CN100562594C - 叶片前缘的保护件 - Google Patents

叶片前缘的保护件 Download PDF

Info

Publication number
CN100562594C
CN100562594C CNB2006100724954A CN200610072495A CN100562594C CN 100562594 C CN100562594 C CN 100562594C CN B2006100724954 A CNB2006100724954 A CN B2006100724954A CN 200610072495 A CN200610072495 A CN 200610072495A CN 100562594 C CN100562594 C CN 100562594C
Authority
CN
China
Prior art keywords
blade
guard member
aluminium alloy
sic
internal layer
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
CNB2006100724954A
Other languages
English (en)
Other versions
CN1847428A (zh
Inventor
杰魁斯·伯纳德
克劳德·芒斯
伊莎贝勒·帕斯勒比
蒂埃里·托马斯
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
Original Assignee
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
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of CN1847428A publication Critical patent/CN1847428A/zh
Application granted granted Critical
Publication of CN100562594C publication Critical patent/CN100562594C/zh
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
    • 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
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/173—Aluminium alloys, e.g. AlCuMgPb
    • 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
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/226—Carbides
    • F05D2300/2261—Carbides of silicon
    • 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
    • F05D2300/70—Treatment or modification of materials
    • F05D2300/702—Reinforcement
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12458—All metal or with adjacent metals having composition, density, or hardness gradient
    • 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
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12736—Al-base component
    • Y10T428/12764—Next to Al-base component
    • 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
    • Y10T428/30—Self-sustaining carbon mass or layer with impregnant or other layer
    • 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
    • Y10T428/31504—Composite [nonstructural laminate]
    • Y10T428/31678—Of metal

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Laminated Bodies (AREA)

Abstract

一种由至少两层，内层(5)和外层(7)，组成的保护件(3)，其外层(7)由用SiC颗粒增强的铝合金制造，SiC颗粒在所述合金中的含量范围为15%至40%重量百分比，而所述内层(5)由铝合金制造，它可随意用SiC颗粒增强，SiC颗粒在各层中含量从里层向外层逐渐增加。所述零件是用于保护叶片的前缘(1a)，特别是涡轮机的动叶和静叶，直升机相旋翼桨叶或螺旋桨桨叶。

