BR112012024948A2 - estrutura unificada da nacela do motor - Google Patents

estrutura unificada da nacela do motor

Info

Publication number
BR112012024948A2
BR112012024948A2 BR112012024948A BR112012024948A BR112012024948A2 BR 112012024948 A2 BR112012024948 A2 BR 112012024948A2 BR 112012024948 A BR112012024948 A BR 112012024948A BR 112012024948 A BR112012024948 A BR 112012024948A BR 112012024948 A2 BR112012024948 A2 BR 112012024948A2
Authority
BR
Brazil
Prior art keywords
nacelle structure
unified motor
motor nacelle
unified
inner liner
Prior art date
Application number
BR112012024948A
Other languages
English (en)
Other versions
BR112012024948B1 (pt
Inventor
David Michael Miller
Patrick J Thrash
Original Assignee
Boeing Co
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 Boeing Co filed Critical Boeing Co
Publication of BR112012024948A2 publication Critical patent/BR112012024948A2/pt
Publication of BR112012024948B1 publication Critical patent/BR112012024948B1/pt

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
    • 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
    • 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
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
    • B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
    • 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
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • 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
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • 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
    • Y10T29/49863—Assembling or joining with prestressing of part
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/13—Hollow or container type article [e.g., tube, vase, etc.]

Landscapes

  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structural Engineering (AREA)
  • Civil Engineering (AREA)
  • Architecture (AREA)
  • Moulding By Coating Moulds (AREA)
  • Wind Motors (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Laminated Bodies (AREA)

Abstract

xestrutura unificada da nacela do motor. a presente invenção refere-se a uma estrutura de cilindro interno para uma nacela do motor. a estrutura de cilindro interno inclui um forro interno, um núcleo de suporte disposto com relação ao forro interno para definir uma pluralidade de cavidades, e uma pluralidade de respectivas divisórias dispostas na cavidade.
BR112012024948-7A 2010-03-31 2011-03-28 Método para a montagem de uma estrutura de cilindro, nacela do motor e aeronave BR112012024948B1 (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US12/752,079 2010-03-31
US12/752,079 US8220588B2 (en) 2010-03-31 2010-03-31 Unitized engine nacelle structure
PCT/US2011/030202 WO2011123392A2 (en) 2010-03-31 2011-03-28 Unitized engine nacelle structure

Publications (2)

Publication Number Publication Date
BR112012024948A2 true BR112012024948A2 (pt) 2016-07-12
BR112012024948B1 BR112012024948B1 (pt) 2020-09-08

Family

ID=44514949

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112012024948-7A BR112012024948B1 (pt) 2010-03-31 2011-03-28 Método para a montagem de uma estrutura de cilindro, nacela do motor e aeronave

Country Status (7)

Country Link
US (1) US8220588B2 (pt)
EP (3) EP3593979B1 (pt)
JP (1) JP5442163B2 (pt)
CN (2) CN105539858B (pt)
BR (1) BR112012024948B1 (pt)
CA (1) CA2794770C (pt)
WO (1) WO2011123392A2 (pt)

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US9370827B2 (en) 2013-08-28 2016-06-21 The Boeing Company System and method for forming perforations in a barrel section
FR3013076B1 (fr) * 2013-11-13 2017-12-08 Ge Energy Products France Snc Structure de protection thermo-acoustique pour machine tournante
US9693166B2 (en) * 2014-06-24 2017-06-27 The Boeing Company Automated production of acoustic structures
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US9771868B2 (en) * 2015-07-21 2017-09-26 The Boeing Company Sound attenuation apparatus and method
US9587563B2 (en) 2015-07-21 2017-03-07 The Boeing Company Sound attenuation apparatus and method
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US10309305B2 (en) 2016-11-18 2019-06-04 Rohr, Inc. Acoustic panel with sidewall stringers
US10316755B2 (en) 2016-11-18 2019-06-11 Rohr, Inc. Acoustic panel with sidewall stringers
US10675768B2 (en) 2018-03-27 2020-06-09 The Boeing Company Robotic end effector assembly, system, and method of using the same
US11052490B2 (en) * 2018-04-27 2021-07-06 The Boeing Company Inner barrel of an engine inlet with laser-machined acoustic perforations
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FR3092871B1 (fr) * 2019-02-15 2022-02-25 Airbus Operations Sas Procede d’assemblage d’une entree d’air d’un turboreacteur d’aeronef
GB2583751B (en) 2019-05-09 2022-02-02 Safran Nacelles Ltd Acoustic panel
US11572850B2 (en) * 2019-06-04 2023-02-07 Rohr, Inc. Acoustic panel with one or more structural stiffeners
FR3097260B1 (fr) * 2019-06-12 2021-06-11 Safran Aircraft Engines Carter de soufflante de turboréacteur
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US20230167774A1 (en) * 2021-12-01 2023-06-01 Rohr, Inc. Attachment ring insulator systems, methods, and assemblies
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CN115783233B (zh) * 2023-02-09 2023-04-21 中国空气动力研究与发展中心计算空气动力研究所 一种基于波纹壁及边界层抽吸的组合式转捩控制装置

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Also Published As

Publication number Publication date
CA2794770A1 (en) 2011-10-06
EP2552781B1 (en) 2016-07-13
WO2011123392A3 (en) 2011-11-24
US8220588B2 (en) 2012-07-17
CN105539858B (zh) 2018-01-02
EP3593979A1 (en) 2020-01-15
CA2794770C (en) 2018-04-10
EP3593979B1 (en) 2021-12-08
US20110244150A1 (en) 2011-10-06
EP3075660A1 (en) 2016-10-05
EP2552781A2 (en) 2013-02-06
CN102834318B (zh) 2016-01-20
CN102834318A (zh) 2012-12-19
JP2013527894A (ja) 2013-07-04
JP5442163B2 (ja) 2014-03-12
EP3075660B1 (en) 2019-08-28
CN105539858A (zh) 2016-05-04
BR112012024948B1 (pt) 2020-09-08
WO2011123392A2 (en) 2011-10-06

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Legal Events

Date Code Title Description
B06F Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]
B06U Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]
B09A Decision: intention to grant [chapter 9.1 patent gazette]
B16A Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 28/03/2011, OBSERVADAS AS CONDICOES LEGAIS.