CN1847428A - 叶片前缘的保护件 - Google Patents

叶片前缘的保护件 Download PDF

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CN1847428A
CN1847428A CNA2006100724954A CN200610072495A CN1847428A CN 1847428 A CN1847428 A CN 1847428A CN A2006100724954 A CNA2006100724954 A CN A2006100724954A CN 200610072495 A CN200610072495 A CN 200610072495A CN 1847428 A CN1847428 A CN 1847428A
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blade
guard member
leading edge
sic
layer
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CN100562594C (zh
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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
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (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，且其特征在于，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。
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、一种提供外保护工作面的保护件，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。
2、根据权利要求1所述的保护件，其特征在于，所述合金中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，它包括至少两层，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，当然也可随意地用SiC颗粒增强，各层中SiC颗粒的含量从里层到外层逐渐增大。
4、根据前述任一项权利要求所述的保护件，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、根据前述任一项权利要求所述的保护件，其特征在于，它的截面大体上是U形。
6、一种根据前述任一项权利要求所述的用于保护所述叶片(1)的前缘(2)的保护件。
7、一种保护叶片(1)的前缘(1a)，具体说是涡轮机动叶或静叶、直升机旋翼桨叶、或螺旋桨桨叶的前缘的方法，使用根据前述任一项权利要求所述的保护竹。
8、一种由具有前缘(1a)的叶片(1)和根据权利要求1至6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。
9、如权利要求8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。
10、根据权利要求8或9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。
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CN102003217A (zh) * 2009-09-01 2011-04-06 劳斯莱斯有限公司 带有抗侵蚀前缘的翼型件
CN102060103A (zh) * 2010-12-29 2011-05-18 张东升 一种木质螺旋桨及其制作方法
CN102116175A (zh) * 2010-01-04 2011-07-06 通用电气公司 用于冲击区域增强的系统
CN102472242A (zh) * 2009-07-16 2012-05-23 贝尔直升机泰克斯特龙公司 一种将抗磨材料涂敷到转子上的方法
CN102947596A (zh) * 2010-06-24 2013-02-27 斯奈克玛 涡轮机叶片金属加强件的制作方法
CN103209890A (zh) * 2010-11-12 2013-07-17 贝尔直升机泰克斯特龙公司 具有用于质量平衡的配重材料的复合旋翼桨叶
CN104271888A (zh) * 2012-04-30 2015-01-07 斯奈克玛 用于由复合材料制成的涡轮发动机叶片的金属结构增强件
CN104508246A (zh) * 2012-07-30 2015-04-08 通用电气公司 金属前缘保护带、对应的翼型件及制造方法
CN104981586A (zh) * 2012-10-23 2015-10-14 通用电气公司 带有单向带翼型件翼梁的复合叶片
CN105189930A (zh) * 2013-03-01 2015-12-23 通用电气公司 复合翼型件金属前缘组件
CN105473870A (zh) * 2013-08-19 2016-04-06 株式会社Ihi 复合材料翼
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
CN109415940A (zh) * 2016-05-06 2019-03-01 通用电气公司 用于复合风扇叶片的金属前缘
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Families Citing this family (42)

* 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
KR101147719B1 (ko) * 2006-08-02 2012-05-24 가부시끼가이샤 도시바 침식방지 방법 및 침식방지부를 구비한 부재
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
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
FR2972126B1 (fr) * 2011-03-01 2014-05-16 Snecma Procede de realisation d'une piece metallique telle qu'un renfort d'aube de turbomachine
FR2972127B1 (fr) * 2011-03-01 2013-04-12 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
BR112013022019B1 (pt) * 2011-03-01 2019-05-21 Snecma Processo de realização de uma peça metálica tal como um reforço de pá de turbomáquina
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
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
FR2994717B1 (fr) * 2012-08-23 2017-04-14 Snecma Aube a bord renforce pour une turbomachine
WO2014158245A1 (en) * 2013-03-14 2014-10-02 Hodgson Benedict N Airfoil with leading edge reinforcement
WO2014143256A1 (en) 2013-03-14 2014-09-18 United Technologies Corporation Frangible sheath for a fan blade of a gas turbine engine
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
EP3044419B1 (en) * 2013-09-09 2019-10-02 United Technologies Corporation Airfoil and manufacturing method
EP3044417B1 (en) * 2013-09-09 2019-10-02 United Technologies Corporation Fan blades and manufacture methods
EP3049632B1 (en) * 2013-09-27 2020-06-24 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
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
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
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
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
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

