公开(公告)号：US20140060058A1

公开(公告)日：2014-03-06

申请号：US14075213

申请日：2013-11-08

申请人： Jens Birkner ,  Walter David ,  Rudolf Gensler ,  Arne Graßmann ,  Knut Halberstadt ,  Beate Heimberg ,  Bora Kocdemir ,  Rainer Nies ,  Jörg Schürhoff ,  Werner Stamm

发明人： Jens Birkner ,  Walter David ,  Rudolf Gensler ,  Arne Graßmann ,  Knut Halberstadt ,  Beate Heimberg ,  Bora Kocdemir ,  Rainer Nies ,  Jörg Schürhoff ,  Werner Stamm

IPC分类号： F02C7/143

CPC分类号： F02C7/143 ,  C09D1/00 ,  C23C18/1254 ,  C25D11/02 ,  F01D25/305 ,  F02C7/1435 ,  F28C3/08 ,  F28F13/18 ,  F28F2245/02

摘要： A gas turbine system includes a compressor; a combustion chamber; a gas turbine; and an evaporative cooler. The evaporative cooler includes a plurality of cooling elements, a flow channel, and a feed device. The plurality of cooling elements are arranged in the flow channel. The feed device supplies a liquid to the plurality of cooling elements. The liquid is evaporated or vaporized. Each of the plurality of cooling elements is a flat cooling sheet, a surface of the cooling sheet having hydrophilic properties at least in a subregion which is specified for forming a liquid film. The evaporative cooler is connected ahead of the compressor on an intake side.

摘要翻译： 燃气轮机系统包括压缩机; 燃烧室; 燃气轮机; 和蒸发冷却器。 蒸发冷却器包括多个冷却元件，流动通道和进给装置。 多个冷却元件布置在流动通道中。 进料装置向多个冷却元件供应液体。 液体被蒸发或汽化。 多个冷却元件中的每一个都是平坦的冷却片，冷却片的至少在形成液膜所规定的次级区域具有亲水性。 蒸发冷却器在进气侧连接在压缩机前方。

公开(公告)号：US20100101234A1

公开(公告)日：2010-04-29

申请号：US12525334

申请日：2008-01-30

申请人： Jens Birkner ,  Walter David ,  Rudolf Gensler ,  Arne Grassmann ,  Knut Halberstadt ,  Beate Heimberg ,  Bora Kocdemir ,  Rainer Nies ,  Jörg Schürhoff ,  Werner Stamm

发明人： Jens Birkner ,  Walter David ,  Rudolf Gensler ,  Arne Grassmann ,  Knut Halberstadt ,  Beate Heimberg ,  Bora Kocdemir ,  Rainer Nies ,  Jörg Schürhoff ,  Werner Stamm

IPC分类号： F02C7/14 ,  F25B39/02

CPC分类号： F02C7/143 ,  C09D1/00 ,  C23C18/1254 ,  C25D11/02 ,  F01D25/305 ,  F02C7/1435 ,  F28C3/08 ,  F28F13/18 ,  F28F2245/02

摘要： An evaporative cooler for cooling a gas stream, in particular an air stream, including a number of cooling elements located in a flow channel, is provided. A liquid, preferably water, is supplied by a feed device and will be vaporized or evaporated. In one aspect, the surface of at least one of the cooling elements has hydrophilic properties, at least in one sub-region designed to form a liquid film.

摘要翻译： 提供了用于冷却气流的蒸发冷却器，特别是包括位于流动通道中的多个冷却元件的气流。 液体，优选水，由进料装置供应，并被蒸发或蒸发。 在一个方面，至少一个冷却元件的表面具有亲水性，至少在设计成形成液膜的一个子区域中。

公开(公告)号：US06440575B1

公开(公告)日：2002-08-27

申请号：US09562877

申请日：2000-05-01

申请人： Beate Heimberg ,  Wolfram Beele ,  Karl Kempter ,  Ulrich Bast ,  Thomas Haubold ,  Michael Hoffmann ,  Axel Endriss ,  Peter Greil ,  Chu-Wan Hong ,  Fritz Aldinger ,  Hans J. Seifert

发明人： Beate Heimberg ,  Wolfram Beele ,  Karl Kempter ,  Ulrich Bast ,  Thomas Haubold ,  Michael Hoffmann ,  Axel Endriss ,  Peter Greil ,  Chu-Wan Hong ,  Fritz Aldinger ,  Hans J. Seifert

IPC分类号： B32B1504

CPC分类号： C23C28/042 ,  C23C4/11 ,  C23C28/00

摘要： An article that is particularly well suited for use as a gas turbine engine component has a metallic substrate and a ceramic thermal barrier layer including a mixed metal oxide system comprising a compound selected from the group consisting of (i) a lanthanum aluminate and (ii) a calcium zirconate, the calcium in which is partially replaced by at least one calcium-substitute element, such as strontium (Sr) or barium (Ba). In addition, the lanthanum in the lanthanum aluminate can be partially replaced by a lanthanum-substitute element from the lanthanide group, particularly gadolinium (Gd). A process for producing such an article comprises providing a pre-reacted mixed metal oxide system as described above and applying it to the substrate by plasma spraying or an evaporation coating process.

