CN1261643A - 汽轮机或燃气轮机的壳体 - Google Patents

汽轮机或燃气轮机的壳体 Download PDF

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Publication number
CN1261643A
CN1261643A CN00100518.9A CN00100518A CN1261643A CN 1261643 A CN1261643 A CN 1261643A CN 00100518 A CN00100518 A CN 00100518A CN 1261643 A CN1261643 A CN 1261643A
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flange
wall thickness
flanges
turbine
housing
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CN1268833C (zh
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克里斯托夫·贝伦斯
约瑟夫·胡斯特尔
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General Electric Technology GmbH
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ABB Alstom Power Switzerland Ltd
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26Double casings; Measures against temperature strain in casings
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24Casings; Casing parts, e.g. diaphragms, casing fastenings

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

Abstract

本发明涉及汽轮机或燃气轮机的壳体。该壳体包括一罩体和两凸缘。罩体在远离凸缘的顶部、两中部和靠近凸缘的两底部的壁厚不同,远离凸缘的顶部的壁厚比靠近凸缘的底部的壁厚厚。中部的壁厚可变,使相邻的顶部和底部互相连续汇合。底部的柔性比凸缘以及中部和顶部大,从而特别在径向上用作一补偿变形的接头。因此,壳体在壳体运行时保持圆形。由于变形减小使壳体与涡轮叶片端部之间径向间隙减小,因此涡轮的运行效率大大提高。

Description

汽轮机或燃气轮机的壳体
本发明涉及汽轮机或燃气轮机的壳体,其包括一个罩体和两个凸缘。
燃气轮机的压缩机壳体是公知的,它包括一个罩体和两个凸缘。这类壳体在罩体的上下区各有一个假凸缘。但其缺点是,由于燃气轮机运行时平均温度高,因此假凸缘区域的径向膨胀增大,从而圆形壳体变得不圆。这一变形使得壳体与涡轮叶片端部之间间隙变大,蒸汽或空气毫无阻挡地从这些间隙流过而不对涡轮做功,从而效率下降。
汽轮机的壳体也是公知的,它包括一个罩体和两个凸缘,水平凸缘中有垂直切口。但是,由于密合凸缘用螺丝连接,罩体和凸缘中的温度分布造成罩体严重变形。这变形发生在壳体的径向和轴向上。在径向上,由于罩体向上膨胀和两个凸缘稍稍向里移动,因此罩体从圆形变成椭圆形。在轴向上,由于不同的温度分布,径向作用在壳体中造成不同结果,从而也造成变形。由于壳体与涡轮叶片端部之间的径向间隙增大,从其间流过的蒸汽气流增大而不对涡轮做功,因此该变形导致效率下降。分开凸缘的切口虽然特别是减小了壳体的轴向变形,但不足以防止径向变形,因此效率下降。
此外,也有人使用收缩环防止汽轮机壳体变形。但是其缺点是成本高,需使用专用装配夹具。
本发明的目的是设计汽轮机或燃气轮机的一种壳体,它在运行时保持圆形或变形较小,从而减小壳体与涡轮叶片端部之间的径向间隙而防止效率下降。此外,它的成本低,无需使用装配夹具。
为实现该目的,按照本发明,罩体在远离凸缘的顶部、两中部或靠近凸缘的两底部上具有不同的壁厚,在此情况下,远离凸缘的顶部的壁厚与靠近凸缘的底部的壁厚相比较是加强的,中部的壁厚是可变的,使得远离凸缘的顶部和靠近凸缘的底部互相连续汇合。
本发明的一个优点是,壳体的罩体壁厚的变动大大减小了在径向和轴向上变形成椭圆形。因此,壳体与涡轮叶片端部之间的径向间隙很小,从而效率比现有技术大大提高。总的来说,本发明使得汽轮机的效率提高0.2%-0.3%。
根据本发明的壳体,远离凸缘的顶部优选为从壳体的中心轴线算起占45°角,与顶部连接的中部优选为占15°角。远离凸缘的顶部的壁厚最多为靠近凸缘的底部的壁厚的两倍。远离凸缘的顶部的壁厚最好为靠近凸缘的底部的壁厚的1.5倍。
图1为本发明壳体一实施例的剖面图。
图1为用于汽轮机或燃气轮机的本发明壳体1的剖面图。该壳体包括两个相同的半壳体,图中只示出其中之一。壳体1包括一罩体2和两凸缘3,这两个凸缘与壳体1的另一半(未示出)的凸缘连接在一起。罩体2在不同部位的壁厚不同。远离凸缘的顶部5的壁厚比靠近凸缘的底部7的壁厚厚。在所示实施例中,远离凸缘的顶部5的壁厚为靠近凸缘的底部7的壁厚的1.5倍。但是顶部的加强程度决定于涡轮的设计,从而决定于工作压力和工作温度。但是,我们发现,远离凸缘的顶部5的壁厚不应超过靠近凸缘的底部7的壁厚的2倍。远离凸缘的顶部5与两边上靠近凸缘的底部7用中部6连接。中部6的壁厚变动,从而使得相邻两部分5、7互相连续汇合。在所示实施例中,远离凸缘的顶部5最好从壳体1的中心轴线4算起占45°角。在两边上与顶部连接的中部6占据15°角。但是,为了获得本发明效果,这些角度也可不同。由于中部6、特别是远离凸缘的顶部5的刚性较之靠近凸缘的底部7由于壁厚增大而增强,因此运行时由温度分布造成的变形减小。靠近凸缘的底部7更容易变形而用作在机加工成非常密合并由螺栓连接的凸缘3与局部加固的中部6以及远离凸缘的加固顶部5之间的接头而起到补偿作用。总之,这使得壳体1的径向和轴向变形减小,从而在涡轮运行时保持圆形。由于壳体1与涡轮叶片(未示出)端部之间的径向间隙减小,因此效率大大提高。
标号与部件对照表
1    壳体
2    罩体
3    凸缘
4    中心轴线
5    顶部
6    中部
7    底部

