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1. 发明公开

EP2781691A1 Method for reconditioning a hot gas path part of a gas turbine 审中-公开
标题翻译：维尔法赫恩·乌克兰
公开(公告)号：EP2781691A1
公开(公告)日：2014-09-24
申请号：EP13160050.4
申请日：2013-03-19
申请人： Alstom Technology Ltd
发明人： Stankowski, Alexander , Zimmermann, Julien Rene Andre , Hoevel, Simone , Grasso, Piero-Daniele , Olliges, Sven , Duval, Sophie Betty Claire
IPC分类号： F01D5/00 , B23P6/00
CPC分类号： F01D5/005 , B23K26/0006 , B23K26/342 , B23K2203/02 , B23K2203/18 , B23K2203/26 , B23P6/005 , B33Y10/00 , C23C4/073 , F01D5/288 , F05D2230/10 , F05D2230/30 , F05D2230/312 , F05D2230/313 , F05D2230/80
摘要： A method for reconditioning a hot gas path part (10) of a gas turbine in order to flexibly adapt an operation regime of said gas turbine for subsequent operation intervals is disclosed.
It comprises the steps of:
a) providing a hot gas path part (10) to be reconditioned;
b) remove a predetermined area of said hot gas path part (10), resulting in a cutout (19) at said hot gas path part (10);
c) manufacture a coupon (20) for being inserted into said cutout (19) to replace said removed area of said hot gas path part (10);
d) inserting said coupon (20) into said cutout (19); and
e) joining said hot gas path part (10) with said inserted coupon (20);
f) whereby said coupon (20) is manufactured by a selective laser melting (SLM) method resulting in a fine grain sized material with significantly improved low cycle fatigue (LCF) lifetime; and
g) whereby said hot gas path part (10) is coated, at least in an area comprising said inserted coupon (20), with a metallic overlay (21) with improved thermo-mechanical fatigue (TMF) and oxidation lifetime.
摘要翻译：公开了一种用于修复燃气轮机的热气体路径部分（10）的方法，以便灵活地适应所述燃气轮机的运行状态用于随后的操作间隔。它包括以下步骤：a）提供待修复的热气路径部分（10）; b）去除所述热气路径部分（10）的预定区域，从而在所述热气路径部分（10）处形成切口（19）。 c）制造用于插入所述切口（19）中以更换所述热气路径部分（10）的去除区域的优惠券（20）; d）将所述优惠券（20）插入所述切口（19）中; 以及e）将所述热气体路径部分（10）与所述插入的试样（20）连接; f），由此通过选择性激光熔化（SLM）方法制造所述试样（20），得到具有显着改善的低循环疲劳（LCF）寿命的细晶粒尺寸的材料; 和g），其中所述热气体路径部分（10）至少在包括所述插入的试样（20）的区域中涂覆有具有改善的热机械疲劳（TMF）和氧化寿命的金属覆盖物（21）。

2. 发明授权

EP2508648B1 Component for a turbomachine and method for manufacturing such a component 有权
标题翻译：组件，其用于涡轮机和方法，用于制造该部件
公开(公告)号：EP2508648B1
公开(公告)日：2015-01-14
申请号：EP12163023.0
申请日：2012-04-03
申请人： ALSTOM Technology Ltd
发明人： Duval, Sophie Betty Claire , Beckel, Daniel , Grasso, Piero-Daniele , Stankowski, Alexander , Szwedowicz, Jaroslaw Leszek
IPC分类号： C23C30/00 , B22F1/00 , B22F1/02 , C22C1/10 , C22C47/04 , C22C47/06 , C22C47/16
CPC分类号： C23C30/00 , B22F1/02 , B22F3/1055 , B22F5/009 , B22F2207/01 , B33Y80/00 , C22C47/04 , C22C47/06 , C22C47/16 , Y02P10/295 , Y10T428/2438 , Y10T428/249921 , Y10T442/20

