CN1869408B - 前短轴的具有涂层的燕尾狭槽 - Google Patents

前短轴的具有涂层的燕尾狭槽 Download PDF

Info

Publication number
CN1869408B
CN1869408B CN2006100844941A CN200610084494A CN1869408B CN 1869408 B CN1869408 B CN 1869408B CN 2006100844941 A CN2006100844941 A CN 2006100844941A CN 200610084494 A CN200610084494 A CN 200610084494A CN 1869408 B CN1869408 B CN 1869408B
Authority
CN
China
Prior art keywords
dovetail slot
compressor
blade
axle
minor axis
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.)
Expired - Fee Related
Application number
CN2006100844941A
Other languages
English (en)
Other versions
CN1869408A (zh
Inventor
F·J·卡萨诺瓦
S·-D·高
R·M·鲁滨逊
R·G·罗
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of CN1869408A publication Critical patent/CN1869408A/zh
Application granted granted Critical
Publication of CN1869408B publication Critical patent/CN1869408B/zh
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • 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
    • F04D29/322—Blade mountings
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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
    • 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
    • F04D29/38—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
    • F05D2230/30—Manufacture with deposition of material
    • 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
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • 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
    • 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
    • F05D2300/611—Coating

Landscapes

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

Abstract

一种压缩器前短轴(10)，包括燕尾狭槽(24)的多个轴向隔开的环形排(12、14、16、18、20、22)，所述多个排的至少第一和第二个排具有部分涂覆有耐磨涂层(41)的燕尾狭槽。

