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1. 发明授权

US08156649B2 Gas turbine hot gas component repair method 有权
标题翻译：燃气轮机热气部件维修方法
公开(公告)号：US08156649B2
公开(公告)日：2012-04-17
申请号：US12420578
申请日：2009-04-08
申请人： Simone Hövel , Alexander Stankowski , Günter Ambrosy , Matthias Hoebel , Alexander Schnell , Hans Bissig , Rainer Kurtz
发明人： Simone Hövel , Alexander Stankowski , Günter Ambrosy , Matthias Hoebel , Alexander Schnell , Hans Bissig , Rainer Kurtz
IPC分类号： B23P6/00
CPC分类号： B23P6/005 , B23K1/0018 , B23K1/0056 , B23K9/0026 , B23K10/00 , B23K26/0093 , B23K28/02 , B23K2101/001 , F01D5/005 , F05D2230/235 , F05D2230/80 , Y10T29/49318 , Y10T29/49728 , Y10T29/49732
摘要： A gas turbine engine hot gas component repair method for defects that do not extend through the thickness of the component is provided. First defects are removed by machining a cavity in the surface of a component. Coupons, fittable within the cavities are manufactured, are for example coated with brazing medium on an inner surface and then joined to the component by joining means such as laser metal forming. The joint holds the coupon during later heat treatment, thereby eliminating a need for holding aids. Before heat treatment, a further brazing medium can be applied to the surface of the coupon overlapping onto the component. A single heat treatment, brazing the coupon to the component and, brazing the brazing medium to the outer surface of the coupon can, then be used to complete the repair.
摘要翻译：提供了一种用于不延伸通过部件的厚度的缺陷的燃气涡轮发动机热气体部件修复方法。通过在部件的表面中加工空腔来去除第一缺陷。制造在空腔内配合的优惠券，例如在内表面上涂覆有钎焊介质，然后通过诸如激光金属成形之类的接合方法与部件接合。在后续的热处理过程中，关节保持优惠券，从而不需要固定助剂。在热处理之前，可以将另外的钎焊介质施加到与组件重叠的试样表面上。单独的热处理，将试样钎焊到部件上，并将钎焊介质钎焊到试样的外表面上，然后用于完成修复。

2. 发明申请

US20090255117A1 GAS TURBINE HOT GAS COMPONENT REPAIR METHOD 有权
标题翻译：燃气涡轮机燃气元件维修方法
公开(公告)号：US20090255117A1
公开(公告)日：2009-10-15
申请号：US12420578
申请日：2009-04-08
申请人： Simone Hovel , Alexander Stankowski , Gunter Ambrosy , Matthias Hoebel , Alexander Schnell , Hans Bissig , Rainer Kurtz
发明人： Simone Hovel , Alexander Stankowski , Gunter Ambrosy , Matthias Hoebel , Alexander Schnell , Hans Bissig , Rainer Kurtz
IPC分类号： B23P6/00
CPC分类号： B23P6/005 , B23K1/0018 , B23K1/0056 , B23K9/0026 , B23K10/00 , B23K26/0093 , B23K28/02 , B23K2101/001 , F01D5/005 , F05D2230/235 , F05D2230/80 , Y10T29/49318 , Y10T29/49728 , Y10T29/49732
摘要： A gas turbine engine hot gas component repair method for defects that do not extend through the thickness of the component is provided. First defects are removed by machining a cavity in the surface of a component. Coupons, fittable within the cavities are manufactured, are for example coated with brazing medium on an inner surface and then joined to the component by joining means such as laser metal forming. The joint holds the coupon during later heat treatment, thereby eliminating a need for holding aids. Before heat treatment, a further brazing medium can be applied to the surface of the coupon overlapping onto the component. A single heat treatment, brazing the coupon to the component and, brazing the brazing medium to the outer surface of the coupon can, then be used to complete the repair.
摘要翻译：提供了一种用于不延伸通过部件的厚度的缺陷的燃气涡轮发动机热气体部件修复方法。通过在部件的表面中加工空腔来去除第一缺陷。制造在空腔内配合的优惠券，例如在内表面上涂覆有钎焊介质，然后通过诸如激光金属成形之类的接合方法与部件接合。在后续的热处理过程中，关节保持优惠券，从而不需要固定助剂。在热处理之前，可以将另外的钎焊介质施加到与组件重叠的试样表面上。单独的热处理，将试样钎焊到部件上，并将钎焊介质钎焊到试样的外表面上，然后用于完成修复。