Description

叶片前缘的保护件
技术领域
本发明涉及例如保护涡轮机叶片，螺旋桨桨叶或直升机旋翼桨叶的前缘的保护件。
背景技术
在航空领域，更具体说，在飞机的涡轮喷气发动机领域，减轻涡轮喷气发动机组成部分的重量永远是首先要注意的事。
因此，业已为涡轮喷气发动机的风扇或者定子开发出用有机基体复合材料(如基于氰酸酯、二顺丁烯二酰亚胺、或环氧树脂基的复合材料)制作的叶片，这样，叶片比金属叶片轻。
不过，这样的叶片，其前缘需要用装配到前缘上的保护零件加以保护，以防磨损和可能的冲打。
迄今，已做成的这种保护零件，其材料为TA6V型钛合金。这种办法在技术上是可行的，这是因为该合金的抗磨损和抗冲打性能好。但却发现这样的保护件重量太大了。
发明内容
本发明的目的是要提出一种重量比钛合金制造的现有技术和零件为轻的保护零件，其足够能实现它们的保护功能。
为实现此目的，本发明提出一种保护零件，它是外保护工作面，所述保护件用于保护叶片前缘，所述外工作面是由SiC颗粒增强的铝合金制成，所述合金中所述SiC颗粒含量范围为15％至40％重量百分比，并以15％至30％为最佳；所述保护件包括至少两层，外层(7)和内层(5)，所述外层由所述增强铝合金制作而所述内层由铝合金制作，外层(7)和内层(5)中SiC颗粒的含量从里层到外层逐渐增大。
SiC增强铝合金的密度比常用的钛合金的密度轻40％左右。这样导致重量减轻不少，且在其它事物中能限制作用在带叶片涡轮盘上的离心力而引起的应力。这样有可能使设计的涡轮盘强度不需要太高，因而重量较轻，从而进一步减轻了涡轮喷气发动机的重量。
SiC颗粒的作用是增加铝的强度，SiC含量低于15％时，强度不够。SiC含量高于40％则合金难以成型。SiC含量低于30％最佳，有利于成形。
在本发明一个特定实施例中，本零件包括至少两层，即外层和内层，所述外层用所述的增强铝合金制造，所述内层用铝合金制造，当然也可随意用SiC颗粒增强，这些层中SiC的含量从所述内层到所述外层逐渐增大。因此，机械强度也在零件中由内向外逐渐增大。
所述内层采用少量增强或完全不增强的铝合金，可容易将所述层固定到所述叶片上。当所述叶片用有机基体的复合材料(相反便是金属基体的复合材料)制造时情况尤其如此，因而所述保护零件可用粘合剂将其粘上。实际上为了将本发明保护零件固定，可应用固定TA6V钛合金的保护零件所用的同样的粘合剂和粘合技术。固而不需要特地为本发明零件开发粘合剂。
本发明的保护零件尤其是为密接到复合材料叶片而开发的，具体说是有机基体的复合材料。不过，它也可密接到某些其它型号材料制造的叶片上。
附图说明
以下参看附图，并阅读详细说明就可对本发明及其优点有较好的理解，其中：
图1是具有本发明的保护零件且密贴在其前缘的叶片的横截面的透视图；和
图2是图1叶片的横截面放大详图；
具体实施方式
图1和图2示出涡轮机叶片1的翼型部分，叶片1的前缘1a覆盖着本发明的保护零件3。
保护零件3的截面基本呈U形，使其能横跨叶片1的前缘1a放置。零件3由二层组成，即内层5和外层7。外层7是用SiC颗粒增强的铝合金制作的，而内层5是同样的牌号的铝合金，但未用SiC增强。对航空用途而言，最好选用7000系列的铝合金。
当然，保护零件可以有二层以上，各层中的SiC颗粒含量从里到外逐渐增加。因此，在一个未示的实施例中，保护件有四层C1、C2、C3、C4，内层C1中SiC的含量为零，C2中的含量为10％左右重量百分比，C3为20％左右重量百分比，外层C4为30％左右重量百分比。
为了将保护件各层彼此组合起来，可采用各种各样的技术。
最好应用混合挤压或辊压接合，这两种技术与铝合金配合好，不管它们是否用SiC增强。
混合挤压在于将一条非增强的铝合金用一层SiC增强的铝合金套管包围，并穿过硬模(一种压轧锥轮)。两种材料在它们接合面靠压力及摩擦生成的热，确保这两层材料基本上粘结。这样产生的条材，其芯子是非增强铝合金，而覆盖层是SiC增强的铝合金。由此获得的条材可用冲击法成形。
辊压接合在于将几层铝合金板材用热压或冷压法压紧在一起。为了获得如图1所示的具有两层5和7的保护件3，将SiC增强的铝合金板压紧在非增强铝合金板上。通常，应用两个圆筒形滚柱，而使板在其间通过。此后，成品板便用锤击或冲压成形。
一旦形成了保护件3，就将它粘合到叶片1的前缘1a。
为了制作SiC增强铝合金的所述套筒或板材，可利用传统的粉末冶金技术，它是将铝合金粉末与SiC粉末混合，并将粉末混合物用热压结法使之密实，以便给予要求的形状。
叶片1是涡轮机叶片或轮叶的翼型部分。更具体地说，它可以成为涡轮喷气发动机的风扇叶片或定子叶片的一部分。叶片的翼型部分是叶根以上部分，而叶根则是用于将叶片固定到涡轮机其余部分上的那部分。
当叶片1是风扇叶片时，它可在纤维预型件上的喷注树脂做成，纤维预型件及树脂随即分别构成最后的复合材料的纤维增强材料及基体材料。纤维预型件可具体用编织法获得，而树脂喷到纤维预型件上可用各种各样已知的方法，包括树脂传递模塑法(resin transfer molding，RTM)。
叶片1也可以是螺旋桨桨叶，或直升机旋翼桨叶。

Claims (10)