3. 发明公开

EP2746428A1 Coating of turbine parts 有权转让
标题翻译： Beschichtung von Turbinenteilen
公开(公告)号：EP2746428A1
公开(公告)日：2014-06-25
申请号：EP13196979.2
申请日：2013-12-12
申请人： Alstom Technology Ltd
发明人： Widmer, Thomas , Olliges, Sven , Stankowski, Alexander , Grasso, Piero-Daniele , Melas, Mauro , Baumann, Thomas
IPC分类号： C23C30/00 , C23C28/02 , C23C18/16 , C23C18/36 , F01D5/28 , F04D29/02
CPC分类号： C23C18/54 , C09D183/04 , C23C18/1662 , C23C18/1692 , C23C18/36 , C23C28/027 , C23C30/00 , C25D3/12 , C25D5/50 , C25D15/00 , F01D5/288 , F05D2230/31 , F05D2230/80 , Y02T50/672 , Y10T428/31663
摘要： A method and a turbine part (20) comprising a coating (10) with a matrix layer comprising high temperature resistant hydrophobic polysiloxane filler (14), wherein the coating (10) has superior mechanical strength and temperature resistance.
摘要翻译：一种包括具有包含耐高温疏水性聚硅氧烷填料（14）的基质层的涂层（10）的方法和涡轮部分（20），其中所述涂层（10）具有优异的机械强度和耐温性。

4. 发明公开

EP2781616A1 Method for coating a component of a turbomachine and coated component for a turbomachine 审中-公开
标题翻译：一种用于涂覆涡轮机和涂布部件的部件用于涡轮机的过程
公开(公告)号：EP2781616A1
公开(公告)日：2014-09-24
申请号：EP13160051.2
申请日：2013-03-19
申请人： ALSTOM Technology Ltd
发明人： Zimmermann, Julien Rene Andre , Stankowski, Alexander , Grasso, Piero-Daniele , Olliges, Sven , Duval, Sophie Betty Claire
IPC分类号： C23C4/00 , C23C4/12
CPC分类号： C23C4/04 , B05B7/14 , B05B7/20 , C23C4/02 , C23C4/12 , C23C4/123 , C23C4/134 , C23C24/08 , C23C24/10
摘要： The invention relates to a coating system (30, 31, 32) for a component of a turbomachine, comprising at least two different base powders (30, 31, 32), whereby each of said at least two different base powders (30, 31, 32) has an individual predetermined distribution within said coating system (30, 31, 32), and wherein each of said at least two different base powders (30, 31, 32) is responsible for a specific property of said coating system.
摘要翻译：本发明涉及涂布系统（30，31，32），用于涡轮机的组件，包括至少两个不同的基础粉末（30，31，32），由此每个所述的至少两个不同的基础粉末（30，31 ，32）具有在所述涂覆系统（30，31，32内的各个预定的分布），并且每个worin的所述至少两个不同的基础粉末（30，31，32）是负责所述涂层系统的具体性质。

5. 发明公开

EP2636763A1 Method for applying a high-temperature stable coating layer on the surface of a component and component with such a coating layer 有权转让
标题翻译：一种用于耐高温涂料层的组分和组分的表面上的应用具有这样的涂料层的过程
公开(公告)号：EP2636763A1
公开(公告)日：2013-09-11
申请号：EP12158129.2
申请日：2012-03-05
申请人： Alstom Technology Ltd
发明人： Duval, Sophie , Grasso, Piero-Daniele , Olliges, Sven , Stankowski, Alexander
IPC分类号： C23C4/02 , C23C4/08 , C23C4/10 , C23C4/12
摘要： The invention proposes a method for applying a high-temperature stable coating layer (12) on the surface of a component (11), comprising the steps of:
a) providing a component (11) with a surface to be coated;
b) providing a powder material containing at least a fraction of submicron powder particles (18);
c) applying said powder material to the surface of the component (11) by means of a spraying technique to build up a coating layer (12), whereby
d) said sub-micron powder particles (18) are each at least partially surrounded by an oxide shell (20) and establish with their oxide shells (20) an at least partially interconnected sub-micron oxide network (22) within said coating layer (12).
摘要翻译：本发明提出了一个部件（11）的表面上施加高温稳定的涂料层（12）的方法，包括以下步骤：a）提供具有表面的部件（11）要被涂覆; b）提供至少含亚微米的粉末颗粒（18）的一小部分的粉末材料; C）通过喷涂技术来建立一个涂层（12），由此d）所述亚微米的粉末颗粒（18来施加所述粉末材料的成分（11）的表面）各自至少部分地由包围到氧化物壳（20），并建立与他们的氧化物壳（20），所述涂层内的至少部分互连的亚微米氧化物网络（22）（12）。

