CN102971217A - 用于飞行器发动机机舱的气流矫直结构 - Google Patents

用于飞行器发动机机舱的气流矫直结构 Download PDF

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CN102971217A
CN102971217A CN2011800290615A CN201180029061A CN102971217A CN 102971217 A CN102971217 A CN 102971217A CN 2011800290615 A CN2011800290615 A CN 2011800290615A CN 201180029061 A CN201180029061 A CN 201180029061A CN 102971217 A CN102971217 A CN 102971217A
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hoop
air
shaped folder
blades
aircraft engine
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贝特朗·德若约
尼古拉斯·德泽斯特雷
奥特·巴尔克
弗朗索瓦·加莱
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Safran Aircraft Engines SAS
Safran Nacelles SAS
Safran Nacelles Ltd
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Hurel Hispano SA
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    • 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

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
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  • Composite Materials (AREA)
  • Ceramic Engineering (AREA)
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Abstract

本发明涉及一种用于飞行器发动机（15）的气流矫直结构，包括：环箍（31），其内部布置有支承风扇（19）轮毂（21）的多个气流矫直叶片（23）；和用于连接到悬挂支柱的U形夹（33）；所述U形夹固定到所述环箍（31）。所述结构的特征在于：选自所述环箍（31）、所述多个叶片（23）、所述轮毂（21）和所述U形夹（33）构成的组中的至少两个元件形成单个部件，即不需要任何组装操作；和选自所述环箍（31）、所述多个叶片（23）、所述轮毂（21）和所述U形夹（33）构成的组中的至少一个元件至少部分地由复合材料形成。

Description

用于飞行器发动机机舱的气流矫直结构
技术领域
本发明涉及一种用于飞行器发动机的气流矫直结构。
背景技术
正如本身已知的，如附图1中所示，用于双流（涡轮喷气）发动机的具有轴线A的机舱传统上包括外部结构1、中间部分5和下游部分9，外部结构1具有形成进气口的上游部分3，中间部分5的内表层6构成发动机的风扇7的壳体，下游部9可包含推力反向装置。
该机舱还包括内部结构11，所述内部结构11具有用于发动机15的整流罩13。
外部结构1与内部结构11一起限定环状的空气管道17，相对于由发动机15产生的热空气，该空气管道17通常被称为“冷空气管道”。
风扇7基本上由设有多个叶片19的推进器组成，所述多个叶片19可转动地安装在固定轮毂21上，例如可以120度的间隔分布，所述固定轮毂21通过多个固定臂25连接到所述风扇壳体6。
这些固定臂的上游是气流矫直叶片23，也被称为OGV（“出口导流叶片”），这使得可以将风扇7产生的冷气流矫直。
发明内容
本发明的目的是简化这种传统的布置，特别旨在减轻重量。
本发明的此目的是利用用于飞行器发动机的气流矫直结构实现，该气流矫直结构包括：
-环箍，其内部布置有支承风扇轮毂的多个气流矫直叶片；和
-U形夹，用于连接到悬挂支柱，所述U形夹固定到所述环箍；
所述结构的特征在于，选自所述环箍、所述多个叶片、所述轮毂和所述U形夹构成的组中的至少两个元件形成单个部件，即不需要任何组装操作；
并且，选自所述环箍、所述多个叶片、所述轮毂和所述U形夹构成的组中的至少一个元件至少部分地由复合材料形成。
将前述元件（环箍、叶片、轮毂和U形夹）中的至少两个元件制成单个部件，使得能够限制在机舱组装过程中待执行的组装操作的次数，并且使这四个元件中的至少一个元件由复合材料制成能够减轻重量。
根据本发明的这种结构的其它可选特征：
-全部的所述元件被制成单个部件且由复合材料制成：以这种方式，组装的容易程度和重量减小方面得到优化；
-所述环箍包含所述风扇的壳体；
-所述环箍包含机舱的进气罩；
-所述环箍包含推力反向器叶栅边缘：这些不同的布置使得可以更进一步减少部件的数量。
本发明还涉及一种用于飞行器发动机的机舱，特征在于，它包括如上所述的气流矫直结构。
附图说明
根据下面的描述并在细阅所附的图后，本发明的其它特征和优点将变得明显，其中：
-图1是在本发明的前文中描述的现有技术的机舱和发动机组件的纵向半剖视图；
-图2是根据本发明的气流矫直结构的立体图，和
-图3是装配有根据本发明的一个具体实施例的气流矫直结构的发动机和相关机舱部分的详细剖视图。
具体实施方式
在所有的这些图中，相同或类似的附图标记表示相同或类似的构件或构件组。
还应当注意的是，在这些图中已经提供了显示X，Y和Z轴的三轴参考系。这三个轴分别代表当发动机被安装在飞行器上时所述发动机的纵向、横向和竖向。
图2示出了根据本发明的气流矫直结构可以包括在径向内轮27和径向外轮29之间延伸的多个气流矫直叶片23，这些叶片和轮子因此形成气流矫直格栅。
较大直径的轮子29设计成固定或包含在作为发动机的外部结构1的中间部分5的内表层的一部分的环箍31的内部。
较小直径的轮子27支承固定轮毂21，在该固定轮毂21上可转动地安装有风扇7。
U形夹33固定在环箍31的上部上，用于从固定到飞行器结构的支柱悬挂机舱：该U形夹使得能够将机舱和其相关联的发动机15连接到飞行器。
优选地，气流矫直叶片23和轮子27，29形成单个部件。
同样优选地，一方面的轮毂21和另一方面的由环箍31和U形夹33所形成的组件也形成单个部件。
优选地，所述构件中的至少一些构件由复合材料例如通过编织制成。
还更优选地，上述构件组，即轮毂21，叶片23，轮子27、29，环箍31和U形夹33形成单个部件并且由复合材料制成。
这使得能够获得总重量远低于其取代的部件组合的多功能单件，并且不需要任何组装操作。
如前述可以理解的，风扇7的轮毂21由气流矫直叶片23直接支承的事实使得能够去除现有技术的机舱中存在的用于该轮毂的支承臂：因此简化了结构、减轻了重量。
图3示出了机舱的上游部分和装配有根据本发明的气流矫直结构的的发动机的部分的详细视图，其示出了环箍31能够包含风扇壳体6和进气罩35。
作为提醒，进气罩35是；形成进气口3的内表层的大致圆柱形部件，其上附接有典型地可具有蜂窝结构的吸音板37，从而形成亥姆霍兹（Helmholtz）共振器。
环箍31也可在其下游部分包含形成叶栅边缘的延伸部37，即限定一个通道壁，使得能够在实施推力反向装置（未示出）期间将冷气流导向机舱的外侧。
可理解的是，在部件组制成单个部件且由复合材料制成时，风扇壳体6、根据本发明的气流矫直结构中的罩35和叶栅边缘37的额外集成还允许增加结构的简化以及重量的减轻。
当然，本发明决不限于所描述和示出的实施例，它们仅作为示例来提供。

