CN104487657A - 用于制造导向叶片的方法以及导向叶片 - Google Patents
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- F05D2230/00—Manufacture
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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Abstract
一种用于制造具有叶身(149)和叶根(145)的涡轮机叶片(130)的方法,所述方法应当用于实现涡轮机的更高的效率。对此,所述方法包括下述步骤:a)将叶身(149)和叶根(145)作为单独的构件制造;b)将冷却空气开口(151)引入到叶身(149)中;和c)在步骤b)之后将叶身(149)和叶根(145)接合。
Description
技术领域
本发明涉及一种用于制造具有叶身和叶根的涡轮机叶片的方法。本发明还涉及这种涡轮机叶片。
背景技术
涡轮机是将流动的流体(液体或气体)的内能(焓)转换成旋转能并且最终转换成机械的驱动能的流体机械。通过尽可能无涡流地层状地环流涡轮机叶片,从流体流中抽取其内能的一部分,这部分转移到涡轮机的转子叶片上。随后,经由所述内能将涡轮机轴置于转动,将可用的功率输出到耦联的做功机械上,例如输出到发电机上。转子叶片和轴是涡轮机的可运动的转子或旋转体的一部分,所述转子或旋转体设置在壳体之内。
通常,多个叶片安装在轴上。在一个平面中安装的转子叶片分别形成叶轮或转动轮。叶片轻微弯曲地成型,类似于机翼。在每个转动轮上游通常存在导向轮。所述导向轮从壳体伸入到流动的介质中并且将所述介质置于涡旋。在导向轮中产生的涡旋(动能)在随后的转动轮中用于将其上安装有转动轮叶片的轴置于旋转。
导向轮和转动轮共同表示成级。通常,依次接入多个这种级。因为导向轮静止,所以其导向叶片能够固定在壳体内部和壳体外部上,从而为转动轮的轴提供支承件。
涡轮机的导向叶片和转子叶片除了具有以空气动力学的方式作用的本来的叶身之外通常具有叶根,所述叶根也称作为平台,所述叶根相对于叶身扩宽并且具有固定设备以用于将相应的叶片例如固定在转子上或固定在壳体上。叶根和叶身通常在制造过程中一件式地共同浇铸并且随后被金属涂覆。
为了冷却涡轮机的、尤其是燃气轮机的加载热气的构件,此外使用薄膜冷却。这也适用于涡轮机叶片。在此,通过柱形的或扩散器类型的冷却空气开口,冷却介质——典型为空气——被引导到要冷却的表面上,以便形成进行保护的冷却薄膜。通过冷却空气开口相对于表面根据局部的流动关系沿着流线倾斜,得到最优的冷却效率。
在制造过程中,冷却空气孔通常通过激光或腐蚀法引入。在涡轮机导向叶片中,在叶身到平台的过渡的区域中,由于在那里出现的凹状的棱边,激光或腐蚀工具的接近在很大程度上受到限制。在叶身的压力侧和平台之间具有小于90°的角度的三维成形的叶身以及通过二次流动效应影响的流线使引入最优定向的冷却空气孔变得不可能。
因为引入最优定向的孔在冷却效率最大的情况下迄今是不可能的,变差的冷却效果必须通过增多数量的并非最优的孔来补偿。由此,冷却空气消耗增多并且叶片组的空气动力学的效率减小。这二者都引起涡轮机效率变差。
发明内容
因此,本发明的目的是,阐明一种用于制造涡轮机叶片的方法以及一种涡轮机叶片,借助其能够实现涡轮机的更高的效率。
关于方法,所述目的根据本发明通过下述方法来实现,所述方法包括下述步骤:
a)将叶身和叶根作为单独的构件制造,
b)将至少一个冷却空气开口引入到叶身或叶根中或者
引入至少两个开口,其中各至少一个开口设置在叶根和叶身中,以及
c)在步骤b)之后将叶身和叶根接合。
在此,本发明基于下述考虑:通过下述方式改进涡轮机的效率,即,能够将冷却空气孔刚好在从叶身到平台的过渡区域中关于环流的介质的流线最优地引入。然而,这仅在用于引入开口的相应的工具具有足够的运动自由度的情况下是可能的。这能够在将平台或叶根和叶身作为分开的构件制造并且在引入开口时才进行接合的情况下实现。因此,能够分别以任意的流线最优的布置将开口在没有被叶根阻碍的情况下引入到叶身中或者将开口在没有被叶身阻碍的情况下引入到叶根中。
