FR2961555B1 - Structure de redressement de flux d'air pour nacelle de moteur d'aeronef - Google Patents

Structure de redressement de flux d'air pour nacelle de moteur d'aeronef

Info

Publication number
FR2961555B1
FR2961555B1 FR1054852A FR1054852A FR2961555B1 FR 2961555 B1 FR2961555 B1 FR 2961555B1 FR 1054852 A FR1054852 A FR 1054852A FR 1054852 A FR1054852 A FR 1054852A FR 2961555 B1 FR2961555 B1 FR 2961555B1
Authority
FR
France
Prior art keywords
air flow
aircraft engine
engine nacelle
rectifying structure
flow rectifying
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.)
Active
Application number
FR1054852A
Other languages
English (en)
Other versions
FR2961555A1 (fr
Inventor
Bertrand Desjoyeaux
Nicolas Dezeustre
Wouter Balk
Francois Gallet
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 Aircraft Engines SAS
Safran Nacelles SAS
Original Assignee
Aircelle SA
SNECMA SAS
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
Priority to FR1054852A priority Critical patent/FR2961555B1/fr
Application filed by Aircelle SA, SNECMA SAS filed Critical Aircelle SA
Priority to CN2011800290615A priority patent/CN102971217A/zh
Priority to EP11735896.0A priority patent/EP2582580A1/fr
Priority to CA2802590A priority patent/CA2802590A1/fr
Priority to PCT/FR2011/051379 priority patent/WO2011157962A1/fr
Priority to BR112012030323A priority patent/BR112012030323A2/pt
Priority to RU2013101809/11A priority patent/RU2013101809A/ru
Publication of FR2961555A1 publication Critical patent/FR2961555A1/fr
Priority to US13/718,562 priority patent/US20130108432A1/en
Application granted granted Critical
Publication of FR2961555B1 publication Critical patent/FR2961555B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • 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
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • 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
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Ceramic Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
FR1054852A 2010-06-18 2010-06-18 Structure de redressement de flux d'air pour nacelle de moteur d'aeronef Active FR2961555B1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
FR1054852A FR2961555B1 (fr) 2010-06-18 2010-06-18 Structure de redressement de flux d'air pour nacelle de moteur d'aeronef
EP11735896.0A EP2582580A1 (fr) 2010-06-18 2011-06-16 Structure de redressement de flux d'air pour nacelle de moteur d'aeronef
CA2802590A CA2802590A1 (fr) 2010-06-18 2011-06-16 Structure de redressement de flux d'air pour nacelle de moteur d'aeronef
PCT/FR2011/051379 WO2011157962A1 (fr) 2010-06-18 2011-06-16 Structure de redressement de flux d'air pour nacelle de moteur d'aéronef
CN2011800290615A CN102971217A (zh) 2010-06-18 2011-06-16 用于飞行器发动机机舱的气流矫直结构
BR112012030323A BR112012030323A2 (pt) 2010-06-18 2011-06-16 estrutura de direcionamento de fluxo de ar para um motor de avião e nacela para motor de avião
RU2013101809/11A RU2013101809A (ru) 2010-06-18 2011-06-16 Система спрямления воздушного потока для гондолы двигателя летательного аппарата
US13/718,562 US20130108432A1 (en) 2010-06-18 2012-12-18 Airflow-straightening structure for the nacelle of an aircraft engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1054852A FR2961555B1 (fr) 2010-06-18 2010-06-18 Structure de redressement de flux d'air pour nacelle de moteur d'aeronef

Publications (2)

Publication Number Publication Date
FR2961555A1 FR2961555A1 (fr) 2011-12-23
FR2961555B1 true FR2961555B1 (fr) 2014-04-18

Family

ID=43533356

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1054852A Active FR2961555B1 (fr) 2010-06-18 2010-06-18 Structure de redressement de flux d'air pour nacelle de moteur d'aeronef

Country Status (8)

Country Link
US (1) US20130108432A1 (fr)
EP (1) EP2582580A1 (fr)
CN (1) CN102971217A (fr)
BR (1) BR112012030323A2 (fr)
CA (1) CA2802590A1 (fr)
FR (1) FR2961555B1 (fr)
RU (1) RU2013101809A (fr)
WO (1) WO2011157962A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BR122015003107B1 (pt) * 2012-06-15 2023-05-09 Gkn Aerospace Sweden Ab Motor de turbina a gás
EP2900941B1 (fr) * 2012-09-26 2016-12-14 United Technologies Corporation Carter de turbine haute pression et carter intermédiaire de turbine combinés
TWI537477B (zh) 2013-07-25 2016-06-11 華碩電腦股份有限公司 葉輪結構及應用葉輪結構的離心風扇
US9816396B2 (en) * 2014-10-16 2017-11-14 Honeywell International Inc. Integrated outer flowpath ducting and front frame system for use in a turbofan engine and method for making same
US20200347736A1 (en) * 2019-05-03 2020-11-05 United Technologies Corporation Gas turbine engine with fan case having integrated stator vanes

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2857093A (en) * 1954-12-02 1958-10-21 Cincinnati Testing & Res Lab Stator casing and blade assembly
GB2161110B (en) * 1984-07-07 1988-03-23 Rolls Royce An annular bladed member having an integral shroud and a method of manufacture thereof
GB2161109B (en) * 1984-07-07 1988-12-21 Rolls Royce Integral bladed member
US6145300A (en) * 1998-07-09 2000-11-14 Pratt & Whitney Canada Corp. Integrated fan / low pressure compressor rotor for gas turbine engine
US6312215B1 (en) * 2000-02-15 2001-11-06 United Technologies Corporation Turbine engine windmilling brake
JP3831265B2 (ja) * 2002-01-21 2006-10-11 本田技研工業株式会社 静翼構造体の製造方法
US6821087B2 (en) * 2002-01-21 2004-11-23 Honda Giken Kogyo Kabushiki Kaisha Flow-rectifying member and its unit and method for producing flow-rectifying member
US7370467B2 (en) * 2003-07-29 2008-05-13 Pratt & Whitney Canada Corp. Turbofan case and method of making
US6843449B1 (en) * 2004-02-09 2005-01-18 General Electric Company Fail-safe aircraft engine mounting system
US8033092B2 (en) * 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US7690190B2 (en) * 2005-05-11 2010-04-06 The Boeing Company Aircraft systems including cascade thrust reversers
WO2009157817A1 (fr) * 2008-06-26 2009-12-30 Volvo Aero Corporation Ensemble aube, procédé de fabrication associé, et turbomachine équipée de cet ensemble aube

Also Published As

Publication number Publication date
RU2013101809A (ru) 2014-07-27
EP2582580A1 (fr) 2013-04-24
US20130108432A1 (en) 2013-05-02
CA2802590A1 (fr) 2011-12-22
CN102971217A (zh) 2013-03-13
WO2011157962A1 (fr) 2011-12-22
BR112012030323A2 (pt) 2016-08-09
FR2961555A1 (fr) 2011-12-23

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Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 7

PLFP Fee payment

Year of fee payment: 8

CD Change of name or company name

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170717

Owner name: SAFRAN NACELLES, FR

Effective date: 20170717

CD Change of name or company name

Owner name: SAFRAN NACELLES, FR

Effective date: 20180125

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20180125

PLFP Fee payment

Year of fee payment: 9

PLFP Fee payment

Year of fee payment: 11

PLFP Fee payment

Year of fee payment: 12

PLFP Fee payment

Year of fee payment: 13

PLFP Fee payment

Year of fee payment: 14