CN1936277A - 较少封闭的cmc导叶和平台的界面 - Google Patents

较少封闭的cmc导叶和平台的界面 Download PDF

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CN1936277A
CN1936277A CNA2006101388236A CN200610138823A CN1936277A CN 1936277 A CN1936277 A CN 1936277A CN A2006101388236 A CNA2006101388236 A CN A2006101388236A CN 200610138823 A CN200610138823 A CN 200610138823A CN 1936277 A CN1936277 A CN 1936277A
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stator
platform
interface
assembly parts
wing
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R·R·凯罗
N·巴特
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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
    • 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
    • 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
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F01D5/284—Selection of ceramic materials
    • 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
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2300/6033—Ceramic matrix composites [CMC]

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Materials Engineering (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

燃气轮机的定子导叶组合件包括一个被夹持在径向上内、外金属平台(38、14)之间的陶瓷基复合材料导叶(36)，其中在该导叶和该径向上内、外平台中至少一个之间的界面形状被制成一条曲折的泄漏路径供从燃气涡轮热燃气路径出来的燃气使用。

Description

较少封闭的CMC导叶和平台的界面
发明领域
本发明总的涉及涡轮喷嘴组合件，特别涉及第2级CMC喷嘴导叶的平台界面构形。
背景技术
高温构件如陶瓷基复合材料(ceramic matrix composite，即CMC)的喷嘴导叶和径向内、外金属连接件或平台之间的密封有很多问题，这些问题关系到与高热应力和缩短构件寿命；有关陡的热梯度，由于冷却空气产生的内部压力造成空气流动壁的扭曲；及由于过去密封的退化而引起的使性能随时间变化的腐蚀。而取消在CMC导叶和金属内、外平台之间的密封可造成一条热燃气吸收的敞开通道。因此，在CMC导叶和径向上内、外金属平台中的一个或两个的界面上就需要有一个新的几何结构，这种结构能适应陶瓷和金属构件匹配时固有的困难，并且也不再需要分开的和分散的密封元件。较少封闭的设计也就是不施加压力的导叶设计的同义语。
本发明概述
较少封闭设计成功的关键在于有控制的泄漏。依靠平台界面、导叶界面或两者的创新的界面形状可以提供有控制的泄漏。在本发明的示范实施例中，提供的创新的界面形状建立起曲折的燃气泄漏路径能增加流动阻力，造成所需的有控制的泄漏。
在这里说明的各个实施例中，CMC定子导叶(这里也被称为翼形壳或简称翼面)被装配在一对径向上内、外的金属平台之间，这两平台可在径向上用一对穿过翼形壳的梁互联。每一平台在其内面上制有适于接纳CMC翼形壳的翼形凹槽。这里所说的较少封闭的构状设计处在翼形壳上及/或在该内及/或外平台的翼形凹槽的贴近内周表面上。
在一个示范的实施例中，在每一个平台凹槽的内周表面和各贴近的翼形壳表面上制有匹配的台阶形接合部。
在第二个示范的实施例中，界面的形状设计为斜面接合部，即在每一个平台凹槽的邻接内周和各翼形壳表面的周围延伸着匹配的倾斜表面。
在第三个示范的实施例中，平台的翼形表面制有多个在侧向上伸出的可磨耗的刃边与翼形壳上贴近的光滑表面邻接。
在第四个示范的实施例中，在每一个平台凹槽的周面上设有一个弯曲的或弹性的界面以便与贴近翼形壳上相关的光滑表面接合。应该知道在弯曲界面的自由端或边缘面上还可如上所述制有台阶形接合部或斜面接合部以便与相关翼形壳上贴近的匹配表面邻接，从而提供所需的曲折迂回的路径。
因此，在一个方面，本发明所涉及的燃气轮机的定子导叶组合件包括一个被夹持在径向上内、外金属平台之间的陶瓷基复合材料翼面，其中该翼面和该径向内、外平台中的至少一个界面的形状被制成为来自燃气涡轮的热燃气路径提供一条曲折的泄漏路径。
在另一个方面，本发明所涉及的燃气轮机的定子导叶组合件包括一个被夹持在径向上内、外金属平台之间的陶瓷基复合材料翼面，其中每一个平台制有一个适于接纳翼形壳的凹槽，该凹槽的内周边的形状与该翼面上贴近表面配合形成该曲折的泄漏路径。