6. 发明公开

EP2508648A1 Component for a turbomachine and method for manufacturing such a component 有权
标题翻译： KomponentefürTurbomaschine und Verfahren zur Herstellung der Komponente
公开(公告)号：EP2508648A1
公开(公告)日：2012-10-10
申请号：EP12163023.0
申请日：2012-04-03
申请人： Alstom Technology Ltd
发明人： Duval, Sophie Betty Claire , Beckel, Daniel , Grasso, Piero-Daniele , Stankowski, Alexander , Szwedowicz, Jaroslaw Leszek
IPC分类号： C23C30/00 , B22F1/00 , B22F1/02 , C22C1/10 , C22C47/04 , C22C47/06 , C22C47/16
CPC分类号： C23C30/00 , B22F1/02 , B22F3/1055 , B22F5/009 , B22F2207/01 , B33Y80/00 , C22C47/04 , C22C47/06 , C22C47/16 , Y02P10/295 , Y10T428/2438 , Y10T428/249921 , Y10T442/20
摘要： The invention relates to a component for a turbomachine, in particular a gas turbine, or another engine containing a hot component, which component (14) is prone to crack formation and propagation by being subjected to high temperatures and/or a corrosive and/or oxidising atmosphere and/or a high mechanical load and/or cyclic thermal load and/or transient conditions, whereby said component (14) contains at least one base material (15). A substantial extension of the component lifetime is achieved by providing said at least one base material (15) with a self healing system in form of an added active phase (16), whereby said active phase (16) comprises a melting point depressant and/or a substance or substances with a softening or melting point below or within the range of the operating temperature of the component (14).
摘要翻译：本发明涉及一种用于涡轮机械，特别是燃气涡轮机的组件或含有热部件的另一发动机，该组件（14）容易经受高温和/或腐蚀性和/或氧化气氛和/或高机械载荷和/或循环热负荷和/或瞬态条件，由此所述组分（14）含有至少一种基础材料（15）。通过向添加的活性相（16）的形式提供所述至少一种基础材料（15）和自愈系统来实现元件寿命的显着延伸，由此所述活性相（16）包含熔点降低剂和/ 或软化点或熔点低于或在组件（14）的工作温度范围内的物质或物质。

7. 发明公开

EP2236648A1 Comprehensive method for local application and local repair of thermal barrier coatings 有权转让
标题翻译： Verfahren zum lokalen Aufbringen und zur lokalen Reparatur vonWärmedämmschichten
公开(公告)号：EP2236648A1
公开(公告)日：2010-10-06
申请号：EP10156168.6
申请日：2010-03-11
申请人： Alstom Technology Ltd
发明人： Reitz, Daniel , Duval, Sophie , Grasso, Piero-Daniele , Stankowski, Alexander , Santos Silverio, Fernando Manuel
IPC分类号： C23C24/00 , C23C28/00 , C23C28/04 , B23P6/04 , F01D5/00 , F01D5/28
CPC分类号： F01D5/005 , C23C24/08 , C23C28/042 , C23C28/322 , C23C28/3455 , F05D2230/30 , F05D2260/80
摘要： Disclosed is a method for the local initial application of a thermal barrier coating layer (3), or for the local repair of coating defects and/or deteriorations of components (1) in the hot gas path of a gas turbine engine which components are coated with a thermal barrier coating layer on a base metal (1) of the component. The proposed method includes at least the following steps:
(I) in case of repair normally overall inspection of the whole component (1) for the determination of location of defect/deterioration as well as of corresponding type of defect/deterioration of each place for a multitude of locations of the component (1);
(II) if needed preparation of the surface in at least one location;
(III) local application of a ceramic tissue together with a wet chemical thermal barrier coating layer deposition material for the formation of a patch (5) of ceramic matrix composite;
(IV) intermediate inspection of the patch and/or the surface
(IV)b in case of repetitive and/or multi-step repair method subsequent layer application of a ceramic tissue together with a wet chemical thermal barrier coating layer deposition material for the formation of a patch (5) of ceramic matrix composite at this location;
(V) if needed surface finishing at the at least one location;
(VI) final inspection of the at least one location

provided that steps (IV)a, (V) and (VI) can be omitted with the provision that at least one of steps (IV)a or (VI) is carried out.
摘要翻译：公开了一种用于局部初始施加热障涂层（3）的方法，或用于在涂覆有部件的燃气涡轮发动机的热气路径中局部修复涂层缺陷和/或部件（1）的劣化的方法在组件的基底金属（1）上具有热障涂层。所提出的方法至少包括以下步骤：（I）在维修的情况下，通常整体检查整个部件（1）以确定缺陷/劣化的位置以及每个位置的相应类型的缺陷/劣化组件（1）的多个位置; （II）如果需要在至少一个位置准备表面; （III）将陶瓷组织与湿化学热障涂层沉积材料一起局部施加，以形成陶瓷基复合材料的贴片（5）; （IV）在重复和/或多步骤修复方法的情况下对贴片和/或表面（IV）b进行中间检查，随后层与陶瓷组织一起施加用于形成的湿化学热障涂层沉积材料在该位置的陶瓷基体复合材料的贴片（5）; （V），如果需要，在所述至少一个位置处进行表面处理; （VI）对至少一个位置的最终检查，条件是可以省略步骤（IV）a，（V）和（VI），其中规定了执行步骤（IV）a或（VI）中的至少一个。

