CN104508251A - 用于燃气涡轮发动机的护罩组件和密封件 - Google Patents
用于燃气涡轮发动机的护罩组件和密封件 Download PDFInfo
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- CN104508251A CN104508251A CN201380022344.6A CN201380022344A CN104508251A CN 104508251 A CN104508251 A CN 104508251A CN 201380022344 A CN201380022344 A CN 201380022344A CN 104508251 A CN104508251 A CN 104508251A
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- cover assembly
- rope seal
- seal part
- assembly according
- housing parts
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Classifications
-
- 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
- F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
-
- 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
- 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
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/28—Arrangement of seals
-
- 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
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gasket Seals (AREA)
Abstract
一种具有设置在护罩吊架与周围外壳结构之间的绳索密封件的护罩组件。
Description
背景技术
本发明涉及用于燃气涡轮发动机中的护罩组件,并且更具体来说涉及一种用于填充涡轮机喷嘴吊架(hanger)与周围机架之间形成的空腔的密封件。
在燃气涡轮发动机中,热气体离开燃烧器并且由涡轮机利用来转化成机械能。这种机械能驱动上游高压压缩机。涡轮机包括由涡轮机转子携带的多个叶片。转子叶片的尖端由多个护罩段紧密限制。护罩由位于护罩径向外部的多个护罩支撑件或“吊架”支撑。护罩和吊架必须周向分段以适应不同热膨胀率并且维持叶片尖端间隙控制。
每个护罩以使得在护罩与吊架间限定集气区域的方式连接至吊架。在运行中,这个集气区域接收冷却剂流,如从压缩机抽出(放出)的空气。护罩组件的众多部件之间的冷却空气的任何泄漏(leakage)都会使所要求的放出空气总量增加,从而降低发动机效率。
因此,需要一种密封改进的护罩组件。
发明内容
在一方面,提供一种具有设置在护罩吊架与周围外壳结构之间的绳索密封件的护罩组件。
附图说明
通过参考结合附图的以下描述,可最佳地理解本说明书所描述的技术,所述附图是燃气涡轮发动机中包括示例性护罩组件的涡轮段的一部分的示意性截面图。
具体实施方式
参考唯一附图,其中相同的附图标记表示贯穿各个视图的相同元件,示例性护罩组件10是高压涡轮机的一部分,所述高压涡轮机进而是已知类型燃气涡轮发动机的一部分。本说明书所描述的原理同样适用于涡轮螺旋桨发动机、涡轮喷气发动机、涡轮风扇发动机和涡轮轴发动机,以及用于其他车辆或静止应用中的涡轮发动机。
护罩组件10包括环绕涡轮机叶片23的弧形护罩段22环形阵列形式的护罩。护罩段22通过弧形护罩吊架24环形阵列来保持在合适位置。吊架24进而由表示为26A和26B的一个或多个静止外壳部件支撑。更具体来说,每个吊架24包括通过主体面板32整体互连的前部或上游导轨28和后部或下游导轨30。前部导轨28具有前部外凸缘34,所述前部外凸缘34与外壳26A的前部钩36径向重叠。类似地,后部导轨30具有后部外凸缘40,所述后部外凸缘40与外壳26B的后部钩42处于径向重叠关系。
每个护罩段22包括底座44,所述底座44分别具有径向向外延伸的前壁46和后壁48。这些壁46和48通过径向向外延伸的间隔分开的壁50接合,以限定护罩空腔52。前壁46包括前部护罩凸缘54,所述前部护罩凸缘54与从位于前部外凸缘34径向向内位置处的前部导轨28延伸的前部内凸缘56重叠。后部内凸缘58从位于后部外凸缘40径向向内位置处的吊架后部导轨30向后延伸,并且通过具有C形截面的大体弧形保持器62(通常称为C形夹)与护罩段后壁48后方的后部护罩凸缘60保持重叠关系。这个保持器62可为具有用于热膨胀的间隙的单环形式,或者可包括多个弧形保持器。
护罩组件10包括若干绳索密封件64。每个绳索密封件64固持在相邻静止部件之间形成的空腔中。第一空腔66形成在前部护罩凸缘54与前部内凸缘56之间,并且接收绳索密封件64。第二空腔68形成在吊架24的后部内凸缘58与后部护罩凸缘60之间,并且接收绳索密封件64。
与现有技术实施相比,护罩组件64还包括吊架24与静止外壳部件26A和26B之间的绳索密封件64。更具体来说,第三空腔70形成在吊架24的前部导轨28与外壳26A之间,并且接收绳索密封件64。第四空腔72形成在吊架24的后部外凸缘40与外壳26B的后部钩42之间,并且接收绳索密封件64。
