CN101405478A - 防漏翼片组 - Google Patents

防漏翼片组 Download PDF

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CN101405478A
CN101405478A CNA2003801053805A CN200380105380A CN101405478A CN 101405478 A CN101405478 A CN 101405478A CN A2003801053805 A CNA2003801053805 A CN A2003801053805A CN 200380105380 A CN200380105380 A CN 200380105380A CN 101405478 A CN101405478 A CN 101405478A
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cover
group
seam
nonlinear
vane cluster
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F·R·祖斯琳
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Raytheon Technologies Corp
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United Technologies Corp
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • F05D2230/12—Manufacture by removing material by spark erosion methods
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • 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
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)

Abstract

一种用于涡轮发动机压缩机或涡轮的翼片组，包括具有非线性缝26的罩12，该缝穿过罩延伸，从而将罩分成热隔离的罩区段24。通过匹配非线性表面28作为缝的边界，用传统的金属丝放电加工设备可以容易、便宜地加工该非线性表面。缝的非线性轮廓有效地阻止了流体泄漏。

Description

防漏翼片组
技术领域
本发明涉及涡轮发动机中所用类型的具有罩的翼片组，尤其涉及具有防漏、分区段罩的组。
背景技术
典型燃气涡轮发动机的压缩机部分包括限定发动机轴线的壳体以及固定翼片和旋转叶片在轴向轮流更替的阵列。每一个翼片阵列可以由若干翼片组构造而成，这些翼片组围绕壳体的内部周向分布，每一个组由壳体支撑。每一个翼片组包括径向内罩、径向外罩以及两个或更多个在罩间延伸的翼面。总起来说，内外罩为工作介质流体限定了部分环状流动路径的内部和外部边界。
在发动机运转期间，翼片组受到不均匀加热和冷却。由于组受应力过大，伴随的温度梯度会导致破坏。为了帮助减轻热诱导应力，两个罩中的一个可以通过缝分成区段，这些缝在两个邻近翼面的周向中间将罩隔开。因为每一个组的外罩将组连接到壳体上，所以通常都是分割内罩而不是外罩。通过允许罩区段彼此独立地膨胀和收缩，缝降低了破坏的风险。
形成缝的一种技术是金属丝放电加工(EDM)。金属丝放电加工使用这种形式的带电电极：围绕源线轴卷绕并且延伸到卷紧线轴的金属丝。翼片组罩暴露在线轴之间的金属丝上。在放电加工操作期间，金属丝从源线轴移动到卷紧线轴，并且同时向罩推进。金属丝电极和罩之间的电荷差异导致了从罩去除材料的放电。当材料被去除时，金属丝通过罩向前移动，直到缝完全形成。
罩缝的一个缺点是：这些缝提供了一个路径，在发动机运转期间，通过该路径，工作介质流体可从流动路径中漏出，或是非工作介质流体可渗入到流动路径中。通过使用小直径的放电加工金属丝来切制薄缝，即一个具有相应狭窄切口的缝，泄漏可得到一定程度的缓解。然而，使用细放电加工金属丝导致了加工时间的增加。此外，在放电加工操作期间，细放电加工金属丝比起粗放电加工金属丝更容易破损。由于翼片组中截留的微小微粒杂质的存在，细放电加工金属丝比起粗放电加工金属丝也更可能发生停转。最终，市场上买得到的能够使用细金属丝的放电加工设备比起能够使用较粗金属丝的放电加工设备更专业。结果，制造商可能发现：投资更专业化的细金属丝设备，在经济上无吸引力。因此，避免薄缝而支持相对较宽的缝是理想的。
减少通过宽缝泄漏的一个方法是：在缝内部提供凹槽，并且在凹槽内安装密封件。美国专利3,728,041、3,970,318以及5,167,485显示了此类型的装置。虽然这样的密封件可以很容易安装在各个翼片的罩之间，或是安装在邻近翼片组的周向末端之间，但这些密封件不易安装在单一翼片组的翼面内的罩缝中。此外，形成缝内凹槽增加了生产成本并且降低了生产量。缓解泄漏的另一个可能的方法是安装外部密封件，例如美国专利4,422,827中所示的密封带78，从而连接每一个缝。然而这样的外部密封件也增加了生产成本。
