CN101122396B - 径向柔顺元件的安装方法和设备 - Google Patents

径向柔顺元件的安装方法和设备 Download PDF

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CN101122396B
CN101122396B CN2007101102799A CN200710110279A CN101122396B CN 101122396 B CN101122396 B CN 101122396B CN 2007101102799 A CN2007101102799 A CN 2007101102799A CN 200710110279 A CN200710110279 A CN 200710110279A CN 101122396 B CN101122396 B CN 101122396B
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CN101122396A (zh
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D·E·布尔曼
T·G·小达金斯
J·A·斯坦普夫
M·S·施洛德
J·J·利平斯基
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • 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
    • 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
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • 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
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
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    • 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
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    • F05D2300/21—Oxide ceramics
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
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    • F05D2300/5021—Expansivity
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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Abstract

本发明提供一种燃气涡轮发动机燃烧室(1)衬套的安装组件，该燃烧室包含燃烧室衬套(9)和径向外环形流动外套(8)。此安装组件包括：环绕衬套径向外表面的内环(208)，此内环包含许多沿轴向伸展的指状物(210)；以及通过多个隔片(228)与此内环连接的径向外环(226)，这些隔片从内环的径向外表面沿径向伸至该外环。

Description

径向柔顺元件的安装方法和设备
关于联邦资助研发项目的说明
本发明是在完成现在由能源部管理的一个项目的过程中形成的，其合同号为DE-FC26-00CH11047，DOE案号S-110587，公开号164632。
技术领域
本发明总的说涉及燃气涡轮发动机燃烧室中陶瓷基质合成材料(CMC)衬套的使用，更具体说，是关于将这类CMC衬套安装在此燃烧室的支撑元件上，以适应在径向，圆周方向，和轴向生长的差别。
背景技术