3. 发明授权

US08740572B2 Wear-resistant and oxidation-resistant turbine blade 有权
标题翻译：耐磨和抗氧化涡轮叶片
公开(公告)号：US08740572B2
公开(公告)日：2014-06-03
申请号：US12917114
申请日：2010-11-01
申请人： Matthias Hoebel , Günter Ambrosy , Felix Reinert , Stephane Barril
发明人： Matthias Hoebel , Günter Ambrosy , Felix Reinert , Stephane Barril
IPC分类号： F01D5/28
CPC分类号： C23C28/00 , C23C24/10 , C23C28/02 , F01D5/20 , F01D5/284 , F01D5/288 , F01D11/12
摘要： A wear- and oxidation-resistant turbine blade and a method for producing the blade are provided. At least portions of the surface of the main blade section are provided with at least one first protective coating comprised of oxidation-resistant material, the first, oxidation-resistant coating is a metallic coating, which is optionally covered by a ceramic thermal barrier coating. The metallic first protective coating is arranged at least at the inner and outer crown edge of the blade tip, but not at the radially outer blade tip. The radially outer blade tip of the turbine blade is comprised of a second, single- or multi-layer wear- and oxidation-resistant protective coating, which is built up by laser metal forming and is comprised of abrasive and binder materials. The second protective coating on the blade tip overlaps along the outer and/or inner crown edge at least partially with the first, metallic protective coating arranged there.
摘要翻译：提供耐磨和抗氧化涡轮叶片以及用于生产叶片的方法。主叶片部分的表面的至少部分设置有由抗氧化材料组成的至少一个第一保护涂层，第一抗氧化涂层是金属涂层，其任选被陶瓷热障涂层覆盖。金属第一保护涂层至少布置在叶片尖端的内冠和外冠边缘处，而不是在径向外叶片尖端处。涡轮叶片的径向外叶片尖端由第二单层或多层耐磨和抗氧化的保护涂层组成，其由激光金属成形构成并由磨料和粘合剂材料组成。叶片尖端上的第二保护涂层至少部分地与第一金属保护涂层布置在外侧和/或内冠冠边缘处重叠。

4. 发明授权

US07014923B2 Method of growing a MCrAlY-coating and an article coated with the MCrAlY-coating 失效
标题翻译：生长MCrAlY涂层的方法和涂覆有MCrAlY涂层的制品
公开(公告)号：US07014923B2
公开(公告)日：2006-03-21
申请号：US10490337
申请日：2002-09-06
申请人： Alexander Schnell , Cyrille Bezencon , Matthias Hoebel , Abdus Suttar Khan , Maxim Konter , Wilfried Kurz
发明人： Alexander Schnell , Cyrille Bezencon , Matthias Hoebel , Abdus Suttar Khan , Maxim Konter , Wilfried Kurz
IPC分类号： B32B15/01 , B05D3/00
CPC分类号： C23C26/02 , C23C24/10 , C30B13/00 , C30B29/52 , Y10S428/926 , Y10S428/939 , Y10T428/12493 , Y10T428/12861 , Y10T428/12937 , Y10T428/12944
摘要： A gas turbine component consists of a superalloy base material with a single crystal structure and a protective MCrAlY-coating. The MCrAlY-coating the MCrAlY has a γ/β-phase and single crystal structure, which is epitaxial with the base material.
摘要翻译：燃气轮机组件由具有单晶结构的超级合金基材和保护性MCrAlY涂层组成。 MCrAlY涂层MCrAlY具有γ/β相和单晶结构，其与基底材料外延。

5. 发明授权

US08647073B2 Abrasive single-crystal turbine blade 有权
标题翻译：研磨单晶涡轮叶片
公开(公告)号：US08647073B2
公开(公告)日：2014-02-11
申请号：US12917071
申请日：2010-11-01
申请人： Matthias Hoebel , Alexander Schnell , Yves Pellaton
发明人： Matthias Hoebel , Alexander Schnell , Yves Pellaton
IPC分类号： F01D11/12
CPC分类号： F01D5/20 , B23K26/34 , B23K35/304 , B23K35/327 , B23K2101/001 , B23K2101/34 , B23K2103/08 , C23C26/00 , C23C28/3215 , C23C28/34 , C23C28/347 , C30B13/24 , C30B29/52 , F01D5/005 , F01D5/28 , F01D5/286 , F01D5/288 , F01D11/12 , F01D11/14 , F05D2230/31
摘要： A turbine blade for a turbine rotor, is provided having a single-crystal basic body which has a blade tip and extends in the radial direction. The turbine blade includes at least one oxidation-resistant intermediate coating, which is applied by laser metal forming and is epitaxially bonded to the basic body, is arranged on the radially outer blade tip, and in that an at least single-layer, wear-resistant and oxidation-resistant coating, which is applied by laser metal forming and consists of oxidation-resistant binder material and abrasive particles embedded therein, is arranged on at least certain regions of said epitaxial intermediate coating.
摘要翻译：一种用于涡轮转子的涡轮机叶片，其具有具有叶片尖端并沿径向方向延伸的单晶基体。涡轮叶片包括至少一个抗氧化中间涂层，其通过激光金属成形而被施加并且外延地结合到基体上，被布置在径向外侧叶片尖端上，并且至少具有单层，由所述外延中间涂层的至少某些区域设置通过激光金属成形施加的抗氧化和抗氧化涂层，其由耐氧化粘合剂材料和嵌入其中的磨料颗粒组成。

