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1. 发明授权

US06773817B1 Antiabrasion coating 有权
标题翻译：抗磨损涂层
公开(公告)号：US06773817B1
公开(公告)日：2004-08-10
申请号：US09868597
申请日：2001-10-09
申请人： Aléxander Sagel , Bertram Kopperger , Erwin Bayer , Wilfried Smarsly
发明人： Aléxander Sagel , Bertram Kopperger , Erwin Bayer , Wilfried Smarsly
IPC分类号： B32B1500
CPC分类号： F01D5/288 , C22C45/001 , C22C45/003 , C22C45/02 , C22C45/04 , C22C45/08 , C22C45/10 , C23C30/00 , Y10S428/937 , Y10T428/12806 , Y10T428/12903 , Y10T428/24994 , Y10T428/31678 , Y10T428/31681
摘要： A wear-resistant layer is applied to a surface, which is to be protected, of a component which is subjected to mechanical and/or fluidic loads and substantially consists of amorphous or amorphous-nanocrystalline metals. The layer for protecting against abrasive or erosive wear substantially consists of an Ni—W-base alloy or substantially consists of an alloy based on Cu—Al—Ti(or —Ta or —Zr) or Pd—Cu—Si or Pt—Al—Si or Ta—Si—N, or substantially consists of an alloy of Al, at least one rare earth and a transition metal, such as Cu or Ni or Co.
摘要翻译：将耐磨层施加到被保护的表面，该表面受到机械和/或流体负载并且基本上由非晶或非晶纳米晶体金属组成。用于防止磨损或侵蚀磨损的层基本上由Ni-W基合金组成或基本上由基于Cu-Al-Ti（或-Ta或-Zr）或Pd-Cu-Si或Pt-Al -Si或Ta-Si-N，或者基本上由Al，至少一种稀土和过渡金属如Cu或Ni或Co的合金组成

2. 发明申请

US20090110560A1 Run-in coating for gas turbines and method for producing same 有权
标题翻译：燃气轮机的润滑涂层及其制造方法
公开(公告)号：US20090110560A1
公开(公告)日：2009-04-30
申请号：US10568394
申请日：2004-07-28
申请人： Erwin Bayer , Wilfried Smarsly
发明人： Erwin Bayer , Wilfried Smarsly
IPC分类号： F01D5/14 , B05D3/02 , C09D1/00 , B32B3/00
CPC分类号： F01D11/122 , Y10T428/12389
摘要： A run-in coating is for gas turbines. The run-in coating is used for sealing a radial gap between a housing of the gas turbine and rotating rotor blades of same, the run-in coating being applied onto the housing. The run-in coating is made of an intermetallic titanium-aluminum material.
摘要翻译：磨损涂层用于燃气轮机。该外接涂层用于密封燃气涡轮机壳体与其旋转的转子叶片之间的径向间隙，该引入式涂层施加到壳体上。导入涂层由金属间钛 - 铝材料制成。

3. 发明授权

US07699581B2 Run-in coating for gas turbines and method for producing same 有权
标题翻译：燃气轮机的润滑涂层及其制造方法
公开(公告)号：US07699581B2
公开(公告)日：2010-04-20
申请号：US10568394
申请日：2004-07-28
申请人： Erwin Bayer , Wilfried Smarsly
发明人： Erwin Bayer , Wilfried Smarsly
IPC分类号： F01D11/12
CPC分类号： F01D11/122 , Y10T428/12389
摘要： A run-in coating is for gas turbines. The run-in coating is used for sealing a radial gap between a housing of the gas turbine and rotating rotor blades of same, the run-in coating being applied onto the housing. The run-in coating is made of an intermetallic titanium-aluminum material.
摘要翻译：磨损涂层用于燃气轮机。该外接涂层用于密封燃气涡轮机壳体与其旋转的转子叶片之间的径向间隙，该引入式涂层施加到壳体上。导入涂层由金属间钛 - 铝材料制成。

4. 发明申请

US20070190352A1 Wear protection coating for a gas turbine component 审中-公开
标题翻译：用于燃气轮机部件的磨损保护涂层
公开(公告)号：US20070190352A1
公开(公告)日：2007-08-16
申请号：US10572770
申请日：2004-08-26
申请人： Erwin Bayer , Wilfried Smarsly , Juergen Steinwandel
发明人： Erwin Bayer , Wilfried Smarsly , Juergen Steinwandel
IPC分类号： B32B15/00 , C25D5/10
CPC分类号： C23C28/321 , C23C8/02 , C23C28/323 , C23C28/34 , C23C28/347 , F01D5/288 , F05D2230/90 , F05D2300/2281 , F05D2300/2284 , Y10T428/12576 , Y10T428/12806
摘要： A wear protection coating, in particular an erosion protection coating for gas turbine components is disclosed. The wear protection coating is applied to a to-be-protected surface of a flow mechanically stressed component. The wear protection coating has an at least double-layer structure, where a first layer is applied to the to-be-protected surface of the component and has a material composition that is adapted to the material composition of the component and where a second layer forms an outer cover coat.
摘要翻译：公开了一种耐磨保护涂层，特别是用于燃气轮机部件的侵蚀保护涂层。磨损保护涂层被施加到流动机械应力部件的待保护表面。磨损保护涂层具有至少双层结构，其中将第一层施加到部件的待保护表面上，并且具有适于组件的材料组成的材料组合物，并且其中第二层形成外覆盖层。