Claims (4)

1、汽轮机或燃气轮机的壳体(1),包括一罩体(2)和两凸缘(3),其特征在于,
罩体(2)在远离凸缘的顶部(5)、两中部(6)和靠近凸缘的两底部(7)的壁厚不同,在这种情况下
-远离凸缘的顶部(5)的壁厚与靠近凸缘的底部(7)的壁厚相比较是加强的,以及
-中部(6)的壁厚是可变的,从而使得远离凸缘的顶部(5)与靠近凸缘的底部(7)互相连续汇合。
2、按权利要求1所述的壳体(1),其特征在于,
远离凸缘的顶部(5)从壳体(1)的中心轴线(4)算起占45°角,与顶部连接的中部(6)占15°角。
3、按权利要求1所述的壳体(1),其特征在于,
远离凸缘的顶部(5)的壁厚最多为靠近凸缘的底部(7)的壁厚的两倍。
4、按权利要求3所述的壳体(1),其特征在于,
远离凸缘的顶部(5)的壁厚为靠近凸缘的底部(7)的壁厚的1.5倍。
CN00100518.9A 1999-01-20 2000-01-20 汽轮机或燃气轮机的壳体 Expired - Fee Related CN1268833C (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP99810037A EP1022439B1 (de) 1999-01-20 1999-01-20 Gehäuse für eine Dampf- oder eine Gasturbine
EP99810037.4 1999-01-20

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CN1261643A true CN1261643A (zh) 2000-08-02
CN1268833C CN1268833C (zh) 2006-08-09

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US (1) US6336789B1 (zh)
EP (1) EP1022439B1 (zh)
JP (1) JP4347977B2 (zh)
CN (1) CN1268833C (zh)
DE (1) DE59909395D1 (zh)
RU (1) RU2244835C2 (zh)

Cited By (4)

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CN102216570A (zh) * 2008-11-19 2011-10-12 西门子公司 燃气涡轮机
CN1840956B (zh) * 2005-03-31 2012-11-14 阿尔斯托姆科技有限公司 机器壳体
CN103080482A (zh) * 2010-08-25 2013-05-01 西门子公司 用于涡轮机的壳体及其制造方法
CN114017134A (zh) * 2021-11-12 2022-02-08 中国航发沈阳发动机研究所 一种通过改变机匣热容调整机匣热变形速率的方法

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DE60310054T2 (de) * 2003-06-26 2007-05-03 Alstom Technology Ltd. Ein Halter für ein reflektierendes Ziel, angewendet zur Messung der Durchbiegung eines Turbinengehäuses
EP1541810A1 (de) * 2003-12-11 2005-06-15 Siemens Aktiengesellschaft Verwendung einer Wärmedämmschicht für ein Bauteil einer Dampfturbine und eine Dampfturbine
US7681601B2 (en) * 2005-08-24 2010-03-23 Alstom Technology Ltd. Inner casing of a rotating thermal machine
CH698879B1 (de) * 2006-06-30 2009-11-30 Alstom Technology Ltd Strömungsmaschine.
US8128353B2 (en) * 2008-09-30 2012-03-06 General Electric Company Method and apparatus for matching the thermal mass and stiffness of bolted split rings
CH700679A1 (de) * 2009-03-17 2010-09-30 Alstom Technology Ltd Abstützung für eine turbine.
US8342009B2 (en) 2011-05-10 2013-01-01 General Electric Company Method for determining steampath efficiency of a steam turbine section with internal leakage
US9279342B2 (en) 2012-11-21 2016-03-08 General Electric Company Turbine casing with service wedge
US9260281B2 (en) 2013-03-13 2016-02-16 General Electric Company Lift efficiency improvement mechanism for turbine casing service wedge
JP2016113992A (ja) * 2014-12-16 2016-06-23 三菱重工業株式会社 圧力容器およびタービン

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Publication number Priority date Publication date Assignee Title
CN1840956B (zh) * 2005-03-31 2012-11-14 阿尔斯托姆科技有限公司 机器壳体
CN102216570A (zh) * 2008-11-19 2011-10-12 西门子公司 燃气涡轮机
CN102216570B (zh) * 2008-11-19 2014-03-05 西门子公司 燃气涡轮机
CN103080482A (zh) * 2010-08-25 2013-05-01 西门子公司 用于涡轮机的壳体及其制造方法
CN103080482B (zh) * 2010-08-25 2016-02-03 西门子公司 用于涡轮机的壳体及其制造方法
CN114017134A (zh) * 2021-11-12 2022-02-08 中国航发沈阳发动机研究所 一种通过改变机匣热容调整机匣热变形速率的方法

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CN1268833C (zh) 2006-08-09
JP2000213305A (ja) 2000-08-02
US6336789B1 (en) 2002-01-08
DE59909395D1 (de) 2004-06-09
EP1022439A1 (de) 2000-07-26
RU2244835C2 (ru) 2005-01-20
JP4347977B2 (ja) 2009-10-21
EP1022439B1 (de) 2004-05-06

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