专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US07172787B2 Method of repairing a Ni-base alloy part 有权
标题翻译： Ni基合金零件的修复方法
公开(公告)号：US07172787B2
公开(公告)日：2007-02-06
申请号：US10733269
申请日：2003-12-12
申请人： Taiji Torigoe , Ikuo Okada , Kouji Takahashi , Minoru Ohara , Kengo Yamaguchi , Sunao Aoki
发明人： Taiji Torigoe , Ikuo Okada , Kouji Takahashi , Minoru Ohara , Kengo Yamaguchi , Sunao Aoki
IPC分类号： B05C13/00 , B05D3/10 , B05D1/36
CPC分类号： C23C28/3215 , C23C4/02 , C23C4/12 , C23C28/3455 , F01D5/005 , F05C2201/0466 , F05D2230/312 , F05D2230/80 , F05D2230/90 , Y02T50/67
摘要： The present invention relates to a method of repairing a Ni-based alloy part having an undercoat layer and a topcoat layer stacked on a Ni-based alloy base when the topcoat layer is damaged, comprising the steps of removing a peeled-off portion of the damaged topcoat layer and a denatured portion of the undercoat layer corresponding to the peeled-off portion, forming another undercoat layer by applying spraying to an opening portion of the undercoat layer in the atmosphere at a spray particle speed of 300 m/s or more and a base-material temperature of 300° C. or less, and forming another topcoat layer in the peeled-off portion of the topcoat layer
摘要翻译：本发明涉及一种在顶涂层损坏时，修复Ni基合金基底上具有底涂层和顶涂层的Ni基合金部件的方法，包括以下步骤：除去损坏的外涂层和对应于剥离部分的底涂层的变性部分，通过以300m / s或更大的喷雾粒子速度在大气中喷涂到底涂层的开口部分上形成另一底涂层;以及基材料温度为300℃以下，在顶涂层的剥离部分中形成另一面涂层

2. 发明申请

US20100062173A1 THERMAL BARRIER COATING MATERIAL AND METHOD FOR PRODUCTION THEREOF, GAS TURBINE MEMBER USING THE THERMAL BARRIER COATING MATERIAL, AND GAS TURBINE 审中-公开
标题翻译：热障涂层材料及其制造方法，使用热障涂层材料的气体涡轮机构件和气体涡轮机
公开(公告)号：US20100062173A1
公开(公告)日：2010-03-11
申请号：US12617740
申请日：2009-11-13
申请人： Taiji Torigoe , Kazutaka Mori , Ikuo Okada , Sunao Aoki , Kouji Takahashi , Minoru Ohara , Takehiko Hirata , Hideaki Kaneko
发明人： Taiji Torigoe , Kazutaka Mori , Ikuo Okada , Sunao Aoki , Kouji Takahashi , Minoru Ohara , Takehiko Hirata , Hideaki Kaneko
IPC分类号： B05D1/08 , B05D3/06
CPC分类号： C23C4/18 , C23C4/073 , C23C4/11 , C23C28/3215 , C23C28/3455 , F01D5/288 , F05D2230/31 , F05D2230/311 , F05D2230/312 , F05D2230/40 , F05D2230/90 , F05D2300/2118
摘要： A thermal barrier coating material, containing a metal binding layer laminated on a base material and ceramic layer laminated on the metal binding layer, the ceramic layer comprising partially stabilized ZrO2 which is partially stabilized by additives of Dy2O3 and Yb2O3.
摘要翻译：一种热障涂层材料，其包含层叠在基底材料上的金属粘合层和层压在金属粘合层上的陶瓷层，陶瓷层包含部分稳定的ZrO 2，其部分被Dy2O3和Yb2O3的添加剂稳定。