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
EP0168868B1 (de) * 1984-07-16 1989-02-01 BBC Brown Boveri AG Verfahren zum Aufbringen einer schutzoxydbildende Elemente enthaltenden Korrosionsschutzschicht auf den Grundkörper einer Gasturbinenschaufel und Korrosionssschutzschicht auf dem Grundkörper einer Gasturbinenschaufel
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
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
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
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

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102472242B (zh) * 2009-07-16 2016-09-07 贝尔直升机泰克斯特龙公司 一种将抗磨材料涂敷到转子上的方法
CN102472242A (zh) * 2009-07-16 2012-05-23 贝尔直升机泰克斯特龙公司 一种将抗磨材料涂敷到转子上的方法
CN102003217A (zh) * 2009-09-01 2011-04-06 劳斯莱斯有限公司 带有抗侵蚀前缘的翼型件
US8807931B2 (en) 2010-01-04 2014-08-19 General Electric Company System for impact zone reinforcement
CN102116175A (zh) * 2010-01-04 2011-07-06 通用电气公司 用于冲击区域增强的系统
CN102116175B (zh) * 2010-01-04 2015-04-01 通用电气公司 用于冲击区域增强的系统
CN102947596A (zh) * 2010-06-24 2013-02-27 斯奈克玛 涡轮机叶片金属加强件的制作方法
CN102947596B (zh) * 2010-06-24 2016-04-20 斯奈克玛 涡轮机叶片金属加强件的制作方法
CN103209890A (zh) * 2010-11-12 2013-07-17 贝尔直升机泰克斯特龙公司 具有用于质量平衡的配重材料的复合旋翼桨叶
CN103209890B (zh) * 2010-11-12 2015-09-16 贝尔直升机泰克斯特龙公司 具有用于质量平衡的配重材料的复合旋翼桨叶
CN102060103A (zh) * 2010-12-29 2011-05-18 张东升 一种木质螺旋桨及其制作方法
CN104271888A (zh) * 2012-04-30 2015-01-07 斯奈克玛 用于由复合材料制成的涡轮发动机叶片的金属结构增强件
CN104271888B (zh) * 2012-04-30 2015-11-25 斯奈克玛 用于由复合材料制成的涡轮发动机叶片的金属结构增强件
CN104508246A (zh) * 2012-07-30 2015-04-08 通用电气公司 金属前缘保护带、对应的翼型件及制造方法
US9885244B2 (en) 2012-07-30 2018-02-06 General Electric Company Metal leading edge protective strips for airfoil components and method therefor
CN104981586A (zh) * 2012-10-23 2015-10-14 通用电气公司 带有单向带翼型件翼梁的复合叶片
CN105189930A (zh) * 2013-03-01 2015-12-23 通用电气公司 复合翼型件金属前缘组件
CN105473870A (zh) * 2013-08-19 2016-04-06 株式会社Ihi 复合材料翼
CN105473870B (zh) * 2013-08-19 2017-10-03 株式会社Ihi 复合材料翼
CN109415940A (zh) * 2016-05-06 2019-03-01 通用电气公司 用于复合风扇叶片的金属前缘
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FR2884550A1 (fr) 2006-10-20
CA2543226C (fr) 2015-02-17
JP4887069B2 (ja) 2012-02-29
CN100562594C (zh) 2009-11-25
DE602006014760D1 (de) 2010-07-22
FR2884550B1 (fr) 2010-09-17
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CA2543226A1 (fr) 2006-10-15

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