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RU2013101809A - AIR FLOW DIRECTION SYSTEM FOR AIRCRAFT ENGINE GONDOLA - Google Patents

AIR FLOW DIRECTION SYSTEM FOR AIRCRAFT ENGINE GONDOLA Download PDF

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Publication number
RU2013101809A
RU2013101809A RU2013101809/11A RU2013101809A RU2013101809A RU 2013101809 A RU2013101809 A RU 2013101809A RU 2013101809/11 A RU2013101809/11 A RU 2013101809/11A RU 2013101809 A RU2013101809 A RU 2013101809A RU 2013101809 A RU2013101809 A RU 2013101809A
Authority
RU
Russia
Prior art keywords
rim
air flow
aircraft engine
hub
bracket
Prior art date
Application number
RU2013101809/11A
Other languages
Russian (ru)
Inventor
Бертран ДЕЖУАЙО
Никола ДЕЗЕСТР
Воутер БАЛК
Франсуа ГАЛЛЕ
Original Assignee
Эрсель
Снекма
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 Эрсель, Снекма filed Critical Эрсель
Publication of RU2013101809A publication Critical patent/RU2013101809A/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

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)

Abstract

1. Система спрямления воздушного потока для двигателя (15) летательного аппарата, содержащая:обод (31), в котором предусмотрен ряд лопаток (23) спрямления потока, удерживающих ступицу (21) вентилятора (19),и скобу (33) для соединения со стойкой подвески, прикрепленную к указанному ободу (31),отличающаяся тем, что по меньшей мере два элемента из группы, включающей в себя указанный обод (31), указанный ряд лопаток (23), указанную ступицу (21) и указанную скобу (33), выполнены за одно целое, т.е. без проведения какой-либо операции сборки,при этом по меньшей мере один элемент из группы, включающей в себя указанный обод (31), указанный ряд лопаток (23), указанную ступицу (21) и указанную скобу (33), выполнен по меньшей мере частично из композитного материала.2. Система по п.1, отличающаяся тем, что за одно целое и из композитного материала выполнены все указанные элементы (21, 23, 31, 33).3. Система по п.1 или 2, отличающаяся тем, что указанный обод (31) включает в себя картер (6) указанного вентилятора (19).4. Система по п.1 или 2, отличающаяся тем, что указанный обод (31) включает в себя кожух (35) воздухозаборника.5. Система по п.1 или 2, отличающаяся тем, что указанный обод (31) включает в себя отклоняющую кромку (37) реверсора тяги.6. Гондола (1) для двигателя летательного аппарата, отличающаяся тем, что она снабжена системой спрямления воздушного потока по любому из предыдущих пунктов.1. Air flow straightening system for an aircraft engine (15), comprising: a rim (31), in which a number of flow straightening blades (23) are provided, holding the hub (21) of the fan (19), and a bracket (33) for connection with suspension strut attached to said rim (31), characterized in that at least two elements from the group including said rim (31), said row of blades (23), said hub (21) and said bracket (33) , are made in one piece, i.e. without carrying out any assembly operation, while at least one element from the group including the specified rim (31), the specified row of blades (23), the specified hub (21) and the specified bracket (33) is made at least partially made of composite material 2. The system according to claim 1, characterized in that all of these elements are made in one piece and made of composite material (21, 23, 31, 33). The system according to claim 1 or 2, characterized in that said rim (31) includes a crankcase (6) of said fan (19). The system according to claim 1 or 2, characterized in that said rim (31) includes an air intake casing (35). The system according to claim 1 or 2, characterized in that said rim (31) includes a deflection edge (37) of the thrust reverser. A nacelle (1) for an aircraft engine, characterized in that it is provided with an air flow straightening system according to any of the preceding claims.

Claims (6)

1. Система спрямления воздушного потока для двигателя (15) летательного аппарата, содержащая:1. An air flow straightening system for an aircraft engine (15), comprising: обод (31), в котором предусмотрен ряд лопаток (23) спрямления потока, удерживающих ступицу (21) вентилятора (19),a rim (31) in which a series of flow straightening vanes (23) are provided, holding the hub (21) of the fan (19), и скобу (33) для соединения со стойкой подвески, прикрепленную к указанному ободу (31),and a bracket (33) for connecting to a suspension strut attached to said rim (31), отличающаяся тем, что по меньшей мере два элемента из группы, включающей в себя указанный обод (31), указанный ряд лопаток (23), указанную ступицу (21) и указанную скобу (33), выполнены за одно целое, т.е. без проведения какой-либо операции сборки,characterized in that at least two elements from the group including said rim (31), said row of blades (23), said hub (21) and said bracket (33) are made in one piece, i.e. without any assembly operation при этом по меньшей мере один элемент из группы, включающей в себя указанный обод (31), указанный ряд лопаток (23), указанную ступицу (21) и указанную скобу (33), выполнен по меньшей мере частично из композитного материала.wherein at least one element from the group comprising said rim (31), said row of blades (23), said hub (21) and said bracket (33) is made at least partially of composite material. 2. Система по п.1, отличающаяся тем, что за одно целое и из композитного материала выполнены все указанные элементы (21, 23, 31, 33).2. The system according to claim 1, characterized in that all these elements (21, 23, 31, 33) are made in one piece and from a composite material. 3. Система по п.1 или 2, отличающаяся тем, что указанный обод (31) включает в себя картер (6) указанного вентилятора (19).3. The system according to claim 1 or 2, characterized in that said rim (31) includes a crankcase (6) of said fan (19). 4. Система по п.1 или 2, отличающаяся тем, что указанный обод (31) включает в себя кожух (35) воздухозаборника.4. The system according to claim 1 or 2, characterized in that said rim (31) includes a casing (35) of the air intake. 5. Система по п.1 или 2, отличающаяся тем, что указанный обод (31) включает в себя отклоняющую кромку (37) реверсора тяги.5. The system according to claim 1 or 2, characterized in that said rim (31) includes a deflecting edge (37) of the thrust reverser. 6. Гондола (1) для двигателя летательного аппарата, отличающаяся тем, что она снабжена системой спрямления воздушного потока по любому из предыдущих пунктов. 6. Gondola (1) for an aircraft engine, characterized in that it is equipped with a straightening system for air flow according to any one of the preceding paragraphs.
RU2013101809/11A 2010-06-18 2011-06-16 AIR FLOW DIRECTION SYSTEM FOR AIRCRAFT ENGINE GONDOLA RU2013101809A (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR10/54852 2010-06-18
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
RU2013101809A true RU2013101809A (en) 2014-07-27

Family

ID=43533356

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2013101809/11A RU2013101809A (en) 2010-06-18 2011-06-16 AIR FLOW DIRECTION SYSTEM FOR AIRCRAFT ENGINE GONDOLA

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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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BR112014031197B1 (en) * 2012-06-15 2021-12-28 United Technologies Corporation TURBINE EXHAUST CASING AND GAS TURBINE ENGINE
US20150226125A1 (en) * 2012-09-26 2015-08-13 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

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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
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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
BR112012030323A2 (en) 2016-08-09
EP2582580A1 (en) 2013-04-24
WO2011157962A1 (en) 2011-12-22
CN102971217A (en) 2013-03-13
FR2961555A1 (en) 2011-12-23
FR2961555B1 (en) 2014-04-18
CA2802590A1 (en) 2011-12-22
US20130108432A1 (en) 2013-05-02

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FA92 Acknowledgement of application withdrawn (lack of supplementary materials submitted)

Effective date: 20151012