先进燃气涡轮发动机的开发使用某些陶瓷材料，它们比目前用于燃烧室衬套等高温应用的金属型材料的高温性能要好。这类非金属低热膨胀材料的一种特殊类别是CMC材料，它们可以工作在比金属高得多的温度，而且对冷却的要求较低，因而可增加引擎的效率和输出。由于其高温性能好，CMC材料大大降低了所需的冷却要求，同时通过消除被称为湍流发生器的对流冷却增强部件，减小了燃烧室的压力降。使用CMC材料作燃烧室衬套可以增加燃气涡轮发动机的净功率输出。但是，为了实现CMC衬套材料工作在高温下的长处，需要有一种新的安装CMC衬套的方法，它可以适应CMC材料的低热膨胀系数，以及相对于普通金属材料更低的失效应变。
发明内容
在一个实施例中，用于燃气涡轮发动机燃烧室衬套的安装组件，包括围绕衬套径向外表面并包含多个沿轴向伸展的指状物的内环。此安装组件还包括通过许多隔片与内环连接的径向外环，这些隔片从内环的径向外表面沿径向伸至该外环。
在另一个实施例中，组装燃气涡轮发动机组件的方法，包括为该燃气涡轮发动机组件提供燃烧室衬套，将此衬套与内环相连接，内环围绕燃烧室衬套外表面沿周向伸展，将内环与基本同心的外环相连接，外环用多个径向向外的隔片与内环径向朝外隔开，并将外环与至少局部环绕燃烧室衬套的环形流动外套相连接。
在还有一个实施例中，燃气涡轮发动机包括与轴连接的压缩机，与该轴相连接的涡轮，以及许多绕该燃气涡轮发动机轴按环形排列的燃烧室。每个燃烧室包括外壳，径向位于此外壳内的流动外套，沿径向位于此流动外套内的燃烧室衬套，其中流动外套包含CMC，和衬套的安装组件。此安装组件包括环绕衬套径向外表面的内环，此内环包含许多沿轴向伸展的指状物，以及通过许多隔片与内环连接的径向外环，这些隔片从内环的径向外表面沿径向伸至外环。
附图说明
图1是按本发明一个实施例的燃气涡轮发动机系统的燃气涡轮发动机燃烧室局部剖面；
图2是用来支撑图1所示衬套前端的连接部件一部分的放大视图；
图3是图2所示连接部件的透视图。
具体实施方式
图1是按本发明一个实施例的燃气涡轮发动机系统2的燃气涡轮发动机燃烧室1的局部剖面。燃气涡轮发动机系统2包括多个环绕燃气涡轮箱5周边的按环形排列的燃烧室1。从压缩机3来的高压空气K，通过一系列沿过渡件7和燃烧室衬套9出口端附近的流动外套8分布的空气入口孔6，流入燃烧室1。提供给燃烧室1的压缩空气K，通过由燃烧室流动外套8和燃烧室衬套9界定的环形通道流入燃烧室入口端(或其同义语，头端)10，那儿安置了许多空气-燃料喷头。例如，在某些结构中，这许多空气-燃料喷头包含一系列外燃料喷咀11和每个燃烧室1一个的中心喷咀12。并不是所有的结构都具有和这里所述相同数量的内喷咀或相同数量的外喷咀。仅仅作为例子，某些结构包含一个以上的中心喷咀12，它被与这里所述数目不同的外喷咀11所包围。
在每个燃烧室1的入口端，压缩空气和燃料被混合并流入燃烧区13。在该燃烧区13的相反一端，热燃烧气体H流入双壁过渡件7，后者把每个燃烧室衬套9的出口端与涡轮喷咀4的入口端相连接，以将热气流H供给涡轮2，在那儿热气流的焓通过流经固定和旋转涡轮翼面(图中未示出)的气体膨胀而转换为涡轮转子轴的功。
每个燃烧室1包括一个基本为柱形的燃烧箱组件，它由两部分组成，即前燃烧箱16和后燃烧箱17。燃烧箱16和17通过螺栓接头19与压缩机排气箱20相连接。前燃烧箱16用螺栓接头18与后燃烧箱17相连接。前燃烧箱16的头端由端盖组件21封闭，此组件还包含燃料和空气供给管，支管和相应的伐门，用来把气体，液体燃料和水(如需要的话)送到燃烧室1。
基本为柱形的流动外套8同心地安装在燃烧箱16和17内。流动外套8的后端与双壁过渡件7的外表面22连接。压缩机空气K流过双壁过渡件7的外通道，跨越流动外套8流入燃烧室1头端10。流动外套8的前端通过径向法兰23在螺栓接头18处与后燃烧箱17连接，在该处前燃烧箱16和后燃烧箱17相连。
在一个实施例中，流动外套8基本与燃烧室衬套9同心地安置，后者的一端与过渡件7的内壁24连接。过渡件7的外表面22，以及在后燃烧箱17与压缩机排气箱20螺栓接头处向后伸展的一部分流动外套8，在它们各自的周边表面上形成一系列小孔或入口孔6，以让空气从压缩机3通过小孔6朝燃烧室1的上游即头端10反向流入流动外套8和燃烧室衬套9之间的环形空间(如流向箭头K所示)。
