CN100343488C - 在闭式涡轮叶片上中心定位的刀齿 - Google Patents

在闭式涡轮叶片上中心定位的刀齿 Download PDF

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CN100343488C
CN100343488C CNB2004800098659A CN200480009865A CN100343488C CN 100343488 C CN100343488 C CN 100343488C CN B2004800098659 A CNB2004800098659 A CN B2004800098659A CN 200480009865 A CN200480009865 A CN 200480009865A CN 100343488 C CN100343488 C CN 100343488C
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cutter tooth
shade
aerofoil
sealing
turbine blade
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CN1774560A (zh
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约翰·P·厄本
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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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F01D11/122—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 with erodable or abradable material
    • F01D11/125—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 with erodable or abradable material with a reinforcing structure
    • 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
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/20—Rotors
    • F05B2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05B2240/31—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor of changeable form or shape
    • 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
    • F05D2240/55—Seals
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/602—Drainage
    • F05D2260/6022—Drainage of leakage having past a seal

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

遮罩(12)包括在该翼面末梢处在该遮罩的前端和后端之间连续延伸的密封件(24)。刀齿(32)大致提供在该遮罩的中间并且大致与穿过该翼面(12)重心的线径向对齐。这样，由于该遮罩的运动产生的任何力矩臂被消除或最小化了，从而降低了该遮罩和该翼面末梢之间的倒角区域的应力，因此增加了该叶片的蠕变寿命。