Description

前短轴的具有涂层的燕尾狭槽
技术领域
本发明总体涉及一种转动机械技术，并且特别是涉及压缩器叶片安装在转子燕尾狭槽内。
背景技术
通常耐磨涂层施加在压缩器叶片的燕尾件部分上以便减小叶片和压缩器轮燕尾狭槽之间的压缩应力和摩擦。主要由于涂层容易施加其上，而将这种涂层施加在叶片燕尾件上。实际上，例如，叶片本身用掩模覆盖，并且可以直接将涂层喷射在叶片燕尾件上，并且如果需要固化，叶片容易进行处理并且运动通过炉子。但是，例如Mos2的某些类型的耐磨涂层以及其它类似的涂层与用于叶片的典型钢C450合金不相容。实际上，施加在C450合金材料上的涂层可降低该材料的耐腐蚀疲劳性能。
因此，需要在压缩器叶片和压缩器轮燕尾件之间提供耐磨性，而不降低叶片的耐腐蚀疲劳性能。
发明内容
在本发明的示例性实施例中，耐磨涂层直接施加在压缩器轮燕尾狭槽上以便在涂层和用于某些燃气轮机中的叶片材料之间减小(如果不是消除)所形成的潜在腐蚀情况。更特别是，在本发明的一个示例性实施例中，在认识到所述问题的情况下，在压缩器前短轴的级1和2中，Alumazite-ZD涂层直接施加在燕尾狭槽内。由于涂层本身是用于减小磨损和压碎应力的传统涂层，这是特别有利的解决方法，并且不需要重新设计任何部件。
因此，在一个方面中，本发明涉及一种压缩器前短轴，该短轴包括燕尾凹槽的多个轴向隔开的环形排，多个排的至少第一和第二排具有部分涂覆有耐磨涂层的燕尾狭槽。
在另一方面中，本发明涉及一种涡轮机机压缩器轴，该轴具有围绕支承叶片的至少一个环形排的轴的周边形成的多个燕尾狭槽，每个燕尾狭槽支承叶片，叶片具有翼面部分和接收在燕尾狭槽内的燕尾件安装部分，其中每个燕尾狭槽的一部分具有施加其上的耐磨涂层。
在又一方面中，本发明涉及一种涡轮机压缩器轴，该轴具有围绕支承叶片的至少一个环形排的轴的周边形成的多个燕尾狭槽，每个燕尾狭槽支承叶片，叶片具有翼面部分和接收在燕尾狭槽内的燕尾件安装部分，其中每个燕尾狭槽包括一对向内伸出的柄脚和通过大致平的过渡表面连接的一对向外指向的凹槽，并且其中热塑铝着色涂层施加在所述过渡表面上。
现在接合下面描述的附图描述本发明。
附图说明
图1是传统压缩器前短轴的透视图；
图2是传统压缩器叶片的透视图；
图3是从图1截取的第一压缩器级的放大局部细节，并且表示按照本发明示例性实施例施加在燕尾狭槽上的涂层；以及
图4是指出已经施加有涂层的表面区域的燕尾狭槽的简化局部端视图。
具体实施方式
图1表示由燕尾狭槽12、14、16、18、20和22的六个整体环形排形成的传统压缩器前短轴10，每个狭槽24构造成支承具有配合燕尾件部分的压缩器叶片。叶片的每排表示压缩器短轴的一级，并且相对于本发明来说，它是特别感兴趣的第一两个排或级12和14。
典型的第一级压缩器叶片26表示在图2中。叶片包括翼面28、平台30和成形为接收在相应燕尾狭槽24(图1)内的燕尾件32。在过去，耐磨涂层(总体虚线所示)在燕尾件32的相对侧上施加在表面34上(表示一个)。但是如上所述，例如Alumazite-ZD的某种涂层与用于叶片26的C450钢合金材料不相容。因此，可以降低叶片的耐腐蚀和疲劳性能。
参考图3和4，局部但更加详细地表示前短轴10的第一级12。每个燕尾狭槽24形成有一对向内指向的柄脚36以及通过平底部表面40连接的一对向外指向的凹槽38。注意到图3内的第一燕尾狭槽24通过狭槽的径向中心线截取，以便理解耐磨涂层的位置。在示例性实施例中，耐磨涂层施加在大致平的表面42的整个轴向长度上，该表面42用作燕尾件柄脚26的凸出半径和燕尾件凹槽38的凹入半径之间的过渡部分。将理解到在每个燕尾狭槽24(见图4)内具有两个这样横向相对的过渡表面42，并且每个狭槽24围绕狭槽排的整个360°范围进行类似涂覆。
在示例性实施例中，对于包括NiCrMoV合金的短轴来说，热塑铝着色涂层施加到0.0008-0.0018英寸之间的厚度。一种这样的涂层可以在市场上从Tiodize Co.，inc.制造的商品名称Alumazite ZD得到。这种涂层(或类似的适当涂层)防止电流和环境氧化，并且与NiCrMoV燕尾件材料相容。认识到工具必须调整以适于接近燕尾件柄脚下侧，该涂层通过传统喷射技术施加。
迄今为止的测试结果证实对燕尾狭槽24进行涂覆是用于避免所述叶片燕尾件32的耐腐蚀疲劳性能退化的可行技术。例如，涂覆有Alumazite ZD的NiCrMoV材料暴露于盐雾中长达405小时，并且涂层处没有腐蚀，只是用刀具切去涂层以暴露材料的根部处出现小腐蚀。在涂覆的NiCrMoV和GT-450之间也进行了耐磨测试，在5000循环以及低摩擦之后，没有显示出蚀斑。
虽然结合被认为是当前最为实用和优选的实施例来描述本发明，应该理解到本发明不局限于所披露的实施例，相反本发明旨在覆盖包括在所附权利要求的精神和范围内的多种变型和等同配置。

Claims (8)