这是所需要的：带有热隔离罩区段的翼片组，并且是经济的，而且容易生产。
发明内容
根据本发明，翼片组包括具有非线性缝的罩，缝延伸穿过罩而将罩分成热隔离的罩区段。利用匹配非线性表面为缝确定边界，用传统的金属丝放电加工设备很容易制造该非线性表面并且花费不多。非线性缝有效地阻止了流体泄漏。
附图说明
图1是翼片组的透视图，本发明所采用的缝将翼片组的径向内罩隔开。
图2-5是图1中所示的缝的放大视图。
图6-8是具有弯曲部分的缝的放大视图。
图9是类似于图1的视图，显示了翼片组，在其内罩的侧末端上具有非线性的轮廓。
具体实施方式
参考图1-5，涡轮发动机的压缩机的翼片组包括径向外罩10、径向内罩12以及两个或更多个在罩间径向或沿翼展方向延伸的翼面14。外罩轴向末端上的钩16促进外罩接附到发动机壳体上，图中未示。内罩轴向末端上的脚18包含内部气封件，图中也未示。组在侧末端20之间周向延伸。当几个这样的组安装在涡轮发动机内时，罩限定了部分环状流体流动路径22的径向内部和外部边界。流动路径限定发动机的轴线，图中未示。翼片组自身一般是精加工到指定尺寸的铸造金属物件。
非线性缝26在周向邻近的翼面14之间将内罩12分为单个的区段24。通过金属丝放电加工或其他适当的处理来形成缝。图1中描述了四种不同类型的缝，然而在给定的组中通常仅使用一种类型的缝。内罩最左端的部分描述为其“铸态”的状态，即没有缝。每一个缝是非线性的，但可以包括两个或更多个直线部分，如在图2-4中所示。一对匹配的表面作为每一个缝的边界，例如28a、28b。如在此使用的，术语“匹配”表面指的是彼此大致精确配对的表面，即彼此互补的表面。这与美国专利3,728,041、3,970,318以及5,167,485中显示的表面不同，其所有表面的特征是缝内的凹槽，这些凹槽导致了邻近缝表面不匹配。
图2-5更详细地显示了四种缝。首先参考图2，非线性缝26包括三个直线部分26a、26b、26c，其中每一个直线部分与至少一个其他部分具有接合点32。每一个接合点与缝内角度方向的变化相应。例如，缝部分26a和26b之间的一个接合点32与从径向到侧向的大约90度的角度方位变化相应。另一个接合点32位于缝部分26b和26c之间，其与另一个从侧向到径向的大约90度的变化相应。累积的角度变化因此大约为180度。
图3显示了一个变形，其中缝包括三个直线部分和两个接合点。每一个接合点与大约120度的角度方位变化相应，累积的角度变化大约为240度。
图4显示了一个变形，其中缝包括七个直线部分和六个接合点。每一个接合点与大约90度的角度方位变化相应，累积的角度变化大约为540度。
接合点32处角度方位的突变帮助防止流体通过缝泄漏，并且因此允许使用低廉安置的、相对宽的缝，在其他情形下本来这些宽缝可能是不能令人满意的。每一个方位变化增加了流体泄漏的阻力。因此，较大的和/或较突然的变化优于较小的和/或较不突然的变化。因此，虽然可以使用仅具有两个直线部分和一个结合头的缝，可以确信：最实用和最具成本效益的缝是那些具有至少三个直线部分和合计至少大约为180度的两个方位变化的缝。期待更多数量的直线部分，从而进一步增加缝的泄漏阻力，但相应较长的缝长度将增加使用金属丝放电加工来切割缝的必要时间。泄漏阻力与生产复杂性之间的权衡是翼片组的设计者和生产者所要考虑的事情。
如在图6-8中所示，非线性缝不需要包含如以上实例中的直线部分，而是可以替代地为具有一个或多个曲率半径的弯曲缝。平均曲率半径R可以沿缝长度连续变化(图6)或不连续变化(图7)，因此限定了缝各个部分26a、26b之间的一个或多个不同的接合点32。如在图8中所示，缝可以包括弯曲和直线部分的组合。因为缝的泄漏阻力取决于方向改变的突然性和次数，平滑的弯曲缝可能提供不令人满意的泄漏阻力。预期具有突然方向变化的弯曲缝将优于平滑弯曲缝，但比起由直线部分组成的缝，其更难生产。图5的蜿蜒形缝是具有若干曲率半径连续变化的弯曲缝的一个实例。
缝不需要周向安置在每个翼面之间，而是可以替代地有选择地安置，例如在每两个或三个翼面之间安置，从而实现需要程度的热隔离。
图1的组是单个阵列或单级翼片的一个扇区。在一些发动机中，翼片组包括两个或更多个周向对准的分支组，其彼此成一整体，但彼此通过级间空间轴向隔开。在完全装配好的发动机中，转子叶片径向延伸到级间空间中。本发明包括这样的多级组，也包括所说明的单级组。
如在图9中所示，也可以使用缝26的非线性几何形状作为邻近翼片组的侧末端20之间的界面。这样的结构包括内部和外部罩10、12，该罩具有至少一个在罩之间延伸的翼面。罩的至少一个，如内罩12的侧末端具有非线性的轮廓，其与侧向相邻的翼片组末端上配对的非线性轮廓相匹配。
虽然利用压缩机的定子翼片说明了本发明，但本发明同样可适用于涡轮。此外，本发明包括这样的组：其中外部罩为分段罩，而不是内部罩。本领域的普通技术人员可以理解：在不超出后附权利要求书中提出的本发明的范围情况下，可以在形式和细节上做出种种改变。

