CN101639080A - 压缩机叶片前缘衬垫及相关方法 - Google Patents

压缩机叶片前缘衬垫及相关方法 Download PDF

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CN101639080A
CN101639080A CN200910165831A CN200910165831A CN101639080A CN 101639080 A CN101639080 A CN 101639080A CN 200910165831 A CN200910165831 A CN 200910165831A CN 200910165831 A CN200910165831 A CN 200910165831A CN 101639080 A CN101639080 A CN 101639080A
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compressor blade
leading edge
liner
blade according
aerofoil profile
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J·C·谢菲尔
S·S·帕布拉
D·A·赫尔米克
J·罗伯茨
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General Electric Co
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General Electric Co
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    • 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
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • 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
    • F01D5/005—Repairing methods or devices
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • 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
    • F05D2260/00—Function
    • F05D2260/95—Preventing corrosion
    • 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
    • F05D2300/228—Nitrides
    • F05D2300/2284—Nitrides of titanium
    • 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
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49337—Composite blade

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

Abstract

本发明涉及压缩机叶片前缘衬垫及相关方法。一种提高压缩机叶片的前缘处的抗腐蚀性的方法，其包括：A)清洁压缩机叶片翼型件的前缘部分；以及B)将一个或多个抗腐蚀或抗侵蚀衬垫附连到前缘部分上。

Description

压缩机叶片前缘衬垫及相关方法
技术领域
[0001]本发明大体涉及涡轮机技术，且更具体地涉及用于减轻由压缩机叶片前缘腐蚀和/或侵蚀导致的损坏的物件和方法。
发明背景
[0002]压缩机叶片前缘腐蚀/侵蚀是涡轮发动机中的普遍问题。涡轮叶片，特别是涡轮压缩机叶片或翼型件的前缘，特别易于受由于暴露于恶劣环境而导致的腐蚀和/或侵蚀的影响。对受损的涡轮叶片进行修理和/或替换要求可能与正常维护间隔不相符的昂贵的停机时间。
[0003]因此，开发用以降低叶片前缘的腐蚀和/或侵蚀的发生率或由叶片前缘的腐蚀和/或侵蚀导致的损坏的技术或工艺将是有利的。
发明内容
[0004]根据一个示例性但非限制性实施例，本发明涉及一种包括翼型件部分和安装部分的压缩机叶片；翼型件部分具有前缘和后缘，前缘具有附连到其上的抗腐蚀或抗侵蚀衬垫(shim)。
[0005]在另一方面中，本发明涉及一种改进压缩机叶片翼型件的前缘处的抗腐蚀性或抗侵蚀性的方法，其包括：a)清洁压缩机叶片翼型件的前缘部分；以及b)将一个或多个抗腐蚀或抗侵蚀衬垫附连到前缘部分上。
[0006]现在将结合以下标示的附图更详细地描述本发明。
附图简述
[0007]图1是根据本发明的一个示例性实施例的压缩机叶片的透视图；以及
[0008]图2是沿图1中的线2-2得到的剖面，但其中按比例放大了衬垫。
具体实施方式
[0009]参看图1，轮叶或叶片10(例如涡轮压缩机叶片)包括翼型件部分12和榫安装部分14。翼型件部分12具有前缘16、后缘18、压力侧20和吸入侧22。
[0010]由于压缩机入口处的进入空气流(包含例如干燥颗粒、盐雾等)，正是前缘16最易受腐蚀和/或侵蚀的影响。
[0011]根据本发明的一个非限制性的示例性实施例，一个或多个衬垫24可应用于翼型件部分的前缘16。进一步参看图2，衬垫24基本包围前缘16，延伸到翼型件的压力侧20和吸入侧22两者中。注意，在图2中，仅为了有助于理解本发明而以非常夸大的比例显示了衬垫。一个衬垫可沿着前缘的一部分或前缘的基本整个长度而延伸，或者，备选地，多个衬垫片段可用于减小翼型件/衬垫交接处的剪切应变。
[0012]在一种优选的构造中，衬垫24具有在从1密耳至30密耳的范围内的厚度。一个或多个衬垫可由抗侵蚀合成物构成，包括高铬材料，例如Ni-25Cr片材；高铝或高钛材料。或者可采用硬的抗腐蚀材料，例如TiN、Ti/TiN、TiN/CrN、NiCrWC等。一个或多个衬垫还可由抗腐蚀聚合材料来构造，例如聚丙烯，或具有约1-10密耳的厚度的抗侵蚀带，例如3M聚亚安酯保护带。将理解的是，一个或多个衬垫还可由涂有抗腐蚀或抗侵蚀材料的适当金属来构造，即使用粉末形式的以上所提到的合成物。
[0013]金属形式的一个或多个衬垫24可通过若干已知技术中的任何一种附连到前缘16上，例如，诸如焊接、钎焊、软焊和/或通过粘合膜。一种适当的粘合膜可从名称为3M结构胶带(3M StructuralAdhesive Tape)的商品获得。可沿着金属衬垫的边缘30、32施用26、28处显示的另外的粘合材料，以便在衬垫边缘与翼型件接合处使衬垫边缘平滑。
[0014]注意到在机器的前端中温度摆动相对温和，即从约70°F至约400°F，在任何情况下，翼型件和衬垫的热膨胀特性都应该匹配到可减小循环应变的量的程度。在这点上，用于附连金属衬垫或者其本身用作衬垫的低温粘合剂是有利的，因为不需要切割，由此保持了基底金属的属性。
[0015]在附连一个或多个衬垫24之前，需要通过铣削、喷击、喷砂处理、振动抛光或上述方法的组合来准备前缘16处的表面。对于通过高压胶带(例如以上提到的3M结构胶带)进行的衬垫附连，需要额外的准备。例如，可对衬垫和翼型件前缘的相向的表面进行漂洗、碱去脂、蚀刻、干燥、填装和固化(cure)。在通过胶带应用了衬垫之后，可将叶片放置在高压灭菌器中，(例如)以使粘合剂固化。
[0016]当将诸如3M聚亚安酯保护带等低温粘合剂用作衬垫时，在应用带之前，相向的表面仅需要进行漂洗和去脂。
[0017]构思了本文所述的衬垫将在制造的时候添加到叶片上。另一方面，只要叶片处于可接受的条件下，就可针对现有叶片来改进衬垫。
[0018]虽然已经结合目前被认为是最实用且最优选的实施例的内容对本发明进行了描述，但是应当理解，本发明不限于所公开的实施例，而是相反，本发明意图覆盖包括在所附的权利要求书的精神和范围之内的各种修改和等效布置。

