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1. 发明授权

US08900512B2 Ni-based single crystal superalloy 有权
标题翻译：镍基单晶超合金
公开(公告)号：US08900512B2
公开(公告)日：2014-12-02
申请号：US13144748
申请日：2010-01-15
申请人： Hiroshi Harada , Tadaharu Yokokawa , Yutaka Koizumi , Toshiharu Kobayashi , Masao Sakamoto , Kyoko Kawagishi , Ikuo Okada , Hidataka Oguma , Taiji Torigoe , Masaki Taneike , Eisaku Ito , Junichiro Masada , Keizo Tsukagoshi , Hidemichi Koyabu
发明人： Hiroshi Harada , Tadaharu Yokokawa , Yutaka Koizumi , Toshiharu Kobayashi , Masao Sakamoto , Kyoko Kawagishi , Ikuo Okada , Hidataka Oguma , Taiji Torigoe , Masaki Taneike , Eisaku Ito , Junichiro Masada , Keizo Tsukagoshi , Hidemichi Koyabu
IPC分类号： C22C19/05 , F01D5/28 , C22F1/00 , C22F1/02 , C22F1/10 , C30B11/00 , C30B29/52
CPC分类号： F01D5/28 , C22C19/057 , C22F1/00 , C22F1/02 , C22F1/10 , C30B11/00 , C30B29/52 , F05D2300/607 , Y02T50/671
摘要： The Ni-based single crystal alloy disclosed here is a single crystal and has a chemical composition containing, as % by mass, Co: 8 to 12%, Cr: 5 to 7.5%, Mo: 0.2 to 1.2%, W: 5 to 7%, Al: 5 to 6.5%, Ta: 8 to 12%. Hf: 0.01 to 0.2%, Re: 2 to 4%, Si: 0.005 to 0.1%, with the balance of Ni and inevitable impurities.
摘要翻译：这里公开的Ni系单晶合金为单晶，其化学组成为：Co：8〜12％，Cr：5〜7.5％，Mo：0.2〜1.2％，W：5〜 7％，Al：5〜6.5％，Ta：8〜12％。 Hf：0.01〜0.2％，Re：2〜4％，Si：0.005〜0.1％，余量由Ni和不可避免的杂质构成。

2. 发明申请

US20120014832A1 Ni-BASED SINGLE CRYSTAL SUPERALLOY 有权
标题翻译：镍基单晶超级合金
公开(公告)号：US20120014832A1
公开(公告)日：2012-01-19
申请号：US13144748
申请日：2010-01-15
申请人： Hiroshi Harada , Tadaharu Yokokawa , Yutaka Koizumi , Toshiharu Kobayashi , Masao Sakamoto , Kyoko Kawagishi , Ikuo Okada , Hidataka Oguma , Tøiji Torigoe , Masaki Taneike , Eisaku Ito , Junichiro Masada , Keizo Tsukagoshi , Hidemichi Koyabu
发明人： Hiroshi Harada , Tadaharu Yokokawa , Yutaka Koizumi , Toshiharu Kobayashi , Masao Sakamoto , Kyoko Kawagishi , Ikuo Okada , Hidataka Oguma , Tøiji Torigoe , Masaki Taneike , Eisaku Ito , Junichiro Masada , Keizo Tsukagoshi , Hidemichi Koyabu
IPC分类号： C22C19/05
CPC分类号： F01D5/28 , C22C19/057 , C22F1/00 , C22F1/02 , C22F1/10 , C30B11/00 , C30B29/52 , F05D2300/607 , Y02T50/671
摘要： The Ni-based single crystal alloy disclosed here is a single crystal and has a chemical composition containing, as % by mass, Co: 8 to 12%, Cr: 5 to 7.5%, Mo: 0.2 to 1.2%, W: 5 to 7%, Al: 5 to 6.5%, Ta: 8 to 12%. Hf: 0.01 to 0.2%, Re: 2 to 4%, Si: 0.005 to 0.1%, with the balance of Ni and inevitable impurities.
摘要翻译：这里公开的Ni系单晶合金为单晶，其化学组成为：Co：8〜12％，Cr：5〜7.5％，Mo：0.2〜1.2％，W：5〜 7％，Al：5〜6.5％，Ta：8〜12％。 Hf：0.01〜0.2％，Re：2〜4％，Si：0.005〜0.1％，余量由Ni和不可避免的杂质构成。

