BR112012030323A2 - airflow targeting structure for an aircraft engine and aircraft engine nacelle - Google Patents

airflow targeting structure for an aircraft engine and aircraft engine nacelle

Info

Publication number
BR112012030323A2
BR112012030323A2 BR112012030323A BR112012030323A BR112012030323A2 BR 112012030323 A2 BR112012030323 A2 BR 112012030323A2 BR 112012030323 A BR112012030323 A BR 112012030323A BR 112012030323 A BR112012030323 A BR 112012030323A BR 112012030323 A2 BR112012030323 A2 BR 112012030323A2
Authority
BR
Brazil
Prior art keywords
aircraft engine
shackle
rim
airflow
central axis
Prior art date
Application number
BR112012030323A
Other languages
Portuguese (pt)
Inventor
Bertrand Desjoyeaux
François Gallet
Nicolas Dezeustre
Wouter Balk
Original Assignee
Aircelle Sa
Snecma
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, Snecma filed Critical Aircelle Sa
Publication of BR112012030323A2 publication Critical patent/BR112012030323A2/en

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

Abstract

estrutura de direcionamento de fluxo de ar para um motor de avião e nacela para motor de avião. essa estrutura de direcionamento de fluxo de ar para um motor de avião (15) compreende: um aro (31) dentro do qual estão dispostas uma pluralidade de pás de direcionamento de fluxo (23) sustentando um eixo central (21) de um ventilador (19), e uma manilha (33) para conectar a um strut de suspensão, referida manilha sendo fixada ao referido aro (31). essa estrutura é notável pelo fato de que pelo menos dois elementos escolhidos de um grupo constituído pelo referido aro (31), referida pluralidade de pás (23), referido eixo central (21) e referida manilha (31) são formados em uma peça, ou seja, sem qualquer operação de montagem, e pelo fato de que um dos elementos escolhidos do grupo constituído pelo referido aro (31), referida pluralidade de pás (23), referido eixo central (21) e referida manilha (33) é pelo menos parcialmente formato de material composto.airflow targeting structure for an aircraft engine and aircraft engine nacelle. Such an airflow directing structure for an aircraft engine (15) comprises: a rim (31) within which are arranged a plurality of flow directional blades (23) supporting a central axis (21) of a fan ( 19), and a shackle (33) for connecting to a suspension strut, said shackle being fixed to said rim (31). this structure is remarkable in that at least two elements selected from a group consisting of said rim (31), said plurality of blades (23), said central axis (21) and said shackle (31) are formed in one piece, that is, without any assembly operation, and the fact that one of the elements chosen from the group consisting of said rim (31), said plurality of blades (23), said central axis (21) and said shackle (33) is at least least partially composite material format.

BR112012030323A 2010-06-18 2011-06-16 airflow targeting structure for an aircraft engine and aircraft engine nacelle BR112012030323A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1054852A FR2961555B1 (en) 2010-06-18 2010-06-18 AIR FLOW RECTIFYING STRUCTURE FOR AN AIRCRAFT ENGINE NACELLE
PCT/FR2011/051379 WO2011157962A1 (en) 2010-06-18 2011-06-16 Airflow-straightening structure for the nacelle of an aircraft engine

Publications (1)

Publication Number Publication Date
BR112012030323A2 true BR112012030323A2 (en) 2016-08-09

Family

ID=43533356

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112012030323A BR112012030323A2 (en) 2010-06-18 2011-06-16 airflow targeting structure for an aircraft engine and aircraft engine nacelle

Country Status (8)

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

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WO2013188722A1 (en) * 2012-06-15 2013-12-19 United Technologies Corporation High durability turbine exhaust case
EP2900941B1 (en) * 2012-09-26 2016-12-14 United Technologies Corporation Combined high pressure turbine case and turbine intermediate case
TWI537477B (en) * 2013-07-25 2016-06-11 華碩電腦股份有限公司 Fan blade structure and centrifugal blower using the same
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)

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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
GB2161109B (en) * 1984-07-07 1988-12-21 Rolls Royce Integral bladed member
GB2161110B (en) * 1984-07-07 1988-03-23 Rolls Royce An annular bladed member having an integral shroud and a method of manufacture thereof
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
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
JP3831265B2 (en) * 2002-01-21 2006-10-11 本田技研工業株式会社 Method for manufacturing stationary blade structure
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
WO2006059971A2 (en) * 2004-12-01 2006-06-08 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 (en) * 2008-06-26 2009-12-30 Volvo Aero Corporation Vane assembly and method of fabricating, and a turbo-machine with such vane assembly

Also Published As

Publication number Publication date
RU2013101809A (en) 2014-07-27
FR2961555A1 (en) 2011-12-23
FR2961555B1 (en) 2014-04-18
EP2582580A1 (en) 2013-04-24
WO2011157962A1 (en) 2011-12-22
CA2802590A1 (en) 2011-12-22
US20130108432A1 (en) 2013-05-02
CN102971217A (en) 2013-03-13

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Legal Events

Date Code Title Description
B08F Application dismissed because of non-payment of annual fees [chapter 8.6 patent gazette]
B08K Patent lapsed as no evidence of payment of the annual fee has been furnished to inpi [chapter 8.11 patent gazette]