在有利的设计方案中,制造叶根和/或叶身通过浇铸进行。由此,以具有小的错误公差的精确的形状确保构件的制造。
引入冷却空气开口有利地通过激光和/或借助于电火花腐蚀进行。由此,能够尤其简单地控制开口的轴线还有其形状。
在有利的设计方案中,冷却空气开口的轴线在叶身的外侧上指向叶根或者冷却空气开口的轴线在叶根的外侧上指向叶身。这种开口刚好在叶身和平台之间的凹状的棱边的区域中是必需的,以便确保冷却空气流沿着热气流线的最优的定向。所述开口同时借助所述方法尤其简单地制造,因为引入工具不被叶根阻碍并且所述引入工具可自由运动。
在其他的有利的设计方案中,该方法包括附加的步骤:
d)用覆层对叶根和叶身的区域涂覆。
由此在将叶根和叶身接合之后能够施加闭合的覆层,所述覆层提高构件的热学的和/或机械的耐抗性。
在此,可能有问题的是,在所述方法中,在引入冷却开口之后才进行涂覆。在此,能够出现冷却空气开口的局部堵塞。如果冷却空气孔的轴线与涂覆方向相反地定向,那么使所述风险最小化。有利地,然而,冷却空气开口锥形地构造。由此,孔之内的金属层不会影响冷却空气穿流。尤其在借助于激光引入时,柱形的设计方案在没有较大的耗费的情况下是可能的。
在方法的替选的或附加的设计方案中,所述方法包括附加的步骤:
e)将冷却空气开口上的覆层通过激光和/或借助于电火花腐蚀移除。
因为在此不再进行深的钻孔、而是仅进行表面移除,所以不需要工具的大的可运动性,使得也能够在构件的组合和覆层之后进行移除。对此,仅需要了解开口的准确位置。
涡轮机叶片有利地借助所述方法制造。
关于涡轮机叶片,所述目的通过下述方式解决:涡轮机叶片包括叶身和叶根,其中叶身具有冷却空气开口,所述冷却空气开口的轴线在叶身的外侧上指向叶根。
涡轮机有利地包括这种涡轮机叶片。
借助本发明实现的优点尤其在于,通过在浇铸之后在单独的叶身上引入冷却空气开口,实现关于开口的轴线的定向的尤其高的灵活性,使得冷却孔能够沿着热气的流线最优地定向,冷却效率进而还有涡轮机的效率提高。通过所述方法,也能够有效地冷却最复杂的3D几何形状。
附图说明
根据附图详细阐述本发明。在附图中示出:
图1示出燃气轮机的部分纵剖图,
图2示出根据现有技术的导向叶片的俯视图,
图3示出根据现有技术的导向叶片的剖视图,
图4示出具有在将叶身和叶根组合之前引入的冷却孔口的导向叶片的俯视图,以及
图5示出具有在将叶身和叶根组合之前引入的冷却孔口的导向叶片的剖视图。
相同的部件在所有附图中设有相同的附图标记。
具体实施方式
图1示出涡轮机100、在此为燃气轮机的部分纵剖图。燃气轮机100在内部中具有围绕旋转轴线102(轴向方向)转动安装的转子103,所述转子也称作为涡轮机旋转体。沿着转子103依次为抽吸壳体104、压缩机105、环面状的燃烧室110、尤其是具有多个同轴设置的燃烧器107的环形燃烧室106、涡轮机108和排气壳体109。
环形燃烧室106与环形的热气体通道111连通。在那里,例如四个依次接入的涡轮级112形成涡轮机108。每个涡轮级112由两个叶片环形成。沿工质113的流动方向观察,在热气体通道111中跟随导向叶片组115的是由转子叶片120形成的排125。
导向叶片130在此固定在定子143上,然而排125的转子叶片120借助于涡轮机盘133安置在转子103上。因此,转子叶片120形成转子的或旋转体103的组成部分。在转子103上耦联有发电机或做功机械(没有示出)。
在燃气轮机100运行期间,由压缩机105通过抽吸壳体104抽吸空气135并且将其压缩。在压缩机105的涡轮机侧的端部上提供的经过压缩的空气被引向燃烧器107并且在那里与燃烧剂混合。随后,混合物在形成工质113的条件下在燃烧室110中燃烧。从那里开始,工质113沿着热气体通道111流过导向叶片130和转子叶片120。工质113在转子叶片120上以传递动量的方式膨胀,使得转子叶片120驱动转子103进而所述转子驱动耦联在其上的做功机械。
暴露于热的工质113的构件在燃气轮机100运行期间经受热负荷。沿工质113的流动方向观察第一涡轮级112的导向叶片130和转子叶片120在对环形燃烧室106加衬的隔热元件附近受到最大热负荷。为了承受住那里存在的温度,将其借助于冷却介质冷却。同样地,叶片120、130能够具有抗腐蚀的覆层(McrAlX;M=Fe、Co、Ni、稀土元素)和抗热的覆层(隔热层,例如ZrO2、Y2O4-ZrO2)。
