CN1932249A - 用于涡轮机叶片的寄生翼密封和选择定子、转子及翼密封型面的方法 - Google Patents
用于涡轮机叶片的寄生翼密封和选择定子、转子及翼密封型面的方法 Download PDFInfo
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- CN1932249A CN1932249A CNA200610141270XA CN200610141270A CN1932249A CN 1932249 A CN1932249 A CN 1932249A CN A200610141270X A CNA200610141270X A CN A200610141270XA CN 200610141270 A CN200610141270 A CN 200610141270A CN 1932249 A CN1932249 A CN 1932249A
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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
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
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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
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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
- F05D2250/00—Geometry
- F05D2250/70—Shape
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- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
本发明公开了用于涡轮机(10)的寄生翼密封(34)。在一方面,涡轮机中位于转子叶片(22)和喷嘴(18,20)之间的寄生翼密封抑制从流经涡轮机进入涡轮机叶轮间隔(40)的热燃气流中摄取热燃气。在一个实施例中,该密封包括从叶片的叶柄(25)延伸并大致伸向喷嘴的密封体(122)。该密封体具有至少一个凹面(116,118)。
Description
技术领域
本发明总体上涉及回转机械,更特别地,涉及寄生翼密封。
背景技术
用来自压缩机的冷却空气吹洗燃气轮机叶轮间隔空腔,以维持叶轮间隔和转子的温度处于理想温度范围内,并防止通路吸入热燃气。提供寄生翼(angelwing)密封来密封该叶轮间隔空腔。特别地,寄生翼密封是涡轮转子叶片即涡轮叶片的轴向延伸,其通过与喷嘴密封区重叠而形成密封,所述密封形成涡轮机已固定元件的一部分。典型地,寄生翼密封是作为叶片或涡轮叶片的一部分而一体铸造。应当选择寄生翼密封的特殊型面和定子表面以有助于防止通路吸入热燃气并减少冷却空气的使用。
发明内容
一方面,描述了涡轮机中转子叶片和喷嘴之间的密封,其用来抑制从流经涡轮机进入涡轮机叶轮间隔的热气流中吸入燃气。在一个示范实施例中,该密封包括从叶柄(shank)延伸并大致伸向喷嘴的密封体。该密封体具有至少一个凹面。
另一方面,描述了在涡轮机中形成密封布置的方法。该涡轮机具有可绕一轴线旋转的转子、由转子承载以随之旋转的叶片和喷嘴。寄生翼密封处于转子叶片和喷嘴之间,以抑制从流经涡轮机进入涡轮机叶轮间隔的热气流中吸入燃气。该寄生翼密封具有从叶片柄延伸并大致伸向喷嘴的主体。该方法包括在寄生翼主体内形成至少一个凹面。
另一方面,描述了可绕涡轮机中一轴线旋转的转子的寄生翼密封。在该涡轮机中,叶片受转子承载以随之旋转,且该涡轮机还包括喷嘴。该寄生翼密封抑制从流经涡轮机进入涡轮机叶轮间隔的热气流中吸入燃气。该寄生翼密封包括从叶片柄延伸并大致伸向喷嘴的主体。该密封主体包括至少一个凹面。
附图说明
图1是涡轮机局部横截面的局部示图;
图2是涡轮机叶片的放大透视图;以及
图3是示范性定子和转子型面的图表。
具体实施方式
图1图示地示意出汽轮机的截面,整体表示为10,其包括具有轴向间隔分布的转子叶轮12和通过多个圆周向间隔分布、轴向延伸的螺栓16而彼此结合的隔叶块14。涡轮机10包括具有喷嘴的各种级,如第一级喷嘴18和具有多个圆周向间隔分布的定子叶片的第二级喷嘴20。在喷嘴之间和随同转子旋转的是多个转子叶片,如分别所示的第一和第二级转子叶片22和24。
参照图2,每个转子叶片,如转子叶片22包括安装在叶柄25上的翼部24,叶柄包括平台26和叶柄腔28,叶柄腔具有整体盖板30和燕尾榫32,所述燕尾榫用来与形成于转子叶轮12上大致对应的燕尾槽相连接(图1)。叶片22典型地是一体浇铸,并包括轴向突出的寄生翼密封34。密封34与形成于相邻喷嘴上的区段36(参见图1)合作,以限制流经热气路流入叶轮间隔40的燃气的吸入,该热气路整体用箭头38表示(图1)。
典型地,寄生翼密封34包括一个寄生翼主体42、位于其远端的上翻或尖端44、分别表示为46和48的上和下寄生翼根部过滤区、及分别表示为50和52的上和下密封主体表面。按照惯例,上和下表面50和52为从根部过渡区向尖端44延伸的线形曲面,典型地上表面50具有关于转子旋转轴线同心的弓形曲面。