在还有另一个方面，本发明所涉及的燃气轮机的定子导叶组合件包括一个被夹持在径向上内、外金属平台之间的陶瓷基复合材料翼面，其中径向上内、外平台中至少一个与导叶的界面被制成柔顺形状与导叶上的光滑表面接合。
现在本发明将结合下面列出的附图详细说明：
附图的简要说明
图1为一CMC翼形壳和相关的用径向梁连接的内、外金属平台的透视分解图；
图2为一CMC翼形壳和一径向内金属平台的界面的基准形状的简图；
图3为按照本发明第一示范实施例的在一CMC翼形壳和一内金属平台之间的台阶形接合界面的简图；
图4为按照本发明第二示范实施例的在一CMC翼形壳和一内金属平台之间的斜面接合界面的简图；
图5为按照本发明第三示范实施例的在一CMC翼形壳和一内金属平台之间的可磨耗刃边界面的简图；
图6为按照本发明第四示范实施例的在一CMC翼形壳和一内金属平台之间的柔顺界面的简图；
图7为按照本发明第四示范实施例的在一CMC翼形壳和一内金属平台之间的复合的柔顺台阶形接合界面的简图；及
图8为按照本发明的第五示范实施例的在一CMC翼形壳和一内金属平台之间的复合的柔顺斜面接合界面的简图。
本发明的详细说明
参阅图1，其中以立体形式示出一个CMC翼形壳和金属平台的组合件10。具体点说，一对径向上内、外的金属平台12、14被一对径向梁16、18互联。在该金属平台表面24、26有一对翼形凹槽20、22分别被制出，这些凹槽的敞开侧互相面对。在该示范的实施例中，较大的梁具有空心通道可将冷却空气供到翼形壳28。在这方面，翼形壳28为一空心件，在装配时能被滑动地接纳在这些梁之上，翼形壳的两端可被接纳在凹槽20、22内。注意在该示范实施例中，平台12、14各制有两个凹槽，因此有一对邻近的翼形壳可被支持在内、外平台之间。
在一个可替代的配置中，梁16、18可被结合成一个单一的翼形通道，其大小还可做到接纳外面的翼形壳28，使它以合适的尺寸公差在其内作伸缩运动。
如图1所示，凹槽20、22被制成与翼形壳28互补的形状。应当知道，必须控制在翼形壳和平台凹槽之间的公差以免发生有害的过度振动，但同时要避免发生与构件间热的不匹配有关的问题。
转到图2，翼形壳28被概略地示出坐落在内金属平台24的翼形凹槽20内。该凹槽20由封闭的周边30限定，该周边与翼形壳28压力侧和吸气侧上的表面32、34对接。本图为下面说明的界面形状提供一个基准。在这方面，这里所说的独特的界面形状是在凹槽表面30和翼形壳在径向内平台24及/或径向外平台14上两个相对面32、34之间的界面上形成的。为了方便起见，只示出在径向内平台上的界面。
现在参阅图3，其中示出装配在内金属平台38上的CMC翼状壳36。在本例中，界面形状为台阶形接合部，其中侧向台阶40、42是在下平台凹槽44的周边43上形成的，垂直于通过导叶的中心线，与在翼形壳36下端形成的侧向肩46、48接合。注意这个配置允许翼形壳从下平台的下方插入。但翼形壳36在另一端的台阶接合部将被反转以便允许从一条路将该壳36安装到内、外平台之间。在各界面之间采用合适的公差，人们将会知道，任何一些从涡轮热燃气路径泄出的燃气必须会被迫沿着曲折的路径通过界面。这样就可建立所需的有控制的泄漏而可不需使用分立的密封元件。
现在参阅图4，其中示出另一个具有比图3的形状设计更简单的界面。具体地说，示出一个被装配在内金属平台52内的CMC翼形壳50。在这实施例中，径向内平台凹槽54被制有一个与通过翼形壳50的径向中心线倾斜成约45°角的周边面。同时，翼形壳50的下表面58也被制成相似的角度。这样在翼形壳和内平台52之间形成一个斜面接合部。这里再一次，为了便于在一个方向上安装，在翼形壳上端的界面将被反转。
在图5中示出还有另一个实施例，其中CMC翼形壳58被坐落在内金属平台60的凹槽62内。在这实施例中，在平台60内的凹槽62的周边63是由多个在径向上互相间隔开、向内突出而可磨耗的刃边64(图中示出四个)构成。该刃边界面64与翼形壳58上的光滑表面邻接，两者之间设有合适的公差。这里再一次可以知道可用通过平台的曲折路径使对燃气泄漏的阻力增加。
在图6中，在CMC翼形壳68和内金属平台70之间设有柔顺的界面。在这实施例中，在内平台凹槽72的周边上制有在径向上延伸而方向相反的切口或槽74、76，结果可使该凹槽72的边80起到具有弹簧性质的作用，从而可与翼形壳的邻近的光滑表面作柔顺的或弹性的“接合”(即只有极小的间隙)。为了引入前几个实施例的曲折的泄漏燃气特性，可以改进平台凹槽72周边80的形状，引入图3中的台阶形接合部或图4中的斜面接合部。这些可替代的界面形状分别概略地在图7和图8中示出。具体地说，图7示出一个柔顺的台阶形接合部，其中CMC翼形壳82被坐落在内金属平台86的凹槽84内，而柔顺的凹槽边88(由槽90形成)制有一个台阶形接合部92，该部可与翼形壳上互补的台阶形接合部94对接。
在图8中，CMC翼形壳96被坐落在内金属平台100的凹槽98内，凹槽84的边102(由槽104形成)制有一个角度表面106，该表面与翼形壳96上的互补的角度周面108对接，这样在界面上形成一个柔顺的斜面接合部。
由于提供增加的流动阻力而得到有控制的泄漏，因此能消除陡峭的热梯度，相关地可减少热应力，提高构件寿命；减除冷却空气产生的内部压力，CMC导叶可用较薄的壁断面；并且由于没有密封件的退化可得到经久一致的功效。
虽然本发明已结合目前认为最实用和较好的实施例说明，但应知道本发明并不仅限于已公开的实施例，而是应该覆盖包括在权利要求书的精神和范围内的各种修改和等同的配置。