Claims (10)

1.一种包括翼型件部分(12)和安装部分(14)的压缩机叶片(10)；所述翼型件部分具有前缘(16)和后缘(18)，所述前缘具有附连到其上的抗腐蚀衬垫(24)。
2.根据权利要求1所述的压缩机叶片，其特征在于，所述衬垫(24)由选自包括TiN、Ti/TiN、TiN/CrN、NiCrWC的组的材料构成。
3.根据权利要求1所述的压缩机叶片，其特征在于，所述衬垫(24)至少部分地由选自由铬、铝或高钛材料组成的组的合成物构成。
4.根据权利要求1所述的压缩机叶片，其特征在于，所述衬垫(24)由涂有抗腐蚀或抗侵蚀材料的金属构成。
5.根据权利要求1所述的压缩机叶片，其特征在于，所述衬垫(24)通过焊接、钎焊或软焊而附连。
6.根据权利要求1所述的压缩机叶片，其特征在于，所述衬垫(24)通过粘合剂附连。
7.根据权利要求1所述的压缩机叶片，其特征在于，所述衬垫(24)包括多个衬垫片段。
8.根据权利要求1所述的压缩机叶片，其特征在于，所述衬垫(24)的介于约1密耳厚和约25密耳厚之间。
9.根据权利要求1所述的压缩机叶片，其特征在于，所述衬垫(24)由聚合材料制成。
10.一种提高压缩机叶片翼型件(12)的前缘部分(16)处的抗腐蚀性/抗侵蚀性的方法，包括：
a)准备所述压缩机叶片翼型件(12)的所述前缘部分(16)；以及
b)将一个或多个衬垫(24)附连到所述前缘部分(16)上。
CN200910165831A 2008-07-31 2009-07-30 压缩机叶片前缘衬垫及相关方法 Pending CN101639080A (zh)