Claims (6)

1.一种用于飞行器发动机（15）的气流矫直结构，包括：
-环箍（31），所述环箍（31）的内部布置有支承风扇（19）的轮毂（21）的多个气流矫直叶片（23）；和
-用于连接到悬挂支柱的U形夹（33），所述U形夹固定到所述环箍（31）；
所述结构的特征在于，
选自所述环箍（31）、所述多个叶片（23）、所述轮毂（21）和所述U形夹（33）构成的组中的至少两个元件形成单个部件，即，不需要任何组装操作；和
选自所述环箍（31）、所述多个叶片（23）、所述轮毂（21）和所述U形夹（33）构成的组中的至少一个元件至少部分地由复合材料形成。
2.根据权利要求1所述的结构，其特征在于，所有所述元件（21，23，31，33）制成单个部件且由复合材料制成。
3.根据前述权利要求中任一项所述的结构，其特征在于，所述环箍（31）包含所述风扇（19）的壳体（6）。
4.根据前述权利要求中任一项所述的结构，其特征在于，所述环箍（31）包含进气罩（35）。
5.根据前述权利要求中任一项所述的结构，其特征在于，所述环箍（31）包含推力反向器叶栅边缘（37）。
6.一种用于飞行器发动机的机舱（1），其特征在于，包括根据前述权利要求中任一项所述的气流矫直结构。
CN2011800290615A 2010-06-18 2011-06-16 用于飞行器发动机机舱的气流矫直结构 Pending CN102971217A (zh)

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FR1054852A FR2961555B1 (fr) 2010-06-18 2010-06-18 Structure de redressement de flux d'air pour nacelle de moteur d'aeronef
FR10/54852 2010-06-18
PCT/FR2011/051379 WO2011157962A1 (fr) 2010-06-18 2011-06-16 Structure de redressement de flux d'air pour nacelle de moteur d'aéronef

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Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10036276B2 (en) * 2012-06-15 2018-07-31 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 (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

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2161110A (en) * 1984-07-07 1986-01-08 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
JP2003214180A (ja) * 2002-01-21 2003-07-30 Honda Motor Co Ltd 静翼構造体の製造方法
US20030185673A1 (en) * 2002-01-21 2003-10-02 Honda Giken Kogyo Kabushiki Kaisha Flow-rectifying member and its unit and method for producing flow-rectifying member
US20050022501A1 (en) * 2003-07-29 2005-02-03 Pratt & Whitney Canada Corp. Turbofan case and method of making
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

Family Cites Families (6)

* 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
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
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

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2161110A (en) * 1984-07-07 1986-01-08 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
JP2003214180A (ja) * 2002-01-21 2003-07-30 Honda Motor Co Ltd 静翼構造体の製造方法
US20030185673A1 (en) * 2002-01-21 2003-10-02 Honda Giken Kogyo Kabushiki Kaisha Flow-rectifying member and its unit and method for producing flow-rectifying member
US20050022501A1 (en) * 2003-07-29 2005-02-03 Pratt & Whitney Canada Corp. Turbofan case and method of making
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

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BR112012030323A2 (pt) 2016-08-09
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FR2961555B1 (fr) 2014-04-18
CA2802590A1 (fr) 2011-12-22
RU2013101809A (ru) 2014-07-27
EP2582580A1 (fr) 2013-04-24
FR2961555A1 (fr) 2011-12-23

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