CN102213109A - 具有径向冷却孔的涡轮轮叶 - Google Patents
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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
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
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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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
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- 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
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- F05D2230/11—Manufacture by removing material by electrochemical methods
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- 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
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- F05D2260/221—Improvement of heat transfer
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Abstract
本发明涉及具有径向冷却孔的涡轮轮叶。具体而言,提供了一种涡轮轮叶,其包括可与转子互连且形成为用以在其中容纳冷却剂的柄部,以及联接到柄部的径向外部上且包括本体的翼型叶片,该本体形成为用以在其中限定大致沿径向延伸的冷却孔,其设置成用以单独地接收容纳在柄部内的冷却剂来用于从本体除去热量,该冷却孔还限定为在本体的预定径向位置处具有大致非圆形的截面形状。
Description
技术领域
本文所公开的主题涉及具有径向冷却孔的涡轮轮叶。
背景技术
在诸如燃气涡轮发动机或蒸汽涡轮发动机的涡轮发动机中,处于相对较高温度的流体接触构造成用以从流体中获取机械能的叶片,从而有助于产生功率和/或电力。尽管该过程对于给定的期间可能效率较高,但随着时间延长,高温流体趋于造成破坏,这会降低性能和增加操作成本。
因此,通常需要且建议的是对叶片进行冷却,以便至少防止或延迟过早损坏。这可通过将相对较冷的压缩空气输送至待冷却叶片来实现。在许多常规燃气轮机中,具体而言,该压缩空气进入待冷却的各叶片的底部,且沿径向流经一个或多个加工成圆形的通路,以便通过对流和传导的组合来冷却叶片。
在这些常规燃气轮机中,当流体的温度升高时,便需要增加穿过叶片的冷却流量。此种流动的增加可通过增大冷却孔的尺寸来实现。然而,当冷却孔尺寸增大时,各孔至叶片外表面的壁厚便减小,且最终冲击叶片的可制造性和结构完整性。
发明内容
根据本发明的一方面,提供了一种涡轮轮叶,其包括可与转子互连且形成为用以在其中容纳冷却剂的柄部,以及连接到柄部的径向外部上且包括本体的翼型叶片,该本体形成为用以在其中限定大致沿径向延伸的冷却孔,其设置成用以单独地接收容纳在柄部内的冷却剂以便从本体除去热量,该冷却孔还限定为在本体的预定径向位置处具有大致非圆形的截面形状。
根据本发明的另一方面,提供了一种涡轮轮叶,其包括可与转子互连且形成为用以在其中容纳冷却剂的柄部,以及连接到柄部的径向外部上且包括本体的翼型叶片,该本体形成为用以在其中限定多个大致沿径向延伸的冷却孔,其分别设置成单独且独立地接收容纳在柄部内的冷却剂来用于从本体除去热量,在该多个冷却孔的子集中的各冷却孔还限定为在本体的预定径向位置处具有大致非圆形的截面形状。
根据本发明的又一方面,提供了一种涡轮轮叶,其包括可与转子互连且形成为用以在其中容纳冷却剂的柄部,以及联接到柄部的径向外部上且包括本体的翼型叶片,该本体具有在相对的前缘和后缘之间延伸的相对的压力表面和吸入表面,且形成为用以在其中限定大致沿径向延伸的冷却孔,其设置成用以单独地接收容纳在柄部内的冷却剂来用于从本体除去热量,该冷却孔还限定为具有长形的侧壁,该侧壁具有与压力表面和吸入表面的轮廓大致平行的轮廓。
通过结合附图的如下描述,这些及其它优点和特征将变得更为明显。
附图说明
在所附权利要求中具体地指出且明确地主张了认作是本发明的主题。通过结合附图的如下详细描述,本发明的前述及其它特征和优点将变得明显,在附图中:
图1为涡轮轮叶的平面视图;
图2为图1中涡轮轮叶的示意性截面图;
图3至图5为根据实施例的湍流器的截面视图;以及
图6至图8为图3至图5中的湍流器的平面视图。