在图2中示出根据现有技术的导向叶片130的俯视图,并且在图3中示出其部分剖视图。参考图1,导向叶片130具有朝向涡轮机108的内壳体138的导向叶片叶根145和与导向叶片叶根145相对置的导向叶片顶部147。导向叶片顶部朝向转子103并且固定在定子143的固定环140上。导向叶片130空心地构造。在内部空间131中,典型为空气的冷却介质循环。
导向叶片130尤其在位于导向叶片叶根145和导向叶片顶部147之间的导向叶片叶身149上具有多个冷却空气开口151。冷却空气开口151在现有技术中被引入到一件式浇铸的导向叶片130中。然而在此,尤其在导向叶片叶根145和导向叶片叶身149之间的过渡的区域中,即在形成凹状的棱边153的位置,用于引入冷却空气开口151的工具的灵活性受到限制。因此,迄今仅能够引入其轴线155不朝向导向叶片叶根145定向的冷却空气开口151。在图2和3中,箭头示出冷却空气K和热气H的流动方向。如图3清楚地示出的那样,流动方向部分地反向定向,使得不确保最优的冷却并且冷却空气消耗增多。
在此,在图4和5中类似于图2或3示出的转子叶片130提供明显的改进。在此,冷却空气开口151的轴线155在棱边153的区域中朝向导向叶片叶根145定向。由此,冷却空气K的流沿着热气H的流线定向并且实现燃气轮机100的明显更好的效率。
冷却空气开口151的所述布置能够通过在下文中阐述的制造方法来实现。首先,将导向叶片叶身149和导向叶片叶根145分开地铸造。随后,将在棱边153的区域中的重要的冷却空气开口151借助于激光或电火花腐蚀引入。在此,工具是可自由运动的。随后,将叶根145和叶身149在图5中示出的接缝157上连接,例如焊接。
随后,例如用金属层对导向叶片130进行涂覆。在此,冷却空气开口151能够由覆层材料阻塞。为了在此不会出现对冷却空气流的损害,冷却空气开口151锥形地构造。替选地或附加地,随后能够借助于激光或电火花腐蚀将冷却空气开口151上的覆层再次移除。同时,能够引入其他的关于可达到性不重要的冷却空气开口。
这样制成的导向叶片130基于改进的冷却效果来提高燃气轮机100的效率。
Claims (10)
1.一种用于制造涡轮机叶片(130)的方法,所述涡轮机叶片具有叶身(149)和叶根(145),所述方法具有下述步骤:
a)将叶身(149)和叶根(145)作为单独的构件制造,
b)将至少一个冷却空气开口(151)引入到所述叶身(149)和/或所述叶根(145)中,和
c)在步骤b)之后将叶身(149)和叶根(145)接合。
2.根据权利要求1所述的方法,
其中根据步骤a)通过浇铸来制造单独的构件(145,149)。
3.根据上述权利要求中任一项所述的方法,
其中根据步骤b)通过激光和/或借助于电火花腐蚀来引入至少一个所述冷却空气开口。
4.根据上述权利要求中任一项所述的方法,
其中所述冷却空气开口(151)的轴线(155)在所述叶身(149)的外侧上朝向所述叶根(145)或相反地定向。
5.根据上述权利要求中任一项所述的方法,所述方法具有下述附加的步骤:
d)用覆层对叶根(145)和叶身(149)的区域进行涂覆。
6.根据权利要求5所述的方法,
其中所述冷却空气开口(151)锥形地构造。
7.根据权利要求5或6所述的方法,所述方法具有下述附加的步骤:
e)通过激光和/或借助于电火花腐蚀将所述冷却空气开口(151)上的覆层移除。
8.一种涡轮机叶片(130),
所述涡轮机叶片借助根据上述权利要求中任一项所述的方法制造。
9.一种具有叶身(149)和叶根(145)的涡轮机叶片(130),其中所述叶身(149)具有冷却开口(151),所述冷却开口的轴线(155)在所述叶身(149)的外侧上朝向所述叶根(145)定向。
10.一种具有根据权利要求8或9所述的涡轮机叶片(130)的涡轮机(100)。
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DE102012213017.9 | 2012-07-25 | ||
