CN1816683A - 涡轮罩片 - Google Patents

涡轮罩片 Download PDF

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CN1816683A
CN1816683A CNA2004800189501A CN200480018950A CN1816683A CN 1816683 A CN1816683 A CN 1816683A CN A2004800189501 A CNA2004800189501 A CN A2004800189501A CN 200480018950 A CN200480018950 A CN 200480018950A CN 1816683 A CN1816683 A CN 1816683A
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turbine
contact member
turbine box
jet
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CN1816683B (zh
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田中崇
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IHI Corp
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IHI Corp
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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
    • F01D5/22—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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F01D25/145—Thermally insulated casings
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3215—Application in turbines in gas turbines for a special turbine stage the last stage of the turbine
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
    • 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

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

Abstract

一种罩片，用于结合在燃气涡轮发动机中，该燃气涡轮发动机具有涡轮箱以及与涡轮箱后端连接以抑制热燃气对涡轮箱及后涡轮箱的影响的后涡轮箱，设有以弧形形成并由涡轮箱支撑的支承板、一体地形成在支承板的内表面上以用于与旋转涡轮叶片接触的接触元件；以及从支承板的后端伸出并径向向内倾斜以将后涡轮箱与热燃气喷气屏蔽开的喷气护罩。

Description

涡轮罩片
技术领域
本发明涉及航空器等的燃气涡轮发动机，尤其涉及燃气涡轮发动机的涡轮罩的罩片。
背景技术
航空器等的燃气涡轮发动机的涡轮设有多级涡轮罩，用于抑制热燃气对涡轮箱的影响。涡轮罩直接暴露于热燃气，从而在那里可能承受很大的热应力。一般地，为了避免额外的热应力，各涡轮罩都被分割。多个罩片(shroud segment)组合形成各涡轮罩。
各罩片都设有支承板，作为其主体，并以弧形形成。支承板的外表面由涡轮箱支撑。支承板的内表面一体地设有接触元件，用于与旋转的涡轮叶片接触，该内表面形成为蜂窝状或类似形状。
最后一级的涡轮罩周围的涡轮箱可以暴露于具有高能量的热燃气的冲击中。这可导致局部和剧烈的升温，并造成涡轮箱的强度降低。为避免这一现象，涡轮进一步在最后一级涡轮罩的后侧设有喷气罩(jet cover)。
喷气罩代替涡轮箱而暴露于热燃气喷气，从而防止涡轮箱的局部升温。罩片进一步防止涡轮箱受到热燃气的影响。
相关技术公开在日本专利申请公开号H11-62509中。
发明内容
喷气罩有效地防止涡轮箱的升温。然而，设置喷气罩导致涡轮发动机的重量的增加和结构的复杂。而且，最后一级的涡轮罩的后侧具有复杂的结构，因此喷气罩的安装需要精细的工作。
本发明实现了上述问题的解决，并用于提供一种罩片，该罩片有效地抑制由热燃气喷气导致的涡轮箱的局部升温而不具有喷气罩。
根据本发明的一种技术方案，一种罩片，用于结合在燃气涡轮发动机中，该燃气涡轮发动机具有涡轮箱以及与涡轮箱后端连接以抑制热燃气对涡轮箱及后涡轮箱的影响的后涡轮箱，设有以弧形形成并由涡轮箱支撑的支承板、一体地形成在支承板的内表面上以用于与旋转涡轮叶片接触的接触元件；以及从支承板的后端伸出并径向向内倾斜以将后涡轮箱与热燃气喷气屏蔽开的喷气护罩。
更优选地，喷气护罩一体地形成在支承板的后端上。
更优选地，接触元件一体地设有后接触元件，该后接触元件布置在接触元件的后部中，并从接触元件径向向内突出。再更优选地，接触元件与喷气护罩构造为满足不等式0.25m[k[0.42m，其中m为喷气护罩从后接触元件的径向突出的长度，k为后接触元件从接触元件的径向突出的长度。
更优选地，该罩片还设有连接在罩片外表面上的前片簧和后片簧，以分别可插入涡轮箱上设置的凹槽中。
附图说明
图1为图5的箭头I处的根据本发明的实施例的罩片的剖视图；
图2为罩片的正面图；
图3为罩片的俯视图；