1、一种提供保护工作面的保护件，所述保护件用于保护叶片前缘，其特征在于，所述的外工作面是用由SiC颗粒增强的铝合金制成，所述SiC颗粒在所述合金中的含量范围为15％至40％重量百分比，所述保护件包括至少两层，外层(7)和内层(5)，所述外层由所述增强铝合金制作而所述内层由铝合金制作，外层(7)和内层(5)中SiC颗粒的含量从里层到外层逐渐增大。
2、根据权利要求1所述的保护件，其特征在于，所述外层中SiC颗粒的含量范围为15％至30％重量百分比。
3、根据权利要求1或2所述的保护件，其特征在于，所述内层(5)用SiC颗粒增强。
4、根据权利要求1所述的保护件，其特征在于，它包括至少两层(5、7)，且各层用混合挤压或辊压接合法组合在一起。
5、根据权利要求1所述的保护件，其特征在于，它的截面大体上是U形。
6、一种保护叶片(1)的前缘(1a)的方法，使用根据前述任一项权利要求所述的保护件，所述叶片(1)包括涡轮机动叶或静叶、直升机旋翼桨叶、或螺旋桨桨叶。
7、一种由具有前缘(1a)的叶片(1)和根据权利要求1至5所述的任意一种保护件(3)组成的组合件，所述保护件(3)密接到所述前缘(1a)上以便保护它。
8、如权利要求7所述的组合件，其特征在于，所述保护件(3)用粘合剂粘合到所述前缘(1a)上。
9、根据权利要求7所述的组合件，其特征在于，所述叶片(1)是由有机基体的复合材料制造。
10、根据权利要求7所述的组合件，其特征在于，所述叶片(1)是涡轮机动叶或静叶、直升机旋翼桨叶、或螺旋桨桨叶。
CNB2006100724954A 2005-04-15 2006-04-17 叶片前缘的保护件 Active CN100562594C (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0503780 2005-04-15
FR0503780A FR2884550B1 (fr) 2005-04-15 2005-04-15 Piece pour proteger le bord d'attaque d'une pale

Publications (2)

Publication Number Publication Date
CN1847428A CN1847428A (zh) 2006-10-18
CN100562594C true CN100562594C (zh) 2009-11-25

Family

ID=35376946

Family Applications (1)

Application Number Title Priority Date Filing Date
CNB2006100724954A Active CN100562594C (zh) 2005-04-15 2006-04-17 叶片前缘的保护件

Country Status (8)

Country Link
US (1) US7510778B2 (zh)
EP (1) EP1719699B1 (zh)
JP (1) JP4887069B2 (zh)
CN (1) CN100562594C (zh)
CA (1) CA2543226C (zh)
DE (1) DE602006014760D1 (zh)
FR (1) FR2884550B1 (zh)
RU (1) RU2006112535A (zh)