摘要翻译： 特别适合用作燃气涡轮发动机部件的制品具有金属基底和陶瓷热障壁，该陶瓷热阻层包括混合金属氧化物体系，该混合金属氧化物系包含选自（i）铝酸镧和（ⅱ） 锆酸钙，其中钙被部分被至少一种钙替代元素替代，例如锶（Sr）或钡（Ba）。 此外，铝酸镧中的镧可以被来自镧系元素的镧替代元素，特别是钆（Gd）部分替代。 制备这种制品的方法包括提供如上所述的预反应的混合金属氧化物体系，并通过等离子体喷涂或蒸发涂覆方法将其施加到基材上。

公开(公告)号：US07500833B2

公开(公告)日：2009-03-10

申请号：US10586231

申请日：2005-01-17

申请人： Boris Bublath ,  Beate Heimberg ,  Wolfgang Hermann ,  Michael Ott

发明人： Boris Bublath ,  Beate Heimberg ,  Wolfgang Hermann ,  Michael Ott

IPC分类号： F01D5/14

CPC分类号： F01D5/282 ,  B23P6/005 ,  Y10T29/49318 ,  Y10T29/49336 ,  Y10T29/49732 ,  Y10T29/49734

摘要： The invention relates to a method for repairing a damaged and/or aged component of a turbomachine, which is made at least in part of a ceramic composite material. The aim of the invention is to create a method which allows the downtime of the turbomachine caused by damaged components to be reduced while making it possible to repair damaged components. The abovementioned aim is achieved by a generic method for repairing a damaged component (1) of a turbomachine made of a ceramic composite material (4), comprising the following steps: the joint of the component is dissolved; the matrix (5) is extracted and/or the component is machined; infiltration to restore and/or renew the ceramic matrix (5) of the component; and the joint is re-established.

摘要翻译： 本发明涉及一种用于修复至少部分由陶瓷复合材料制成的涡轮机的损坏和/或老化部件的方法。 本发明的目的是创建一种方法，其允许由损坏的部件引起的涡轮机的停机时间减少，同时可以修复损坏的部件。 上述目的通过一种用于修复由陶瓷复合材料（4）制成的涡轮机的损坏部件（1）的通用方法来实现，包括以下步骤：将部件的接头溶解; 提取矩阵（5）和/或加工零件; 渗透以恢复和/或更新组分的陶瓷基体（5）; 并重新建立联合。

公开(公告)号：US06764771B1

公开(公告)日：2004-07-20

申请号：US09530653

申请日：2000-12-22

申请人： Beate Heimberg ,  Wolfram Beele ,  Karl Kempter ,  Ulrich Bast ,  Thomas Haubold ,  Michael Hoffmann ,  Axel Endriss ,  Peter Greil ,  Chu-Wan Hong ,  Fritz Aldinger ,  Hans J. Seifert

发明人： Beate Heimberg ,  Wolfram Beele ,  Karl Kempter ,  Ulrich Bast ,  Thomas Haubold ,  Michael Hoffmann ,  Axel Endriss ,  Peter Greil ,  Chu-Wan Hong ,  Fritz Aldinger ,  Hans J. Seifert

IPC分类号： C23C3000

CPC分类号： C23C30/00 ,  F01D5/288 ,  F05D2230/90 ,  F05D2300/212 ,  Y02T50/67

摘要： The invention relates to a product (1), particularly a gas turbine blade that can be exposed to a hot aggressive gas (7). The product (1) has a metallic basic body (2), which is provided with a thermal barrier coating (4) having a spinel of the composition AB2O4.

