CN100538018C - 涡轮罩片 - Google Patents

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CN100538018C
CN100538018C CNB2004800189484A CN200480018948A CN100538018C CN 100538018 C CN100538018 C CN 100538018C CN B2004800189484 A CNB2004800189484 A CN B2004800189484A CN 200480018948 A CN200480018948 A CN 200480018948A CN 100538018 C CN100538018 C CN 100538018C
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hook
cover sheet
support plate
turbine
slit
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CN1816681A (zh
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田中崇
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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
    • 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
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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)
  • Supercharger (AREA)

Abstract

一种结合在燃气涡轮发动机中的罩片，用于抑制热燃气对涡轮箱的影响，该涡轮箱具有与罩片接合的凹槽和钩。罩片设有：弧形支承板，该支承板的前端由凹槽支撑，以允许燃气涡轮发动机轴向位移；在支承板外表面上沿周向形成的狭槽，该狭槽与钩接合，以进行轴向固定；和接触元件，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。狭槽构造为满足不等式v＜t≤(v+0.1mm)，其中v为钩的长度，t为狭槽的宽度。

Description

涡轮罩片
技术领域
本发明涉及飞机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
飞机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，从而在那里可能被施加严重的热应力。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。支承板的前端可移动地固定于涡轮箱，其中该前端可沿涡轮轴线方向移动。支承板的后端不可移动地固定于涡轮箱。这一固定方式允许轴线方向的支承板的热位移。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。
涡轮箱设有后箱钩，并且具有C字截面形状的C形夹支撑支承板的后端与后箱钩，其方式为支承板的后端的外表面与后箱钩的内表面接触。从而，支承板的后端固定到涡轮箱，其间的轴向间隙被密封，使从那里通过的向涡轮箱的热燃气的流动得到抑制。
罩片和涡轮箱使涡轮箱免受热燃气的影响。
相关技术公开在日本专利申请公开号H11-62509中。
发明内容
在罩片的支承板因大的热应力而变得弯曲不足的情况下，其后端与涡轮箱之间的轴向间隙变宽。这可导致减弱C形夹对空隙的密封。涡轮箱不能充分防止热燃气的影响。同时，C形夹本身导致涡轮发动机的重量增加。
本发明实现了上述问题的解决，并用于提供一种罩片，其有效地抑制热燃气对涡轮箱的影响，而无需具有C形夹。
根据本发明的第一个技术方案，一种罩片，用于结合在燃气涡轮发动机中，以抑制热燃气对涡轮箱的影响，该涡轮箱具有与罩片接合的凹槽和钩，罩片设有：弧形支承板，该支承板的前端由凹槽支撑，以允许燃气涡轮发动机轴向位移；在支承板外表面上沿周向形成的狭槽，该狭槽与钩接合，以进行轴向固定；和接触元件，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。狭槽构造为满足不等式v<t≤(v+0.1mm)，其中v为钩的长度，t为狭槽的宽度。
优选地，该罩片还设有在支承板的前端上一体地形成并沿轴向向前突出的环形片钩，该片钩与凹槽可滑动地接合。
更优选地，该罩片还设有从弧形突缘轴向向前突出的环形突缘，弧形突缘从支承板的前端径向向内伸出，用于支撑在罩片前面并邻近罩片设置的涡轮喷嘴的外圈。
再优选地，环形突缘构造为满足不等式2k≤s≤2.8k，其中k为环形片钩的长度，s为环形突缘的长度。
附图说明
图1为图6的箭头I处的根据本发明的实施例的罩片的剖视图；
图2为图1的箭头II处的绕罩片后端的罩片的放大图；
图3为图1的箭头III处的绕罩片前端的罩片的放大图；
图4为罩片的正面图；
图5为罩片的俯视图；以及
图6为装有罩片的飞机的低压涡轮的剖视图。
具体实施方式
下面将参考图1至6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至3和6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6。飞机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，其中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5中所示的罩片35分割自第二涡轮罩29。各罩片35设有以弧形形成的支承板37。
片钩41以环状一体地形成在支承板37的前端上，并向前突出。片钩41可以可滑动地配合到形成在主涡轮箱5的内表面上的凹槽39。间隙形成在片钩41的前端与凹槽39的底部之间，以允许支承板37沿横向的热位移。从而支承板37的前端由主涡轮箱5可移动地支撑。
如图1和3中所示，环状形成的片突缘45从弧形突缘的内周沿轴线向前突出，该弧形突缘从支承板37的前端一体地径向向内(即，向低压涡轮1的轴线)伸出。片突缘45构造为支撑在罩片35前面并邻近罩片35布置的涡轮喷嘴13的外圈43。片突缘45与片钩41构造为满足下述的特定关系。为了有效地抑制热燃气流动，片突缘45应该与片钩41关联地较长。优选地应该满足不等式2k≤s，如图3中所示，其中k为片钩41的长度，s为片突缘45的长度。为了避免提供超长的突缘，长度s应该较小。优选地应该满足不等式s≤2.8k。因此，片突缘45与片钩41构造为满足不等式2k≤s≤2.8k。
如图4和5中所示，片突缘45设有凹部47，由此，固定到主涡轮箱5的销钉49被接合，从而其相对旋转被钉固。
如图1和2中所示，在支承板37的后端处及外表面上，沿周向形成片槽53，以紧固地与主涡轮5的箱钩51连接。片槽53主要由朝后的第一表面53fa、与第一表面53fa相对的第二表面53fb以及朝外的第三表面53fc。在第三表面53fc上，沿周向形成突棱55，以可滑动地接触箱钩51。
片槽53构造为即便在罩片35沿轴向热位移时也有效地密封片槽53与箱钩51之间的轴向间隙。为了获得这一功能，第一表面53fa和第二表面53fb都被机械修整，以满足不等式v<t≤(v+0.1mm)，如图2中所示，其中箱钩51的长度为v，片槽53的宽度为t。
支承板37的内表面一体地设有蜂巢单元57，用于接触旋转涡轮叶片21的端片。蜂巢单元57的后端可滑动地与在蜂巢单元57后部中并邻近蜂巢单元57布置的涡轮喷嘴15接合。涡轮喷嘴15设有与箱钩51可滑动地接合的外圈59。从而，罩片35和涡轮喷嘴15共同与箱钩51接合，从而后部37的后端由箱钩51固定地支撑。
后部37的两侧表面都分别设有密封槽63。类似地，片突缘45的两个侧表面都分别设有与密封槽63相通的密封槽65。密封槽63和65接收塞缝片密封板61，用于密封热燃气。
下面将描述根据本实施例的罩片35的工作方式和效果。
片槽53的尺寸设计为满足不等式v<t≤(v+0.1mm)，其中v为箱钩51的长度，t为片槽53的宽度。从而，即便在支承板37因大热应力而变得弯曲不足时，也防止箱钩51与片槽53之间的轴向间隙变宽。经由支承板37的后端的流向主涡轮箱5的热燃气被有效地抑制。抑制热燃气流不需要任何附加的元件，比如C形夹。
片突缘45向前突出，并布置在片钩41的内侧处，从而片突缘45有效地抑制热燃气向片钩41流动。由热燃气造成的片突缘45的热位移被抑制，向低压涡轮箱3的热燃气流也被抑制。如上所述，片突缘45与片钩41构造为满足不等式2k≤s≤2.8k，其中k为片钩41的长度，s为片突缘45的长度。从而，无需提供过长的突缘，向片钩41的热燃气流也被有效地抑制。
即便无需比如C形夹的任何附加元件，本实施例的罩片35也可以有效地抑制热燃气流对低压涡轮箱3的影响。由于省略了这一附加元件，所以可获得低压涡轮1的重量减小。
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
根据本发明的罩片有效地抑制由热燃气造成的对涡轮箱的影响，而无需具有C形夹。