Families Citing this family (59)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2842828B1 (fr) * 2002-07-25 2005-04-29 Snecma Moteurs Piece mecanique, et procede de fabrication d'une telle piece mecanique
US20090308847A1 (en) * 2006-08-02 2009-12-17 Kabushiki Kaisha Toshiba Erosion prevention method and member with erosion preventive section
DE102007031932A1 (de) * 2007-07-09 2009-01-15 Mtu Aero Engines Gmbh Turbomaschinenschaufel
US7736130B2 (en) * 2007-07-23 2010-06-15 General Electric Company Airfoil and method for protecting airfoil leading edge
US20090120101A1 (en) * 2007-10-31 2009-05-14 United Technologies Corp. Organic Matrix Composite Components, Systems Using Such Components, and Methods for Manufacturing Such Components
WO2011008211A1 (en) * 2009-07-16 2011-01-20 Bell Helicopter Textron Inc. Method of applying abrasion resistant materials to rotors
GB0915087D0 (en) * 2009-09-01 2009-09-30 Rolls Royce Plc Aerofoil with erosion resistant leading edge
US8807931B2 (en) * 2010-01-04 2014-08-19 General Electric Company System for impact zone reinforcement
FR2961866B1 (fr) * 2010-06-24 2014-09-26 Snecma Procede de realisation d’un renfort metallique d’aube de turbomachine
FR2965202B1 (fr) * 2010-09-28 2012-10-12 Snecma Procede de fabrication d'une piece et piece massive composite obtenue par ce procede
US9222362B2 (en) 2010-11-05 2015-12-29 Barnes Group Inc. Hybrid metal leading edge part and method for making the same
WO2012064335A1 (en) * 2010-11-12 2012-05-18 Bell Helicopter Textron Inc. Composite rotor blade having weighted material for mass balancing
CN102060103A (zh) * 2010-12-29 2011-05-18 张东升 一种木质螺旋桨及其制作方法
JP6026439B2 (ja) * 2011-03-01 2016-11-16 スネクマ タービンエンジンブレード補強材などの金属部品を製造するプロセス
FR2972127B1 (fr) * 2011-03-01 2013-04-12 Snecma Procede de realisation d'une piece metallique telle qu'un renfort d'aube de turbomachine
FR2972126B1 (fr) * 2011-03-01 2014-05-16 Snecma Procede de realisation d'une piece metallique telle qu'un renfort d'aube de turbomachine
FR2972124B1 (fr) * 2011-03-01 2014-05-16 Snecma Procede de realisation d'une piece metallique telle qu'un renfort d'aube de turbomachine
FR2972128B1 (fr) * 2011-03-01 2013-03-29 Snecma Procede de realisation d'une piece metallique telle qu'un renfort de turbomachine
DE102011077804A1 (de) 2011-06-20 2012-12-20 Siemens Aktiengesellschaft Schaufel für eine thermische Strömungsmaschine
CH705171A1 (de) 2011-06-21 2012-12-31 Alstom Technology Ltd Turbinenschaufel mit einem Schaufelblatt aus Verbundwerkstoff und Verfahren zum Herstellen davon.
US9279328B2 (en) * 2011-10-25 2016-03-08 Whitcraft Llc Airfoil devices, leading edge components, and methods of making
FR2985208B1 (fr) * 2011-12-28 2014-09-19 Snecma Procede de fabrication d'une piece et piece obtenue par ce procede
US20130199934A1 (en) 2012-02-06 2013-08-08 United Technologies Corporation Electroformed sheath
FR2989991B1 (fr) * 2012-04-30 2016-01-08 Snecma Renfort structurel metallique d'aube de turbomachine
FR2992426B1 (fr) * 2012-06-20 2014-07-18 Snecma Procede de determination de la contrainte a la rupture par cisaillement d'une piece d'epaisseur determinee
US20140010663A1 (en) * 2012-06-28 2014-01-09 Joseph Parkos, JR. Gas turbine engine fan blade tip treatment
JP2015532695A (ja) * 2012-07-30 2015-11-12 ゼネラル・エレクトリック・カンパニイ 金属前縁保護ストリップ、対応する翼形部および製造方法
FR2994717B1 (fr) * 2012-08-23 2017-04-14 Snecma Aube a bord renforce pour une turbomachine
US20140112796A1 (en) * 2012-10-23 2014-04-24 General Electric Company Composite blade with uni-tape airfoil spars
JP6184039B2 (ja) * 2013-03-01 2017-08-23 ゼネラル・エレクトリック・カンパニイ 複合材翼形部の金属前縁組立体
US20160010470A1 (en) * 2013-03-14 2016-01-14 United Technologies Corporation Frangible Sheath for a Fan Blade of a Gas Turbine Engine
WO2014158245A1 (en) * 2013-03-14 2014-10-02 Hodgson Benedict N Airfoil with leading edge reinforcement
JP6150054B2 (ja) * 2013-07-02 2017-06-21 株式会社Ihi 静翼構造及びこれを用いたターボファンジェットエンジン
EP3037675B1 (en) 2013-08-19 2019-05-15 IHI Corporation Composite vane
US10487843B2 (en) * 2013-09-09 2019-11-26 United Technologies Corporation Fan blades and manufacture methods
US10458428B2 (en) * 2013-09-09 2019-10-29 United Technologies Corporation Fan blades and manufacture methods
WO2015047752A1 (en) * 2013-09-27 2015-04-02 United Technologies Corporation Fan blade assembly
FR3025735B1 (fr) * 2014-09-17 2016-12-09 Europe Tech Procede de traitement d'une piece composite
US10202854B2 (en) 2014-12-18 2019-02-12 Rolls-Royce North America Technologies, Inc. Abrasive tips for ceramic matrix composite blades and methods for making the same
DE102014226700A1 (de) 2014-12-19 2016-06-23 Rolls-Royce Deutschland Ltd & Co Kg Kompressorschaufel einer Gasturbine
US9745851B2 (en) 2015-01-15 2017-08-29 General Electric Company Metal leading edge on composite blade airfoil and shank
US10619886B2 (en) 2015-10-01 2020-04-14 Acme Engineering And Manufacturing Corp. Airfoil damper
US11149642B2 (en) 2015-12-30 2021-10-19 General Electric Company System and method of reducing post-shutdown engine temperatures
US11053861B2 (en) 2016-03-03 2021-07-06 General Electric Company Overspeed protection system and method
US10677259B2 (en) * 2016-05-06 2020-06-09 General Electric Company Apparatus and system for composite fan blade with fused metal lead edge
US10337405B2 (en) 2016-05-17 2019-07-02 General Electric Company Method and system for bowed rotor start mitigation using rotor cooling
US10583933B2 (en) 2016-10-03 2020-03-10 General Electric Company Method and apparatus for undercowl flow diversion cooling
CN110691906B (zh) * 2017-05-31 2022-07-01 西门子歌美飒可再生能源公司 具有定位标记的保护壳体
US10612386B2 (en) * 2017-07-17 2020-04-07 Rolls-Royce Corporation Apparatus for airfoil leading edge protection
US10947993B2 (en) 2017-11-27 2021-03-16 General Electric Company Thermal gradient attenuation structure to mitigate rotor bow in turbine engine
CN108032979A (zh) * 2017-12-04 2018-05-15 惠阳航空螺旋桨有限责任公司 一种铝合金基体桨叶的前缘防护结构
JP6968006B2 (ja) * 2018-03-09 2021-11-17 三菱重工業株式会社 前縁カバー部材、前縁カバー部材ユニット、複合材翼、前縁カバー部材の製造方法及び複合材翼の製造方法
CN109590192B (zh) * 2018-11-27 2019-11-12 中国航空制造技术研究院 一种复合材料叶片保护壳体制造方法
US11156100B2 (en) 2018-12-04 2021-10-26 Raytheon Technologies Corporation Composite fan blade
US11725524B2 (en) 2021-03-26 2023-08-15 General Electric Company Engine airfoil metal edge
CN113104210B (zh) * 2021-05-19 2022-02-01 清华大学 三维机织复合材料整体成型的旋翼桨叶及制作方法
US11879411B2 (en) 2022-04-07 2024-01-23 General Electric Company System and method for mitigating bowed rotor in a gas turbine engine
US11767607B1 (en) 2022-07-13 2023-09-26 General Electric Company Method of depositing a metal layer on a component
CN117165803A (zh) * 2023-11-02 2023-12-05 国网山东省电力公司烟台供电公司 一种连接金具用铝基复合材料板材的制备方法

