CN100443735C - 一种用于燃气涡轮发动机的导流叶片组件 - Google Patents

一种用于燃气涡轮发动机的导流叶片组件 Download PDF

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CN100443735C
CN100443735C CNB2004100632864A CN200410063286A CN100443735C CN 100443735 C CN100443735 C CN 100443735C CN B2004100632864 A CNB2004100632864 A CN B2004100632864A CN 200410063286 A CN200410063286 A CN 200410063286A CN 100443735 C CN100443735 C CN 100443735C
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guide vane
circumferential spacing
vane
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assembly
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CN1576611A (zh
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H·-T·刘
W·A·拜利
J·D·尼德梅尔
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General Electric Co
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/66Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
    • 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
    • F01D5/26Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/40Casings; Connections of working fluid
    • F04D29/52Casings; Connections of working fluid for axial pumps
    • F04D29/54Fluid-guiding means, e.g. diffusers
    • F04D29/541Specially adapted for elastic fluid pumps
    • F04D29/542Bladed diffusers
    • F04D29/544Blade shapes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/66Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/666Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/96Preventing, counteracting or reducing vibration or noise
    • F05D2260/961Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient propulsion technologies, e.g. for aircraft
    • YGENERAL 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
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00Metal working
    • Y10T29/49Method of mechanical manufacture
    • Y10T29/49316Impeller making
    • Y10T29/4932Turbomachine making
    • Y10T29/49323Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

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

Abstract

一种用于燃气涡轮发动机(10)的导流叶片组件,其包括多个周向隔开的导流叶片(502),其中至少包括有第一、第二和第三导流叶片(532,534,536)。第二导流叶片位于第一和第三导流叶片之间。所述多个导流叶片定位成使得在第一和第二导流叶片之间形成了第一周向间距(540),在第二和第三导流叶片之间形成了第二周向间距(542)。第二周向间距不同于第一周向间距。