1.一种压缩器前短轴(10)，其包括燕尾狭槽(24)的多个轴向隔开的环形排(12、14、16、18、20、22)，所述多个排的至少第一排和第二排具有部分涂覆有耐磨涂层的燕尾狭槽，其中所述短轴(10)由NiCrMoV合金构成，并且所述耐磨涂层包括热塑铝着色涂层。
2.如权利要求1所述的压缩器前短轴，其特征在于，每个燕尾狭槽(24)包括一对向内伸出的柄脚(36)和通过平底部(40)连接的一对向外指向的凹槽(38)。
3.如权利要求2所述的压缩器前短轴，其特征在于，每个燕尾狭槽(24)还包括在所述一对柄脚(36)和所述一对凹槽(38)之间的大致平的过渡表面(42)。
4.如权利要求3所述的压缩器前短轴，其特征在于，所述耐磨涂层只施加在所述大致平的过渡表面(42)上。
5.一种涡轮机压缩器轴，其具有围绕轴的周边形成的多个燕尾狭槽(24)，所述轴支承叶片(26)的至少一个环形排，每个燕尾狭槽(24)支承叶片(26)，叶片(26)具有翼面部分(28)和接收在所述燕尾狭槽内的燕尾件安装部分(32)，其中每个燕尾狭槽包括通过大致平的过渡表面(42)连接的一对向内伸出的柄脚(36)和一对向外指向的凹槽(38)，其中热塑铝着色涂层施加在所述过渡表面上；所述轴由NiCrMoV合金构成。
6.如权利要求5所述的涡轮机压缩器轴，其特征在于，所述叶片由C450钢合金构成。
7.如权利要求5所述的涡轮机压缩器轴，其特征在于，所述热塑铝着色涂层只施加在所述大致平的过渡表面(42)上。
8.如权利要求5所述的涡轮机压缩器轴，其特征在于，所述轴包括压缩器前短轴(10)，该短轴支承叶片的至少三个环形排，其中叶片的所述至少三个环形排中至少第一排和第二排安装在具有施加在所述过渡表面(42)上的所述热塑铝着色涂层的所述燕尾狭槽(24)内。
CN2006100844941A 2005-05-24 2006-05-24 前短轴的具有涂层的燕尾狭槽 Expired - Fee Related CN1869408B (zh)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US11/135470 2005-05-24
US11/135,470 US7217099B2 (en) 2005-05-24 2005-05-24 Coated forward stub shaft dovetail slot
US11/135,470 2005-05-24

Publications (2)

Publication Number Publication Date
CN1869408A CN1869408A (zh) 2006-11-29
CN1869408B true CN1869408B (zh) 2012-11-14

Family

ID=36933499

Family Applications (1)

Application Number Title Priority Date Filing Date
CN2006100844941A Expired - Fee Related CN1869408B (zh) 2005-05-24 2006-05-24 前短轴的具有涂层的燕尾狭槽

Country Status (5)