如本说明书所使用,在提及每个空腔66、68、70和72时,术语“形成在…之间”是指存在尺寸和形状设定为容纳绳索密封件64的体积。空腔可为整体形成在两个配合部件之一中、或部分形成在两个配合部件中的每一个中的凹槽或沟槽形式。
绳索密封件64是根据现有技术实施构造而成。每个绳索密封件64具有大体圆形的截面形状,并且可由诸如不锈钢编织物或填充有二氧化硅的INCONEL合金编织物之类材料制成。所述材料以可切割成一定尺寸的连续长度提供,并且形成为圆圈,并且以端部相互对接的方式放置到空腔66、68、70、72中。
对空腔66、68、70、72和绳索密封件64的相对尺寸和形状进行选择,使得当每个绳索密封件安装在其相应空腔中并且配合零件已组装完成时,绳索密封件64将部分受挤压以便确保连续的金属至金属接触。此外,每个绳索密封件64跨越整个360度弧,从而减少***线式(split-line)泄漏路径。
在运行中,绳索密封件64可有效减少或消除护罩组件10的各个部件之间的泄漏。应注意,绳索密封件64的这些具***置仅用于说明目的并且可发生变化以适应特定应用。另外,特定应用可使用更小或更大数量的绳索密封件。
前文已描述一种用于燃气涡轮发动机的涡轮机护罩装置。虽然已描述本发明的特定实施例,但所属领域技术人员应清楚,在不脱离本发明的精神和范围的情况下,可以作出对本发明的各种修改。因此,对本发明的优选实施例和用于实施本发明的最佳模式的上述说明仅提供用于说明目的而不是用于限制目的。
Claims (10)
1.一种用于燃气涡轮发动机的护罩组件,所述护罩组件包括:
弧形护罩段环形阵列;
环绕所述护罩段的多个静止外壳部件;
位于所述护罩段与所述静止外壳部件之间并且支撑所述护罩段的多个弧形护罩吊架;以及
设置在所述护罩吊架与所述静止外壳部件之间的至少一个绳索密封件。
2.根据权利要求1所述的护罩组件,其中所述护罩组件包括多个绳索密封件。
3.根据权利要求1所述的护罩组件,其中所述绳索密封件由选自由以下各项组成的组的材料形成:不锈钢编织物、填充有二氧化硅的INCONEL合金编织物、及其组合。
4.根据权利要求1所述的护罩组件,其中所述绳索密封件固持在所述护罩吊架与所述静止外壳部件之间形成的空腔中。
5.根据权利要求1所述的护罩组件,其中所述绳索密封件具有大体圆形的截面形状。
6.根据权利要求1所述的护罩组件,其中所述绳索密封件在所述护罩吊架与所述静止外壳部件之间部分受挤压。
7.根据权利要求1所述的护罩组件,其中所述绳索密封件跨越整个360度弧。
8.根据权利要求1所述的护罩组件,其中所述护罩组件包括至少两个绳索密封件。
9.根据权利要求1所述的护罩组件,其中所述护罩组件包括至少三个绳索密封件。
10.根据权利要求1所述的护罩组件,其中所述绳索密封件固持在所述护罩吊架的相对凸缘与所述静止外壳部件之间形成的空腔中。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
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US201261639416P | 2012-04-27 | 2012-04-27 | |
US61/639416 | 2012-04-27 | ||
PCT/US2013/038346 WO2013163505A1 (en) | 2012-04-27 | 2013-04-26 | Shroud assembly and seal for a gas turbine engine |
Publications (2)
Publication Number | Publication Date |
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CN104508251A true CN104508251A (zh) | 2015-04-08 |
CN104508251B CN104508251B (zh) | 2016-08-24 |
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Application Number | Title | Priority Date | Filing Date |
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CN201380022344.6A Active CN104508251B (zh) | 2012-04-27 | 2013-04-26 | 用于燃气涡轮发动机的护罩组件和密封件 |
Country Status (7)
Country | Link |
---|---|
US (1) | US9745854B2 (zh) |
EP (1) | EP2850289A1 (zh) |
JP (1) | JP5997834B2 (zh) |
CN (1) | CN104508251B (zh) |
BR (1) | BR112014026803A2 (zh) |
CA (1) | CA2870713C (zh) |
WO (1) | WO2013163505A1 (zh) |
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CN109139129A (zh) * | 2017-06-27 | 2019-01-04 | 通用电气公司 | 间隙控制装置 |