摘要翻译： 本发明涉及一种产品（1），特别是可暴露于热侵蚀性气体（7）的燃气轮机叶片。 产品（1）具有金属基体（2），其具有具有组合物AB2O4的尖晶石的热障涂层（4）。

公开(公告)号：US06602553B2

公开(公告)日：2003-08-05

申请号：US10187504

申请日：2002-07-01

申请人： Beate Heimberg ,  Wolfram Beele ,  Karl Kempter ,  Ulrich Bast ,  Thomas Haubold ,  Michael Hoffmann ,  Axel Endriss ,  Peter Greil ,  Chu-Wan Hong ,  Fritz Aldinger ,  Hans J. Seifert

发明人： Beate Heimberg ,  Wolfram Beele ,  Karl Kempter ,  Ulrich Bast ,  Thomas Haubold ,  Michael Hoffmann ,  Axel Endriss ,  Peter Greil ,  Chu-Wan Hong ,  Fritz Aldinger ,  Hans J. Seifert

IPC分类号： B05D102

CPC分类号： C23C28/042 ,  C23C4/11 ,  C23C28/00

摘要： An article that is particularly well suited for use as a gas turbine engine component has a metallic substrate and a ceramic thermal barrier layer including a mixed metal oxide system comprising a compound selected from the group consisting of (i) a lanthanum aluminate and (ii) a calcium zirconate, the calcium in which is partially replaced by at least one calcium-substitute element, such as strontium (Sr) or barium (Ba). In addition, the lanthanum in the lanthanum aluminate can be partially replaced by a lanthanum-substitute element from the lanthanide group, particularly gadolinium (Gd). A process for producing such an article comprises providing a pre-reacted mixed metal oxide system as described above and applying it to the substrate by plasma spraying or an evaporation coating process.

公开(公告)号：US06416882B1

公开(公告)日：2002-07-09

申请号：US09562876

申请日：2000-05-01

申请人： Wolfram Beele ,  Beate Heimberg

发明人： Wolfram Beele ,  Beate Heimberg

IPC分类号： C23C408

CPC分类号： C23C28/3215 ,  C23C28/00 ,  C23C28/345 ,  C23C28/3455 ,  Y10T428/12535 ,  Y10T428/12611 ,  Y10T428/12618

摘要： An article that is particularly well suited for use as a gas turbine engine component has a ceramic thermal insulation layer overlaying a bonding layer. The bonding layer is an alloy comprising iron, cobalt and/or nickel and either: the following group 1 elements (by weight percent): Chromium: 3% to 50% Aluminum: 3% to 20% Yttrium and/or a rare-earth element: 0.01% to 0.5% Lanthanum: 0.1% to 10% Hafnium: 0 to 10% Magnesium: 0 to 10% Silicon: 0 to 2%, or the following group 2 elements (by weight percent): Chromium: 3% to 50% Aluminum: 3% to 20% Yttrium and/or a rare-earth element: 0 to 0.5% Lanthanum: 0.1% to 10% Hafnium: 0.1% to 10% Magnesium: 0 to 10% Silicon: 0 to 2%.

摘要翻译： 特别适合用作燃气涡轮发动机部件的制品具有覆盖接合层的陶瓷绝热层。 接合层是包含铁，钴和/或镍的合金，以及以下组中的1种元素（重量百分比）：铬：3％至50％铝：3％至20％钇和/或稀土 元素：0.01％至0.5％镧：0.1％至10％铪：0至10％镁：0至10％硅：0至2％或以下2族元素（重量％）：铬：3％至50 ％铝：3％〜20％钇和/或稀土元素：0〜0.5％镧：0.1％〜10％铪：0.1％〜10％镁：0〜10％硅：0〜2％。

公开(公告)号：US20080229567A1

公开(公告)日：2008-09-25

申请号：US10586231

申请日：2005-01-17

申请人： Boris Bublath ,  Beate Heimberg ,  Wolfgang Hermann ,  Michael Ott

发明人： Boris Bublath ,  Beate Heimberg ,  Wolfgang Hermann ,  Michael Ott

IPC分类号： B23P6/00

CPC分类号： F01D5/282 ,  B23P6/005 ,  Y10T29/49318 ,  Y10T29/49336 ,  Y10T29/49732 ,  Y10T29/49734

摘要： The invention relates to a method for repairing a damaged and/or aged component of a turbomachine, which is made at least in part of a ceramic composite material. The aim of the invention is to create a method which allows the downtime of the turbomachine caused by damaged components to be reduced while making it possible to repair damaged components. Said aim is achieved by a generic method for repairing a damaged component (1) of a turbomachine made of a ceramic composite material (4), comprising the following steps: the joint of the component is dissolved; the matrix (5) is extracted and/or the component is machined; infiltration to restore and/or renew the ceramic matrix (5) of the component; and the joint is re-established.

摘要翻译： 本发明涉及一种用于修复至少部分由陶瓷复合材料制成的涡轮机的损坏和/或老化部件的方法。 本发明的目的是创建一种方法，其允许由损坏的部件引起的涡轮机的停机时间减少，同时可以修复损坏的部件。 所述目的通过用于修复由陶瓷复合材料（4）制成的涡轮机的损坏部件（1）的一般方法来实现，包括以下步骤：部件的接头被溶解; 提取矩阵（5）和/或加工零件; 渗透以恢复和/或更新组分的陶瓷基体（5）; 并重新建立联合。