3. 发明授权

US07655326B2 Thermal barrier coating material and method for production thereof, gas turbine member using the thermal barrier coating material, and gas turbine 有权
标题翻译：隔热涂料及其制造方法，使用该热障涂层材料的燃气轮机部件和燃气轮机
公开(公告)号：US07655326B2
公开(公告)日：2010-02-02
申请号：US10478690
申请日：2002-06-14
申请人： Taiji Torigoe , Kazutaka Mori , Ikuo Okada , Sunao Aoki , Kouji Takahashi , Minoru Ohara , Takehiko Hirata
发明人： Taiji Torigoe , Kazutaka Mori , Ikuo Okada , Sunao Aoki , Kouji Takahashi , Minoru Ohara , Takehiko Hirata
IPC分类号： B32B15/04 , B32B18/00
CPC分类号： C23C4/18 , C23C4/073 , C23C4/11 , C23C28/3215 , C23C28/3455 , F01D5/288 , F05D2230/31 , F05D2230/311 , F05D2230/312 , F05D2230/40 , F05D2230/90 , F05D2300/2118
摘要： A thermal barrier coating material, containing a metal binding layer laminated on a base material and a ceramic layer laminated on the metal binding layer, the ceramic layer comprising partially stabilized ZrO2 which is partially stabilized by additives of Dy2O3 and Yb2O3.
摘要翻译：一种隔热涂料，其包含层叠在基材上的金属粘合层和层压在金属粘合层上的陶瓷层，所述陶瓷层包含部分稳定化的ZrO 2，其通过Dy2O3和Yb2O3的添加剂部分稳定。

4. 发明授权

US06916551B2 Thermal barrier coating material, gas turbine parts and gas turbine 有权
标题翻译：隔热涂层材料，燃气轮机部件和燃气轮机
公开(公告)号：US06916551B2
公开(公告)日：2005-07-12
申请号：US10274132
申请日：2002-10-21
申请人： Taiji Torigoe , Sunao Aoki , Kazutaka Mori , Ikuo Okada , Kouji Takahashi
发明人： Taiji Torigoe , Sunao Aoki , Kazutaka Mori , Ikuo Okada , Kouji Takahashi
IPC分类号： F01D5/28 , C23C4/10 , C23C28/00 , C23C30/00 , F02C7/00 , B32B15/04 , F03B3/12
CPC分类号： C23C28/3215 , C23C4/11 , C23C28/3455 , C23C30/00 , Y02T50/67 , Y10T428/1259 , Y10T428/12611 , Y10T428/12618 , Y10T428/249953 , Y10T428/249956 , Y10T428/249967
摘要： A thermal barrier coating material can prevent spall-off from occurring during operation at high temperatures and has a high heat insulating effect. A turbine parts and a gas turbine that are protected with the thermal barrier coating material are also provided. The thermal barrier coating material of the present invention comprises a ceramic layer 23, which is formed on a high temperature heat-resistant alloy base 21 to protect the base 21 from high temperatures, the ceramic layer 23 being applied via a bonding coat layer 22 provided as a metal bonding layer and is made of ZrO2 with Er2O3 added thereto as a stabilizing agent. The turbine parts and the gas turbine of the present invention are coated with the thermal barrier coating material on the surfaces thereof.
摘要翻译：热障涂层材料可以防止在高温运行时发生剥落，并且具有高隔热效果。还提供了用热障涂层材料保护的涡轮部件和燃气轮机。本发明的隔热涂料包括陶瓷层23，该陶瓷层23形成在高温耐热合金基体21上，以保护基底21免受高温的影响，陶瓷层23通过提供的接合涂层22施加作为金属结合层，并且由添加有Er 2 O 3 N 3的ZrO 2 2作为稳定剂制成。本发明的涡轮机部件和燃气轮机在其表面上涂覆有热障涂层材料。

5. 发明授权

US07354663B2 Thermal barrier coating, manufacturing method thereof, turbine part and gas turbine 有权
标题翻译：热障涂层，其制造方法，涡轮机部件和燃气轮机
公开(公告)号：US07354663B2
公开(公告)日：2008-04-08
申请号：US10815734
申请日：2004-04-02
申请人： Taiji Torigoe , Kazutaka Mori , Sunao Aoki , Kouji Takahashi , Minoru Ohara
发明人： Taiji Torigoe , Kazutaka Mori , Sunao Aoki , Kouji Takahashi , Minoru Ohara
IPC分类号： B32B9/00
CPC分类号： C23C4/11 , B32B15/04 , C23C28/3215 , C23C28/3455 , F05B2230/90 , F05C2253/12 , Y02T50/67 , Y10T428/12618
摘要： A thermal barrier coating enabling to prevent peeling of layer in a high temperature use and still having a high thermal barrier effect, a turbine part coated by this thermal barrier coating and a gas turbine comprising this turbine part are provided. The thermal barrier coating comprises a base material 21 of high temperature heat resistant alloy and a ceramics layer 23 formed on the base material 21. The ceramics layer 23 comprises ZrO2 added with Yb2O3 as stabilizer and is laminated on the base material via a bond coat layer 22 laminated as a metallic bond layer. A plurality of cracks 23A are preferably introduced in the ceramics layer 23. The turbine part is constructed having its surface coated with the above thermal barrier coating.
摘要翻译：提供能够防止在高温使用中并且仍然具有高热障效应的层的剥离的热障涂层，由该热障涂层涂覆的涡轮部分和包括该涡轮部的燃气轮机。隔热涂层包括高温耐热合金的基材21和形成在基材21上的陶瓷层23。陶瓷层23由添加了Yb 2 O 3 O 3的稳定剂构成的ZrO 2 2层叠在基材上，层叠有粘接层22 作为金属结合层。在陶瓷层23中优选引入多个裂纹23A。涡轮机部件被构造成具有涂覆有上述热障涂层的表面。

