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CN100419218C - 频率调整的压缩机定子叶片和相关方法 - Google Patents

频率调整的压缩机定子叶片和相关方法 Download PDF

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CN100419218C
CN100419218C CNB2005100626302A CN200510062630A CN100419218C CN 100419218 C CN100419218 C CN 100419218C CN B2005100626302 A CNB2005100626302 A CN B2005100626302A CN 200510062630 A CN200510062630 A CN 200510062630A CN 100419218 C CN100419218 C CN 100419218C
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stator blade
compressor stator
base part
groove
frequency
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CN1690366A (zh
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N·F·马丁
T·R·蒂普顿
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General Electric Co
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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
    • 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
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
    • 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
    • F05D2230/10—Manufacture by removing material
    • 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
    • Y10T29/4932—Turbomachine making
    • Y10T29/49325—Shaping integrally bladed rotor
    • 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
    • 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
    • Y10T29/49716—Converting
    • 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
    • Y10T29/49764—Method of mechanical manufacture with testing or indicating
    • Y10T29/49771—Quantitative measuring or gauging
    • Y10T29/49774—Quantitative measuring or gauging by vibratory or oscillatory movement

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

Abstract

一种调整具有一个基座部分(30)和一个翼面部分(32)，以达到所希望的自然频率的方法。它包括：a)鉴别该压缩机定子叶片的自然频率；b)确定该压缩机定子叶片的不同的目标自然频率；和c)从该压缩机定子叶片的基座部分(30)上除去一定量和一定形状的材料，以达到该目标自然频率。一个频率协调的压缩机定子叶片(28)包括一个翼面部分(32)和一个基座部分(30)。该基座部分基本上为连续的矩形形状，在该基座部分(30)的宽度尺寸上切出一条槽(34)，该槽的尺寸选择成可得到该翼部分预先确定的自然频率。