图4为表示两个罩片之间的对接状态的放大正面图；以及
图5为罩片安装其上的航空器的低压涡轮的剖视图。
具体实施方式
下面将参考图1至5描述本发明的实施例。在整个说明书中，方向的定义，比如前和后，与实际使用中的元件的方向一致。例如，前端在图1和5中表示在左手边。内和外通过邻近和远离涡轮发动机的轴线而定义。
现在参见图5。航空器的涡轮发动机的低压涡轮1设有涡轮箱3。涡轮箱3设有主涡轮箱5以及与涡轮箱5的后端一体连接的后涡轮箱7。主涡轮箱5的前端与高压涡轮箱9连接。
用于调整热燃气的多个涡轮喷嘴13、15和17固定并容纳在主涡轮箱5中。各涡轮喷嘴13、15和17都被分割为多个喷嘴段(nozzle segment)，其端与端对接而形成完整的环。多个涡轮转子交替地与涡轮喷嘴13、15及17一起布置，并分别设有涡轮叶片19、21、23及25。涡轮转子统一地旋转，并连接到低压压缩机(未示出)的转子以及风扇(未示出)的风扇转子。涡轮罩27、29、31和33分别绕涡轮转子布置。各涡轮罩27、29、31及33都被分割为多个罩片，其端与端对接而形成完整的环。
具有能量的热燃气从燃烧室(未示出)提供到低压涡轮1，以旋转涡轮转子，低压压缩机和风扇连接到涡轮转子。从而，低压涡轮1从热燃气中提取能量，并将它转换为驱动低压压缩机和风扇的能量。
图1至4中所示的罩片35分割自涡轮罩33，其布置在低压涡轮1的最后一级处。各罩片35设有以弧形形成的支承板37。前片簧41连接在支承板37的外表面上，并可滑动地配合到主涡轮箱5上设置的前槽39。在支承板37的外表面上，还有一个后片簧45连接在前片簧41的后部中。后片簧45可滑动地配合到主涡轮箱5上设置的后槽43。
支承板37由插入前槽39中的前片簧41与插入后槽43中的后片簧45支撑。支承板37的前端构造为支撑在罩片35前面并邻近罩片35布置的涡轮喷嘴17的外圈47。
在支承板37的外表面上设有沿其宽度方向延伸的连接板49。如图3中所示，连接板49的两端都从支承板49突出，以分别形成第一连接片51与第二连接片53。如图4中所示，第一连接片51和第二连接片53形成为互补形状，从而第一连接片51接合并支撑邻近的支承板37的第二连接片53。
支承板37的内表面一体地设有蜂巢57，用于接触旋转涡轮叶片25的端鳍(tip fin)55。蜂巢57的前端设有台阶部分57a。蜂巢57的后端一体地设有后蜂巢61。后蜂巢61从蜂巢57沿径向向内稍微突出。
支承板37的后端部分进一步延伸并沿径向向内倾斜，以形成喷嘴护罩(jet shield)63，用于防护后涡轮箱7免受从后蜂巢61与后端鳍59之间的间隙通过的燃气喷气J的影响。
前蜂巢57、后蜂巢61与喷气护罩63构造为满足下面所述的特定关系。为了有效地减弱燃气喷气气流，后蜂巢61的突出应该为长于喷气护罩63的关系。如图1中所示，优选地应该满足不等式0.25m[k，其中m为喷气护罩63从后蜂巢61的径向突出的长度，k为后蜂巢61从前蜂巢57的径向突出的长度。为了避免设置过长的突出，径向突出的长度k应该较小。优选地应该满足不等式k[0.42m。因此，前蜂巢57、后蜂巢61与喷气护罩63构造为满足不等式0.25m[k[0.42m。
如图1至3中所示，片突缘(segment flange)45的前端设有凹部65，由此，固定到主涡轮箱5的销钉67被接合，从而其相对旋转被钉住。
下面将描述根据本实施例的罩片35的工作方式和效果。
喷气护罩63承受燃气喷气J。从而，具有喷气护罩63的罩片35替代现有技术的喷气罩而防止后涡轮箱7直接暴露于燃气喷气J及由其造成的局部加热。
从前蜂巢57伸出的后蜂巢61使流经蜂巢57与后端鳍59之间的间隙的燃气喷气J减弱。如上所述，前蜂巢57、后蜂巢61与喷气护罩63构造为满足不等式0.25m[k[0.42m，其中m为喷气护罩63从后蜂巢61的径向突出的长度，k为后蜂巢61从前蜂巢57的径向突出的长度。因而，尽管后蜂巢61防止了过载，但燃气喷气J在撞击喷气护罩63前还是被有效地减弱。
喷气护罩63与支承板37的后端一体地形成，从而防止喷气护罩63的分离与位移。
除了前述防止后涡轮箱7的局部升温的功能外，形成涡轮罩27的多个罩片35还将低压涡轮箱3与热燃气屏蔽开，从而防止低压涡轮箱3的过度升温。
前述功能可以没有附加元件地实现。由于省略了这种附加元件，所以可获得低压涡轮1的重量减轻。而且，能够使低压涡轮1具有长寿命，从而涡轮发动机具有长寿命。
尽管本发明通过参考本发明的某些实施例而被如上地描述，但本发明并不限于上述实施例。本领域技术人员根据上述教导，会做出上述实施例的改进和变化。
工业适用性
本发明提供不具有喷气罩的罩片，其有效抑制涡轮箱的升温。

Claims (5)

1.一种罩片，用于结合在燃气涡轮发动机中，该燃气涡轮发动机具有涡轮箱以及与涡轮箱后端连接以抑制热燃气对涡轮箱及后涡轮箱的影响的后涡轮箱，具有：
支承板，其以弧形形成并由涡轮箱支撑；
接触元件，其一体地形成在支承板的内表面上，用于与旋转涡轮叶片接触；以及
喷气护罩，其从支承板的后端伸出并径向向内倾斜，以将后涡轮箱与热燃气喷气屏蔽开。
2.如权利要求1所述的罩片，其特征在于，
喷气护罩一体地形成在支承板的后端上。
3.如权利要求1所述的罩片，其特征在于，
接触元件一体地包括后接触元件，该后接触元件布置在接触元件的后部中，并从接触元件径向向内突出。
4.如权利要求3所述的罩片，其特征在于，
接触元件与喷气护罩构造为满足不等式0.25m[k[0.42m，其中m为喷气护罩从后接触元件径向突出的长度，k为后接触元件从接触元件径向突出的长度。
5.如权利要求1所述的罩片，其特征在于，进一步具有：
连接在罩片外表面上的前片簧和后片簧，以分别可插入涡轮箱上设置的凹槽中。
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