本详细说明通过举例的方式参照附图,阐述了本发明的实施例以及优点和特征。
零件清单
10涡轮轮叶
20柄部
21柄部本体
22通路
23平台
40翼型叶片
41翼型本体
42冷却孔
43实心部分
44压力表面
45吸入表面
46前缘
47后缘
48弧线(camberline)
50长轴
51短轴
60非圆形的截面形状
70壁
71侧壁
80湍流器
81第一构造
82第二构造
83第三构造
90,91,92组合
具体实施方式
参看图1,提供了一种涡轮轮叶10,且该涡轮轮叶10包括柄部20和翼型叶片40。柄部20可与诸如燃气涡轮发动机的涡轮发动机的转子互连并可围绕其旋转,且包括柄部本体21,该本体21形成为用以在其中限定腔体或多个通路22。腔体可铸造在柄部本体21中,以及该多个通路22可机械加工而成。尽管腔体和多个通路22两者都可采用,但出于清楚和简明的目的,在下文中柄部本体21将描述成形成为用以仅限定多个通路22。该多个通路22可容纳冷却剂,例如从压缩机获取的压缩空气。
柄部本体21可形成为具有杉树形状,其在安装于转子燕尾形密封组件内时,将柄部20相对于转子固定到适当位置上。在该位置,该多个通路22中的各个例如经由涡轮轮叶10的径向内端与冷却剂供送源流体地连通。
翼型叶片40可联接到柄部20径向外部处的平台23上,且可包括翼型本体41,该翼型本体41形成为用以在其中限定大致沿径向延伸的冷却孔42。冷却孔42例如可通过电化学加工工艺(ECM)机械加工而成,且设置成用以单独地接收容纳在柄部20中的冷却剂。即是说,冷却孔42不与任何其它的冷却孔或冷却回路连通,且因此不从柄部20之外的任何其它来源接收冷却剂。
通过流体压力和/或通过离心力,冷却剂在径向上沿冷却孔42的长度流动。当冷却剂流动时,在翼型本体41与冷却剂之间发生热传递。具体而言,冷却剂从翼型本体41除去热量,且此外,趋于导致在翼型本体41的实心部分43内的传导性热传递。传导性热传递可由金属材料形成的翼型本体41而得以促进,该金属材料例如为金属和/或金属合金,其能够经受相对较高的温度状态。总体的热传递降低了翼型叶片40的温度,否则,该温度将是翼型叶片40与例如流经燃气涡轮发动机的相对较高温度的流体之间接触的结果。
参看图2,翼型本体41可沿径向从平台23延伸,且可包括在前缘46与后缘47之间延伸的相对的压力表面44和吸入表面45,以便共同地限定弧线48。弧线48限定长轴50和垂直于长轴50的短轴51。
冷却孔42可限定为在翼型本体41任何一个或多个预定径向位置处具有大致非圆形的截面形状60。该非圆形状60容许冷却孔42增大周长和使得横截面积更大,且导致较大程度的热传递,而不用牺牲壁70的厚度至超过保持可制造性和结构完整性所需的壁厚度。
在冷却孔42为非圆形的情况下,冷却孔42可具有各种备选形状,包括但不限于椭圆或另外的长形形状。冷却孔42可为圆形或成角的、规则或不规则的。冷却孔42可关于预定轴线为对称的,或关于任何预定轴线为非对称的。冷却孔42可限定为具有长形的侧壁71,该侧壁71其轮廓模仿压力表面44和吸入表面45的局部轮廓,使得壁70为长形的,其厚度等于或大于保持可制造性和结构完整性所需的壁厚度。类似的是,冷却孔42可在翼型本体41的轴向上比在其周向上更长,和/或可非包含性地相对于弧线48具有小于或大于1的长宽比。
冷却孔42的大致非圆度可局部化,可沿冷却孔42的部分径向长度延伸,或可沿冷却孔42的整个径向长度延伸。这样,通过冷却孔42的大致非圆度而得以促进增强的热传递可仅提供给翼型本体41长度的一部分,或提供给沿翼型本体41整个长度的一部分。
参照图3至图5以及图6至图8,涡轮轮叶10还可包括定位在冷却孔42内的湍流器80。湍流器80,且更具体而言是湍流器80所定位处的冷却孔42湍流区段可用于加强翼型本体41中的热传递。湍流用于使冷却剂经由冷却孔42流动往返,这产生了具有增大的局部化热传递系数的边界重新开始层。湍流可沿孔的整个周长,或位于部分区段处,且可容许翼型本体41的零件寿命延长和减少所需量的冷却流。湍流器80可由各种工艺形成,例如电化学加工(ECM)。
湍流器80可为冷却孔42内的单个构件,或在数目上可为多个。在湍流器80在数目上为多个的情况下,一系列的湍流器80可在径向上沿冷却孔42的长度排列。
如图3和图6中所示,湍流器80可关于任何预定轴线为对称的。在此情况下,湍流器80可设有第一构造81,在其中,湍流器80围绕冷却孔42的整个圆周延伸。如图4和图7中所示,湍流器80可关于轴向(即,A方向)对称,在此情况下,湍流器80可设有第二构造82。如图5和图8中所示,湍流器80可关于周向(即,B方向)对称,在此情况下,湍流器80可设有第三构造83。更进一步而言,湍流器80可为非对称和/或无规则的。
回头参照图1和图2,翼型本体41可形成为用以限定多个大致沿径向延伸的冷却孔42。这里,各冷却孔42均设置成用以单独且独立地接收柄部20内容纳的冷却剂,用于从翼型本体41除去热量。如上文所述,在限定多个冷却孔42的情况下,冷却孔42彼此独立,且并未流体地连通。