Description

在闭式涡轮叶片上中心定位的刀齿
技术领域
本发明涉及一种具有翼面末梢遮罩的涡轮叶片，尤其涉及一种具有末梢密封件的遮罩和沿叶片旋转方向定位在该遮罩相对端中间的刀齿。
背景技术
涡轮叶片的翼面经常提供有末梢遮罩。该遮罩可防止翼面在高度疲劳下由于振动应力引起的破坏。通常提供有从该遮罩外表面径向向外突出并且沿涡轮转子旋转方向在遮罩的相对端之间延伸的密封件。末梢遮罩密封件照常规延伸入成型在对立于旋转末梢遮罩的固定遮罩内的槽中。该固定遮罩具有蜂窝通道。胜于在该末梢遮罩和该固定遮罩之间提供导致该翼面不稳定的零公差密封件，已经发现可以在该末梢遮罩上提供泄露通道，这将去除这样的不稳定。典型地，刀齿提供在该末梢遮罩的前缘以在该固定遮罩的蜂窝内切割出宽于该末梢密封件宽度的槽。这在延伸于槽内的密封件对立侧的高低压力区域之间实现了泄流。虽然这不利地导致了由于密封能力的下降所致的穿过该翼面的压力降被降低，但是效率的牺牲通过翼面稳定性的增加得以补偿。
然而，因为该齿的重量没有定位在与该翼面的重心相同的径向线上，所以发现沿着该翼面和该末梢遮罩之间的倒角区域出现了高应力。这种在高温下增加的应力导致了该遮罩的高蠕变率，并最终可能导致该遮罩的破坏，例如，破裂或劈裂。应该理解，单个叶片遮罩的破坏会导致涡轮机必然离线。因此，由于该末梢遮罩和该翼面之间的倒角区域处增加的应力所致的遮罩破坏需要耗时和昂贵的维修，包括使涡轮机离线，即除实现维修所必需的人力和替换部件外的停工时间。
发明内容
根据本发明的优选实施例，翼面末梢遮罩上的刀齿位于该遮罩相对端的中间，并且优选地与该翼面的质量中心大致径向对齐。因此，该刀齿沿周向大致位于该遮罩长度的中间并且紧邻穿过该叶片重心的径向线。因此，处于该遮罩中心的该刀齿使该刀齿的质量与贯穿该翼面重心的径向线更加一致。这就最小化了由该刀齿的额外重量产生的力矩，导致了更低的倒角应力。该降低的应力延长了该倒角的蠕变寿命，该倒角常常是该部件的寿命极限位置。
在根据本发明的优选实施例中，提供了一种涡轮叶片，包括具有末梢遮罩的翼面，从所述遮罩径向向外突出并且沿所述翼面围绕涡轮轴的旋转方向在该遮罩的端部边缘之间连续延伸的密封件，由所述遮罩支撑并且沿通常平行于该涡轮轴的方向突出到所述密封件至少一侧的刀齿，用以切割相对固定的遮罩内的槽，所述刀齿沿该密封件的方向具有短于该密封件长度的分立长度并且位于该遮罩末端的中间。
在根据本发明的其他优选实施例中，提供了一种涡轮叶片，包括具有末梢遮罩的翼面，从所述遮罩径向向外突出并且沿所述翼面围绕涡轮轴的旋转方向在该遮罩的端部边缘之间连续延伸的密封件，由所述遮罩支撑并且沿通常平行于该涡轮轴的方向突出到所述密封件至少一侧的刀齿，用以切割相对固定的遮罩内的槽，所述刀齿沿该密封件的方向具有短于该密封件长度的分立长度并且大致位于该密封件长度的中间。
在根据本发明的其他优选实施例中，提供了一种涡轮叶片，包括具有末梢遮罩的翼面，从所述遮罩径向向外突出并且沿所述翼面围绕涡轮轴的旋转方向在该遮罩的端部边缘之间连续延伸的密封件，由所述遮罩支撑并且沿通常平行于该涡轮轴的方向突出到所述密封件至少一侧的刀齿，用以切割相对固定的遮罩内的槽，所述刀齿沿该密封件的方向具有短于该密封件长度的分立长度并且放置得大致与穿过该翼面重心的径向线径向对齐。
附图说明
图1是根据现有技术的具有密封件和刀齿的遮罩的径向向内的视图；
图2是大致关于图1中线2-2所做的剖视图；和
图3是与图1相似的视图，图示了根据本发明优选实施例的刀齿的位置。
具体实施方式
现在参阅图1，其中图示了安装在翼面12末梢的遮罩10。图示的遮罩10位于相邻翼面末梢的相邻遮罩14和16之间。翼面12和形成其一部分的叶片的旋转方向由箭头18指示，旋转轴由箭头20指示。应该理解的是，相邻的遮罩没有相互连接。而是，相邻的遮罩沿它们的配准端形状22相互支撑。
参阅图1和2，遮罩10包括一般径向定向的密封件24，用以密封成型在相邻固定遮罩28(图2)内的槽26。典型地，该固定遮罩包括蜂窝结构30。因此，该密封件24在翼面12的相对侧上提供了差压。
为了消除由于密封件24啮合在蜂窝30内引起的翼面不稳定，并在密封件24相对各侧的高低压区域之间建立连接通道，刀齿32沿转子的旋转方向形成在遮罩10的前缘。该刀齿32沿旋转方向在密封件24的相对各侧在该密封件和遮罩的前缘处包括侧向扩大部。因此，该刀齿32扩大了固定遮罩蜂窝内的槽26的轴向广度或宽度，从而在除刀齿32之外的区域中提供了穿过该密封件24的由图2中箭头所示的泄漏通道。该泄漏通道微弱地减小了压差并随之引起效率损失，然而，该效率损失通过增加的稳定性和由于应力降低而改善的蠕变寿命得以补偿。
现在参阅图3并根据本发明的优选实施例，其中提供了一种相似地安装在翼面42末梢的遮罩。该遮罩40的前缘和后缘成型得与图1的现有技术中所示的相似。然而在本实施例中，刀齿44放置在该遮罩40相对端的中间，并且优选地大致在该遮罩40长度的中间。如图所示，该刀齿44径向地覆盖在该翼面42的中心部分。这样，该刀齿44大致与横贯该翼面重心的径向线径向对齐。这使得由刀齿的额外重量产生的任何力矩被最小化，并且因此在该遮罩和该翼面末梢的接合处产生更低的倒角应力。更低的倒角应力依次延长了蠕变寿命，该蠕变寿命经常是该部件的极限寿命位置。
该刀齿44的功能与现有技术的刀齿26相同。然而，大致处于该遮罩中间并且大致与穿过该翼面重心的半径一致的该刀齿44的位置不仅提供了现有刀齿的优点，而且降低了倒角区域的应力并且从而增加了蠕变寿命。
虽然本发明已经结合目前被认为是最实用的和最优选的实施例进行了描述，但是应该理解，本发明不限于公开的实施例，相反，本发明想要覆盖包括在所附权利要求的实质和范围内的各种修改和等价布置。