6. 发明申请

US20050221109A1 Thermal barrier coating, manufacturing method thereof, turbine part and gas turbine 有权
标题翻译：热障涂层，其制造方法，涡轮机部件和燃气轮机
公开(公告)号：US20050221109A1
公开(公告)日：2005-10-06
申请号：US10815734
申请日：2004-04-02
申请人： Taiji Torigoe , Kazutaka Mori , Sunao Aoki , Kouji Takahashi , Minoru Ohara
发明人： Taiji Torigoe , Kazutaka Mori , Sunao Aoki , Kouji Takahashi , Minoru Ohara
IPC分类号： B32B15/04 , C23C4/10 , C23C28/00
CPC分类号： C23C4/11 , B32B15/04 , C23C28/3215 , C23C28/3455 , F05B2230/90 , F05C2253/12 , Y02T50/67 , Y10T428/12618
摘要： A thermal barrier coating enabling to prevent peeling of layer in a high temperature use and still having a high thermal barrier effect, a turbine part coated by this thermal barrier coating and a gas turbine comprising this turbine part are provided. The thermal barrier coating comprises a base material 21 of high temperature heat resistant alloy and a ceramics layer 23 formed on the base material 21. The ceramics layer 23 comprises ZrO2 added with Yb2O3 as stabilizer and is laminated on the base material via a bond coat layer 22 laminated as a metallic bond layer. A plurality of cracks 23A are preferably introduced in the ceramics layer 23. The turbine part is constructed having its surface coated with the above thermal barrier coating.
摘要翻译：提供能够防止在高温使用中并且仍然具有高热障效应的层的剥离的热障涂层，由该热障涂层涂覆的涡轮部分和包括该涡轮部的燃气轮机。隔热涂层包括高温耐热合金的基材21和形成在基材21上的陶瓷层23。陶瓷层23包含添加有Yb 2 O 3 O 3的稳定剂的ZrO 2，并且通过层压的粘合涂层22层压在基材上作为金属结合层。在陶瓷层23中优选引入多个裂纹23A。涡轮机部件被构造成具有涂覆有上述热障涂层的表面。

7. 发明授权

US06756131B2 High temperature corrosion resistant alloy, thermal barrier coating material, and gas turbine using high temperature corrosion resistant alloy 有权
标题翻译：高温耐腐蚀合金，热障涂层材料和采用高温耐腐蚀合金的燃气轮机
公开(公告)号：US06756131B2
公开(公告)日：2004-06-29
申请号：US10316070
申请日：2002-12-11
申请人： Hidetaka Oguma , Ikuo Okada , Taiji Torigoe , Kouji Takahashi
发明人： Hidetaka Oguma , Ikuo Okada , Taiji Torigoe , Kouji Takahashi
IPC分类号： F03B312
CPC分类号： C23C28/3215 , C22C19/058 , C23C4/02 , C23C4/073 , C23C28/345 , C23C28/3455 , C23C30/00 , Y02T50/67 , Y10T428/12535 , Y10T428/1259 , Y10T428/12611 , Y10T428/12618 , Y10T428/12944
摘要： A high temperature corrosion resistant alloy composition comprising, in addition to Ni, 0.1 to 12% by weight of Co, 10 to 30% by weight of Cr, 4 to 15% by weight of Al, 0.1 to 5% by weight of Y, and 0.5 to 10% by weight of Re. The high temperature corrosion resistant alloy composition has an excellent oxidation resistance and ductility and is suitable for use in a bonding layer of a thermal barrier coating material.
摘要翻译：一种高温耐腐蚀合金组合物，除了Ni之外还包含0.1〜12重量％的Co，10〜30重量％的Cr，4〜15重量％的Al，0.1〜5重量％的Y，和0.5〜10重量％的Re。高温耐腐蚀合金组合物具有优异的抗氧化性和延展性，并且适用于热障涂层材料的粘合层。