5. 发明申请

US20110189026A1 MATERIAL FOR A GAS TURBINE COMPONENT, METHOD FOR PRODUCING A GAS TURBINE COMPONENT AND GAS TURBINE COMPONENT 有权
标题翻译：气体涡轮组件的材料，用于生产气体涡轮组件和气体涡轮组件的方法
公开(公告)号：US20110189026A1
公开(公告)日：2011-08-04
申请号：US12739929
申请日：2008-10-18
申请人： Wilfried Smarsly , Helmut Clemens , Volker Guether , Sascha Kremmer , Andreas Otto , Harald Chladil
发明人： Wilfried Smarsly , Helmut Clemens , Volker Guether , Sascha Kremmer , Andreas Otto , Harald Chladil
IPC分类号： F01D5/14 , C22C14/00 , C22C30/00 , B21D22/00
CPC分类号： C22C14/00 , C22F1/183
摘要： A material for a gas turbine component, to be specific a titanium-aluminum-based alloy material, including at least titanium and aluminum. The material has a) in the range of room temperature, the β/B2-Ti phase, the α2-Ti3Al phase and the γ-TiAl phase with a proportion of the β/B2-Ti phase of at most 5% by volume, and b) in the range of the eutectoid temperature, the β/B2-Ti phase, the α2-Ti3Al phase and the γ-TiAl phase, with a proportion of the β/B2-Ti phase of at least 10% by volume.
摘要翻译：用于燃气轮机部件的材料，特别是至少包括钛和铝的钛 - 铝基合金材料。该材料具有a）在室温的范围内，bgr / / B-Ti相，α2-Ti3Al相和γ-TiAl相，其中bgr / B2-Ti相的比例最多为5％，通过体积，b）在共析温度，＆Bgr / / B-Ti相，α2-Ti3Al相和γ-TiAl相的范围内，bgr / B-Ti相的比例至少为10 按体积计。

6. 发明授权

US08882442B2 Component for a gas turbine and a method for the production of the component 有权
标题翻译：用于燃气轮机的组件和用于生产组件的方法
公开(公告)号：US08882442B2
公开(公告)日：2014-11-11
申请号：US12998411
申请日：2009-10-14
申请人： Wilfried Smarsly , Joachim Bamberg , Joerg Esslinger
发明人： Wilfried Smarsly , Joachim Bamberg , Joerg Esslinger
IPC分类号： F01D5/34 , B23K20/12 , B23P15/00
CPC分类号： F01D5/34 , B23K20/1205 , B23K2101/001 , B23K2103/14 , B23P15/006 , F05B2230/239 , F05C2201/0466 , F05D2230/50 , F05D2300/133 , Y10T29/49336 , Y10T29/49337 , Y10T29/49968
摘要： A component for a gas turbine, especially a blisk or a bling, whereby the component includes a rotor base (12) made of a high temperature-resistant nickel alloy and a plurality of turbine blades (14) joined to the rotor base, whereby each turbine blade includes a rotor blade (16) made of a titanium alloy and a blade root. The blade root is configured as an adapter element (18) that is made of a material that can be welded to the titanium alloy as well as to the high temperature-resistant nickel alloy and that is integrally joined to the rotor base (12) and to the rotor blade (16) fusion. A method for the production of the component is also described.
摘要翻译：一种用于燃气轮机的部件，特别是叶片或叶片，其中部件包括由耐高温镍合金制成的转子基座（12）和与转子基座接合的多个涡轮机叶片（14），由此涡轮叶片包括由钛合金和叶片根部制成的转子叶片（16）。叶片根部被配置为由能够焊接到钛合金以及耐高温镍合金并且与转子基座（12）整体接合的材料制成的适配器元件（18），并且到转子叶片（16）的融合。还描述了用于制造组件的方法。

7. 发明申请

US20090202381A1 MATERIAL FOR COMPONENTS OF A GAS TURBINE 有权
标题翻译：气体涡轮机组件的材料
公开(公告)号：US20090202381A1
公开(公告)日：2009-08-13
申请号：US12158202
申请日：2006-12-15
申请人： Wilfried Smarsly , Gerhard Sauthoff
发明人： Wilfried Smarsly , Gerhard Sauthoff
IPC分类号： C22C38/18 , F01D25/00 , C22C38/06 , C22C30/00
CPC分类号： C22C38/18 , C22C38/002 , C22C38/005 , C22C38/06 , C22C38/12
摘要： The presently described technology relates to a material for components of a gas turbine, in particular for components of a gas turbine aircraft engine, having a matrix of an iron-based alloy material, wherein the matrix of the iron-based alloy material being hardened by means of an intermetallic material of the Laves phase.
摘要翻译：目前描述的技术涉及一种用于燃气涡轮机的部件的材料，特别是用于具有铁基合金材料的基体的燃气涡轮机飞机发动机的部件，其中铁基合金材料的基体被 Laves相的金属间化合物的手段。

