CN102650222B - 涡轮护罩和用于制造涡轮护罩的方法 - Google Patents
涡轮护罩和用于制造涡轮护罩的方法 Download PDFInfo
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- 238000004519 manufacturing process Methods 0.000 title abstract description 7
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- 238000007789 sealing Methods 0.000 claims abstract description 45
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Classifications
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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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
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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
- F01D11/08—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
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
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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
- 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
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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
- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
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- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/237—Brazing
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- 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
- F05D2260/20—Heat transfer, e.g. cooling
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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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49229—Prime mover or fluid pump making
- Y10T29/49297—Seal or packing making
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
本发明涉及涡轮护罩和用于制造涡轮护罩的方法。具体而言,一种涡轮护罩包括具有多个侧部的本体。第一向内面向的凹槽由本体的第一侧部限定,且第一密封件覆盖第一向内面向的凹槽以沿着本体的第一侧部在第一向内面向的凹槽中限定第一流体通道。第一入口端口穿过第一密封件并成流体连通地穿过第一密封件而进入第一流体通道中。一种用于形成涡轮护罩的方法包括形成内表面和形成与内表面相对的外表面,其中外表面构造成暴露于热气路径。该方法还包括在内表面中限定第一槽口和延伸第一密封件跨越第一槽口以沿着内表面在第一槽口中限定第一流体通道。
Description
技术领域
本发明主要涉及可定位在涡轮的热气路径中的涡轮护罩。本发明的具体实施例可包括用于制造涡轮护罩的方法。
背景技术