图3示出了根据本发明一个实施例的寄生翼100、转子主体102和定子104的型面。这些型面易于产生叶轮间隔106中高压和低压的分布。至少部分地基于柏努利法则(Bernoulli’s law)选择这些型面,该法则规定,对于稳流中的非粘性、不能压缩的流体,每单元体积压力、势能和动能的总和在任一点都是恒定的。更具体地,柏努利法则描述了在不同流动条件和高度下流体的特性,并提供了以下的方程:
P+1/2pv2+pgh=常数
其中P为静压(牛顿/每平方米),p为流体密度(kg/每立方米),v为流体流动速率(米/每秒),g为重力加速度,h为高于参照面的高度。该等式中的第二项为熟知的动压。
如图3和示范实施例中所示,定子104包括凹面108、110和定子突起112,转子主体102包括一转子突起114。寄生翼100还包括凹面116和118及向外弯曲的下表面120。定子104、转子102和寄生翼100的这些型面特征可以通过以下方法即浇铸、机加工、焊接和TBC/可研磨涂层中任一种或它们的组合来形成。
至于寄生翼100(在此有时表示密封),翼100包括从叶片柄延伸且大致伸向喷嘴104的密封主体122。密封主体122具有至少一个凹面。在该示范实施例中,密封主体122具有位于其尖端124的第一凹面116和沿主体部126的长度从转子延伸的第二凹面118。密封主体122还具有沿主体部126的长度向外弯曲的表面120。喷嘴104具有朝向转子102延伸的第一突起112和凹面108、110。转子102具有突起114。
当然,许多其它的构造和型面都是可能的。通常,突起112和114导致压力降低,凹面108、110、116和118导致压力增大。更特别地,泄漏硫动区域中的改变导致速率和压力的随之增加或降低。在从较高速率转换至较低速率的过程中,空气膨胀,且叶轮间隔空腔中的压力增大,使得增大的压力产生“缓冲”。
如有时在此描述的那样,定子104和转子102(包括寄生翼100)形成密封装置或组件,防止通路吸入热燃气,同时使冷却空气得到有效使用从而冷却转子102,使转子102维持在选定操作温度范围和温度梯度内。尽管在此已描述和/或已说明的方法和系统是关于旋转机器特别是汽轮机做出的描述和/或说明,但在此描述和/或说明的方法和系统的应用并不限于汽轮机。更确切地,在此描述和/或说明的方法和系统适合于在多种不同类型涡轮机包括例如蒸汽轮机上密封装配。
密封装置的示范实施例已在上面详细描述。这些方法并不限于在此描述的特定实施例,也不限于特定装配的密封装置,而该密封装置可以独立和分离于在此描述的其它方法而使用,或用于装配在此未描述的密封装置。例如,其它密封装置也可以使用在此描述的方法得到装配。
虽然本发明已经根据各种具体实施例做出了描述,但是,本领域技术人员应该认识到,本发明可以在权利要求书的精神和范围内进行修改而实施。
部件列表
10 | 涡轮机 |
12 | 转子叶轮 |
14 | 隔叶块 |
16 | 螺栓 |
18 | 第一级喷嘴 |
20 | 第二级喷嘴 |
22 | 转子叶片 |
24 | 翼部 |
25 | 叶柄 |
26 | 平台 |
28 | 叶柄腔 |
30 | 盖板 |
32 | 燕尾槽 |
34 | 寄生翼密封 |
36 | 区段 |
38 | 箭头 |
40 | 叶轮间隔 |
42 | 寄生翼主体 |
44 | 上翻或尖端 |
46 | 上寄生翼根部过滤区 |
48 | 下寄生翼根部过滤区 |
50 | 上密封主体表面 |
52 | 下密封主体表面 |
100 | 寄生翼 |
102 | 转子主体 |
104 | 定子 |
106 | 叶轮间隔 |
108 | 凹面 |
110 | 凹面 |
112 | 定子突起 |
114 | 转子突起 |
116 | 第一凹面 |
118 | 第二凹面 |
120 | 向外弯曲的下表面 |
122 | 密封体 |
124 | 尖端 |
126 | 主体部 |
Claims (10)
1、在具有可绕轴线旋转的转子、由所述转子承载以随之旋转的叶片(22)和喷嘴(18,20)的涡轮机(10)中,在一转子叶片和喷嘴之间用来抑制从流经涡轮机进入涡轮机叶轮间隔(40)的热气流中摄取热气的密封(34)包括:
从所述叶片的一叶柄(25)延伸并大致伸向喷嘴的密封体(122);
所述密封体包括至少一个凹面(116,118)。
2、根据权利要求1的密封,其中所述密封体(122)包括位于其上一尖端(124)的第一凹面(116)。
3、根据权利要求1的密封,其中所述密封体(122)包括沿主体部(126)的长度从转子延伸的第二凹面(118)。
4、根据权利要求1的密封,其中所述密封体(122)包括沿主体部(126)的长度从转子延伸的向外弯曲的面(120)。
5、根据权利要求1的密封,其中喷嘴(104)包括向转子延伸的第一突起(112)。
6、根据权利要求1的密封,其中喷嘴(104)包括至少一个凹面(108,110)。
7、根据权利要求1的密封,其中转子包括至少一个突起(114)。
8、可绕涡轮机(10)中一轴线旋转的寄生翼密封(34),叶片(22)由转子承载以随之旋转,该涡轮机还包括喷嘴(18,20),所述寄生翼密封用以抑制从流经涡轮机进入涡轮机叶轮间隔(40)的热燃气流中摄取热燃气,所述寄生翼密封包括从所述叶片的一叶柄(25)延伸并大致伸向喷嘴的密封体(122),所述密封体包括至少一个凹面(116,118)。
9、根据权利要求8的寄生翼密封(34),其中所述密封体(122)包括位于其上一尖端(124)的第一凹面(116)和沿主体部(126)的长度从转子延伸的第二凹面(118)。