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3762835A (en) * 1971-07-02 1973-10-02 Gen Electric Foreign object damage protection for compressor blades and other structures and related methods
US3981616A (en) * 1974-10-22 1976-09-21 The United States Of America As Represented By The Secretary Of The Air Force Hollow composite compressor blade
US4010530A (en) * 1975-07-24 1977-03-08 United Technologies Corporation Method for making blade protective sheaths
DE3568065D1 (en) * 1984-07-16 1989-03-09 Bbc Brown Boveri & Cie Process for the deposition of a corrosion-inhibiting layer, comprising protective oxide-forming elements at the base of a gas turbine blade, and a corrosion-inhibiting layer
JP2827387B2 (ja) * 1990-01-26 1998-11-25 石川島播磨重工業株式会社 耐酸化性炭素系材料
GB2242848A (en) * 1990-04-12 1991-10-16 Frictec Ltd Depositing coating on materials
US5160822A (en) * 1991-05-14 1992-11-03 General Electric Company Method for depositing material on the tip of a gas turbine engine airfoil using linear translational welding
DE4137839A1 (de) * 1991-11-16 1993-05-19 Asea Brown Boveri Verfahren zum anbringen einer erosionsschutzschicht
US5620791A (en) * 1992-04-03 1997-04-15 Lanxide Technology Company, Lp Brake rotors and methods for making the same
US5511603A (en) * 1993-03-26 1996-04-30 Chesapeake Composites Corporation Machinable metal-matrix composite and liquid metal infiltration process for making same
US5632600A (en) * 1995-12-22 1997-05-27 General Electric Company Reinforced rotor disk assembly
US5873699A (en) * 1996-06-27 1999-02-23 United Technologies Corporation Discontinuously reinforced aluminum gas turbine guide vane
FR2787366B1 (fr) * 1998-12-17 2001-02-16 Eurocopter France Procede et dispositif d'enlevement d'une plaque retenue par adhesif a une piece support
JP2001355081A (ja) * 2000-06-14 2001-12-25 Osaka Gas Co Ltd 耐熱部材およびその製造方法
JP2002144527A (ja) * 2000-11-08 2002-05-21 Taiheiyo Cement Corp ブレード
FR2842828B1 (fr) * 2002-07-25 2005-04-29 Snecma Moteurs Piece mecanique, et procede de fabrication d'une telle piece mecanique
JP2004084524A (ja) * 2002-08-26 2004-03-18 Mitsubishi Heavy Ind Ltd ファンのブレード、ファン及びファンのブレードの補強方法
FR2893268B1 (fr) * 2005-11-15 2008-02-08 Snecma Sa Procede de realisation d'un rebord situe a l'extremite libre d'une aube, aube obtenue par ce procede et turbomachine equipee de cette aube
FR2893359A1 (fr) * 2005-11-15 2007-05-18 Snecma Sa Lechette annulaire destinee a un laryrinthe d'etancheite, et son procede de fabrication
FR2893358A1 (fr) * 2005-11-15 2007-05-18 Snecma Sa Piece thermomecanique de turbomachine de revolution autour d'un axe longitudinal, comprenant une lechette annulaire, et son procede de fabrication
FR2893360A1 (fr) * 2005-11-15 2007-05-18 Snecma Sa Procede de realisation d'une lechette de labyrinthe d'etancheite, piece thermomecanique et turbomachine comprenant une telle lechette