涡轮广泛地用于各种航空、工业以及动力生成应用中来做功。各种涡轮通常都包括交替的沿周边安装的定子导叶和旋转叶片的级。定子导叶可附接到诸如包绕涡轮的壳体的静止构件上,而旋转叶片可附接到沿着涡轮的轴向中心线定位的转子上。压缩工作流体,例如蒸汽、燃烧气体或空气,沿着经过涡轮的气体路径流动来做功。定子导叶使压缩工作流体加速并将其引导到后续级的旋转叶片上以使旋转叶片运动,由此转动转子并做功。围绕定子导叶或旋转叶片泄漏或旁路通过(或绕过)定子导叶或旋转叶片的压缩工作流体降低了涡轮的效率。因此,包绕涡轮的壳体通常包括包绕和限定气体路径外周界的护罩或护罩部段的内壳以减少旁路通过定子导叶或旋转叶片的压缩工作流体的量。
涡轮护罩持续暴露于气体路径可导致过度加热涡轮护罩的外表面和/或导致涡轮护罩的外表面故障,尤其是在利用高温压缩工作流体进行操作的涡轮如燃气涡轮和蒸汽涡轮的情况下。尽管已开发出若干系统和方法来冷却涡轮护罩,但高效且节省成本地冷却涡轮护罩外表面的能力仍很困难。例如,美国专利第5,957,657号描述了一种用于在涡轮护罩中形成冷却通道的方法,其包括在涡轮护罩的外表面中形成凹槽并利用插塞(plug)覆盖凹槽以沿着外表面形成冷却通道。尽管向外面向的冷却通道可能易于机械加工成现有的护罩,但插塞持续暴露于气体路径以及气体路径中的相关温度变化可减弱和/或损坏插塞,从而有可能引入破坏性的碎屑到气体路径中。美国专利第7,284,954描述了一种涡轮护罩,其包括机械加工成涡轮护罩的多个流体通道,并且诸如压缩空气的冷却流体可供送经过各个流体通道以冷却涡轮护罩的外表面。虽然美国专利第7,284,954号克服了插塞暴露于气体路径的已有不足,但形成流体通道所需的机械加工可能相对较为困难、耗时,并且成本高昂。此外,虽然流体通道使得冷却流体与涡轮护罩的外表面连通,但冷却流体经过流体通道的相对较高的流率并未充分利用冷却流体的热容量。因此,持续改进用于冷却涡轮护罩的系统和制造涡轮护罩的方法将是有用的。
发明内容
本发明的方面和优点在以下说明中阐述,或可根据本说明而清楚,或可通过本发明的实施而懂得。
本发明的一个实施例是一种涡轮护罩,其包括具有多个侧部的本体。第一向内面向的凹槽由本体的第一侧部限定,以及第一密封件覆盖第一向内面向的凹槽以沿着本体的第一侧部在第一向内面向的凹槽中限定第一流体通道。第一入口端口穿过第一密封件并提供穿过第一密封件进入第一流体通道中的流体连通。
本发明的另一实施例是一种涡轮护罩,其包括内表面和与内表面相对的外表面。该外表面构造成用以暴露于热气路径。第一槽口由内表面限定,以及第一密封件延伸跨越第一槽口以沿着内表面在第一槽口中限定第一流体通道。
本发明的具体实施例还可包括用于形成涡轮护罩的方法。该方法包括形成内表面和形成与内表面相对的外表面,其中,外表面构造成用以暴露于热气路径。该方法还包括在内表面中限定第一槽口和使得第一密封件延伸跨越第一槽口以沿着内表面在第一槽口中限定第一流体通道。
研读说明书,本领域的普通技术人员将会更好地了解这些实施例的特征和方面等。
附图说明
在包括参照附图的余下说明书中向本领域的普通技术人员更为具体地阐述了本发明的包括其最佳模式的完整和能够实施的公开内容,在附图中:
图1是根据本发明一个实施例的涡轮的简化截面图;
图2是根据本发明一个实施例的图1中所示的护罩的放大侧截面视图;
图3是沿着线A-A截取的图2中所示的护罩的轴向截面图;以及
图4是图2中所示的护罩的顶平面视图。
零件清单
10涡轮
12壳体
14定子导叶
16旋转叶片
18转子
20压缩工作流体
22护罩
24本体
26前侧部
28后侧部
30横向侧部
32凹口或凹部(indent)
34内表面
36外表面
38热障涂层
40第一向内面向的凹槽或槽口
42第二向内面向的凹槽或槽口
44凹槽或槽口中的开口
46第一密封件
48第二密封件
50流体通道
52入口端口
54出口端口
具体实施方式
现在将详细描述本发明的现有实施例,其中的一个或多个实例已在附图中示出。详细描述使用了数字和字母标记来指代附图中的特征。附图和描述中相同或相似的标记用于指代本发明的相同或相似的部分。
各实例均是通过阐释本发明的方式来提供的,而非对本发明进行限制。实际上,本领域普通技术人员将清楚,在不脱离本发明的范围或精神的情况下可在本发明中进行修改和变型。例如,作为一个实施例的一部分所示或描述的特征可用于另一实施例上以产生又一实施例。因此,本发明意图涵盖归入所附权利要求及其等同方案的范围内的这些修改和变型。
图1提供了根据本发明一个实施例的涡轮10的一部分的简化截面图。如图1中所示,涡轮10可包括由壳体12包绕的静止构件和旋转构件。静止构件可包括例如附接到壳体12上的静止喷嘴或定子导叶14。旋转构件可包括例如附接到转子18上的旋转叶片16。诸如蒸汽、燃烧气体或空气的压缩工作流体20沿着经过涡轮10的热气路径如图1中所示从左至右流动。第一级的定子导叶14使压缩工作流体20加速并将其引导到第一级的旋转叶片16上,从而导致第一级的旋转叶片16以及转子18旋转。压缩工作流体20然后流动越过第二级定子导叶14,这使得压缩工作流体20加速并将其再次引导至下一级旋转叶片(未示出),并且该过程对于各个后续级重复。