Description

一种用于燃气涡轮发动机的导流叶片组件
技术领域
本发明大体上涉及燃气涡轮发动机,更具体地涉及燃气涡轮发动机所用的导流叶片组件。
背景技术
燃气涡轮发动机通常包括用来压缩工作流体如空气的压缩系统,其可由单个压缩机或多个以不同速度旋转的压缩机组成。压缩的空气被引导到燃烧室中,在此处其与燃料混合并点燃以产生燃气,这些燃气被引导至涡轮处。涡轮从燃气中抽取能量以驱动压缩机并产生有用功,以便推动飞机飞行或驱动某个负载,例如发电机或船用螺旋桨。
许多已知的压缩机包括出口导流叶片组件。出口导流叶片具有翼型状横截面。已知的出口导流叶片(OGV)组件包括多个周向间隔开的叶片,这些叶片围绕着压缩机出口基本上均匀地间隔开。已知的OGV组件还包括多个支柱,它们为压缩系统和OGV组件提供了结构支撑。
在工作期间,由支柱产生的阻碍会诱发处于支柱上游的非均匀流场,并在各个支柱前缘的附近产生了局部高压区域,这会对发动机的运转产生负面的影响。另外,在至少某些已知的燃气涡轮发动机中,当可调排气阀(VBV)的活门打开时,流场压力的不均匀性增加,而且受影响的区域向上游进一步扩散。在紧邻于出口导流叶片组件的上游处的一排转子叶片上会引发额外的应力。
为了便于降低转子组件上的应力,至少某些已知的发动机限制了VBV活门的操作。为了便于将应力保持在预定限值之下,其它已知的发动机修改了叶片与支柱的比率,增大了出口导流叶片和支柱之间的流向间距,和/或使用了多个不同形状的出口导流叶片。
发明内容
在本发明的一个方面提供了一种用于装配燃气涡轮发动机的方法,包括将发动机内壳和发动机外壳连接起来以使在其间形成了环形的流动通道,在内、外壳之间连接多个周向隔开的支柱,并将流动通道内的处于支柱上游的多个周向隔开的出口导流叶片连接起来,使得在第一导流叶片和第二导流叶片之间形成了第一周向间距,并且在第二导流叶片和第三导流叶片之间形成了第二周向间距。导流叶片设置成使得第二导流叶片处于第一和第三导流叶片之间,而且第二周向间距不同于第一周向间距。
在本发明的另一方面提供了一种用于燃气涡轮发动机的导流叶片组件。导流叶片组件包括多个周向隔开的导流叶片,其至少包括第一、第二、第三和第四导流叶片。第二导流叶片位于第一和第三导流叶片之间。所述多个导流叶片定位成使得在第一和第二导流叶片之间形成了第一周向间距,而在第二和第三导流叶片之间形成了第二周向间距。第二周向间距不同于第一周向间距。第二导流叶片平行于第三导流叶片,并且第一和第四导流叶片相对于第二和第三导流叶片倾斜地设置
在本发明的另一方面提供了一种燃气涡轮发动机,其包括由发动机的内外壳来限定边界的环形的压缩机排气流动通道,以及多个设置在流动通道内的周向隔开的导流叶片。所述多个导流叶片至少包括第一、第二和第三导流叶片。第二导流叶片位于第一和第三导流叶片之间。所述多个导流叶片定位成使得在第一和第二导流叶片之间形成了第一周向间距,而在第二和第三导流叶片之间形成了第二周向间距,并且第二周向间距不同于第一周向间距。
附图说明
图1是燃气涡轮发动机的示意图;
图2是增压器和包括有VBV活门的核心管道(core duct)的示意图。
图3是用于图1所示发动机的高压压缩机的一部分的示意图。
图4是用于图1所示发动机的示例性出口导流叶片组件的一部分的正面透视图。
图5是用于图1所示发动机的示例性支柱组件的一部分的正面透视图。
图6是可用于图1所示发动机的出口导流叶片组件的示意图。
图7是图6所示导流叶片的放大视图。
图8是显示了图7所示导流叶片的层叠轴线的示意图。
图中各标号的含义如下:10燃气涡轮发动机;12低压压缩机;13核心管道;14高压压缩机;16燃烧室;17支柱;18高压涡轮;20低压涡轮;24第一轴;26第二轴;28低压压缩机出口;30高压压缩机入口;32发动机的上游侧;50压缩机级;52转子叶片;56叶片组件;58转子盘;62定子机匣;74定子叶片;100出口导流叶片组件;110上安装凸缘;120下安装凸缘;130出口导流叶片;140压缩机出口流动通道;200支柱组件;210支柱的上安装凸缘;220支柱的下安装凸缘;230支柱;500导流叶片组件;502导流叶片;504导流叶片的侧壁;506导流叶片的侧壁;507内基部;508导流叶片的前缘;510导流叶片的后缘;512导流叶片的弦线;513导流叶片的层叠点;514导流叶片的中线;516导流叶片;520支柱;522支柱前缘;524支柱后缘;526支柱弦线;528支柱的周向间距;530导流叶片的周向间距;532第一导流叶片;534第二导流叶片;536第三导流叶片;538第四导流叶片;540第一周向间距;542第二周向间距;544第三周向间距。
具体实施方式
图1是燃气涡轮发动机10的示意图,其包括低压压缩机12、高压压缩机14以及燃烧室16。发动机10还包括高压涡轮18以及设置成串联轴流关系的低压涡轮20。压缩机12和涡轮20通过第一轴24相连,压缩机14和涡轮18通过第二轴26相连。在一个实施例中,发动机10是可从美国俄亥俄州辛辛那提市的通用电器公司买到的GE90发动机。
图2显示了将低压压缩机12和高压压缩机14相连的核心管道13。核心管道13包括多个出口导流叶片130、可调排气阀的活门15以及多个周向隔开的支柱17,通过排气阀15可从燃气通道中抽取排气。
在工作期间,空气从发动机10的上游侧32流过低压压缩机12,并通过核心管道13将被压缩的空气从低压压缩机12提供给高压压缩机14。然后将压缩空气传送到燃烧室组件16中,在燃烧室内其与燃料混合并被点燃。燃气从燃烧室16引出以驱动涡轮18和20。