Also Published As

Publication number Publication date
EP1719699B1 (fr) 2010-06-09
RU2006112535A (ru) 2007-11-10
FR2884550A1 (fr) 2006-10-20
CA2543226C (fr) 2015-02-17
CA2543226A1 (fr) 2006-10-15
US7510778B2 (en) 2009-03-31
US20060275626A1 (en) 2006-12-07
EP1719699A1 (fr) 2006-11-08
DE602006014760D1 (de) 2010-07-22
JP2006300057A (ja) 2006-11-02
JP4887069B2 (ja) 2012-02-29
FR2884550B1 (fr) 2010-09-17
CN1847428A (zh) 2006-10-18

Similar Documents

Publication Publication Date Title
CN100562594C (zh) 叶片前缘的保护件
EP2243929B1 (en) Hybrid structure fan blade
CA1042350A (en) Transition reinforcement of composite blade dovetails
US5141400A (en) Wide chord fan blade
EP3228419B1 (en) Rotor blade with bonded cover
US20140050589A1 (en) Hybrid structure airfoil
EP1980714B1 (en) Rotor blade and corresponding turbine
CA1085304A (en) Composite rotor blade
US8075274B2 (en) Reinforced composite fan blade
US7547194B2 (en) Rotor blade and method of fabricating the same
US20110070092A1 (en) Hybrid component
US20130255277A1 (en) Gas turbine engine nose cone
CN106870452A (zh) 用于发动机环境的耐用凸肋
CN110094237B (zh) 增强的复合叶片及制作叶片的方法
US4043703A (en) Impact resistant composite article comprising laminated layers of collimated filaments in a matrix wherein layer-layer bond strength is greater than collimated filament-matrix bond strength
US10968758B2 (en) Attachment of structures having different physical characteristics
US20160003060A1 (en) Hybrid fan blades for jet engines
JP2015527522A (ja) タービンブレード封止構造体
EP2699764B1 (de) Schaufel für eine thermische strömungsmaschine
RU2350757C1 (ru) Композиционная лопатка турбомашины
US20120118400A1 (en) Leading edge structure, in particular for the air intake of the nacelle of an aircraft engine
CN106762813B (zh) 一种风扇叶片
RU2617752C2 (ru) Рабочее колесо вентилятора и компрессора и способ его изготовления из композиционного материала
CN110296103A (zh) 用于航空发动机风扇的叶盘结构及其制造方法
CN103291370B (zh) 涡轮机叶片

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
C14 Grant of patent or utility model
GR01 Patent grant