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US12/222,067 US20100028160A1 (en) 2008-07-31 2008-07-31 Compressor blade leading edge shim and related method
US12/222067 2008-07-31

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102326003A (zh) * 2009-02-19 2012-01-18 涡轮梅坎公司 用于压缩机轮的侵蚀指示器
CN102562177A (zh) * 2010-12-27 2012-07-11 株式会社日立制作所 钛合金制叶轮机叶片
CN104593720A (zh) * 2015-01-22 2015-05-06 中国人民解放军空军工程大学航空航天工程学院 航空发动机压气机叶片抗沙尘冲蚀复合涂层及其制备方法

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8425196B2 (en) * 2011-01-28 2013-04-23 General Electric Company Wind turbine blades with a hardened substrate construction
US8906181B2 (en) * 2011-06-30 2014-12-09 United Technologies Corporation Fan blade finishing
US20130045105A1 (en) * 2011-08-17 2013-02-21 Howard Daniel Driver Wind turbine blade and method of protecting the same
US10260351B2 (en) * 2012-03-16 2019-04-16 United Technologies Corporation Fan blade and method of manufacturing same
US20140030497A1 (en) * 2012-07-30 2014-01-30 United Technologies Corporation Localized transitional coating of turbine components
DE112013004639T5 (de) * 2012-09-21 2015-06-25 Mitsubishi Hitachi Power Systems, Ltd. Verfahren zum Verschweißen von erosionsbeständigem Metallmaterial und Turbinenschaufel
DE102012112967B4 (de) 2012-12-21 2016-06-16 Sqwin Sa online Transaktionssystem
CA2921486C (en) * 2013-08-19 2016-12-13 Ihi Corporation Composite vane
DE102014212227A1 (de) * 2013-12-03 2015-06-03 Bosch Mahle Turbo Systems Gmbh & Co. Kg Verdichterrad
EP2915743B1 (fr) * 2014-03-03 2017-11-29 Airbus Nappe de protection de bords d'attaque d'éléments de voilures d'aéronefs
JP6320134B2 (ja) * 2014-04-07 2018-05-09 三菱日立パワーシステムズ株式会社 動翼、エロージョンシールドの形成方法及び動翼製造方法
FR3025735B1 (fr) * 2014-09-17 2016-12-09 Europe Tech Procede de traitement d'une piece composite
FR3041684B1 (fr) * 2015-09-28 2021-12-10 Snecma Aube comprenant un bouclier de bord d'attaque et procede de fabrication de l'aube
US10089501B2 (en) 2016-03-11 2018-10-02 Parabit Systems, Inc. Multi-media reader apparatus, secure transaction system and methods thereof
GB2549113A (en) * 2016-04-05 2017-10-11 Rolls Royce Plc Composite bodies and their manufacture
AU2016423471B2 (en) * 2016-09-13 2019-04-18 Polytech A/S Wind turbine blade including protective cover
WO2018146862A1 (ja) * 2017-02-08 2018-08-16 株式会社Ihi ファンブレード
EP3620648A1 (en) * 2018-09-10 2020-03-11 Siemens Gamesa Renewable Energy A/S Method of providing an edge seal for a rotor blade add-on
CN113508225A (zh) * 2019-03-08 2021-10-15 西门子歌美飒可再生能源公司 成形用于转子叶片附加物的边缘密封件的方法
JP7245215B2 (ja) * 2020-11-25 2023-03-23 三菱重工業株式会社 蒸気タービン動翼
JP7352534B2 (ja) * 2020-11-25 2023-09-28 三菱重工業株式会社 蒸気タービン動翼、蒸気タービン動翼の製造方法及び改造方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS62694A (ja) * 1985-06-26 1987-01-06 Mitsubishi Heavy Ind Ltd 被覆翼
CA2484438A1 (en) * 2003-10-31 2005-04-30 General Electric Company Method for repairing gas turbine compressor rotor blades
CN1644304A (zh) * 2004-03-08 2005-07-27 斯奈克玛马达公司 用于风机叶片的增强前边或后边的制造方法
US20050227078A1 (en) * 2004-02-25 2005-10-13 Honeywell International Inc. Turbine engine compressor blade erosion preventative diamond-like coating

