CN103527517A - 用于燃气涡轮的压缩机 - Google Patents

用于燃气涡轮的压缩机 Download PDF

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CN103527517A
CN103527517A CN201310264743.5A CN201310264743A CN103527517A CN 103527517 A CN103527517 A CN 103527517A CN 201310264743 A CN201310264743 A CN 201310264743A CN 103527517 A CN103527517 A CN 103527517A
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compressor
central ring
blade
housing
rotor
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T.斯特芬
M.劳奇
M.科拉迪
B.维斯
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General Electric Technology GmbH
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Alstom Technology AG
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/02—Gas-turbine plants characterised by the use of combustion products as the working fluid using exhaust-gas pressure in a pressure exchanger to compress combustion-air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/057—Control or regulation
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • 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
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • 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
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49236—Fluid pump or compressor making
    • Y10T29/49238—Repairing, converting, servicing or salvaging

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

本发明涉及用于燃气涡轮的压缩机。具体而言，一种尤其用于燃气涡轮的压缩机(10)，包括围绕轴线(17)旋转的转子(15)和同轴地包绕所述转子(15)的壳体(11)，从而限定了用于待压缩的流体的在转子(15)与壳体(11)之间的流动通道(14)，由此交替的成排的静叶(13)和叶片(16)布置在流动通道(14)内，静叶(13)安装于壳体(11)的内壁，且叶片(16)安装于转子(15)的外壁。通过将中间环(18)设在相邻的成排的静叶(13)之间的壳体(11)的内壁中，从而实现了快速可更换性和/或修理与便利的重新调节机器的结合，使得流动通道(14)的外壁实质上由所述静叶(13)和中间环(18)形成。

