CN1314882C - 用于保持密封条连接的装置 - Google Patents
用于保持密封条连接的装置 Download PDFInfo
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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
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
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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
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
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- 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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Abstract
本发明涉及一种将条状密封垫保持在涡轮机喷嘴上的装置,所述喷嘴由多个具有导流片的扇形体构成,所述导流片在内和外平台元件之间延伸,至少一个所述平台元件包括径向设置在所述平台元件和相邻结构元件之间的空间中的密封条(30),以在所述元件之间提供流体密封,两相邻扇形体的对应密封条相互接触,并且它们的接缝由设置在所述密封条之间的接缝盖条(31)和用于将所述密封条保持在密封位置的保持部件所覆盖。
Description
技术领域
本发明涉及在涡轮机中运送热气体的空气动力学气流与将冷空气输送到例如喷嘴的腔室之间设置密封的问题。
更具体地,本发明涉及将条状密封垫保持到轴向设置在两个结构元件之间的喷嘴上的装置,所述喷嘴由具有在内和外平台元件之间延伸的导流片的多个扇形体(sector)构成,至少一个所述平台元件包括径向设置在所述平台元件和邻近结构元件之间的空间中的密封条,以便在所述元件之间提供流体密封,对应于两个相邻扇形体的密封条相互接触,它们的接头被设置在所述相互接触的密封条之间的接缝盖条、和一个用于将所述密封条保持在密封位置的部件所覆盖。
背景技术
条密封装置通常用于在由燃烧室所输送的热气体流和在燃烧室内外侧并输送用于冷却喷嘴和转动叶片的环形腔室之间提供流体密封。
密封条被设置在平台元件和结构元件之间的环形空间中,并且在密封位置时它们压靠所述元件的生成线。
这些密封条经受施加到它们两侧的压力。通常,冷却气体的压力高于热气体的压力,并且密封条设置成使得压力差有利地作用在期待的密封上。然而,由于飞机涡轮机要经受各种工作条件,会出现很多问题,特别是由于在某些飞行阶段的膨胀和振动以及小的压差。
这就是为什么密封装置包括用于将密封条连续推压到密封位置的偏压装置的原因。
因此,FR 2649463描述了一种条密封垫,其中密封条可滑动地安装在轴向销上,并且由分别包括安装在销子上的一部分的弹簧加压。
FR 2786222描述了一种密封条保持架,其一端压靠密封条,第二端弯曲成发夹形状并啮合在一个结构元件的凹槽中,以提供轴向定位。密封条和保持架具有弯曲片,以使保持架也轴向定位密封条。该条件提供了由两相邻喷嘴扇形体支撑的保持架,以压在接缝盖条上。
在这两个实施中,弹性元件作用在由扇形体携带的密封条上,弹簧或保持架安装在扇形体上。
发明内容
本发明的目的在于克服上述现有技术缺陷,提供一种相对平坦的保持部件,其可以很好地控制周向延伸的弹性片与接缝盖条之间的接触点的位置。
本发明的保持装置特征在于,它由每个扇形体携带的并在所述扇形体的周边周向延伸的片构成,所述片的自由端在所述扇形体外的环形区域中压靠接缝盖条。
这种设置可以限制所述片的周向位移并控制它的压靠点位置。
优选地通过轴向铆钉提供连接,铆钉体干穿过形成在片上的开口。密封条也可滑动地安装在铆钉的体干上。
可滑动连接优选地设置在所述片远离自由端的端部,并且它被轴向固定。与此不同的是,通过连续地将所述片推向密封条的发夹式***可提供另外的片连接。
附图说明
根据以下结合附图和示例的详细说明,本发明的其它特征和优点变得更加明显,其中:
图1是涡轮机的一部分的剖视图,显示了本发明的密封装置可用于其中的环境的示例;
图2是用于保持喷嘴两相邻扇形体的密封条的装置的径向平面图;
图3是图2保持装置的展开轴向视图;
图4是本发明的保持片的立体图;
图5是用于图4的保持片的铆钉和发夹式紧固件装置的立体图;和
图6是接缝盖条的轴向视图。
具体实施方式
图1所示的涡轮机具有燃烧室2,紧随燃烧室的是由一级或多级构成的高压涡轮。每级涡轮包括以现有方式交替设置的一排导流片4和一排转动叶片5。高压涡轮由一个结构支承,该结构包括在其径向外侧由螺栓相互连接的燃烧室外壳6、涡轮外环7和涡轮壳体8。在涡轮3的径向内侧,涡轮内壳9与燃烧室的内壳10连接。燃烧室2是环形的,并由外套壳11和内套壳12限定。按照现有方式,高压冷却空气绕着环形燃烧室2在由燃烧室2的外壳6和外套壳11限定的外部环形腔室13、以及由燃烧室2的内壳10和内套壳12限定的内部环形腔室14内流动。冷却空气向下游流过形成在将外壳6下游端连接到燃烧室2的外套壳11的壁16上的孔口15,以冷却导流片4,冷却空气还向下游流过形成在将燃烧室2的内壳10下游端与内套壳12相互连接起来的壁18上的孔口17,以冷却导流片4的内平台19。
按照现有方式,所述一排导流片4由一体式扇形体S构成,每个扇形体包括将外平台元件20和内平台元件19相互连接起来的多个导流片4。必须防止扇形体S的平台元件19、20与相邻结构元件之间的任何空气泄漏。
因此,第一密封垫设置在外平台元件20的上游端22和壁16之间的空间21中、外平台元件20的下游端24和涡轮的外环7之间的空间23中、以及内平台19的上游端26和壁18之间的空间25中。
每个密封垫由多个弯曲和相互接触的密封条30构成,每个密封条由喷嘴扇形体S携带并压靠相应的凸肩40,凸肩40在外平台元件20的上游端22和下游端24以及在内平台元件19的上游端26形成在扇形体S上。这些密封条30径向向外延伸成封闭空间21和23的密封条,它们径向向内延伸成封闭空间25的密封条,而且它们的生成线压靠相邻结构元件。
在同一密封垫中的相邻密封条30a、30b在将两个邻接的扇形体S1和S2分开的平面P1上相互接触。如图2所示,在这两个密封条30a和30b之间的接缝被设置在这些密封条的相邻端部之间的接缝盖条31和将密封垫推压到密封位置的部件32所覆盖。