10、根据权利要求8的寄生翼密封(34),其中所述密封体(122)包括沿主体部(126)的长度从转子延伸的向外弯曲的面(120)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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US11/229096 | 2005-09-16 | ||
US11/229,096 US7465152B2 (en) | 2005-09-16 | 2005-09-16 | Angel wing seals for turbine blades and methods for selecting stator, rotor and wing seal profiles |
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Publication Number | Publication Date |
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CN1932249A true CN1932249A (zh) | 2007-03-21 |
CN1932249B CN1932249B (zh) | 2012-03-21 |
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CN200610141270XA Expired - Fee Related CN1932249B (zh) | 2005-09-16 | 2006-09-15 | 用于涡轮机叶片的寄生翼密封和选择定子、转子及翼密封型面的方法 |
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US (1) | US7465152B2 (zh) |
JP (1) | JP2007085340A (zh) |
CN (1) | CN1932249B (zh) |
CH (1) | CH704034B1 (zh) |
DE (1) | DE102006043744A1 (zh) |
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- 2006-09-13 DE DE102006043744A patent/DE102006043744A1/de not_active Withdrawn
- 2006-09-14 JP JP2006249241A patent/JP2007085340A/ja not_active Ceased
- 2006-09-15 CN CN200610141270XA patent/CN1932249B/zh not_active Expired - Fee Related
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CN101153548B (zh) * | 2006-09-29 | 2012-06-20 | 通用电气公司 | 具有增强约束气体流的表面特征的定子-转子组件及工艺 |
CN101315032B (zh) * | 2007-05-30 | 2013-06-19 | 通用电气公司 | 具有增强的气流封闭表面特征的定子-转子组件和方法 |
CN102733863A (zh) * | 2011-03-31 | 2012-10-17 | 通用电气公司 | 具有气体流的增强抑制特征的定子-转子组件及相关方法 |
CN103143796A (zh) * | 2011-12-06 | 2013-06-12 | 通用电气公司 | 用于可磨损天使翼的蜂窝结构 |
CN103216277A (zh) * | 2012-01-24 | 2013-07-24 | 通用电气公司 | 可翻新的级间成角密封件 |
CN103939149A (zh) * | 2013-01-23 | 2014-07-23 | 株式会社日立制作所 | 燃气轮机 |
CN104919141A (zh) * | 2013-01-23 | 2015-09-16 | 西门子公司 | 燃气轮机的内围带中的带槽密封组件 |
US9617867B2 (en) | 2013-01-23 | 2017-04-11 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine |
CN104919141B (zh) * | 2013-01-23 | 2017-09-01 | 西门子公司 | 燃气轮机的内围带中的带槽密封组件 |
Also Published As
Publication number | Publication date |
---|---|
US20070224035A1 (en) | 2007-09-27 |
CN1932249B (zh) | 2012-03-21 |
CH704034B1 (de) | 2012-05-15 |
US7465152B2 (en) | 2008-12-16 |
JP2007085340A (ja) | 2007-04-05 |
DE102006043744A1 (de) | 2007-03-22 |
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