Description

频率调整的压缩机定子叶片和相关方法
技术领域
本发明总的涉及回转机器技术，具体地说，涉及压缩机定子叶片的制造或改进。
背景技术
过去，压缩机定子叶片的自然频率的调整是通过改进该叶片的翼面部分的形状来完成的。然而，希望不改变该翼面的形状，而能够改变压缩机定子叶片的翼面的自然频率。
而且，一篇美国授权专利US 5,022,818公开了一种用于燃气涡轮的压缩机隔板组件，其包括多个叶片翼面，每个叶片翼面是采用整体的内罩盖和整体的外罩盖制成的，其通过多个连接杆连接在一起，多个所述连接杆在叶片翼面和涡轮壳体槽之间传输负荷，在涡轮壳体槽内悬挂叶片翼面。
发明内容
本发明涉及不改变该叶片小翼面部分(或简单地，翼面)，而调整压缩机定子叶片的自然频率的方法。这个方法可使在需要调整频率时，继续使用用户现有的压缩机定子叶片。另外，这里所述的频率调整方法也可以用于新的压缩机定子叶片的制造。
在本发明的一个示例性，但不是限制性的实施例中，通过作出完全在基座宽度上延伸的一条槽，从该压缩机定子叶片的基座或安装部分上除去材料。然而，本发明并不仅限于作出一条形状均匀的槽。例如，多条槽也可产生相同的所希望的结果。另外，可以改变一条或多条槽的深度和/或宽度。这样，通过适当地除去该定子叶片基座或安装部分的材料，可以改变该叶片的翼面部分的基础刚度，这也可以改变该翼面的自然频率。
因此，在更广的方面，提供了调整具有一个基座部分和一个翼面部分的压缩机定子叶片以达到所希望的自然频率的调整方法。该方法包括：a)鉴别该压缩机定子叶片的自然频率，b)确定该压缩机定子叶片的不同的目标自然频率，和c)从该压缩机定子叶片的基座部分除去一定量和一定构形的材料，以达到该目标自然频率。
在另一个方面中，提供了调整压缩机定子叶片，以达到所希望的自然频率的方法。该定子叶片具有一个翼面部分和一个基本上为矩形的基座部分，并具有一对较长的侧表面，一对较短的端面，一个顶部表面和一个底部表面。该方法包括：a)鉴别该压缩机定子叶片的自然频率，b)确定该压缩机定子叶片的不同的目标自然频率，和c)从该压缩机定子叶片的基座部分上除去作成槽形式的材料，以达到该目标自然频率。
在再一个方面中，提供了一种压缩机定子叶片。该叶片包括一个翼面部分和一个基座部分。该基座部分具有基本上完整的矩形形状，并且在横贯该基座部分的宽度尺寸上切出至少一条槽。选择该槽的尺寸，以得到该翼面部分的一个预定的自然频率。
现在，结合下面的附图，详细地说明本发明。
附图说明
图1为一个已知的压缩机定子叶片的翼面的侧视图；
图2为图1所示的翼面的透视图；
图3为根据本发明的一个非限制性实施例的一个压缩机定子叶片的翼面的侧视图；和
图4为图3所示的翼面的透视图。
具体实施方式
首先，参见图1和图2，一个已知的压缩机定子叶片10包括一个基座或安装部分和一个翼面部分14。该基座或安装部分12一般为矩形形状，带有一对较长的侧表面16，18和一对较短的端面20，22，还具有一个径向的内表面24和一个径向外表面26。该基座部分还可以作成平行四边形，即其平行的端面不与平行的侧表面垂直。过去，为了改变该翼面部分14的自然频率，必需改变该翼面本身的形状。
图3和图4表示根据本发明的一个非限制性的示例性实施例的压缩机定子叶片。在这个实施例中，该压缩机定子叶片28也包括一个基座或安装部分30，和一个翼面部分32。在确定了该叶片的自然频率后，和鉴别了一个目标自然频率后，通过有选择地从该基座或安装部分30上去除材料，来改变该定子叶片。具体地是，通过切削或加工完全横贯该基座或安装部分宽度(即与端面40，42平行，仅侧表面36至侧表面38)延伸的槽，在该基座或安装部分上形成一个宽的槽34。可以看出，该槽的宽度基本上横跨该翼面部分32的整个弦长。在这种情况下，该槽34具有平行的侧表面44，46和平的基座或基座表面48。基座表面48与该基座或安装部分30的径向内表面50和径向外表面52平行。
技术熟练的人知道，从该基座或安装部分上除去的材料量取决于所希望的自然频率。这样，该槽的宽度“W”和深度“D”可根据需要改变，以达到该目标自然频率。另外，该槽34的侧面44、46不是必需为直线或平行，并且，该槽的深度“D”可以在该槽的平的基座表面48上改变。例如，表面44、46可以向相反方向弯曲(凸或凹形)，而该深度D可以在该槽的长度和/或宽度上线性或非线性地改变。通过作出一个或更多的尺寸和形状相同或不同的另外的槽，也可以达到所希望的频率。
为了调整翼面的自然频率，而从该定子叶片的基座或安装部分上除去材料为一种概念，它不但可适用于现有的压缩机定子叶片，而且可以用在压缩机定子叶片的开始设计和制造中。在现有的压缩机定子叶片中，能够使用本发明，则可以提供与生产一个翼面形状改变的新的定子叶片的正常循环比较，比较快速的与频率有关的问题的硬件解决方法。
虽然结合目前认为是最实际和优选的实施例说明了本发明，但应理解，本发明不是仅局限于所述的实施例，相反，在所附的请求保护书的精神和范围内，它涵盖各种改进和等同的结构。
零件表
压缩机定子叶片    10
基座或安装部分    12
翼面部分          14
侧表面            16，18
端面              20，22
径向内表面        24
径向外表面        26
压缩机定子叶片    28
基座或安装部分    30
翼面部分          32
宽的槽            34
侧表面            36，38
端面              40，42
侧表面            44，46
基座表面          48
径向内表面        50
径向外表面        52

Claims (10)