保持部件32是通过两个铆钉40a和40b固定到扇形体例如S1上的保持片33的自由圆形端,铆钉40a,40b固定到平台元件19或20的相应凸出部41a和41b上。这些铆钉的体干穿过重合地形成在保持片33、密封条30a、以及接缝盖条31a和31b上的孔口。保持片33远离自由端32的端部34弯曲成U形形状,并具有两个圆柱形孔口50a、50b,以提供周向固定的连接,因为所述端部34被轴向地固定在位。铆钉40b和保持片33之间的连接是通过将保持片33的中部推向密封条30a的发夹形装置43提供,该连接沿周向是自由的。如图3所示,保持片33在扇形体S1的平台元件上周向延伸,但压靠接缝盖条31a的自由端32位于扇形体S1外侧,并且在图2和3所示实施例中位于扇形体S2所占据的角形区域中。在图3中,可以看出,接缝盖条31在其端部具有相对的凹口35,由两相邻扇形体S1和S2携带的相邻铆钉的体干穿过凹口35。
图4是保持片33的立体图。端部34的分支包括圆柱形孔口50a和50b,铆钉40a的体干对齐地穿过孔口50a和50b。该图也显示了由铆钉40b的体干穿过的椭圆形孔口51,以提供周向可滑动连接。
图5显示了铆钉40b和跨骑地设置在凸出部41b上的发夹形装置43,发夹形装置43的部分52压靠孔口51周围的保持片33的中间部分。
图6显示了用于覆盖两相邻密封条30a和30b的邻近端部的接缝盖条31。接缝盖条31的端部具有相对的凹口35,用于接收安装在两相邻扇形体上的两相邻铆钉40a和40b的体干。
Claims (7)
1、一种涡轮机,包括轴向设置在两结构元件之间的喷嘴,所述喷嘴由多个具有导流片的扇形体构成,所述导流片在内和外平台元件之间延伸,至少一个所述平台元件包括径向设置在所述平台元件和相邻结构元件之间的空间中的密封条(30),以在所述元件之间提供流体密封,两相邻扇形体的对应密封条相互接触,并且它们的接缝由设置在所述密封条之间的接缝盖条(31)和用于将所述密封条保持在密封位置的保持部件所覆盖;
所述涡轮机的特征在于,所述保持部件由一个扇形体(S1)所携带的并且在所述扇形体周边周向延伸的片(33)构成,所述片(33)的自由端(32)在所述扇形体(S1)外侧的角形区域压靠接缝盖条(31)。
2、如权利要求1所述的涡轮机,其特征在于,所述片(33)通过两个周向偏移的连接保持在所述扇形体上。
3、如权利要求2所述的涡轮机,其特征在于,所述连接之一能够周向滑动。
4、如权利要求3所述的涡轮机,其特征在于,所述连接通过穿过形成在所述片(33)上的开口的轴向铆钉(40a、40b)来提供。
5、如权利要求4所述的涡轮机,其特征在于,所述滑动连接是通过连续地将所述片(33)推向所述密封条(30)的发夹形装置(43)来提供。
6、如权利要求5所述的涡轮机,其特征在于,所述片的另一连接设置在所述片(33)远离其自由端(32)的端部(34)、并且是轴向固定的。
7、如权利要求4到6任一所述的涡轮机,其特征在于,所述接缝盖条(31)在其端部具有相对凹口(35),所述凹口(35)使得两邻近扇形体(S1,S2)的相邻铆钉(40a,40b)从其穿过。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0112133A FR2829796B1 (fr) | 2001-09-20 | 2001-09-20 | Dispositif de maintien des joints de plates-formes de secteurs de distributeur de turbomachine a lamelles d'etancheite |
FR01/12133 | 2001-09-20 |
Publications (2)
Publication Number | Publication Date |
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CN1556893A CN1556893A (zh) | 2004-12-22 |
CN1314882C true CN1314882C (zh) | 2007-05-09 |
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Application Number | Title | Priority Date | Filing Date |
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CNB02818453XA Expired - Lifetime CN1314882C (zh) | 2001-09-20 | 2002-09-18 | 用于保持密封条连接的装置 |
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Country | Link |
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US (1) | US7037071B2 (zh) |
EP (1) | EP1296023B1 (zh) |
JP (1) | JP4051031B2 (zh) |
CN (1) | CN1314882C (zh) |
CA (1) | CA2461149C (zh) |
DE (1) | DE60203574T2 (zh) |
ES (1) | ES2236465T3 (zh) |
FR (1) | FR2829796B1 (zh) |
MA (1) | MA26215A1 (zh) |
RU (1) | RU2296865C2 (zh) |
UA (1) | UA79094C2 (zh) |
WO (1) | WO2003025350A1 (zh) |
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Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
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US4126405A (en) * | 1976-12-16 | 1978-11-21 | General Electric Company | Turbine nozzle |
FR2649463A1 (fr) * | 1989-07-10 | 1991-01-11 | Gen Electric | Dispositif d'etancheite a feuille |