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3815906A1 (de) * 1988-05-10 1989-11-23 Mtu Muenchen Gmbh Luftschraubenblatt aus faserverstaerktem kunststoff
US4895491A (en) * 1988-06-17 1990-01-23 Environmental Elements Corp. Fan blade protection system
US5123814A (en) * 1990-07-27 1992-06-23 The Marley Cooling Tower Company Industrial cooling tower fan blade having abrasion resistant leading edge
DE4208842C1 (zh) * 1992-03-19 1993-04-08 Eurocopter Hubschrauber Gmbh, 8000 Muenchen, De
US5603603A (en) * 1993-12-08 1997-02-18 United Technologies Corporation Abrasive blade tip
US5449273A (en) * 1994-03-21 1995-09-12 United Technologies Corporation Composite airfoil leading edge protection
US5655883A (en) * 1995-09-25 1997-08-12 General Electric Company Hybrid blade for a gas turbine
US5778960A (en) * 1995-10-02 1998-07-14 General Electric Company Method for providing an extension on an end of an article
JPH1054204A (ja) * 1996-05-20 1998-02-24 General Electric Co <Ge> ガスタービン用の多構成部翼
US5725354A (en) * 1996-11-22 1998-03-10 General Electric Company Forward swept fan blade
US5931641A (en) * 1997-04-25 1999-08-03 General Electric Company Steam turbine blade having areas of different densities
GB2365078B (en) * 2000-07-27 2004-04-21 Rolls Royce Plc A gas turbine engine blade
US6532656B1 (en) * 2001-10-10 2003-03-18 General Electric Company Gas turbine engine compressor blade restoration method
US6607358B2 (en) * 2002-01-08 2003-08-19 General Electric Company Multi-component hybrid turbine blade
US7186092B2 (en) * 2004-07-26 2007-03-06 General Electric Company Airfoil having improved impact and erosion resistance and method for preparing same
US7104761B2 (en) * 2004-07-28 2006-09-12 General Electric Company Hybrid turbine blade and related method
US7334997B2 (en) * 2005-09-16 2008-02-26 General Electric Company Hybrid blisk
US7811063B2 (en) * 2006-11-03 2010-10-12 General Electric Company Damping element for a wind turbine rotor blade

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS62694A (ja) * 1985-06-26 1987-01-06 Mitsubishi Heavy Ind Ltd 被覆翼
CA2484438A1 (en) * 2003-10-31 2005-04-30 General Electric Company Method for repairing gas turbine compressor rotor blades
US20050227078A1 (en) * 2004-02-25 2005-10-13 Honeywell International Inc. Turbine engine compressor blade erosion preventative diamond-like coating
CN1644304A (zh) * 2004-03-08 2005-07-27 斯奈克玛马达公司 用于风机叶片的增强前边或后边的制造方法

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102326003A (zh) * 2009-02-19 2012-01-18 涡轮梅坎公司 用于压缩机轮的侵蚀指示器
CN102562177A (zh) * 2010-12-27 2012-07-11 株式会社日立制作所 钛合金制叶轮机叶片
CN102562177B (zh) * 2010-12-27 2015-06-03 三菱日立电力***株式会社 钛合金制叶轮机叶片
CN104593720A (zh) * 2015-01-22 2015-05-06 中国人民解放军空军工程大学航空航天工程学院 航空发动机压气机叶片抗沙尘冲蚀复合涂层及其制备方法

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