Claims (10)

1.一种翼片组，其包括：
外部罩；
内部罩；
至少两个在罩之间延伸的翼面；
罩之一具有非线性缝，该缝在邻近翼面之间穿过罩延伸，从而限定罩区段，每一个缝由匹配非线性表面确定边界。
2.根据权利要求1所述的组，其特征在于：非线性缝包括至少两个缝部分，在其之间具有接合点，每个接合点对应于角度方位的变化。
3.根据权利要求2所述的组，包括至少三个缝部分，具有至少两个角度方位变化。
4.根据权利要求3所述的组，其特征在于：角度方位变化限定了至少约180度的累积角度变化。
5.根据权利要求1所述的组，其特征在于：非线性缝包括弯曲部分。
6.根据权利要求1所述的组，其特征在于：每一个非线性缝包括至少两个直线区段。
7.根据权利要求1所述的组，其特征在于：具有通过罩延伸的非线性缝的罩为内罩。
8.根据权利要求1所述的组，其特征在于：在组的每个邻近翼面之间，具有非线性缝。
9.根据权利要求1所述的组，其特征在于：通过放电加工形成缝。
10.一种翼片组，其包括：
具有外部侧末端的外部罩；
具有内部侧末端的内部罩；
至少一个在罩之间延伸的翼面；
外部和内部罩中的至少一个罩的侧末端具有非线性轮廓，该非线性轮廓与侧向邻近翼片组的侧末端上配对的非线性轮廓匹配。
CNA2003801053805A 2002-10-08 2003-10-08 防漏翼片组 Pending CN101405478A (zh)

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US10/266,649 US6910854B2 (en) 2002-10-08 2002-10-08 Leak resistant vane cluster
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DE (1) DE60313716T2 (zh)
IL (1) IL158258A (zh)
SG (1) SG126730A1 (zh)
TW (1) TWI266828B (zh)
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CN103119249A (zh) * 2010-09-30 2013-05-22 西门子公司 叶片环扇段、流体机械及其制造方法
CN104279008A (zh) * 2013-07-03 2015-01-14 航空技术空间股份有限公司 轴流式涡轮机的具有双固定装置的定子叶片扇区
CN105378227A (zh) * 2013-06-26 2016-03-02 西门子公司 具有阶梯状的和倾斜的平台棱边的涡轮叶片
CN114320488A (zh) * 2021-10-20 2022-04-12 中国航发四川燃气涡轮研究院 航空发动机涡轮导向器叶片缘板的封严结构
CN118046052A (zh) * 2024-04-16 2024-05-17 成都和鸿科技股份有限公司 一种叶片表面加工槽的定位方法

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US7128522B2 (en) * 2003-10-28 2006-10-31 Pratt & Whitney Canada Corp. Leakage control in a gas turbine engine
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