燃烧衬套盖组件25支撑多个预混合管组件28，与每个燃料喷咀组件11和12同心地安装。每个预混合管组件28的前端和后端分别被前板29和后板30支撑在燃烧衬套盖组件25内，每块板有多个与端部敞开的预混合管组件28对准的开口。每个预混合管组件28包含一个由预混合管呼拉圈密封31隔开的双管组件，这种密封可以让双管组件在燃烧衬套盖组件25从冷的非工作状态变为热工作状态而热膨胀时改变长度。换句话说，随着前板29和后板30间的距离由于整个组件的热膨胀而变化，预混合管组件28也相应地沿一条对称轴线自由膨胀。
燃烧衬套盖组件25的后板30安装在多个向前伸展的浮动凸肩36(每个预混合管组件28一个，基本与后板30内的开口对齐地安置)上，每个凸肩支撑一个空气离心式喷咀37(这里也叫做”离心式翼片”)，后者可以与燃料喷咀11和12做成一体(这里也叫做”燃料注入喷咀”，”燃料喷口”，或”燃料喷咀组件”)。此装置是这样的：在燃烧室衬套9和流动外套8之间流动的空气被迫在燃烧室1入口端10(在端盖组件21和燃烧衬套盖组件25之间)处反向，并流过空气离心式喷咀37和预混合管组件28。与每个空气离心式喷咀37做成一体的燃料通道将燃料送过多小孔装置，后者根椐燃气涡轮发动机组件10的工作模式将气体燃料连续引入经过的空气内，从而造成燃料与空气的混合物，它后来在燃烧区13内被连续点燃。
图2是用来支撑衬套9前端的连接组件200一部分的放大图。在此实施例中，衬套9用CMC材料加工而成。用CMC材料作燃烧室衬套的困难是，要形成与现有高性价比系统(它满足寿命和成本的要求)中金属设备的接口。这里所述的组件由于采用了径向柔顺安装而有利于用CMC材料作燃烧室衬套。
CMC材料具有在设计和应用燃烧室衬套9这类物件时经过考验的机械性能，这类物件必须与强度和热膨胀特性高得多的金属设备相交接。较高温度本领的CMC材料由燃气涡轮燃烧室系统内的金属元件支撑并与之密封。对于金属衬套，连接件容易用铜焊，电焊，打桩或别的成熟可靠的连接方法与金属衬套相连接。这些连接件在径向，轴向和切向为柱形衬套提供支撑。这里所述的CMC加工方法展现出包含复杂的安装件的能力，它们在结构上是燃气涡轮应用可以接受的。
至少某些己知的CMC型材料的热膨胀系数(CTE)范围在1.5-3.5微英寸/英寸/°F，显著不同于用在燃烧室衬套和约束支撑或支架中的商用高温金属合金，后者的典型CTE范围约为7-10微英寸/英寸/°F。除了热膨胀系数低以外，CMC型材料还具有较低的张力延展性，这是因为它比金属材料具有较低的失效应变的缘故。
一般市场出售的CMC材料包括陶瓷型纤维，如SiC，它被BN等柔顺材料涂敷。纤维被架设在陶瓷型基质内，它的一种形式是SiC。通常CMC材料的室温张力延展性不大于1％，这表示材料的延展性较低。CMC型材料的室温张力延展性一般在0.4-0.7％。作为比较，金属衬套和/或支撑结构或支架材料的室温张力延展性至少在5％-15％之间。
连接组件200为CMC衬套9提供径向，切向，和轴向支撑，衬套可以是如图2所示的柱形或锥形。衬套9在安装时是用在衬套9前端206和后端(未示出)上的呼拉圈密封204基本与径向内表面202对中。连接组件200将压力负荷反作用于衬套9，以沿衬套9的圆柱轴线(图2中未示出)在衬套9上产生向前的净负荷。
连接组件200包含一个径向内环208，后者围绕衬套9的前端206。内环208包括多个朝前伸展的指状物210，它们绕内环208的前边缘212在圆周方向隔开。在每个指状物210的远端214，小孔216与衬套9内的辅助小孔218对齐以接纳紧固件220。邻近紧固件220，衬套9径向朝外跨至轴向点221，以便在装配时进行清洗。