如图1中所示,壳体12的沿径向向内部分包括连接到壳体12上的一系列分段护罩22,这些护罩22周向地包绕和限定热气路径以减少旁路通过定子导叶14或旋转叶片16的压缩工作流体20的量。如文中所用,用语“护罩”可包含和包括事实上在热气路径中的经受与压缩工作流体20相关联的温度和压力的任何静态或静止硬件(hardware)。例如,在图1中所示的具体实施例中,护罩22沿径向定位在旋转叶片16的外部,而在其它具体实施例中护罩22还可沿径向定位在旋转叶片16的内部或沿径向定位在定子导叶14的内部或外部。
图2提供了根据本发明一个实施例的图1中所示的护罩22的放大侧截面视图。图3提供了沿着线A-A截取的图2中所示的护罩22的轴向截面图,以及图4提供了图2中所示的护罩22的顶平面视图。如图2至图4中所示,护罩22通常包括具有多个侧部的本体24。具体而言,前侧部26和后侧部28以及横向侧部30可构造成用以连接到邻近的护罩(未示出)上或与邻近的护罩相配合。例如,如图2和图3中更为清楚地所示,前侧部26、后侧部28和/或横向侧部30可包括用以容纳销或部段(未示出)的凹口或凹部32。该销或部段可装配在邻近护罩之间的凹口或凹部32中或壳体12中以将护罩22挠性地保持就位,同时仍最大限度地减小或防止压缩工作流体20从邻近护罩之间的热气路径逸出。此外,本体24可包括内表面34和与内表面34相对的外表面36。如文中所用,内表面34指的是本体24的远离热气路径面向的表面,而外表面36指的是本体24的朝向热气路径面向并构造成用以暴露于热气路径的表面。例如,如图2和图3中更为清楚地所示,本体24的外表面36可包括热障涂层38或其它耐热表面以保护外表面36免受热气路径中存在的过高温度。
护罩22还包括一个或多个向内面向的凹槽或槽口,这些凹槽或槽口形成在侧部26、28、30和/或内表面34中或由侧部26、28、30和/或内表面34限定。如文中所用,用语“凹槽”和“槽口”意指是可互换的且包含或包括由侧部26、28、30和/或内表面34限定的任何槽道、缺口、凹口或凹部。具体而言,向内面向的凹槽(多个)或槽口(多个)可横向地延伸跨越前侧部26和/或后侧部28的宽度和/或轴向地沿着横向侧部30中的一个或两者的长度延伸。例如,如图2和图3中所示,第一向内面向的凹槽或槽口40和第二向内面向的凹槽或槽口42可由横向侧部30和/或内表面34限定,使得向内面向的凹槽或槽口40,42轴向地沿着本体24的长度延伸。向内面向的凹槽或槽口40,42可通过常规的机械加工,例如通过磨削凹槽或槽口40,42到侧部26、28、30和/或内表面34中,而形成在侧部26、28、30和/或内表面34中。作为备选,本体24可围绕合适的模具锻造或铸造,从而在侧部26、28、30和/或内表面34中的期望位置处限定向内面向的凹槽或槽口40,42。
如在图3和图4中更为清楚地所示,护罩22还包括密封件,该密封件紧接通过各个向内面向的凹槽或槽口40,42所生成的开口44,例如通过焊接或硬钎焊而连接到侧部26、28、30和/或内表面34上。例如,第一密封件46可覆盖第一向内面向的凹槽或槽口40中的开口44,而第二密封件48可覆盖第二凹槽或槽口42中的开口44。以此方式,各个密封件46,48均覆盖、横跨,或延伸跨越由向内面向的凹槽或槽口40,42所生成的开口44以在各自的凹槽或槽口40,42中限定流体通道50。各个密封件46,48均可包括穿过密封件46,48的一个或多个入口端口52,这些端口提供穿过密封件46,48并进入紧接的或相关流体通道50中的流体连通。此外,护罩22或本体24还可包括穿过本体24的侧部26、28、30和/或外表面36的一个或多个出口端口54。出口端口54可沿着紧接各个流体通道50或与各个流体通道50相关联的侧部26、28、30定位以提供从流体通道50穿过紧接的或相关侧部26、28、30和/或外表面36的流体连通。以此方式,入口端口52和出口端口54的结合可提供穿过各个密封件46,48而进入紧接的或相关流体通道50并离开紧接的或相关侧部26、28、30或外表面36的连续流体通路。
如在图4中更为清楚地所示,流体可提供至各个护罩22以对护罩22除热或冷却护罩22。该流体可包括例如压缩空气、惰性气体,或蒸汽,并且本发明不限于用于冷却护罩22的任何特定流体。流体可首先冲击本体24的中央部分以提供对本体24的大部分(bulk)的冲击冷却。然后,流体可流动经过一个或多个入口端口52以穿过密封件46,48传送并进入流体通道50中而对本体24的侧部26、28、30除热。例如,如在图4的底部所示,沿着第二密封件48布置的入口端口52可引导流体穿过第二密封件48并抵靠本体24的侧部30而提供对本体24侧部30的附加冲击冷却。然后,流体在经过出口端口54离开流体通道50之前可流动经过流体通道50以通过对流冷却而从本体24的侧部30和底表面36除去附加热量。作为备选,或此外,如在图4的顶部所示,定位在第一密封件46的一端处的入口端口52可引导流体穿过第一密封件46而进入流体通道50中,且然后该流体可流动经过流体通道50以在经过出口端口54离开流体通道50之前通过对流冷却而从本体24的侧部30除热。