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EP3080403B1 (en) * | 2013-12-12 | 2019-05-01 | General Electric Company | Cmc shroud support system |
CN106460560B (zh) | 2014-06-12 | 2018-11-13 | 通用电气公司 | 护罩吊架组件 |
JP6775425B2 (ja) | 2014-06-12 | 2020-10-28 | ゼネラル・エレクトリック・カンパニイ | シュラウドハンガーアセンブリ |
JP6574208B2 (ja) | 2014-06-12 | 2019-09-11 | ゼネラル・エレクトリック・カンパニイ | シュラウドハンガアセンブリ |
JP5717904B1 (ja) * | 2014-08-04 | 2015-05-13 | 三菱日立パワーシステムズ株式会社 | 静翼、ガスタービン、分割環、静翼の改造方法、および、分割環の改造方法 |
US10100659B2 (en) | 2014-12-16 | 2018-10-16 | Rolls-Royce North American Technologies Inc. | Hanger system for a turbine engine component |
US10378371B2 (en) * | 2014-12-18 | 2019-08-13 | United Technologies Corporation | Anti-rotation vane |
US9874104B2 (en) | 2015-02-27 | 2018-01-23 | General Electric Company | Method and system for a ceramic matrix composite shroud hanger assembly |
US10221715B2 (en) * | 2015-03-03 | 2019-03-05 | Rolls-Royce North American Technologies Inc. | Turbine shroud with axially separated pressure compartments |
US10301960B2 (en) * | 2015-07-13 | 2019-05-28 | General Electric Company | Shroud assembly for gas turbine engine |
US10822972B2 (en) | 2015-12-08 | 2020-11-03 | General Electric Company | Compliant shroud for gas turbine engine clearance control |
US10746037B2 (en) * | 2016-11-30 | 2020-08-18 | Rolls-Royce Corporation | Turbine shroud assembly with tandem seals |
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- 2013-04-26 CA CA2870713A patent/CA2870713C/en not_active Expired - Fee Related
- 2013-04-26 US US14/396,811 patent/US9745854B2/en active Active
- 2013-04-26 JP JP2015509168A patent/JP5997834B2/ja not_active Expired - Fee Related
- 2013-04-26 CN CN201380022344.6A patent/CN104508251B/zh active Active
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CN109139129A (zh) * | 2017-06-27 | 2019-01-04 | 通用电气公司 | 间隙控制装置 |
Also Published As
Publication number | Publication date |
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JP5997834B2 (ja) | 2016-09-28 |
CA2870713A1 (en) | 2013-10-31 |
WO2013163505A1 (en) | 2013-10-31 |
CN104508251B (zh) | 2016-08-24 |
EP2850289A1 (en) | 2015-03-25 |
JP2015515579A (ja) | 2015-05-28 |
US20150098829A1 (en) | 2015-04-09 |
US9745854B2 (en) | 2017-08-29 |
BR112014026803A2 (pt) | 2017-06-27 |
CA2870713C (en) | 2017-02-14 |
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