图3是高压压缩机14的一部分的示意图。压缩机14包括有多个级50,每一级都包括一排转子叶片52和一排定子叶片74。转子叶片52由转子盘58支撑并与转子轴26相连。定子机匣62围绕转子叶片32和定子叶片组件56周向地延伸,因此定子叶片74由机匣62支撑。
图4是用于发动机10(图1所示)的示例性出口导流叶片组件100的一部分的正面透视图。出口导流叶片(OGV)组件100包括多个出口导流叶片130,它们各自在上安装凸缘110和下安装凸缘120之间大致径向地延伸,并且围绕着压缩机14周向间隔开。在一个实施例中,OGV组件100制造成凸缘110和120均与叶片130相连的弧段。在另一实施例中,OGV组件100形成为一个整体式组件。
图5是用于发动机10(图1所示)的示例性支柱组件200的一部分的正面透视图。支柱组件200包括多个各自在上安装凸缘210和下安装凸缘220之间延伸的支柱230。支柱组件200是发动机10的用于促进保持各个部件在发动机10内的方位的多个框架和支撑组件中的其中之一。更具体地说,这种框架和支撑组件与固定的部件相连,并为转子轴承提供支撑。支柱组件230连接在压缩机14的出口(未示出)的附近,使得支柱230围绕压缩机14的出口周向间隔开,并且在流动通道140上从压缩机14的出口处延伸出来。OGV组件100定位在支柱组件200的上游并由支柱组件200来支撑。导流叶片130也在流动通道140上从压缩机14的出口处延伸出来。
图6是用于燃气涡轮发动机10(图1所示)的出口导流叶片组件500的示意图。图7是包含在导流叶片组件500内的导流叶片502的放大视图。导流叶片组件500包括多个周向隔开的导流叶片502,其在压缩机出口流动通道140上延伸。各导流叶片502包括一对在前缘508和后缘510处连接起来的侧壁504和506。各导流叶片502的弦线512分别在各自的前缘508和后缘510之间延伸。
图8是导流叶片502的示意图,其显示了层叠轴线516。侧壁504和506从内基部507处径向向外地延伸到外端(未示出)。图7所示的截面垂直于侧壁504和506。在从导流叶片502的基部507到外端的各个这种截面上,从前缘508到后缘510所形成的中线514将叶片基本上分成两半。层叠点513沿着中线514形成在前缘508和后缘510之间的基本上一半距离的位置处。层叠轴线516在叶片502的从基部507到外端的叶片长度上沿着由层叠点513所形成的线而延伸。
导流叶片组件500位于核心管道13(图2所示)内,其还包括在出口流动通道140上延伸的多个支柱520。各支柱520都连接在导流叶片502的下游,而且各支柱520均包括前缘522和后缘524。各支柱520的弦线526分别在各支柱的前缘522和后缘524之间延伸。更具体地说,支柱520位于流动通道140上,使得形成于相邻支柱520之间的周向间距528在整个核心管道13上是基本上均匀的。
通常,相邻导流叶片502之间形成的周向间距530围绕着导流叶片组件500是基本上均匀的。然而,在紧邻于各相应支柱520的上游处,四个相邻的导流叶片532,534,536和538是以非均匀的周向间距相连并且错开,这一点如下所详述。更具体地说,虽然导流叶片532,534,536和538与其它导流叶片502相同地构造而成,但是叶片532,534,536和538的定位不同于叶片502。具体地说,形成于叶片532和534之间的第一周向间距540基本上等于均匀的间距530。然而,形成于相邻叶片534和536之间的第二周向间距542不同于第一周向间距540。在该示例性实施例中,第二周向间距542至少比第一周向间距540宽30%。形成于第三导流叶片536和相邻导流叶片538之间的第三周向间距544基本上等于第一周向间距540。
导流叶片532,534,536和538还周向定位成使得延伸穿过第二叶片534的层叠轴线在流动通道140的方向上与至少一个支柱520的前缘522基本上处于同一直线。而且,虽然导流叶片534和536基本上平行于其余导流叶片502来设置,然而第一导流叶片532和第四导流叶片538定位成偏开或错开一个角度θ,这个角度是相对导流叶片502来测量的。因此,第一导流叶片532和第四导流叶片538分别相对于其余导流叶片502的定向而倾斜地设置。在一个实施例中,叶片532和538偏开至少约1度的角度θ。在另一实施例中,第一导流叶片532偏开至少约-1度的角度θ,使得第一导流叶片532相对于流动通道的轴线而言处于更敞开的方位,而第四导流叶片538偏开至少约+1度的角度θ,使得第四导流叶片538相对于流动通道的轴线而言处于更封闭的方位。
在工作期间,叶片534和536之间的增大的周向间距542为流经各支柱520的气流提供了附加的引导,从而降低了作用在各支柱520两侧上的压力差。更具体地说,增大的周向间距542便于减小因叶片支柱连接所引起的不均匀的压力场传播。另外,由于这种增大的周向间距542,包括于组件500内的叶片502的数量也可在周向上减少,这样就减小了导流叶片组件500的整体重量。在一个实施例中,导流叶片组件500所包括的叶片502减少了超过5%。
上述出口导流叶片组件提供了用于减轻因OGV级和支柱组件之间的刚性连接所引起的压力场影响的成本效率合算的方法。这种装置能够显著地降低紧邻于叶片组件的上游处的那排叶片上的最大叶片应力,还具有可提高发动机性能并降低发动机的重量和成本的优点。
在上文中已经详细地介绍了导流叶片组件的示例性实施例。导流叶片组件并不限于本文所介绍的具体实施例,而是各组件的零件都可单独地且独立于本文所述的其它零件来使用。例如,各导流叶片组件的零件也都可与其它导流叶片零件相结合地使用。
虽然已经针对各种具体的实施例介绍了本发明,然而本领域的技术人员应当理解,在权利要求限定的精神和范围内,本发明可通过各种改进方式来实施。