Country Link
US (1) US7217099B2 (zh)
EP (1) EP1726831A3 (zh)
JP (1) JP5762662B2 (zh)
KR (1) KR101329892B1 (zh)
CN (1) CN1869408B (zh)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7665439B2 (en) * 2007-05-10 2010-02-23 Ingersoll Rand Company Single piece rotor
US8240042B2 (en) * 2008-05-12 2012-08-14 Wood Group Heavy Industrial Turbines Ag Methods of maintaining turbine discs to avert critical bucket attachment dovetail cracks
JP2010259250A (ja) * 2009-04-27 2010-11-11 Toshiba Mitsubishi-Electric Industrial System Corp 回転子
EP2657454B1 (en) 2012-04-26 2014-05-14 Alstom Technology Ltd Turbine diaphragm construction
JP2013249756A (ja) * 2012-05-31 2013-12-12 Hitachi Ltd 圧縮機
US20140003959A1 (en) * 2012-06-27 2014-01-02 General Electric Company Modified rotor component and method for modifying a wear characteristic of a rotor component in a turbine system
US20140003954A1 (en) * 2012-06-27 2014-01-02 General Electric Company Modified rotor blade and method for modifying a wear characteristic of a rotor blade in a turbine system
CN102797509B (zh) * 2012-08-24 2014-09-17 中国南方航空工业(集团)有限公司 一种涡轮叶片的减震润滑结构
WO2014137438A1 (en) * 2013-03-07 2014-09-12 United Technologies Corporation Aluminum fan blades with root wear mitigation
EP2832957A1 (en) * 2013-07-31 2015-02-04 ALSTOM Technology Ltd Rotor with groove having a compliant layer
US10400784B2 (en) 2015-05-27 2019-09-03 United Technologies Corporation Fan blade attachment root with improved strain response
KR20170018718A (ko) 2015-08-10 2017-02-20 삼성전자주식회사 비정질 합금을 이용한 투명 전극 및 그 제조 방법
KR102054888B1 (ko) * 2019-09-17 2019-12-11 김충호 마모방지 기능이 향상된 바이오 중유용 스크루펌프 및 이의 제조방법
US11808214B2 (en) 2021-05-24 2023-11-07 General Electric Company Midshaft rating for turbomachine engines
US12071978B2 (en) 2021-05-24 2024-08-27 General Electric Company Midshaft rating for turbomachine engines
US11603801B2 (en) 2021-05-24 2023-03-14 General Electric Company Midshaft rating for turbomachine engines
US11724813B2 (en) 2021-05-24 2023-08-15 General Electric Company Midshaft rating for turbomachine engines

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4016636A (en) * 1974-07-23 1977-04-12 United Technologies Corporation Compressor construction
US5368444A (en) * 1993-08-30 1994-11-29 General Electric Company Anti-fretting blade retention means
US6267558B1 (en) * 1999-05-26 2001-07-31 General Electric Company Dual intensity peening and aluminum-bronze wear coating surface enhancement
US6751863B2 (en) * 2002-05-07 2004-06-22 General Electric Company Method for providing a rotating structure having a wire-arc-sprayed aluminum bronze protective coating thereon

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2994507A (en) * 1959-01-23 1961-08-01 Westinghouse Electric Corp Blade locking structure
DE3133158C1 (de) * 1981-08-21 1982-12-16 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Pressflaechen-Zwischenlage aus Metall und Verfahren zur Herstellung derselben
GB2171150B (en) * 1985-02-12 1989-07-26 Rolls Royce Plc Bladed rotor assembly for a turbomachine
EP0237170B1 (en) * 1986-02-05 1994-05-11 Hitachi, Ltd. Heat resistant steel and gas turbine composed of the same
US5141401A (en) 1990-09-27 1992-08-25 General Electric Company Stress-relieved rotor blade attachment slot
US5356545A (en) * 1991-01-15 1994-10-18 General Electric Company Curable dry film lubricant for titanium alloys
US5240375A (en) 1992-01-10 1993-08-31 General Electric Company Wear protection system for turbine engine rotor and blade
JPH0658168A (ja) * 1992-08-06 1994-03-01 Hitachi Ltd ガスタービン用圧縮機及びガスタービン
EP0750689B1 (en) * 1994-03-17 2002-09-04 The Westaim Corporation Low friction cobalt-based coatings for titanium
US5431542A (en) 1994-04-29 1995-07-11 United Technologies Corporation Ramped dovetail rails for rotor blade assembly
JP3845875B2 (ja) * 1994-12-13 2006-11-15 株式会社日立製作所 ガスタービン用圧縮機及びガスタービン
US5573377A (en) 1995-04-21 1996-11-12 General Electric Company Assembly of a composite blade root and a rotor
US6089828A (en) * 1998-02-26 2000-07-18 United Technologies Corporation Coated article and method for inhibiting frictional wear between mating titanium alloy substrates in a gas turbine engine
US6290466B1 (en) 1999-09-17 2001-09-18 General Electric Company Composite blade root attachment
US6672838B1 (en) * 2000-07-27 2004-01-06 General Electric Company Method for making a metallic article with integral end band under compression
JP2003082476A (ja) * 2001-06-26 2003-03-19 Toshiba Corp 耐食・耐摩耗タービン部材および製造方法
JP2004124750A (ja) * 2002-09-30 2004-04-22 Toshiba Corp ガスタービンプラントおよびガスタービンプラントの補修方法
US6749951B1 (en) 2003-03-14 2004-06-15 General Electric Company Coated article having a quasicrystalline-ductile metal layered coating with high wear resistance, and its preparation and use
GB0324704D0 (en) * 2003-10-23 2003-11-26 Rolls Royce Plc An apparatus and a method of applying a dry film lubricant to a rotor slot
GB0403064D0 (en) * 2004-02-12 2004-03-17 Rolls Royce Plc Gas turbine engine rotor blade, rotor disc and bladed disc assembly, and a bearing arrangement for reducing the effects of dynamic contact stresses

