTION BETWEEN AN AIR INLET AND A MOTORIZATION
FR2998547B1 (en) * 2012-11-23 2016-01-29 Airbus Operations Sas AIRCRAFT NACELLE COMPRISING A DEFORMABLE CONNECTION BETWEEN AN AIR INLET AND A MOTORIZATION
US10077671B2 (en) 2013-03-13 2018-09-18 United Technologies Corporation Thermally conformable liner for reducing system level fan blade out loads
US9260281B2 (en) 2013-03-13 2016-02-16 General Electric Company Lift efficiency improvement mechanism for turbine casing service wedge
WO2014197053A2 (en) * 2013-03-13 2014-12-11 United Technologies Corporation Thermally conforming acoustic liner cartridge for a gas turbine engine
FR3016159B1 (en) * 2014-01-03 2016-01-01 Airbus Operations Sas AIRCRAFT TURBO BURNER BOAT COMPRISING AN INCREASED RIGIDITY AIR INTAKE ASSEMBLY
US10180082B2 (en) 2014-06-05 2019-01-15 Rolls-Royce Corporation Fan case
US10370113B2 (en) 2014-07-23 2019-08-06 Shield Aerodynamics Llc Flow drag mitigation device
CN105756723B (en) * 2014-12-15 2017-06-06 中航商用航空发动机有限责任公司 A kind of active device for fusing, method and aero-engine
US20160356180A1 (en) * 2015-06-03 2016-12-08 The Boeing Company Nacelle inlet having an angle or curved aft bulkhead
US10738738B2 (en) 2016-06-17 2020-08-11 Rohr, Inc. Nacelle with bifurcation extension and integral structural reinforcement
CN106640378B (en) * 2016-11-24 2018-06-29 中国航空工业集团公司沈阳飞机设计研究所 A kind of main bearing structure of air intake duct and the main bearing structure deformation control method of air intake duct
FR3079499B1 (en) * 2018-03-28 2020-09-04 Airbus Operations Sas FRONT PART OF NACELLE CONTAINING A RIGIDIFICATION FRAME CONSTITUTES SEVERAL ADJACENT ELEMENTS ASSEMBLED ON A FIRST RING AND A SECOND RING
FR3085182B1 (en) * 2018-08-27 2020-09-11 Safran Nacelles AIR SAMPLING ECOPE FOR AIRCRAFT
FR3095418B1 (en) * 2019-04-26 2021-09-24 Safran Nacelles Nacelle air inlet and nacelle having such an air inlet
FR3095417B1 (en) * 2019-04-26 2021-09-24 Safran Nacelles Nacelle air inlet and nacelle having such an air inlet
US11946413B2 (en) * 2019-07-29 2024-04-02 The Boeing Company Inlet bulkheads for large diameter aircraft engines
FR3115223B1 (en) * 2020-10-21 2023-05-12 Safran Nacelles Manufacture of an air inlet lip or an annular sector of an air inlet lip incorporating openings with a recessed edge
US11668205B2 (en) 2021-02-08 2023-06-06 Honeywell International Inc. Containment systems for engine

Citations (4)

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Publication number Priority date Publication date Assignee Title
GB1427339A (en) * 1972-11-15 1976-03-10 Rolls Royce Gas turbine engine
EP1176089A2 (en) * 2000-07-27 2002-01-30 Construcciones Aeronauticas, S.A. Leading edge of aerodynamic surfaces of aircraft
US20040255572A1 (en) * 2003-06-18 2004-12-23 Airbus France Aircraft engine in which there is a small clearance separating the fan cowls and the thrust inverter cowls
US20050269443A1 (en) * 2004-03-29 2005-12-08 Airbus France Air intake structure for aircraft engine

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US4749150A (en) 1985-12-24 1988-06-07 Rohr Industries, Inc. Turbofan duct with noise suppression and boundary layer control
US4759513A (en) 1986-09-26 1988-07-26 Quiet Nacelle Corporation Noise reduction nacelle
USH648H (en) 1988-08-12 1989-07-04 The United States Of America As Represented By The Secretary Of The Air Force Air passage device
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US5225016A (en) 1991-08-02 1993-07-06 Rohr Industries, Inc. Method of manufacturing an advanced composite duct having integral ribs
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GB2266080A (en) 1992-04-16 1993-10-20 Rolls Royce Plc Mounting arrangement for a gas turbine engine.
DE4340951A1 (en) 1992-12-04 1994-06-09 Grumman Aerospace Corp One-piece engine inlet sound tube
US5350136A (en) 1993-05-14 1994-09-27 United Technologies Corporation Nacelle arrangement
GB9407632D0 (en) 1994-04-18 1994-06-08 Short Brothers Plc An aircraft propulsive power unit
GB9424495D0 (en) 1994-12-05 1995-01-25 Short Brothers Plc Aerodynamic low drag structure
FR2738283B1 (en) * 1995-08-30 1997-09-26 Snecma TURBOMACHINE ARRANGEMENT INCLUDING A VANE GRILLE AND AN INTERMEDIATE HOUSING
FR2756323B1 (en) 1996-11-28 1998-12-31 Hispano Suiza Sa DEVICE FOR CONNECTING A DRIVE INVERTER TO A TURBOMOTOR
FR2787509B1 (en) * 1998-12-21 2001-03-30 Aerospatiale AIR INTAKE STRUCTURE FOR AIRCRAFT ENGINE
US6220546B1 (en) 1999-12-29 2001-04-24 The Boeing Company Aircraft engine and associated aircraft engine cowl
US6340135B1 (en) 2000-05-30 2002-01-22 Rohr, Inc. Translating independently mounted air inlet system for aircraft turbofan jet engine
FR2831922B1 (en) 2001-11-02 2004-04-30 Airbus France AIR INTAKE FOR COMMERCIAL AIRCRAFT REACTION ENGINE NACELLE
US6968675B2 (en) 2002-10-29 2005-11-29 Rohr, Inc. Cascadeless fan thrust reverser with plume control
US6920958B2 (en) * 2003-10-17 2005-07-26 The Boeing Company Annular acoustic panel
FR2868124B1 (en) 2004-03-29 2006-06-23 Airbus France Sas AIR INTAKE STRUCTURE FOR AN AIRCRAFT ENGINE
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Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1427339A (en) * 1972-11-15 1976-03-10 Rolls Royce Gas turbine engine
EP1176089A2 (en) * 2000-07-27 2002-01-30 Construcciones Aeronauticas, S.A. Leading edge of aerodynamic surfaces of aircraft
US20040255572A1 (en) * 2003-06-18 2004-12-23 Airbus France Aircraft engine in which there is a small clearance separating the fan cowls and the thrust inverter cowls
US20050269443A1 (en) * 2004-03-29 2005-12-08 Airbus France Air intake structure for aircraft engine

Also Published As

Publication number Publication date
EP2041399A2 (en) 2009-04-01
EP2336500B1 (en) 2015-09-02
US20080016844A1 (en) 2008-01-24
US7721525B2 (en) 2010-05-25
US20110167606A1 (en) 2011-07-14
EP2041399B1 (en) 2013-08-21
WO2008085542A2 (en) 2008-07-17
EP2336500A2 (en) 2011-06-22
EP2336500A3 (en) 2012-09-05
US8438857B2 (en) 2013-05-14

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