6. 发明申请

US20070120326A1 LEAF SEAL, IN PARTICULAR FOR A GAS TURBINE, AND METHOD OF PRODUCING IT 有权
标题翻译：叶片密封，特别用于气体涡轮机，以及生产它的方法
公开(公告)号：US20070120326A1
公开(公告)日：2007-05-31
申请号：US11537211
申请日：2006-09-29
申请人： Nigel Rhodes , Matthias Hoebel , Walter Brehm , Alexander Schnell
发明人： Nigel Rhodes , Matthias Hoebel , Walter Brehm , Alexander Schnell
IPC分类号： F16J15/44
CPC分类号： F16J15/3292
摘要： A leaf seal for sealing a shaft rotating about an axis, in particular in a gas turbine, includes a plurality of spaced-apart leaves arranged in a concentric circle around the axis and fixed in position by brazing, the leaves having surfaces oriented essentially parallel to the axis. The leaves are brazed to one another via intermediate spacers made of a brazing foil, so that a brazed joint is produced by brazing alloy from the brazing foils. The brazing temperature may be set to an optimum value just above the solidus temperature of the brazing foil, at which partial melting of the brazing foil occurs and penetration of liquid brazing alloy into the gap between the leaves is avoided.
摘要翻译：用于密封围绕轴旋转的轴的叶片密封件，特别是在燃气轮机中，包括多个间隔开的叶片，该叶片围绕轴线以同心圆排列并且通过钎焊固定在适当位置，叶片具有基本平行于轴。通过由钎焊箔制成的中间隔板将叶片彼此钎焊，从而通过钎焊钎焊合金制造钎焊接头。钎焊温度可以设定为刚好高于钎焊箔的固相线温度的最佳值，在该温度下发生钎焊箔的部分熔化，并且避免了液体钎焊合金渗透到叶片之间的间隙中。

7. 发明授权

US07094475B2 MCrAlY-coating 有权
标题翻译： MCrAlY涂层
公开(公告)号：US07094475B2
公开(公告)日：2006-08-22
申请号：US10490018
申请日：2002-09-06
申请人： Alexander Schnell , Cyrille Bezencon , Matthias Hoebel , Abdus Suttar Khan , Maxim Konter , Wilfried Kurz
发明人： Alexander Schnell , Cyrille Bezencon , Matthias Hoebel , Abdus Suttar Khan , Maxim Konter , Wilfried Kurz
IPC分类号： B32B15/01 , F03B3/12
CPC分类号： C23C30/00 , C23C24/106 , C30B13/00 , C30B29/52 , Y10T428/12458 , Y10T428/12931 , Y10T428/12937 , Y10T428/12944
摘要： A gas turbine component consists of a superalloy base material with a single crystal structure and a protective MCrAlY-coating (6). The MCrAlY-coating (6) has a g/g′ single crystal structure, which is epitaxial with the base material. It has be determined the critical factors for the successful epitaxial and crack-free growth of the MCrAlY-coating (6).
摘要翻译：燃气轮机部件由具有单晶结构的高温合金基材和保护性MCrAlY涂层（6）组成。 MCrAlY涂层（6）具有g / g'单晶结构，其与基底材料外延。已经确定了MCrAlY涂层的成功的外延和无裂纹生长的关键因素（6）。

8. 发明授权

US06998568B2 Method for fabricating, modifying or repairing of single crystal or directionally solidified articles 有权
标题翻译：制造，修改或修复单晶或定向凝固制品的方法
公开(公告)号：US06998568B2
公开(公告)日：2006-02-14
申请号：US10721268
申请日：2003-11-26
申请人： Walter Brehm , Matthias Hoebel , Edward Obbard , Alexander Schnell
发明人： Walter Brehm , Matthias Hoebel , Edward Obbard , Alexander Schnell
IPC分类号： B23K26/00 , B23K26/34
CPC分类号： B23K26/032 , B23K1/0056 , B23K26/034 , B23K26/0344 , B23K26/32 , B23K26/34 , B23K35/38 , B23K2101/001 , B23K2103/08 , B23P6/002 , B33Y10/00 , B33Y40/00 , F01D5/005 , F01D5/28
摘要： It is disclosed a method for fabricating, modifying or repairing of single crystal or directionally solidified articles. Two single crystal or directionally solidified prefabricated parts are joint by isothermally brazing using a brazing material. After that an epitaxial or non-epitaxial layer on the surface of the created article and of the braze joint is applied using a laser metal forming process.
摘要翻译：公开了制造，修改或修复单晶或定向凝固制品的方法。两个单晶或定向凝固的预制部件通过使用钎焊材料的等温钎焊接合。之后，使用激光金属成形工艺施加所产生的制品和钎焊接头的表面上的外延或非外延层。