Claims (5)

1.一种用于燃气涡轮发动机(10)的导流叶片组件,所述导流叶片组件包括多个周向隔开的导流叶片(502),其至少包括第一、第二、第三和第四导流叶片(532,534,536),所述第二导流叶片(534)位于所述第一和第三导流叶片(532,536)之间,所述多个导流叶片(502)定位成使得在所述第一和第二导流叶片(532,534)之间形成了第一周向间距(540),而在所述第二和第三导流叶片(534,536)之间形成了第二周向间距(542),所述第二周向间距(542)不同于所述的第一周向间距(540),并且所述第二导流叶片(534)平行于所述第三导流叶片(536),所述第一和第四导流叶片(532,538)相对于所述第二和第三导流叶片(534,536)倾斜地设置。
2.根据权利要求1所述的导流叶片组件,其特征在于,所述导流叶片组件还包括多个周向隔开的支柱(520),所述支柱位于所述多个导流叶片(502)的下游,使得延伸穿过所述第二导流叶片(534)的层叠轴线(513)在流动通道(140)的方向上与所述多个支柱(520)中的至少一个支柱的前缘(522)处于同一直线。
3.根据权利要求2所述的导流叶片组件,其特征在于,所述第四导流叶片(538)与所述第三导流叶片(536)相邻,使得所述第三导流叶片(536)位于所述第二和所述第四导流叶片(534,538)之间,形成于所述第三和第四导流叶片(536,538)之间的第三周向间距(544)等于所述第一周向间距(540)。
4.根据权利要求1所述的导流叶片组件,其特征在于,所述第一和第四导流叶片(502,504)与所述第二和第三导流叶片(534,536)偏开至少1度。
5.根据权利要求1所述的导流叶片组件,其特征在于,所述第二周向间距(542)至少比所述第一周向间距(540)宽30%。
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