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4016636A (en) * 1974-07-23 1977-04-12 United Technologies Corporation Compressor construction
US5368444A (en) * 1993-08-30 1994-11-29 General Electric Company Anti-fretting blade retention means
US6267558B1 (en) * 1999-05-26 2001-07-31 General Electric Company Dual intensity peening and aluminum-bronze wear coating surface enhancement
US6751863B2 (en) * 2002-05-07 2004-06-22 General Electric Company Method for providing a rotating structure having a wire-arc-sprayed aluminum bronze protective coating thereon

Also Published As

Publication number Publication date
KR20060121730A (ko) 2006-11-29
EP1726831A3 (en) 2012-04-11
CN1869408A (zh) 2006-11-29
US7217099B2 (en) 2007-05-15
KR101329892B1 (ko) 2013-11-15
US20060269415A1 (en) 2006-11-30
EP1726831A2 (en) 2006-11-29
JP2006329195A (ja) 2006-12-07
JP5762662B2 (ja) 2015-08-12

Similar Documents

Publication Publication Date Title
CN1869408B (zh) 前短轴的具有涂层的燕尾狭槽
US6832896B1 (en) Blade platforms for a rotor assembly
EP1965031B1 (en) Blade outer air seal assembly
US7802963B2 (en) Pivot ring
US6832897B2 (en) Second stage turbine bucket airfoil
US20060245916A1 (en) Stator blades, turbomachines comprising such blades and method of repairing such blades
EP1676978A3 (en) Gas turbine engine blade tip clearance apparatus and method
US20070245532A1 (en) Grouped reaction nozzle tip shrouds with integrated seals
EP2423442B1 (en) Electroformed conforming rubstrip
US8282356B2 (en) Apparatus and method for reducing wear in disk lugs
EP1914384A3 (en) Part span shrouded fan blisk
US9598968B2 (en) Attaching the blades to the drum of an axial turbocompressor
CN103422903A (zh) 涡轮隔板构造
EP1790827B1 (en) Tip shroud attachment for stator vane
EP1925783B1 (en) Variable stator blade assembly
US20070071605A1 (en) Integrated nozzle and bucket wheels for reaction steam turbine stationary components and related method
US20050220624A1 (en) Compressor blade platform extension and methods of retrofitting blades of different blade angles
US11459912B2 (en) Flow guide, steam turbine, inside member, and method for manufacturing flow guide
EP2930306B1 (en) Gas turbine engine fan with discrete platforms for electrically grounding sheaths of fan airfoils
JP2017502191A (ja) ブレード付きロータ
US10099323B2 (en) Rotating structure and a method of producing the rotating structure
US8414254B2 (en) Sealing assembly for a turbine engine
US20130261034A1 (en) Coating for turbomachinery
JP4479935B2 (ja) ガスタービンの熱媒体供給部品の潤滑システム
JP5458356B2 (ja) ２段バランス式消防用ポンプ

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
CF01 Termination of patent right due to non-payment of annual fee

Granted publication date: 20121114

CF01 Termination of patent right due to non-payment of annual fee