8. 发明公开

EP2233600A1 Method for the protection of a thermal barrier coating system and a method for the renewal of such a protection 有权转让
标题翻译： Verfahren zum Schutz eines TBC-系统与Verfahren zur Erneuerung des Schutzes
公开(公告)号：EP2233600A1
公开(公告)日：2010-09-29
申请号：EP09156358.5
申请日：2009-03-26
申请人： Alstom Technology Ltd
发明人： Duval, Sophie , Grasso, Piero-Daniele , Stankowski, Alexander
IPC分类号： C23C4/18 , C23C14/58 , C23C26/00 , C23C28/00
CPC分类号： C23C4/18 , C23C26/00 , C23C28/00 , C23C28/30 , F05B2230/90 , Y10T428/31678
摘要： Disclosed is a method for the application and/or renewal of a protection for a thermal barrier coating system of a heat engine, said thermal barrier coating system comprising a bond coat layer (2) and a thermal barrier coating layer (3) of porous structure (4), wherein the bond coat layer (2) is located between and in contact with a base metal (1) of a heat engine component and with the thermal barrier coating layer (3) and bonds the thermal barrier coating layer (3) to the base metal (1). The method is characterised in that at least one substance is applied inside the engine as a liquid or carried by a liquid by means of spraying and/or by flowing it across a hot gas exposed surface (9) of the barrier coating layer (3) of the heat engine component mounted within the heat engine in the assembled state prior to the initial start-up of the engine, so before the first operation interval, or during a washing cycle of the thermal engine and/or at the end of an operation interval, before a subsequent operation interval, wherein the substance covers and/or at least partly penetrates into the porous structure (4), and concomitantly or subsequently hardens to remain within the pores (4) and/or on the upper surface (9) of the thermal barrier coating layer. Preferably (but not necessarily) for the application the turbine washing equipment of the engine is used. The invention furthermore relates to heat engine components protected using such a method for the application of substances, and to uses of corresponding substances in such a method.
摘要翻译：公开了一种用于应用和/或更新热发动机的热障涂层系统的保护的方法，所述热障涂层系统包括粘结涂层（2）和多孔结构的热障涂层（3）（4），其中所述粘合涂层（2）位于热发动机部件的基体金属（1）之间并与所述热障涂层（3）接触并且与所述热障涂层（3）接合，到贱金属（1）。该方法的特征在于，将至少一种物质作为液体施加到发动机内部或通过喷雾和/或通过使其流过阻隔涂层（3）的热气体暴露表面（9）而被液体携带，在发动机初始启动之前，在第一操作间隔之前，或在热机的洗涤循环期间和/或在操作结束时，在组装状态下安装在热机内部的热机组件间隔，在所述后续操作间隔之前，其中所述物质覆盖和/或至少部分地渗透到所述多孔结构（4）中，并且伴随地或随后硬化以保留在所述孔（4）和/或所述上表面（9）内，的隔热涂层。优选（但不一定）应用的是使用发动机的涡轮洗涤设备。本发明还涉及使用这种用于物质应用的方法保护的热机组件以及在这种方法中使用相应物质。

9. 发明公开

EP2781617A1 Method for coating a component of a turbomachine and coated component for a turbomachine 有权转让
标题翻译：一种用于涂覆涡轮机和涂布部件的部件用于涡轮机的过程
公开(公告)号：EP2781617A1
公开(公告)日：2014-09-24
申请号：EP14158366.6
申请日：2014-03-07
申请人： Alstom Technology Ltd
发明人： Zimmermann, Julien Rene Andre , Stankowski, Alexander , Grasso, Piero-Daniele , Olliges, Sven , Duval, Sophie Betty Claire
IPC分类号： C23C4/00 , C23C4/12
CPC分类号： C23C4/04 , B05B7/14 , B05B7/20 , C23C4/02 , C23C4/12 , C23C4/123 , C23C4/134 , C23C24/08 , C23C24/10
摘要： The invention relates to a coating system (30, 31, 32) for a component of a turbomachine, comprising at least two different base powders (30, 31, 32), whereby each of said at least two different base powders (30, 31, 32) has an individual predetermined distribution within said coating system (30, 31, 32), and wherein each of said at least two different base powders (30, 31, 32) is responsible for a specific property of said coating system.

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