9. 发明授权

US08220802B2 Leaf seal, in particular for a gas turbine, and method of producing it 有权
标题翻译：叶片密封件，特别是用于燃气轮机的密封件及其制造方法
公开(公告)号：US08220802B2
公开(公告)日：2012-07-17
申请号：US11537211
申请日：2006-09-29
申请人： Nigel Anthony Rhodes , Matthias Hoebel , Walter Brehm , Alexander Schnell
发明人： Nigel Anthony Rhodes , Matthias Hoebel , Walter Brehm , Alexander Schnell
IPC分类号： F16J15/447
CPC分类号： F16J15/3292
摘要： A leaf seal for sealing a shaft rotating about an axis, in particular in a gas turbine, includes a plurality of spaced-apart leaves arranged in a concentric circle around the axis and fixed in position by brazing, the leaves having surfaces oriented essentially parallel to the axis. The leaves are brazed to one another via intermediate spacers made of a brazing foil, so that a brazed joint is produced by brazing alloy from the brazing foils. The brazing temperature may be set to an optimum value just above the solidus temperature of the brazing foil, at which partial melting of the brazing foil occurs and penetration of liquid brazing alloy into the gap between the leaves is avoided.
摘要翻译：用于密封围绕轴旋转的轴的叶片密封件，特别是在燃气轮机中，包括多个间隔开的叶片，该叶片围绕轴线以同心圆排列并且通过钎焊固定在适当位置，叶片具有基本平行于轴。通过由钎焊箔制成的中间隔板将叶片彼此钎焊，从而通过钎焊钎焊合金制造钎焊接头。钎焊温度可以设定为刚好高于钎焊箔的固相线温度的最佳值，在该温度下发生钎焊箔的部分熔化，并且避免了液体钎焊合金渗透到叶片之间的间隙中。

10. 发明申请

US20060081571A1 Method for controlling the microstructure of a laser metal formed hard layer 有权
标题翻译：用于控制形成激光金属的硬质层的微结构的方法
公开(公告)号：US20060081571A1
公开(公告)日：2006-04-20
申请号：US11071171
申请日：2005-03-04
申请人： Matthias Hoebel , Edward Obbard , Alexander Schnell
发明人： Matthias Hoebel , Edward Obbard , Alexander Schnell
IPC分类号： B23K26/34 , B23K26/03
CPC分类号： B23K26/032 , B22F3/1055 , B22F5/009 , B22F2003/1056 , B23K26/034 , B23K26/144 , B23K35/327 , B33Y10/00 , B33Y80/00 , C21D1/09 , C23C4/12 , C23C24/10 , Y02P10/295
摘要： It is disclosed a method of applying a coating (12) with a controlled laser metal forming process. A light source with a specific power and a signal capturing apparatus is moved over an article (1) to form locally a melt pool (7) on the surface (5) of the article (1) to which a coating powder (8) is injected. An optical signal (13) is captured from the melt pool (7), and the monitored optical signal (13) is used for the determination of the temperature and temperature fluctuations of the melt pool (7). Furthermore, a control system (16) is used to adjust at least one process parameter such as the power of the light source to obtain desired melt pool properties. Subsequently the melt pool (7) solidifies. The high degree of control over the microstructure provides an efficient tool for generating laser metal formed hard coatings (12) with optimised wear properties.
摘要翻译：公开了一种用受控的激光金属成形方法涂覆涂层（12）的方法。具有特定功率的光源和信号捕获设备在物品（1）上移动以在制品（1）的表面（5）上局部形成熔池（7），涂料粉末（8）注射从熔池（7）捕获光信号（13），并且使用监视的光信号（13）来确定熔池（7）的温度和温度波动。此外，控制系统（16）用于调节至少一个过程参数，例如光源的功率，以获得所需的熔池性质。随后，熔池（7）固化。对微观结构的高度控制提供了用于产生具有优化的耐磨性能的激光金属成形硬涂层（12）的有效工具。

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