3. 发明申请

US20110262770A1 THERMAL BARRIER COATING MATERIAL, THERMAL BARRIER COATING, TURBINE MEMBER, AND GAS TURBINE 审中-公开
标题翻译：热障涂层材料，热障涂层，涡轮部件和气体涡轮
公开(公告)号：US20110262770A1
公开(公告)日：2011-10-27
申请号：US13125897
申请日：2009-11-27
申请人： Taiji Torigoe , Ichiro Nagano , Ikuo Okada , Keizo Tsukagoshi , Koji Takahashi , Yoshifumi Okajima , Soji Kasumi , Eisaku Ito , Kazutaka Mori
发明人： Taiji Torigoe , Ichiro Nagano , Ikuo Okada , Keizo Tsukagoshi , Koji Takahashi , Yoshifumi Okajima , Soji Kasumi , Eisaku Ito , Kazutaka Mori
IPC分类号： B32B15/04 , C04B35/48 , B32B18/00
CPC分类号： C04B35/486 , C04B2235/3224 , C04B2235/96 , C04B2235/9607 , C23C4/04 , C23C4/11 , C23C28/3215 , C23C28/345 , C23C28/3455 , F01D5/288 , F05D2230/90 , Y10T428/12618
摘要： A thermal barrier coating material that exhibits superior high-temperature crystal stability to YSZ, as well as a high degree of toughness and an excellent thermal barrier effect. Also provided are a thermal barrier coating, which has a ceramic layer formed using the thermal barrier coating material and exhibits excellent durability to heat cycling, and a turbine member and a gas turbine which are each provided with the thermal barrier coating. The thermal barrier coating material comprises mainly ZrO2 which contains Yb2O3 and Sm2O3 as stabilizers, wherein the amount of the stabilizers is not less than 2 mol % and not more than 7 mol %, and the amount of the Sm2O3 is not less than 0.1 mol % and not more than 2.5 mol %.
摘要翻译：对YSZ显示优异的高温晶体稳定性以及高韧性和优异的热障效果的热障涂层材料。还提供了一种隔热涂层，其具有使用该热障涂层材料形成的陶瓷层，并显示出优异的热循环耐久性，以及每个设置有该热障涂层的涡轮机构件和燃气轮机。热障涂层材料主要包含含有Yb2O3和Sm2O3作为稳定剂的ZrO 2，其中稳定剂的量不小于2mol％且不大于7mol％，并且Sm2O3的量不小于0.1mol％不超过2.5摩尔％。

4. 发明授权

US08550778B2 Cooling system of ring segment and gas turbine 有权
标题翻译：环段和燃气轮机的冷却系统
公开(公告)号：US08550778B2
公开(公告)日：2013-10-08
申请号：US12763723
申请日：2010-04-20
申请人： Hidemichi Koyabu , Satoshi Hada , Junichiro Masada , Keizo Tsukagoshi
发明人： Hidemichi Koyabu , Satoshi Hada , Junichiro Masada , Keizo Tsukagoshi
IPC分类号： F01D5/18
CPC分类号： F02C7/12 , F01D11/24 , F05D2240/11
摘要： In a cooling system of ring segment that cools a ring segment of a gas turbine, the segment body of the ring segment is constituted from a collision plate that has a small hole that blows out cooling air, a cooling space that is enclosed by the collision plate and the main body of the segment body; a first cavity that receives the cooling air from the cooling space; and a first cooling passage, of which one end communicates with the first cavity, and the other end blows out the cooling air from openings that are arranged in the side end portion into combustion gas; the openings of the first cooling passages being arranged so that the arrangement pitch of the openings becomes smaller or the opening area of the openings becomes larger on the upstream in the flow direction of the combustion gas than the openings on the downstream, and are arranged so that the arrangement pitch of the openings becomes larger or the opening area of the openings becomes smaller on the downstream in the flow direction of the combustion gas than the openings on the upstream.
摘要翻译：在冷却燃气轮机的环段的环段的冷却系统中，环段的节段主体由具有吹出冷却空气的小孔的碰撞板，被碰撞包围的冷却空间构成板体和主体的主体; 从冷却空间接收冷却空气的第一腔; 以及第一冷却通路，其一端与第一空腔连通，另一端从布置在侧端部的开口吹出冷却空气为燃烧气体; 第一冷却通道的开口被布置成使得开口的排列间距变得更小，或者在燃烧气体的流动方向上游的开口面积比下游的开口更大，并且被布置成在燃烧气体的流动方向的下游，开口的排列间距比上游的开口变大，开口的开口面积变小。

