CN1250863C - 轴流式透平的输出级 - Google Patents

轴流式透平的输出级 Download PDF

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Publication number
CN1250863C
CN1250863C CN98123390.2A CN98123390A CN1250863C CN 1250863 C CN1250863 C CN 1250863C CN 98123390 A CN98123390 A CN 98123390A CN 1250863 C CN1250863 C CN 1250863C
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guide vane
blade
vector
rotor
output stage
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Expired - Lifetime
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CN1217419A (zh
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C·穆姆
A·维斯
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General Electric Technology GmbH
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Alstom SA
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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
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12Blades
    • F01D5/14Form or construction
    • F01D5/141Shape, i.e. outer, aerodynamic form
    • F01D5/142Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • 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
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12Blades
    • F01D5/14Form or construction
    • F01D5/141Shape, i.e. outer, aerodynamic form
    • 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
    • F01D9/00Stators
    • F01D9/02Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

一种带有一扩大的流道的轴流式透平的输出级,并带有一排弯曲的导流叶片(10)和一排缩小的旋转工作叶片(20)。由于转子侧的流道边界(2)的曲线原因,该导流叶片沿轴向在其转子侧端头部侧所示出的矢量为正,而在其定子侧端部侧所示出的矢量为负。该导流叶片后棱(12)的正矢量相对平行于该工作叶片(20)的前棱(21)的径向距离的大部分延伸。通过在高度上多出的部分,该导流叶片沿圆周方向倾斜。