Description

用于燃气涡轮的压缩机
技术领域
本发明涉及燃气涡轮技术。其涉及根据权利要求1的前序部分的压缩机。其还涉及用于对如此的压缩机进行修理和/或改变几何形状和/或保养的方法。
背景技术
根据现有技术，燃气涡轮(GT)压缩机的静止部分由壳体(且或许静叶载体)和压缩机静叶构成。压缩机的流动通道直接由壳体(且或许静叶载体)和转子构成。图1中示出了示例性的现有技术的压缩机的静止部分。
图1中的压缩机10'包括壳体11'，壳体11'同轴地包绕转子(未示出)。壳体11'与转子之间的环状中间空间为流动通道14'，待压缩的流体(例如，空气)流过该流动通道14'。壳体11'配备有多个(静止)静叶13'，静叶13'成排地以间隔关系布置。一排(旋转)叶片(未示出)设在两排相邻的静叶13'之间，叶片安装于转子上。如可从图1中容易地看到那样，流动通道14'的几何形状一方面由静叶13'(在成排的静叶13'的区域中)的平台确定，而另一方面由壳体(在相邻的成排的静叶13'之间的区域中)的内壁确定。
对于图1中所示类型的压缩机，以下几点导致了比所需更长的停工时间：
·壳体11'的内壁处的运转的叶片出现的擦痕的修理几乎不可能实现或难以实现；
·对于潜在的压缩机升级(更大的环隙空间等)，整个压缩机壳体11'需要改造或替换。
此外，由于壁处的叶片的可能的刮擦不是最佳的且可导致叶片损坏等，故不可减小壳体与压缩机叶片之间的公差。因此，泄漏比所需的更大，且GT的效率未达到最大可能值。
发明内容
本发明的一个目的在于提供一种用于燃气涡轮的压缩机，其没有现有技术的前述缺陷，且将快速可更换性和/或修理与便利的重新调节机器结合。
本发明的另一个目的在于提供一种用于对如此的压缩机进行修理和/或改变几何形状和/或保养的方法。
这些和其它目的通过根据权利要求1所述的压缩机和根据权利要求10所述的方法达到。
根据本发明的压缩机包括围绕轴线旋转的转子和同轴地包绕所述转子的壳体，从而限定转子与壳体之间的流动通道来用于待压缩的流体，由此交替的成排的静叶和叶片布置在流动通道内，静叶安装于壳体的内壁，且叶片安装于转子的外壁。
其特征在于，中间环设在相邻的成排的静叶之间的壳体的内壁中，使得流动通道的外壁实质上由所述静叶与中间环形成。
根据本发明的实施例，所述中间环邻近叶片的末端。
具体而言，所述中间环在其与叶片的末端刚好相对的内侧上载有涂层。
更具体而言，所述涂层为可磨耗涂层。
甚至更具体而言，中间环的内侧被所述可磨耗涂层完全地覆盖。
根据本发明的另一个实施例，中间环的内侧仅在与相应的叶片的末端相对的区域中仅被所述可磨耗涂层覆盖。
根据本发明的另一个实施例，所述可磨耗涂层包括填充有可磨耗材料的蜂窝结构。
根据本发明的另一个实施例，中间环安装于设在壳体的内壁中的周向安装凹槽。
根据本发明的另一个实施例，中间环沿周向方向分段。
根据本发明的方法的特征在于，中间环被更换和/或从压缩机移除、进行处理并放回到压缩机中。
根据发明性方法的另一个实施例，流动通道的外径在升级中通过更换中间环和静叶而增加。
附图说明
现在借助于不同实施例且参照附图来更近一步阐释本发明。
图1示出了根据现有技术的燃气涡轮的压缩机的一部分；
图2示出了根据本发明的实施例的燃气涡轮的压缩机的一部分，由此将示出中间环的细节放大；以及
图3示出了具有可磨耗涂层的中间环的三个不同实施例。
具体实施方式
本发明的中心构想在于借助压缩机叶片和布置在连续的成排的叶片之间的中间环来限定燃气涡轮压缩机的流动通道。通过关于通道几何形状的该灵活性，增加了所使用的材料的范围和耐用性。
图2示出了根据本发明的实施例。图2中的压缩机10包括围绕机器轴线17旋转的转子15。壳体11同轴地包绕转子15，从而限定转子15与壳体11之间的环状流动通道14。压缩机10的叶片包括成排的旋转叶片16和静止静叶13的交替布置。静叶13被设在壳体11的内壁中的周向安装凹槽12收纳。叶片16安装于转子15上。与叶片16的末端相对，中间环18被相应的安装凹槽22收纳，使得流动通道14在其外侧借助于静叶13和中间环18而被完全地限定。
作为该构造的结果，压缩机的环隙空间可在随后的时间通过简单地更换静叶13和中间环18而增加。图2中示出了大致不同于原有轮廓19的相应的升级的轮廓20。代替更换中间环18，中间环18可改造成具有更大的直径。
通过将各个中间环分成多个节段来减轻中间环的这样分解和/或更换。节段的数目取决于情形。
图3示出了用于涂布中间环节段的三个不同选择(a)、(b)和(c)。例如，这些涂层允许减小压缩机10内的泄漏，从而增加燃气涡轮的效率。图3(a)中的中间环18a的涂层21a包括填充有可磨耗材料的蜂窝结构。图3(b)中的中间环18b的涂层21b为完全地覆盖中间环节段的内壁的可磨耗涂层。图3(c)中的中间环18c的涂层21c为仅覆盖中间环节段的内壁的该部分的可磨耗涂层，该可磨耗涂层实际上与旋转叶片的末端相对。
为了在压缩机的流动通道14处修理压缩机或通过改变其几何形状而将其升级，中间环18(且或许静叶13)可从压缩机移除且相应地改造，或被不同的环(静叶的环)替换。
新压缩机设计的优点为：
·快速组装、分别更换性；
·容易实现不同的几何形状(更大的环隙空间等)；
·容易实现接触表面的重新调节；
·如果需要，则椭圆磨削刚好对于中间环是可能的(或可适合)，代替了整个壳体(以补偿壳体部分组装期间的变形)；
·容易实现对于插入环的内表面的可能的可磨耗涂层或其它选择；
·用于更高质量流的潜在压缩机升级"仅"需要新静叶和中间环。将不需要新壳体或改造的壳体；
·由于更少的接触表面而有更佳的压缩机壳体热性能；
·允许了备选材料结合(例如，不同的热膨胀或摩擦系数)；
·在转子就位的情况下的环的可更换性；
·在潜在压缩机损坏的情况下，可很快完成修正，因为部分"仅"需要替换而代替了改造等；
·高灵活性。
部件列表
10、10'：压缩机
11、11'：壳体
12、12'：安装凹槽(静叶)
13、13'：静叶
14、14'：流动通道
15：转子
16：叶片
17：轴线
18、18a-18c：中间环
19：第一升级轮廓
20：第二升级轮廓
21、21a-21c：涂层
22：安装凹槽(中间环)