5. 发明授权

US08480353B2 Cooling system of ring segment and gas turbine 有权
标题翻译：环段和燃气轮机的冷却系统
公开(公告)号：US08480353B2
公开(公告)日：2013-07-09
申请号：US12913397
申请日：2010-10-27
申请人： Hidemichi Koyabu , Satoshi Hada , Junichiro Masada , Keizo Tsukagoshi
发明人： Hidemichi Koyabu , Satoshi Hada , Junichiro Masada , Keizo Tsukagoshi
IPC分类号： F04D29/58
CPC分类号： F01D25/246 , F01D9/04 , F01D11/005 , F01D11/24 , F01D25/12 , F05D2240/11 , F05D2260/205
摘要： A cooling system of a ring segment for a gas turbine, which includes first cooling passages disposed in an axial direction of the rotating shaft of a main body of the segment body, second cooling passages disposed at one end portion in a direction approximately perpendicular to the first cooling passages, and blowing a cooling air toward the end portion of a neighboring segment body, and third cooling passages connecting a first cavity, which is disposed approximately perpendicular to the axial direction of the rotating shaft at the upstream-end portion, with a cooling space, which is surrounded by the segment body and a collision plate having a plurality of small holes. The first cooling passages include cooling passages of a first region and a second region having a smaller passage cross-sectional area than the first-region cooling passages or a greater arrangement pitch than the first-region cooling passages.
摘要翻译：一种用于燃气轮机的环段的冷却系统，其包括沿着所述节段主体的主体的轴的轴向设置的第一冷却通道，第二冷却通道，其设置在大致垂直于所述节段主体的方向的一个端部处第一冷却通道，朝向相邻段体的端部吹送冷却空气;以及第三冷却通道，其将在上游侧部分大致垂直于旋转轴的轴向设置的第一空腔与第一空腔连接，冷却空间，其被节段主体包围，具有多个小孔的碰撞板。第一冷却通道包括具有比第一区域冷却通道更小的通道横截面面积的第一区域和第二区域的冷却通道或比第一区域冷却通道更大的排列间距。

6. 发明申请

US20110182724A1 COOLING SYSTEM OF RING SEGMENT AND GAS TURBINE 有权
标题翻译：环形和气体涡轮冷却系统
公开(公告)号：US20110182724A1
公开(公告)日：2011-07-28
申请号：US12913397
申请日：2010-10-27
申请人： Hidemichi Koyabu , Satoshi Hada , Junichiro Masada , Keizo Tsukagoshi
发明人： Hidemichi Koyabu , Satoshi Hada , Junichiro Masada , Keizo Tsukagoshi
IPC分类号： F01D5/08
CPC分类号： F01D25/246 , F01D9/04 , F01D11/005 , F01D11/24 , F01D25/12 , F05D2240/11 , F05D2260/205
摘要： A cooling system of a ring segment for a gas turbine, which includes first cooling passages disposed in an axial direction of the rotating shaft of a main body of the segment body, second cooling passages disposed at one end portion in a direction approximately perpendicular to the first cooling passages, and blowing a cooling air toward the end portion of a neighboring segment body, and third cooling passages connecting a first cavity, which is disposed approximately perpendicular to the axial direction of the rotating shaft at the upstream-end portion, with a cooling space, which is surrounded by the segment body and a collision plate having a plurality of small holes. The first cooling passages include cooling passages of a first region which are disposed adjacent to the end portion on a rear side in a rotation direction, and cooling passages of a second region which are disposed on a farther front side in the rotation direction than the first-region cooling passages and have a smaller passage cross-sectional area than the first-region cooling passages or a greater arrangement pitch than the first-region cooling passages. The first-region cooling passages are disposed adjacent to the second cooling passages of the neighboring segment body.
摘要翻译：一种用于燃气轮机的环段的冷却系统，其包括沿着所述节段主体的主体的轴的轴向设置的第一冷却通道，第二冷却通道，其设置在大致垂直于所述节段主体的方向的一个端部处第一冷却通道，朝向相邻段体的端部吹送冷却空气;以及第三冷却通道，其将在上游侧部分大致垂直于旋转轴的轴向设置的第一空腔与冷却空间，其被节段主体包围，具有多个小孔的碰撞板。第一冷却通路包括第一区域的冷却通道，第一区域与沿着旋转方向的后侧的端部相邻设置，并且第二区域的冷却通道设置在比第一区域的旋转方向更远的前侧并且具有比第一区域冷却通道更小的通道横截面面积或比第一区域冷却通道更大的排列间距。第一区域冷却通道邻近相邻段体的第二冷却通道设置。