在存在多个冷却孔42的情况下,所有或仅子集可进一步限定为具有大致非圆形的截面形状。该子集可包括冷却孔42中的一个或多个。一个或多个湍流器80可定位在子集中的至少一个冷却孔42内。在此情况下,各湍流器80在冷却孔42内的位置与另一湍流器80在另一冷却孔42中的位置相关或独立。
取决于设计考虑,该多个冷却孔42可布置成一个、两个或多个组合,如组合90,91和92。这里,各组合均可包括一个或多个冷却孔42。在这些之中,零个、一个或多个冷却孔42可限定为在预定的径向位置处具有大致非圆形的截面形状。另外,一个或多个湍流器80可定位在子集中的至少一个冷却孔42内。在此情况下,各湍流器80在冷却孔42内的位置与另一湍流器80在另一冷却孔42中的位置相关或独立。
尽管本发明仅结合了有限数量的实施例进行详细描述,但应当容易理解,本发明并不限于这些公开的实施例。确切而言,本发明可进行修改,以结合任意数目的此前并未描述但与本发明的精神和范围相匹配的变型、备选方案、替换方案或等效布置。此外,尽管已经描述了本发明的多种实施例,但应当理解,本发明的方面可仅包括所述实施例中的一些。因此,本发明不应看作是由以上说明限制,而是仅由所附权利要求的范围来限制。
Claims (10)
1.一种涡轮轮叶(10),包括:
柄部(20),其可与转子互连且形成为用以在其中容纳冷却剂;以及
翼型叶片(40),其联接到所述柄部(20)的径向外部上,且包括本体(41),所述本体(41)形成为用以在其中限定大致沿径向延伸的冷却孔(42),所述冷却孔(42)设置成用以单独地接收容纳在所述柄部(20)内的所述冷却剂来用于从所述本体(41)除去热量,
所述冷却孔(42)还限定为在所述本体(41)的预定径向位置处具有大致非圆形的截面形状(60)。
2.根据权利要求1所述的涡轮轮叶(10),其特征在于,所述柄部(20)包括柄部本体(21),加工而成的冷却通路延伸穿过所述柄部本体(21)。
3.根据权利要求1所述的涡轮轮叶(10),其特征在于,所述柄部(20)包括腔体限定于其中的柄部本体(21)。
4.根据权利要求1所述的涡轮轮叶(10),其特征在于,所述冷却孔(42)在一个维度上比在另一个维度上更长。
5.根据权利要求1所述的涡轮轮叶(10),其特征在于,所述冷却孔(42)的大致非圆度沿所述冷却孔的部分径向长度延伸。
6.根据权利要求1所述的涡轮轮叶(10),其特征在于,所述冷却孔(42)关于预定轴线为对称和非对称中的一种。
7.根据权利要求1所述的涡轮轮叶(10),其特征在于,所述冷却孔(42)关于预定轴线为非对称的。
8.根据权利要求1所述的涡轮轮叶(10),其特征在于,所述涡轮轮叶(10)还包括定位在所述冷却孔内的湍流器(80)。
9.一种涡轮轮叶(10),包括:
柄部(20),其可与转子互连且形成为用以在其中容纳冷却剂;以及
翼型叶片(40),其联接到所述柄部(20)的径向外部上,且包括本体(41),所述本体(41)形成为用以在其中限定多个大致沿径向延伸的冷却孔(42),所述冷却孔(42)分别设置成用以单独且独立地接收容纳在所述柄部(20)内的所述冷却剂来用于从所述本体(41)除去热量,
所述多个冷却孔(42)的子集中的各冷却孔(42)还限定为在所述本体(41)的预定径向位置处具有大致非圆形的截面形状(60)。
10.一种涡轮轮叶(10),包括:
柄部(20),其可与转子互连且形成为用以在其中容纳冷却剂;以及
翼型叶片(40),其联接到所述柄部(20)的径向外部上,且包括本体(41),所述本体(41)具有在相对的前缘(46)和后缘(47)之间延伸的相对的压力表面(44)和吸入表面(45),
所述本体形成为用以在其中限定大致沿径向延伸的冷却孔(42),所述冷却孔(42)设置成用以单独地接收容纳在所述柄部(20)内的所述冷却剂来用于从所述本体(41)除去热量,
所述冷却孔(42)还限定为具有长形的侧壁(71),所述侧壁(71)具有的轮廓与所述压力表面(44)和所述吸入表面(45)的轮廓大致平行。
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US12/758,320 US8727724B2 (en) | 2010-04-12 | 2010-04-12 | Turbine bucket having a radial cooling hole |
US12/758320 | 2010-04-12 |
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US20110250078A1 (en) | 2011-10-13 |
JP2011220337A (ja) | 2011-11-04 |
EP2374998B1 (en) | 2019-09-25 |
JP5848019B2 (ja) | 2016-01-27 |
CN102213109B (zh) | 2015-08-19 |
EP2374998A3 (en) | 2013-07-10 |
US8727724B2 (en) | 2014-05-20 |
EP2374998A2 (en) | 2011-10-12 |
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