Claims (11)

1. 一种压缩机(10)，尤其用于燃气涡轮，所述压缩机包括围绕轴线(17)旋转的转子(15)和同轴地包绕所述转子(15)的壳体(11)，从而限定用于待压缩的流体的在转子(15)与壳体(11)之间的流动通道(14)，由此交替成排的静叶(13)和叶片(16)布置在所述流动通道(14)内，所述静叶(13)安装于所述壳体(11)的内壁，且所述叶片(16)安装于所述转子(15)的外壁，其特征在于，中间环(18、18a-18c)设于相邻成排的静叶(13)之间的所述壳体(11)的内壁，使得所述流动通道(14)的外壁实质上由所述静叶(13)和中间环(18、18a-18c)形成。
2. 根据权利要求1所述的压缩机，其特征在于，所述中间环(18、18a-18c)邻近所述叶片(16)的末端。
3. 根据权利要求2所述的压缩机，其特征在于，所述中间环(18、18a-18c)在其刚好与所述叶片(19)的末端相对的内侧上载有涂层(21、21a-21c)。
4. 根据权利要求3所述的压缩机，其特征在于，所述涂层(21、21a-21c)为可磨耗涂层。
5. 根据权利要求4所述的压缩机，其特征在于，所述中间环(18、18a、18b)的内侧被所述可磨耗涂层(21、21a、21b)完全覆盖。
6. 根据权利要求4所述的压缩机，其特征在于，所述中间环(18、18a、18b)的内侧仅在与所述相应的叶片(16)的末端相对的区域中仅被所述可磨耗涂层(21c)覆盖。
7. 根据权利要求4所述的压缩机，其特征在于，所述可磨耗涂层(21a)包括填充有可磨耗材料的蜂窝结构。
8. 根据权利要求1至7中的一项所述的压缩机，其特征在于，所述中间环(18、18a-18c)安装于设在所述壳体(11)的内壁中的周向安装凹槽(22)。
9. 根据权利要求1至8中的一项所述的压缩机，其特征在于，所述中间环(18、18a-18c)沿周向方向分段。
10. 一种用于对根据权利要求1至9中的一项所述的压缩机(10)进行修理和/或改变几何形状和/或保养的方法，其特征在于，所述中间环(18、18a-18c)被更换和/或从所述压缩机(10)移除、进行处理并放回到所述压缩机(10)中。
11. 根据权利要求10所述的方法，其特征在于，所述流动通道(14)的外径在升级中通过更换所述中间环(18、18a-18c)和静叶(13)而增加(20)。
CN201310264743.5A 2012-06-28 2013-06-28 用于燃气涡轮的压缩机 Pending CN103527517A (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP12004855.8A EP2679777A1 (en) 2012-06-28 2012-06-28 Compressor for a gas turbine and method for repairing and/or changing the geometry of and/or servicing said compressor
EP12004855.8 2012-06-28

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CN103527517A true CN103527517A (zh) 2014-01-22

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