1. 一种调整具有一个基座部分(30)和一个翼面部分(32)的压缩机定子叶片(28)，以达到所希望的自然频率的方法，它包括：
a)鉴别该压缩机定子叶片的自然频率；
b)确定该压缩机定子叶片的不同的目标自然频率；和
c)从该压缩机定子叶片(28)的基座部分(30)上去除一定量和一定构形的材料，以达到该目标自然频率。
2. 如权利要求1所述的方法，其特征为，频率c)是通过在该基座部分上作出至少一条槽(34)来完成的。
3. 如权利要求2所述的方法，其特征为，所述的槽(34)具有平行的侧面(44，46)和基本上平的底面(48)。
4. 如权利要求3所述的方法，其特征为，所述的槽(34)具有固定不变的深度。
5. 如权利要求3所述的方法，其特征为，所述槽(34)具有固定不变的宽度。
6. 如权利要求2所述的方法，其特征为，所述槽(34)完全横穿该基座部分(30)的宽度。
7. 如权利要求7所述的方法，其特征为，所述基座部分(30)为矩形，具有一对较长的侧表面(36，38)，一对较短的端面(40，42)，一个径向内表面(50)和一个径向外表面(52)。
8. 如权利要求7所述的方法，其特征为，步骤c)是通过在该基座部分(30)上形成至少一条槽(34)来完成的。
9. 如权利要求8所述的方法，其特征为，所述槽(34)完全横穿所述基座部分(30)，从一个侧表面(36)至另一个侧表面(38)延伸。
10. 一种采用如权利要求1所述的方法制造的压缩机定子叶片(28)，该压缩机定子叶片包括一个翼面部分(32)和一个基座部分(30)，该基座部分(30)具有完整的矩形形状，并且横跨所述基座部分的宽度尺寸切出至少一条槽(34)，该槽(34)的尺寸被选成能得到该翼面部分的预定的自然频率。
CNB2005100626302A 2004-04-01 2005-04-01 频率调整的压缩机定子叶片和相关方法 Expired - Fee Related CN100419218C (zh)

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US10/814221 2004-04-01
US10/814,221 US7024744B2 (en) 2004-04-01 2004-04-01 Frequency-tuned compressor stator blade and related method

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CN100419218C true CN100419218C (zh) 2008-09-17

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104728170A (zh) * 2015-03-25 2015-06-24 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种压气机调频结构

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005006414A1 (de) * 2005-02-12 2006-08-24 Mtu Aero Engines Gmbh Verfahren zum Bearbeiten eines integral beschaufelten Rotors
GB0601837D0 (en) * 2006-01-31 2006-03-08 Rolls Royce Plc An aerofoil assembly and a method of manufacturing an aerofoil assembly
US7507073B2 (en) * 2006-02-24 2009-03-24 General Electric Company Methods and apparatus for assembling a steam turbine bucket
US7618234B2 (en) * 2007-02-14 2009-11-17 Power System Manufacturing, LLC Hook ring segment for a compressor vane
KR20090087930A (ko) * 2007-06-22 2009-08-18 미츠비시 쥬고교 가부시키가이샤 정익환 및 이것을 사용한 축류 압축기
US7854583B2 (en) * 2007-08-08 2010-12-21 Genral Electric Company Stator joining strip and method of linking adjacent stators
DE102007059155A1 (de) * 2007-12-06 2009-06-10 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Herstellung von in Integralbauweise ausgebildeten Laufrädern für Verdichter und Turbinen
US20100166550A1 (en) * 2008-12-31 2010-07-01 Devangada Siddaraja M Methods, systems and/or apparatus relating to frequency-tuned turbine blades
US8381379B2 (en) * 2009-04-17 2013-02-26 General Electric Company Apparatus and tools for use with compressors
US8534965B2 (en) * 2009-04-17 2013-09-17 General Electric Company Apparatus and tools for use with compressors
CA2761208C (en) 2010-12-08 2019-03-05 Pratt & Whitney Canada Corp. Blade disk arrangement for blade frequency tuning
US8757962B2 (en) * 2011-06-16 2014-06-24 General Electric Company System and method for adjusting a shroud block in a casing
CN104265681B (zh) * 2014-08-01 2016-08-31 中国人民解放军第五七一九工厂 改变叶片自身固有频率的方法
US10215194B2 (en) 2015-12-21 2019-02-26 Pratt & Whitney Canada Corp. Mistuned fan
CA2958459A1 (en) 2016-02-19 2017-08-19 Pratt & Whitney Canada Corp. Compressor rotor for supersonic flutter and/or resonant stress mitigation
US10533581B2 (en) 2016-12-09 2020-01-14 United Technologies Corporation Stator with support structure feature for tuned airfoil
US10823203B2 (en) 2017-03-22 2020-11-03 Pratt & Whitney Canada Corp. Fan rotor with flow induced resonance control
US10458436B2 (en) 2017-03-22 2019-10-29 Pratt & Whitney Canada Corp. Fan rotor with flow induced resonance control
US10480535B2 (en) 2017-03-22 2019-11-19 Pratt & Whitney Canada Corp. Fan rotor with flow induced resonance control
US10876417B2 (en) 2017-08-17 2020-12-29 Raytheon Technologies Corporation Tuned airfoil assembly
CN113606189B (zh) * 2021-08-23 2024-07-02 中国联合重型燃气轮机技术有限公司 压气机叶片及其调频槽口尺寸的确定方法、压气机和燃气轮机
US12043368B2 (en) 2022-03-23 2024-07-23 General Electric Company Rotating airfoil assembly