Description

轴流式透平的输出级
本发明涉及一种带有一扩大的流道的轴流式透平的输出级,其带有一排弯曲的导流叶片和一排缩小的旋转工作叶片。
为了降低因边界层的转向而在工作叶片中产生的二次损耗,特别安装了弯曲的导流叶片。
例如在DE-A-3743738中公开了一种带有只沿圆周方向弯曲的工作叶片的透平。在此,对该叶片进行了图示并作出了说明。该工作叶片在叶片高度上的弯曲朝向在圆周方向邻近的工作叶片的压力侧。从该文献中还可知道:该叶片在叶片高度上的弯曲也可总是朝着在圆周方向上相邻的各工作叶片的吸入侧弯曲。因此,可有效地使径向及圆周方向分布的边界层-压力梯度变小,从而可因此减小空气动力学损失。不管该所述叶片朝着邻近叶片的哪一侧弯曲,但在任何情况下,它都是正好在圆周方向延伸。这就意味着:对所示的圆柱形叶片来说至少其前棱在整个叶片高度上处于同一轴向平面中。
带有在轴向及圆周方向弯曲的导流叶片的透平例如可从DE-A-4228879中得知。在工作叶栅的上游设有一固定导向叶栅。其叶片都是从满负荷流动技术考虑根据其数量及所述的弦与节距的比进行了优化。这给流体带来了对流入工作叶栅所必须的涡旋。叶片的弯曲相对弦垂直延伸,这一点可由在圆周方向及轴向方向的外形加工产生的偏离而获得。该导流叶片的弯曲朝向在圆周方向上相邻的导流叶片的压力侧。该弯曲构成为一个连续的弧形,该弧形与该叶片支承件及轮毂形成一锐角。由于该弯曲垂直于叶片的弦,所以,在径向方向伸展的叶片表面大于公知的在圆周方向上的所述弯曲形成的表面。因此,作用于工作介质上的径向力提高;该力压在流道壁上,所以在哪里的边界层减小。
本发明的任务在于:为一个本文开头所述类型的轴流式透平,特别是一个带有小的轮毂比的透平,提供一种措施,利用这种措施可避免相对轮毂产生流体分离,并借助于该措施可以在安装叶片的高度范围内得到均匀的压力分布。
根据本发明,该任务的技术解决方案为一种带有一扩大的流道的轴流式透平的输出级,并带有一排弯曲的导流叶片和一排缩小的旋转工作叶片,其中,由于转子侧的流道边界的曲线原因,该导流叶片沿轴向在其转子侧端头部侧所示出的矢量为正,而在其定子侧端部侧所示出的矢量为负,其特征在于,该导流叶片的正矢量伸展超过叶片高度的2/3,然后过度成负矢量;在该正矢量的范围,该导流叶片后棱平行于该工作叶片的前棱延伸,而在该负矢量范围,则在该导流叶片和工作叶片之间形成一个相对该边界壁连续设置的轴流式扩压器使得流体介质的轴向部件更加滞后。
本发明的另一方面的的优点是:由于改善了流体的流入,从而使用一个基本上弯曲的工作叶片结构就足够了。
在附图中根据一蒸汽透平紧邻的低压级示出了本发明的一个实施例。其中:
图1是该透平的局部纵剖视图;
图2是该透平的局部横剖视图。
为了便于理解本发明,图中只示出了主要部件。没有示出的例如是叶跟部,通过该叶跟部将叶片之主要部分挂装好,并且利用可能的盖板改善密封作用。工作介质的流动方向由矢量示出。
在图1所示的蒸汽透平中,构成流道1的边界的墙体一边是转子侧的流道边界3,另一边是定子边界5。该输出级由一排导流叶片10和一排工作叶片20构成。该导流叶片以没有示出的方式固定于定子4中,叶片支承件自身以适当的方式将叶片可挂装于一外壳中。该工作叶片20用没有示出的方式固定于转子2中。工作叶片的叶片段沿其长度方向是变小的并强烈扭曲的。该叶片的叶片段的尖部相对定子侧的流道边界5保持密封。
在叶片的整个安装区,该转子侧流道边界3是圆柱形的,但由于膨胀的工作介质拥有一定的体积,因此定子侧的流道边界5构成为锥形的,并且对高负荷机器来说,设置一个张开直到60°的张开角。显然,内流道的形状也可构成为锥形。
根据本发明,该导流叶片10沿轴向在其转子侧端头部侧所示出的矢量为正,而在其定子侧端部侧所示出的矢量为负。矢量不但用于表示导流叶片前棱11也表示导流叶片后棱12,并且在此用于表示转子侧流道边界2的圆柱形曲线。矢量角A是如此选择的,即导流叶片后棱12至少相对工作叶片20的前棱21近似平行地延伸。这些表示正的矢量一直伸展到叶片高度的大约2/3处。它可使一个作用在流动流体上的作用力作用到转子侧流道边界上,正如从点划线6的曲线中可看出的那样。
根据转子侧流道形状,该正矢量在叶片的大约2/3处变成一负矢量。这一点是如此选择的,即在定子侧端,该导流叶片后棱12和导流叶片前棱11至少大致垂直于流道边界壁5。利用这样的措施可以使定子区域的流线6垂直该导流叶片前棱11。
可以想到,该导流叶片的非直线和非径向延伸的进出口棱边可使叶片高度实现空气动力学的优化设计。
此外,该个根据与工作叶片前棱21的曲线配合而选取的导流叶片后棱12的形状可使在导流叶片排-工作叶片排之间的自由叶片轴流式扩压器的径向易变的优化长度的调节保持处于小于流道的2/3的范围内。由于流道强烈扩大,因此该轴流式扩压器形成于该自由叶片空间中,该轴流式扩压器例如具有一宽度C。该轴流式扩压器设计得越细长,则可对后续的工作叶片的设计产生月有利的作用。在该区域其轴向部件中的流体介质拖延时间越短,则后续叶片曲线的安装角选取得越大。通过这样的分析,叶片高度可得到这样的结果:即各叶片的叶片段必须形成扭曲程度更小的扭曲。
在定子侧流道边界的区域中可得出正好相反的结果,此时,负的矢量占优势。此时,在导流叶片-和工作叶片之间的叶片高度的最后三分之一中,一个相对该边界壁连续设置的轴流式扩压器使流体介质的轴向部件更加迟后。其作用是:使后续的叶片形状的安装角必须被选择得增大一些。依据这种分析,可以再一次得到这样的结果,即各叶片的叶片段必须形成扭曲程度更小的扭曲。
该正负矢量一起使该导流叶片及一个后续的工作叶片带有一径向优化的扭曲分布,这也可以对工作叶片的强度产生有利的影响。
图2中示出了另一种措施,该措施对流体朝着转子侧流道边界偏离具有有利的作用。至此,该导流叶片10相对一个其径向距离的大部分在圆周方向产生倾斜,并且尽管如此,该斜度是相对该总是在圆周方向邻近的导流叶片10’的吸入侧13得出的。该导流叶片径向朝向其转子侧端。从径向距离的大约15%处,该导流叶片向圆周方向倾斜,并且在定子侧端再折回至半径R处。相对半径R的倾角B的范围是10-17°,最好是12-15°,从而因流动可产生一个径向足够大的并作用于转子上的力,该流体再压使该转子旋转。
标                     号
1,流道,               2,转子,
3,转子侧流道边界,     4,定子,叶片支承件,
5,定子侧流道边界,     6,介质流线,
10,导流叶片,          11,导流叶片前棱,
12,导流叶片后棱,        13,导流叶片-吸入侧,
14,导流叶片-压力侧,     20,工作叶片,
21,工作叶片前棱,        R,半径
A,矢量示出的角度,       B,倾角,
C,10和20之间的轴流式扩压器的宽度