DE102012213017.9A DE102012213017A1 (de) | 2012-07-25 | 2012-07-25 | Verfahren zur Herstellung einer Turbinenschaufel |
PCT/EP2013/064886 WO2014016149A1 (de) | 2012-07-25 | 2013-07-15 | Verfahren zur herstellung einer leitschaufel sowie leitschaufel |
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CN104487657A true CN104487657A (zh) | 2015-04-01 |
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CN201380039681.6A Pending CN104487657A (zh) | 2012-07-25 | 2013-07-15 | 用于制造导向叶片的方法以及导向叶片 |
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US (1) | US20150198048A1 (zh) |
EP (1) | EP2877702A1 (zh) |
JP (1) | JP2015528876A (zh) |
CN (1) | CN104487657A (zh) |
DE (1) | DE102012213017A1 (zh) |
IN (1) | IN2015DN00258A (zh) |
RU (1) | RU2015106136A (zh) |
WO (1) | WO2014016149A1 (zh) |
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CN105904043A (zh) * | 2016-06-06 | 2016-08-31 | 南京航空航天大学 | 错合型阴极进给环形供液的叶片全轮廓电解系统及方法 |
CN106246232A (zh) * | 2015-06-12 | 2016-12-21 | 安萨尔多能源英国知识产权有限公司 | 用于制造叶片部件组件的方法和叶片部件组件 |
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US9988932B2 (en) | 2013-12-06 | 2018-06-05 | Honeywell International Inc. | Bi-cast turbine nozzles and methods for cooling slip joints therein |
US9885245B2 (en) | 2014-05-20 | 2018-02-06 | Honeywell International Inc. | Turbine nozzles and cooling systems for cooling slip joints therein |
FR3025563B1 (fr) * | 2014-09-04 | 2019-04-05 | Safran Aircraft Engines | Aube a plateforme et excroissance creusee |
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DE102012213017A1 (de) | 2014-01-30 |
EP2877702A1 (de) | 2015-06-03 |
US20150198048A1 (en) | 2015-07-16 |
RU2015106136A (ru) | 2016-09-20 |
IN2015DN00258A (zh) | 2015-06-12 |
JP2015528876A (ja) | 2015-10-01 |
WO2014016149A1 (de) | 2014-01-30 |
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