Claims (10)

1.一种燃气轮机定子导叶组合件，包括一个被夹持在径向内、外金属平台(38、14)之间的陶瓷基复合材料翼面(36)，其中将在所说翼面和所说径向上内、外平台中至少一个界面形状制成为来自燃气涡轮的燃气形成一条曲折的泄漏路径。
2.权利要求1的定子导叶组合件，其特征在于，所说界面为匹配的台阶形表面(40、42)。
3.权利要求1的定子导叶组合件，其特征在于，所说界面为匹配的斜面接合部(56、58)。
4.权利要求1的定子导叶组合件，其特征在于，所说界面在所说径向内平台上具有多个可磨耗的刃边(64)，与在所说翼面上的光滑表面(66)贴近。
5.权利要求1的定子导叶组合件，其特征在于，所说界面位于所说径向内平台(38)上。
6.权利要求5的定子导叶组合件，其特征在于，第二个基本相同的界面位于所说径向外平台(14)上。
7.权利要求2的定子导叶组合件，其特征在于，所说匹配的台阶形表面(40、42)包括至少两个垂直于通过所说导叶的径向中心线的台阶。
8.权利要求3的定子导叶组合件，其特征在于，所说斜面接合部包括与通过所说导叶的径向中心线成约45°角的匹配表面(56、58)。
9.权利要求4的定子导叶组合件，其特征在于，所说多个可磨耗的刃边(64)具有至少四个终止于径向表面的突出部，与所说导叶上的光滑表面(66)贴近。
10.一种燃气轮机的定子导叶组合件，包括一个被夹持在径向上内、外金属平台(38、14)之间的陶瓷基复合材料翼面(16)，其中每一个所说平台制有一个适于接纳所说内、外平台的凹槽，每一凹槽包括一个周边，所说周边的形状被制成与所说翼面上的贴近表面配合，形成所说曲折的泄漏路径。
CNA2006101388236A 2005-09-19 2006-09-19 较少封闭的cmc导叶和平台的界面 Pending CN1936277A (zh)

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US11/228251 2005-09-19
US11/228,251 US7329087B2 (en) 2005-09-19 2005-09-19 Seal-less CMC vane to platform interfaces

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Cited By (3)

* Cited by examiner, † Cited by third party
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CN102213108A (zh) * 2010-04-06 2011-10-12 通用电气公司 复合型涡轮轮叶组件
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US7329087B2 (en) 2008-02-12
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EP1764481A3 (en) 2008-12-17
US20070065285A1 (en) 2007-03-22

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