Claims (12)

1.一种涡轮叶片，包括：
具有末梢遮罩的翼面；
从所述遮罩径向向外突出并且沿所述翼面围绕涡轮轴的圆周旋转方向在该遮罩的各末梢边之间连续延伸的密封件；
沿所述密封件由所述遮罩支撑并且沿大致平行于该涡轮轴的方向突出到所述密封件的径向相对侧的刀齿，用于切割槽，该槽与相对固定遮罩内的所述刀齿基本一致；
所述刀齿沿该密封件的方向具有短于该密封件长度的长度并且位于该遮罩相对端的中间部分。
2.如权利要求1所述的涡轮叶片，其中所述刀齿大致位于该密封件长度的中间部分附近。
3.如权利要求1所述的涡轮叶片，其中所述刀齿定位得与所述翼面的一部分径向对齐。
4.如权利要求1所述的涡轮叶片，其中所述刀齿大致位于该密封件长度的中间，所述刀齿突出到该密封件的相对侧。
5.如权利要求1所述的涡轮叶片，其中所述刀齿定位得与所述翼面的一部分径向对齐，所述刀齿突出到该密封件的相对侧。
6.如权利要求1所述的涡轮叶片，其中所述刀齿大致上与穿过翼面重心的径向线径向对齐。
7.一种涡轮叶片，包括：
具有末梢遮罩的翼面；
从所述遮罩径向向外突出并且沿所述翼面围绕涡轮轴的圆周旋转方向在该遮罩的各末梢边之间连续延伸的密封件；
沿所述密封件由所述遮罩支撑并且沿大致平行于该涡轮轴的方向突出到所述密封件的径向相对侧的刀齿，用于切割槽，该槽与相对固定遮罩内的所述刀齿基本一致；
所述刀齿沿该密封件的方向具有短于该密封件长度的长度并且大致上位于所述密封件长度的中间部分附近。
8.如权利要求7所述的涡轮叶片，其中所述刀齿定位得与所述翼面的一部分径向对齐。
9.如权利要求7所述的涡轮叶片，其中所述刀齿定位得与所述翼面的一部分径向对齐，所述刀齿突出到该密封件的相对侧。
10.如权利要求7所述的涡轮叶片，其中所述刀齿放置得大致与穿过该翼面重心的径向线径向对齐。
11.一种涡轮叶片，包括：
具有末梢遮罩的翼面；
从所述遮罩径向向外突出并且沿所述翼面围绕涡轮轴的圆周旋转方向在该遮罩的各末梢边之间连续延伸的密封件；
沿所述密封件由所述遮罩支撑并且沿通常平行于该涡轮轴的方向突出到所述密封件的径向相对侧的刀齿，用以切割相对固定遮罩内的槽；
所述刀齿沿该密封件的方向具有短于该密封件长度的长度并且放置得大致与穿过该翼面重心的径向线径向对齐。
12、如权利要求11所述的涡轮叶片，其中所述刀齿大致位于该密封件长度的中间部分附近。
CNB2004800098659A 2003-04-18 2004-04-15 在闭式涡轮叶片上中心定位的刀齿 Expired - Fee Related CN100343488C (zh)

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US10/418,116 US6805530B1 (en) 2003-04-18 2003-04-18 Center-located cutter teeth on shrouded turbine blades
US10/418,116 2003-04-18

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CN100343488C true CN100343488C (zh) 2007-10-17

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JP (1) JP2006523803A (zh)
KR (1) KR20060003358A (zh)
CN (1) CN100343488C (zh)
CZ (1) CZ2005655A3 (zh)
DE (1) DE112004000657T5 (zh)
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JP2006523803A (ja) 2006-10-19
KR20060003358A (ko) 2006-01-10
CN1774560A (zh) 2006-05-17
US20040208743A1 (en) 2004-10-21
CZ2005655A3 (cs) 2006-03-15

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