7. 发明申请

US20110255989A1 Cooling system of ring segment and gas turbine 有权
标题翻译：环段和燃气轮机的冷却系统
公开(公告)号：US20110255989A1
公开(公告)日：2011-10-20
申请号：US12763723
申请日：2010-04-20
申请人： Hidemichi Koyabu , Satoshi Hada , Junichiro Masada , Keizo Tsukagoshi
发明人： Hidemichi Koyabu , Satoshi Hada , Junichiro Masada , Keizo Tsukagoshi
IPC分类号： F01D5/18
CPC分类号： F02C7/12 , F01D11/24 , F05D2240/11
摘要： In a cooling system of ring segment that cools a ring segment of a gas turbine, the segment body of the ring segment is constituted from a collision plate that has a small hole that blows out cooling air, a cooling space that is enclosed by the collision plate and the main body of the segment body; a first cavity that receives the cooling air from the cooling space; and a first cooling passage, of which one end communicates with the first cavity, and the other end blows out the cooling air from openings that are arranged in the side end portion into combustion gas; the openings of the first cooling passages being arranged so that the arrangement pitch of the openings becomes smaller or the opening area of the openings becomes larger on the upstream in the flow direction of the combustion gas than the openings on the downstream, and are arranged so that the arrangement pitch of the openings becomes larger or the opening area of the openings becomes smaller on the downstream in the flow direction of the combustion gas than the openings on the upstream.
摘要翻译：在冷却燃气轮机的环段的环段的冷却系统中，环段的节段主体由具有吹出冷却空气的小孔的碰撞板，被碰撞包围的冷却空间构成板体和主体的主体; 从冷却空间接收冷却空气的第一腔; 以及第一冷却通路，其一端与第一空腔连通，另一端从布置在侧端部的开口吹出冷却空气为燃烧气体; 第一冷却通道的开口被布置成使得开口的排列间距变得更小，或者在燃烧气体的流动方向上游的开口面积比下游的开口更大，并且被布置成在燃烧气体的流动方向的下游，开口的排列间距比上游的开口变大，开口的开口面积变小。

8. 发明申请

US20100215148A1 SPECIMEN COLLECTING METHOD AND BLADE TEMPERATURE ESTIMATING METHOD 有权
标题翻译：样本收集方法和叶片温度估计方法
公开(公告)号：US20100215148A1
公开(公告)日：2010-08-26
申请号：US12526213
申请日：2008-01-30
申请人： Taiji Torigoe , Masahiro Yamada , Ikuo Okada , Toshio Sakon , Hidetaka Oguma , Takeshi Naito , Koji Takahashi , Soji Kasumi , Keizo Tsukagoshi
发明人： Taiji Torigoe , Masahiro Yamada , Ikuo Okada , Toshio Sakon , Hidetaka Oguma , Takeshi Naito , Koji Takahashi , Soji Kasumi , Keizo Tsukagoshi
IPC分类号： G01N23/20 , B26D1/00
CPC分类号： G01N1/286 , G01N2001/2873 , Y10T83/04
摘要： In a specimen collecting method according to the present invention, a specimen is collected from a surface (114a) of a blade. An ultrasonic cutter having a cylindrical cutting blade is fed from the surface (114a) of the blade to a surface (110a) of a base material (100), and thus, a cylindrical incision is formed. After performing cutting to expand the incision outwardly, a rotating cutter (220) having a disc-shaped cutting blade (222) performs cutting inwardly from the cylindrical incision. Thus, a part (20a) situated inside the incision is cut away. The part (20a) becomes the specimen.
摘要翻译：在根据本发明的样本收集方法中，从叶片的表面（114a）收集样本。具有圆柱形切割刀片的超声波切割器从叶片的表面（114a）进给到基材（100）的表面（110a），从而形成圆柱形切口。在执行切割以向外扩张切口之后，具有盘形切割刀片（222）的旋转切割器（220）从圆柱形切口向内切割。因此，位于切口内部的部分（20a）被切除。部件（20a）成为样品。

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.

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