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3326523A (en) * 1965-12-06 1967-06-20 Gen Electric Stator vane assembly having composite sectors
US4014627A (en) * 1974-08-21 1977-03-29 Shur-Lok International S.A. Compressor stator having a housing in one piece
EP0384166A2 (en) * 1989-02-21 1990-08-29 Westinghouse Electric Corporation Compressor diaphragm assembly
US5429479A (en) * 1993-03-03 1995-07-04 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Stage of vanes free at one extremity

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4118147A (en) * 1976-12-22 1978-10-03 General Electric Company Composite reinforcement of metallic airfoils
JPS61192597U (zh) * 1985-05-24 1986-11-29
FR2619330B1 (fr) * 1987-08-12 1994-03-11 Snecma Procede de realisation d'etages de stator de compresseur ou de turbine, aubes et grilles d'aubes ainsi obtenues
US5123813A (en) * 1991-03-01 1992-06-23 General Electric Company Apparatus for preloading an airfoil blade in a gas turbine engine
US6375419B1 (en) * 1995-06-02 2002-04-23 United Technologies Corporation Flow directing element for a turbine engine
US5939006A (en) * 1995-06-28 1999-08-17 General Electric Company Method for forming a composite airfoil structure
US5720597A (en) * 1996-01-29 1998-02-24 General Electric Company Multi-component blade for a gas turbine
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
US5931641A (en) * 1997-04-25 1999-08-03 General Electric Company Steam turbine blade having areas of different densities
US6042338A (en) * 1998-04-08 2000-03-28 Alliedsignal Inc. Detuned fan blade apparatus and method
DE19905501B4 (de) 1999-02-10 2005-05-19 MediGene AG, Gesellschaft für molekularbiologische Kardiologie und Onkologie Verfahren zur Herstellung eines rekombinanten Adeno-assoziierten Virus, geeignete Mittel hierzu sowie Verwendung zur Herstellung eines Arzneimittels
JP2001012390A (ja) * 1999-06-24 2001-01-16 Hitachi Ltd ガスタービンの圧縮機翼
US6331100B1 (en) * 1999-12-06 2001-12-18 General Electric Company Doubled bowed compressor airfoil
US6398489B1 (en) * 2001-02-08 2002-06-04 General Electric Company Airfoil shape for a turbine nozzle
US6604285B2 (en) * 2001-06-07 2003-08-12 General Electric Company Method and apparatus for electronically determining nozzle throat area and harmonics
US6607358B2 (en) * 2002-01-08 2003-08-19 General Electric Company Multi-component hybrid turbine blade

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3326523A (en) * 1965-12-06 1967-06-20 Gen Electric Stator vane assembly having composite sectors
US4014627A (en) * 1974-08-21 1977-03-29 Shur-Lok International S.A. Compressor stator having a housing in one piece
EP0384166A2 (en) * 1989-02-21 1990-08-29 Westinghouse Electric Corporation Compressor diaphragm assembly
US5022818A (en) * 1989-02-21 1991-06-11 Westinghouse Electric Corp. Compressor diaphragm assembly
US5429479A (en) * 1993-03-03 1995-07-04 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Stage of vanes free at one extremity

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104728170A (zh) * 2015-03-25 2015-06-24 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种压气机调频结构

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US20050220615A1 (en) 2005-10-06

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