认识到的是,图2至图4中所示护罩22的各种实施例可相比于此前的铸造设计以更低的成本制造。具体而言,护罩22的本体24可经铸造或锻造而形成前侧部26、后侧部28、横向侧部30、内表面34,以及外表面36,如前文所述。同时或单独的是,向内面向的凹槽或槽口40,42可通过机械加工、铸造或锻造而限定在侧部26、28、30和/或内表面34中,且密封件46,48可焊接或硬钎焊到侧部26、28、30和/或内表面34上,使得密封件46,48延伸跨越各个凹槽或槽口40,42以在其中限定紧接或相关的流体通道50。入口端口52和或出口端口54可例如通过钻取(或钻孔)而易于机械加工到各自的密封件46,48和/或侧部26、28、30和/或外表面36中。以此方式,护罩22可容易地制造成包括对侧部26、28、30和外表面36提供冷却的期望流体通道50,并且形成流体通道50的密封件46,48将不会暴露于热气路径。
本书面描述使用了包括最佳模式的实例来公开本发明,并且还使得本领域普通技术人员能够实施本发明,包括制作和使用任何装置或系统以及执行任何所结合的方法。本发明可取得专利的范围由权利要求限定,并且可包括本领域普通技术人员所想到的其它实例。如果这些其它实例具有与权利要求的文字语言并无不同的结构元件或者如果这些其它实例包括与权利要求的文字语言无实质差异的同等结构元件,则认为这些其它实例处在权利要求的范围内。
Claims (13)
1.一种涡轮护罩,包括:
a.具有多个侧部的本体;
b.由所述本体的第一侧部限定的第一向内面向的凹槽;
c.第一密封件,所述第一密封件覆盖所述第一向内面向的凹槽以沿着所述本体的所述第一侧部在所述第一向内面向的凹槽中限定第一流体通道;以及
d.穿过所述第一密封件的第一入口端口,其中所述第一入口端口提供穿过所述第一密封件进入所述第一流体通道中的流体连通。
2.根据权利要求1所述的涡轮护罩,其特征在于,所述涡轮护罩还包括穿过所述本体的所述第一侧部的至少一个出口端口,其中所述至少一个出口端口提供从所述第一流体通道穿过所述本体的所述第一侧部的流体连通。
3.根据权利要求1或权利要求2所述的涡轮护罩,其特征在于,所述涡轮护罩还包括穿过所述第一密封件进入所述第一流体通道中并离开所述本体的所述第一侧部的连续流体通路。
4.根据权利要求1或权利要求2所述的涡轮护罩,其特征在于,所述第一密封件跨越所述第一向内面向的凹槽进行焊接。
5.根据权利要求1或权利要求2所述的涡轮护罩,其特征在于,所述第一向内面向的凹槽沿着所述本体的长度轴向地延伸。
6.根据权利要求1或权利要求2所述的涡轮护罩,其特征在于,所述涡轮护罩还包括由所述本体的第二侧部限定的第二向内面向的凹槽,以及第二密封件,所述第二密封件覆盖所述第二向内面向的凹槽以沿着所述本体的所述第二侧部在所述第二向内面向的凹槽中限定第二流体通道。
7.根据权利要求6所述的涡轮护罩,其特征在于,所述涡轮护罩还包括穿过所述第二密封件的第二入口端口,其中所述第二入口端口提供穿过所述第二密封件进入所述第二流体通道中的流体连通。
8.一种用于形成涡轮护罩的方法,包括:
a.形成内表面;
b.形成与所述内表面相对的外表面,其中所述外表面构造成用以暴露于热气路径;
c.在所述内表面中限定第一槽口;以及
d.延伸第一密封件跨越所述第一槽口以沿着所述内表面在所述第一槽口中限定第一流体通道。
9.根据权利要求8所述的方法,其特征在于,所述方法还包括穿过所述第一密封件形成第一入口端口,其中所述第一入口端口提供穿过所述第一密封件进入所述第一流体通道中的流体连通。
10.根据权利要求8至权利要求9中任一项所述的方法,其特征在于,所述方法还包括穿过所述外表面形成至少一个输出端口。
11.根据权利要求8至权利要求9中任一项所述的方法,其特征在于,所述方法还包括将所述第一密封件焊接到所述内表面上。
12.根据权利要求8至权利要求9中任一项所述的方法,其特征在于,所述方法还包括在所述内表面中限定第二槽口和延伸第二密封件跨越所述第二槽口以沿着所述内表面在所述第二槽口中限定第二流体通道。
13.根据权利要求12所述的方法,其特征在于,所述方法还包括穿过所述第二密封件形成第二入口端口,其中,所述第二入口端口提供穿过所述第二密封件进入所述第二流体通道中的流体连通。
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EP2492446A3 (en) | 2017-08-16 |
US20120219404A1 (en) | 2012-08-30 |
US8845272B2 (en) | 2014-09-30 |
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EP2492446B1 (en) | 2020-07-29 |
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