US5118120A (en) * | 1989-07-10 | 1992-06-02 | General Electric Company | Leaf seals |
US5289677A (en) * | 1992-12-16 | 1994-03-01 | United Technologies Corporation | Combined support and seal ring for a combustor |
US5797723A (en) * | 1996-11-13 | 1998-08-25 | General Electric Company | Turbine flowpath seal |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2786222B1 (fr) | 1998-11-19 | 2000-12-29 | Snecma | Dispositif d'etancheite a lamelle |
US6418727B1 (en) * | 2000-03-22 | 2002-07-16 | Allison Advanced Development Company | Combustor seal assembly |
-
2001
- 2001-09-20 FR FR0112133A patent/FR2829796B1/fr not_active Expired - Fee Related
-
2002
- 2002-09-18 DE DE60203574T patent/DE60203574T2/de not_active Expired - Lifetime
- 2002-09-18 WO PCT/FR2002/003182 patent/WO2003025350A1/fr active Application Filing
- 2002-09-18 RU RU2004108041/06A patent/RU2296865C2/ru active
- 2002-09-18 CA CA002461149A patent/CA2461149C/fr not_active Expired - Lifetime
- 2002-09-18 ES ES02292281T patent/ES2236465T3/es not_active Expired - Lifetime
- 2002-09-18 US US10/489,306 patent/US7037071B2/en not_active Expired - Lifetime
- 2002-09-18 JP JP2003528957A patent/JP4051031B2/ja not_active Expired - Lifetime
- 2002-09-18 CN CNB02818453XA patent/CN1314882C/zh not_active Expired - Lifetime
- 2002-09-18 EP EP02292281A patent/EP1296023B1/fr not_active Expired - Lifetime
- 2002-09-18 UA UA2004032031A patent/UA79094C2/uk unknown
-
2004
- 2004-03-11 MA MA27572A patent/MA26215A1/fr unknown
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4126405A (en) * | 1976-12-16 | 1978-11-21 | General Electric Company | Turbine nozzle |
FR2649463A1 (fr) * | 1989-07-10 | 1991-01-11 | Gen Electric | Dispositif d'etancheite a feuille |
US5118120A (en) * | 1989-07-10 | 1992-06-02 | General Electric Company | Leaf seals |
US5289677A (en) * | 1992-12-16 | 1994-03-01 | United Technologies Corporation | Combined support and seal ring for a combustor |
US5797723A (en) * | 1996-11-13 | 1998-08-25 | General Electric Company | Turbine flowpath seal |
Also Published As
Publication number | Publication date |
---|---|
CA2461149C (fr) | 2009-06-16 |
JP4051031B2 (ja) | 2008-02-20 |
DE60203574D1 (de) | 2005-05-12 |
FR2829796B1 (fr) | 2003-12-12 |
US20040239050A1 (en) | 2004-12-02 |
CN1556893A (zh) | 2004-12-22 |
EP1296023A1 (fr) | 2003-03-26 |
RU2004108041A (ru) | 2005-05-20 |
WO2003025350A1 (fr) | 2003-03-27 |
CA2461149A1 (fr) | 2003-03-27 |
DE60203574T2 (de) | 2006-02-09 |
RU2296865C2 (ru) | 2007-04-10 |
JP2005503509A (ja) | 2005-02-03 |
US7037071B2 (en) | 2006-05-02 |
EP1296023B1 (fr) | 2005-04-06 |
UA79094C2 (uk) | 2007-05-25 |
MA26215A1 (fr) | 2004-07-01 |
FR2829796A1 (fr) | 2003-03-21 |
ES2236465T3 (es) | 2005-07-16 |
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