8. 发明授权

US5882586A Heat-resistant nickel-based alloy excellent in weldability 失效
标题翻译：耐热镍基合金，焊接性优良
公开(公告)号：US5882586A
公开(公告)日：1999-03-16
申请号：US899587
申请日：1997-07-24
申请人： Itaru Tamura , Kazunori Tokoro , Takashi Kawabata , Tsuyoki Kokubun , Toshio Mochizuki , Shuichi Sakashita , Hisataka Kawai , Ikuo Okada , Ichiro Tsuji , Kouji Takahashi , Taiji Torigoe
发明人： Itaru Tamura , Kazunori Tokoro , Takashi Kawabata , Tsuyoki Kokubun , Toshio Mochizuki , Shuichi Sakashita , Hisataka Kawai , Ikuo Okada , Ichiro Tsuji , Kouji Takahashi , Taiji Torigoe
IPC分类号： C22C19/05
CPC分类号： C22C19/056
摘要： A heat-resistant nickel-based alloy having excellent welding properties, said nickel-based alloy consisting essentially of, in terms of wt. %, 0.05 to 0.25% of C, 18 to 25% of Cr, 15 to 25% of Co, at least one selected from the group consisting of up to 3.5% of Mo and 5 to 10% of W, with W+1/2Mo being 5 to 10%, 1.0 to 5.0% of Ti, 1.0 to 4.0% of Al, 0.5 to 4.5% of Ta, 0.2 to 3.0% of Nb, 0.005 to 0.10% of Zr, 0.001 to 0.01% of B and the balance being Ni and unavoidable impurities, wherein the (Al+Ti) content and the (W+1/2Mo) content are within the range surrounded by the lines connecting points A (Al+Ti: 5%, W+1/2Mo: 10%), B (Al+Ti: 5%, W+1/2Mo: 5%), C (Al+Ti: 7%, W+1/2Mo: 5%), and D (Al+Ti: 7%, W+1/2Mo: 10%) excluding the line A-B in FIG. 1. Another alloy has substantially the same composition as described above except that the Cr content is 10 to 20% and the (Al+Ti) content and the (W+1/2Mo) content are within the range surrounded by the lines connecting points A, B, E (Al+Ti: 4%, W+1/2Mo: 5%), F (Al+Ti: 4%, W+1/2Mo: 0.5%), G (Al+Ti: 7%, W+1/2Mo: 0.5%) and D, excluding the line A-B-E, in FIG. 1.
摘要翻译：一种具有优异焊接性能的耐热镍基合金，所述镍基合金基本上以重量计。，0.05〜0.25％的C，18〜25％的Cr，15〜25％的Co，至少1种选自高达3.5％的Mo和5〜10％的W，W + E，fra 1/2 + EE Mo为5〜10％，Ti为1.0〜5.0％，Al为1.0〜4.0％，Ta为0.5〜4.5％，Nb为0.2〜3.0％，Zr为0.005〜0.10％ 0.001〜0.01％的B，余量为Ni和不可避免的杂质，其中（Al + Ti）含量和（W ++ E，fra 1/2 + EE Mo）含量在连接点 A（Al + Ti：5％，W ++ E，fra 1/2 + EE Mo：10％），B（Al + Ti：5％，W ++ E，fra 1/2 + EE Mo：），C（Al + Ti：7％，W ++ E，fra 1/2 + EE Mo：5％）和D（Al + Ti：7％，W ++ E，：10％），不包括图1中的线AB。另一种合金具有与上述基本相同的组成，不同之处在于Cr含量为10〜20％，（Al + Ti）含量和（W ++ E，fra 1/2 + EE Mo）含量在连接点A，B，E（Al + Ti：4％，W ++ E，fra 1/2 + EE Mo：5％），F（Al + Ti：4％，W ++ E ，1/2 + EE Mo：0.5％），G（Al + Ti：7％，W ++ E，fra 1/2 + EE Mo：0.5％）和D，不包括线ABE。 1。