Claims (4)

1.一种罩片，用于结合在燃气涡轮发动机中，以抑制热燃气对涡轮箱的影响，该涡轮箱具有接合罩片的凹槽和钩，该罩片包括：
弧形支承板，该支承板的前端由所述凹槽支撑，以允许燃气涡轮发动机轴向位移；
在支承板外表面上沿周向形成的狭槽，该狭槽与所述钩接合，以进行轴向固定；和
接触元件，一体地形成在支承板的内表面上，用于接触旋转涡轮叶片；
其中，所述狭槽的尺寸构造为满足不等式v<t≤(v+0.1mm)，以保持与所述钩紧密接合而无需具有C形夹，其中v为所述钩的长度，t为所述狭槽的宽度。
2.如权利要求1所述的罩片，还包括：
在支承板的前端上一体地形成并轴向向前突出的环形片钩，该片钩可滑动地接合所述凹槽。
3.如权利要求2所述的罩片，还包括：
自一弧形突缘轴向向前突出的环形片突缘，所述弧形突缘自支承板的前端径向向内伸出，用于支撑在罩片前面并邻近罩片设置的涡轮喷嘴的外圈。
4.如权利要求3所述的罩片，其中：
所述片突缘构造为满足不等式2k≤s≤2.8k，其中k为所述片钩的长度，s为所述片突缘的长度。
CNB2004800189484A 2003-07-04 2004-07-02 涡轮罩片 Expired - Lifetime CN100538018C (zh)

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US7407368B2 (en) 2008-08-05
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