指状物11的厚度222和长度224应能支撑由衬套9上的差动压力产生的轴向负荷，同时让指状物210沿径向偏离，以适应低CTE CMC衬套9和较高CTE金属内环208在热膨胀上的差别，内环是通过多个隔片228与径向外环226相连接。这些指状物210用螺栓头230与CMC衬套9刚性连接，此螺栓头与CMC衬套9的径向内表面轮廓相匹配。紧固件220的结构基本上不需要有面对CMC衬套9的位置，而此位置可能产生失效的开始点。CMC燃烧室衬套9的重量由呼拉圈密封204承受，这些圈使衬套9的中心处在柱形衬套9前端214和后端上。由于用密封204对中外环226，在流动外套8和衬套9之间保持一个径向间隙232。衬套9的轴向压力负荷肯定是由夹紧的紧固件220的结构造成的摩擦来承受，它对燃气涡轮发动机系统2在高振动环境下的磨损不敏感。衬套9的轴向负荷通过隔片228传给外环226。外环226包括前伸出部234，它从外环226的前边缘236沿轴向伸出。前伸出部234的远端连接到向外伸出的法兰238，后者在结构上连至流动外套8的法兰240和前燃烧箱16的法兰242。
在此实施例中，紧固件220的夹紧连接结构利用几种金属的组合来补偿CMC衬套的低CTE，以在高工作温度下保持夹紧，从而承受夹紧紧固件220造成的全部正常工作摩擦负荷。夹紧连接是在衬套9己冷却的低应力区实现的，温度几乎在金属元件(具体在本实施例中是螺栓和螺母构成的紧固件220)材料的极限。
在本实施例中，连接组件200使轴向压力负荷分配在以往结构十倍的位置处。例如，在本实施例中，指状物210的数目是32，而以往的结构仅包含3个分开的凸耳。径向隔片的数量正好是指状物210数目的一半。
这样的安置使每个指状物210负荷均匀，以使对称的螺栓接头结构承受较小部分的轴向摩擦负荷，从而延长燃气涡轮的使用期限。非对称结构必须考虑到某些指状物210和/或螺栓的轴向负荷要大得多。在本实施例中，指状物210和内环208是用具有高CTE的类似材料(如A286不锈钢)制成。但是，高CTE的A286使得内环208和低CTE CMC衬套9之间的径向失配较大。在另一个实施例中，内环208和指状物210被加工成双金属元件，使得内环208和指状物210包含CTE彼此不同的材料。举例来说，如用AISI 410不锈钢等低CTE的双金属内环208与高CTE A286金属指状物210使螺栓接头夹紧，将使在工作温度下内环208和衬套9之间的径向热失配比较小。此特例使CMC衬套9和内环208之间的径向失配大约减半。
图3是示于图2的连接组件200的透视图。在此实施例中，衬套9用紧固件220夹紧在指状物210上。指状物210与内环208连接或者与内环208做成一体。衬套9的轴向负荷通过指状物210传至内环208并通过隔片228传至外环226。然后轴向负荷通过隔片228传至法兰238。
连接组件200为32个紧固件提供均匀负荷，紧固件再将CMC衬套9的压力负荷传给燃烧箱法兰240。在这个实施例，连接组件200包含8个2支座隔片从外环226支撑内环208，外环同心地装在流动外套8内。
上述径向柔顺前向连接组件的性价比高且很可靠。此组件提供一种径向柔顺的前向CMC衬套安装方法，将它同心地安装在流动外套内和燃烧室圆盖外面。流动外套将冷却流体从衬套后端沿衬套外面传送。对流冷却空气向前流过光滑CMC衬套的对流背面，使衬套保持在其温度限制以内。因而，这种径向前向柔顺的连接组件能使燃气涡轮发动机的工作性价比高而且可靠。
上面对径向前向柔顺的连接组件各元件的多个实施例作了详细说明。这些元件并不限于这里所述的具体实施例，相反，每个组件的元件可以独立和分别于此处所述其它元件而使用。每个径向前向柔顺的连接组件元件还可与其它径向前向柔顺的连接组件联合使用。
虽然我们是通过各种具体实施例来说明本发明，但本专业技术人员清楚，可以在权利要求书的精神和范围内对本发明作修改。
部件列表
1燃烧室
2燃气涡轮发动机系统
3压缩机
4涡轮喷咀
5燃气涡轮箱
6空气入口孔或小孔
7过渡件
8流动外套
9燃烧室衬套
10燃烧室入口端或头端
11外燃料喷咀
12中心喷咀
13燃烧区
16前燃烧箱
17后燃烧箱
18螺栓接头
20压缩机放气箱
21端盖组件
22外壁
23径向法兰
24内壁
25燃烧衬套盖组件
28混合管组件
29前板
30后支撑板
31混合管呼拉圈密封
36浮动凸肩
37空气离心式喷咀
200连接组件
202径向内表面
204呼拉圈密封
208内环
210指状物
212前边缘
214前端
216小孔