9. 发明申请

US20130202912A1 PROCESS FOR PRODUCING THERMAL BARRIER COATING, TURBINE MEMBER PROVIDED WITH THERMAL BARRIER COATING, AND GAS TURBINE 有权
标题翻译：制造热障涂层的方法，用热障涂层提供的涡轮部件和气体涡轮
公开(公告)号：US20130202912A1
公开(公告)日：2013-08-08
申请号：US13387206
申请日：2010-08-30
申请人： Taiji Torigoe , Ichiro Nagano , Ikuo Okada , Keizo Tsukagoshi , Kazutaka Mori , Yoshiaki Inoue , Yoshitaka Uemura , Yoshifumi Okajima , Hideaki Kaneko , Masahiko Mega
发明人： Taiji Torigoe , Ichiro Nagano , Ikuo Okada , Keizo Tsukagoshi , Kazutaka Mori , Yoshiaki Inoue , Yoshitaka Uemura , Yoshifumi Okajima , Hideaki Kaneko , Masahiko Mega
IPC分类号： C23C4/04 , F01D5/28
CPC分类号： C23C4/04 , C23C4/02 , C23C4/06 , C23C4/10 , C23C4/11 , C23C4/12 , C23C4/134 , C23C28/30 , C23C28/3215 , C23C28/345 , C23C28/3455 , F01D5/28 , F01D5/284 , F01D5/286 , F01D5/288 , Y10T428/12611 , Y10T428/12618 , Y10T428/12931 , Y10T428/12937 , Y10T428/12944 , Y10T428/12979
摘要： A process for producing a thermal barrier coating having an excellent thermal barrier effect and superior durability to thermal cycling. Also, a turbine member having a thermal barrier coating that has been formed using the production process, and a gas turbine. The process for producing a thermal barrier coating includes: forming a metal bonding layer (12) on a heat-resistant alloy substrate (11), and forming a ceramic layer (13) on the metal bonding layer (12) by thermal spraying of thermal spray particles having a particle size distribution in which the 10% cumulative particle size is not less than 30 μm and not more than 100 μm.
摘要翻译：一种制造具有优异的隔热效果和优异的热循环耐久性的热障涂层的方法。此外，具有使用该制造方法形成的热障涂层的涡轮部件和燃气轮机。制造隔热涂料的方法包括：在耐热合金基材（11）上形成金属粘结层（12），并在金属粘合层（12）上通过热喷涂形成陶瓷层（13）具有10％累积粒径不小于30μm且不大于100μm的粒度分布的喷雾颗粒。

10. 发明授权

US09822437B2 Process for producing thermal barrier coating 有权
公开(公告)号：US09822437B2
公开(公告)日：2017-11-21
申请号：US13387206
申请日：2010-08-30
申请人： Taiji Torigoe , Ichiro Nagano , Ikuo Okada , Keizo Tsukagoshi , Kazutaka Mori , Yoshiaki Inoue , Yoshitaka Uemura , Yoshifumi Okajima , Hideaki Kaneko , Masahiko Mega
发明人： Taiji Torigoe , Ichiro Nagano , Ikuo Okada , Keizo Tsukagoshi , Kazutaka Mori , Yoshiaki Inoue , Yoshitaka Uemura , Yoshifumi Okajima , Hideaki Kaneko , Masahiko Mega
IPC分类号： C23C4/04 , F01D5/28 , C23C4/12 , C23C4/10 , C23C4/02 , C23C4/06 , C23C28/00 , C23C4/11 , C23C4/134
CPC分类号： C23C4/04 , C23C4/02 , C23C4/06 , C23C4/10 , C23C4/11 , C23C4/12 , C23C4/134 , C23C28/30 , C23C28/3215 , C23C28/345 , C23C28/3455 , F01D5/28 , F01D5/284 , F01D5/286 , F01D5/288 , Y10T428/12611 , Y10T428/12618 , Y10T428/12931 , Y10T428/12937 , Y10T428/12944 , Y10T428/12979
摘要： A process for producing a thermal barrier coating having an excellent thermal barrier effect and superior durability to thermal cycling. Also, a turbine member having a thermal barrier coating that has been formed using the production process, and a gas turbine. The process for producing a thermal barrier coating includes: forming a metal bonding layer (12) on a heat-resistant alloy substrate (11), and forming a ceramic layer (13) on the metal bonding layer (12) by thermal spraying of thermal spray particles having a particle size distribution in which the 10% cumulative particle size is not less than 30 μm and not more than 100 μm.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式