8. 发明申请

US20070261813A1 Method for Producing a Cast Component 有权
标题翻译：生产铸件的方法
公开(公告)号：US20070261813A1
公开(公告)日：2007-11-15
申请号：US11632774
申请日：2005-07-16
申请人： Manfred Renkel , Wilfried Smarsly
发明人： Manfred Renkel , Wilfried Smarsly
IPC分类号： B22D23/06
CPC分类号： B22D23/06 , B22D21/005 , B22D21/007 , B22D27/15 , B22D39/02
摘要： The invention relates to a method for producing a cast component, particularly a gas turbine component, by casting. According to the invention, the method comprises at least the following steps: a) preparing a melting crucible; b) preparing a semifinished granular material from an intermetallic titanium/aluminum material; c) filling the melting crucible with the semifinished granular material, whereby the quantity of the semifinished granular material placed inside the melting crucible corresponds to the quantity necessary for casting the component; d) melting the semifinished granular material made of the intermetallic titanium/aluminum material inside the melting crucible; e) preparing a casting mold; f) pouring the melt into the casting mold; g) solidifying the melt inside the casting mold, and; h) removing the cast component from the casting mold.
摘要翻译：本发明涉及通过铸造生产铸件，特别是燃气轮机件的方法。根据本发明，该方法至少包括以下步骤：a）制备熔化坩埚; b）从金属间钛/铝材料制备半成品颗粒材料; c）用半成品颗粒材料填充熔化的坩埚，由此放置在熔化坩埚内部的半成品颗粒材料的量相当于铸造组分所需的量; d）在熔融坩埚内熔化由金属间钛/铝材料制成的半成品粒状材料; e）制备铸模; f）将熔体倒入铸模中; g）固化铸模内部的熔体， h）从铸模中去除铸造组件。

9. 发明授权

US5073459A Sintered light-weight structural material and method of its manufacture 失效
标题翻译：烧结轻质结构材料及其制造方法
公开(公告)号：US5073459A
公开(公告)日：1991-12-17
申请号：US469781
申请日：1990-01-24
申请人： Wilfried Smarsly , Wolfgang Track
发明人： Wilfried Smarsly , Wolfgang Track
IPC分类号： B22F3/11 , C22C1/04 , F01D5/28
CPC分类号： C22C1/0433 , B22F3/1112 , C22C1/0491 , F01D5/28 , B22F2999/00 , Y02T50/671 , Y10T428/12042 , Y10T428/2982
摘要： A sintered metallic light-weight structural material consists of spherical voids and lattice-type webs of intermetallic compounds. Owing to its weight-specific strength, which is superior to that of conventional super-alloys, this material is suited especially for application in aircraft and turbine engine construction.
摘要翻译：烧结的金属轻质结构材料由球形空隙和晶格型的金属间化合物组成。由于其重量比强度优于常规超合金，因此该材料特别适用于飞机和涡轮发动机的施工。

10. 发明申请

US20140202601A1 FORGED TiAl COMPONENTS, AND METHOD FOR PRODUCING SAME 审中-公开
标题翻译：锻造TiAl组分及其制造方法
公开(公告)号：US20140202601A1
公开(公告)日：2014-07-24
申请号：US14237929
申请日：2012-08-09
申请人： Dietmar Helm , Falko Heutling , Ulrike Habel , Wilfried Smarsly
发明人： Dietmar Helm , Falko Heutling , Ulrike Habel , Wilfried Smarsly
IPC分类号： C22F1/18 , C22C14/00
CPC分类号： C22F1/183 , C22C14/00 , F01D5/28 , F05D2300/174
摘要： The present invention relates to a method for producing forged components of a TiAl alloy, in particular turbine blades, wherein the components are forged and undergo a two-stage heat treatment after the forging process, the first stage of the heat treatment comprising a recrystallization annealing process for 50 to 100 minutes at a temperature below the γ/α transition temperature, and the second stage of the heat treatment comprising a stabilization annealing process in the temperature range of from 800° C. to 950° C. for 5 to 7 hrs, and the cooling rate during the first heat treatment stage being greater than or equal to 3° C./sec, in the temperature range between 1300° C. to 900° C.
摘要翻译：本发明涉及一种用于生产TiAl合金，特别是涡轮叶片的锻造部件的方法，其中锻件在锻造之后被锻造并进行两级热处理，第一阶段的热处理包括再结晶退火在低于γ/α转变温度的温度下处理50至100分钟，第二阶段的热处理包括在800℃至950℃的温度范围内的稳定退火工艺5至7小时在1300℃〜900℃的温度范围内，第一热处理阶段的冷却速度大于或等于3℃/秒。

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