218辅助小孔
220夹紧紧固件
221轴上点
226外环
228隔片
230螺栓头
234前伸物
236前边缘
238法兰

Claims (8)

1.一种燃气涡轮发动机燃烧室(1)衬套的安装组件，该燃烧室包含燃烧室衬套(9)和径向外环形流动外套(8)，此安装组件包括：
环绕衬套径向外表面的内环(208)，此内环包含多个沿轴向伸展的指状物(210)；以及
通过多个隔片(228)与此内环连接的径向外环(226)，这些隔片的每一个从内环的径向外表面沿径向伸至该外环，所述隔片将轴向负荷从内环(208)传至外环(226)，外环(226)包括前伸出部(234)，前伸出部从外环(226)的前边缘(236)沿轴向伸出，前伸出部(234)的远端连接到向外伸出的法兰(238)，向外伸出的法兰(238)在结构上连至径向外环形流动外套(8)的法兰(240)和前燃烧箱(16)的法兰(242)；
所述多个轴向伸展的指状物(210)利用夹紧紧固件(220)与衬套(9)刚性连接，此夹紧紧固件(220)包含一个头匹配表面(230)，它与衬套的径向内表面轮廓互补。
2.如权利要求1的组件，其中所述衬套(9)包含陶瓷基质合成材料(CMC)。
3.如权利要求1的组件，其中所述多个轴向伸展的指状物(210)围绕内环(208)的前边缘(212)在圆周方向隔开。
4.如权利要求1的组件，其中所述多个轴向伸展的指状物(210)包含第一种材料，内环(208)包含第二种材料，第一种材料不同于第二种材料。
5.如权利要求1的组件，其中所述多个轴向伸展的指状物(210)包含第一种材料，所述内环包含第二种材料，其中第一种材料的热膨胀系数大于第二种材料的热膨胀系数。
6.一种燃气涡轮发动机(2)，包括：
压缩机(3)，它与一根轴相连接；
与此轴连接的涡轮(5)；和
多个燃烧室(1)，围绕燃气涡轮发动机轴安排成环状阵列，每个燃烧室包括：
外壳(1)；
沿径向安置在该外壳内的流动外套(8)；
沿径向安置在流动外套内的燃烧室衬套(9)，该衬套包含陶瓷基质合 成材料(CMC)；和
用于此衬套的安装组件，它包括：
环绕衬套径向外表面的内环(208)，此内环包含许多沿轴向伸展的指状物(210)；和
通过多个隔片与此内环连接的径向外环(226)，这些隔片的每一个从内环的径向外表面沿径向伸至该外环，所述隔片将轴向负荷从内环(208)传至外环(226)，外环(226)包括前伸出部(234)，前伸出部从外环(226)的前边缘(236)沿轴向伸出，前伸出部(234)的远端连接到向外伸出的法兰(238)，向外伸出的法兰(238)在结构上连至径向外环形流动外套(8)的法兰(240)和前燃烧箱(16)的法兰(242)；
所述多个轴向伸展的指状物(210)利用夹紧紧固件(220)与衬套(9)刚性连接，此夹紧紧固件(220)包含一个头匹配表面(230)，它与衬套的径向内表面轮廓互补。
7.如权利要求6所述的燃气涡轮发动机(2)，其中所述多个轴向伸展的指状物(210)包含第一种材料，所述内环(208)包含第二种材料，其中第一种材料的热膨胀系数大于第二种材料的热膨胀系数。
8.如权利要求6所述的燃气涡轮发动机(2)，其中所述多个轴向伸展的指状物(210)利用夹紧紧固件与衬套(9)刚性连接，此夹紧紧固件包含多种金属，其被构型为可以补偿衬套和内环之间的热生长差，使得该紧固件产生的夹紧力得以在高的工作温度下维持。 
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JP5178053B2 (ja) 2013-04-10
JP2008038897A (ja) 2008-02-21
KR20080013705A (ko) 2008-02-13
US20080034759A1 (en) 2008-02-14
CH701279B1 (de) 2010-12-31
KR101346491B1 (ko) 2013-12-31
US8141370B2 (en) 2012-03-27

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