Claims (4)

1.一种带有一扩大的流道的轴流式透平的输出级,并带有一排弯曲的导流叶片(10)和一排缩小的旋转工作叶片(20),其中,由于转子侧的流道边界(3)的曲线原因,该导流叶片(10)沿轴向在其转子侧端头部侧所示出的矢量为正,而在其定子侧端部侧所示出的矢量为负,其特征在于,该导流叶片(10)的正矢量伸展超过叶片高度的2/3,然后过度成负矢量;在该正矢量的范围,该导流叶片后棱(12)平行于该工作叶片(20)的前棱(21)延伸,而在该负矢量范围,则在该导流叶片(10)和工作叶片(20)之间形成一个相对该边界壁(5)连续设置的轴流式扩压器,使得流体介质的轴向部件更加滞后。
2.如权利要求1所述的输出级,其特征在于:在定子侧端的负矢量是如此选取的,即该导流叶片后棱(12)和/或导流叶片前棱(11)至少大约垂直于流道边界壁(5)。
3.如权利要求1所述的输出级,其特征在于:该导流叶片(10)朝着其转子侧端部,从径向距离的大约15%处,该导流叶片沿圆周方向朝着相邻导流叶片(10’)的吸入侧(13)倾斜,并且在定子侧端至少再折回至半径(R)处。
4.如权利要求3所述的输出级,其特征在于:相对半径(R)的倾角(B)为大约12-15°。
CN98123390.2A 1997-11-17 1998-11-17 轴流式透平的输出级 Expired - Lifetime CN1250863C (zh)

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Application Number Priority Date Filing Date Title
EP97810873.6 1997-11-17
EP97810873A EP0916812B1 (de) 1997-11-17 1997-11-17 Endstufe für axialdurchströmte Turbine

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CN1217419A CN1217419A (zh) 1999-05-26
CN1250863C true CN1250863C (zh) 2006-04-12

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US (1) US6099248A (zh)
EP (1) EP0916812B1 (zh)
KR (1) KR19990045318A (zh)
CN (1) CN1250863C (zh)
DE (1) DE59709447D1 (zh)

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CN1217419A (zh) 1999-05-26
EP0916812A1 (de) 1999-05-19
EP0916812B1 (de) 2003-03-05
US6099248A (en) 2000-08-08
KR19990045318A (ko) 1999-06-25
DE59709447D1 (de) 2003-04-10

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