公开(公告)号：US20110123351A1

公开(公告)日：2011-05-26

申请号：US12644633

申请日：2009-12-22

申请人： Satoshi Hada ,  Keizo Tsukagoshi

发明人： Satoshi Hada ,  Keizo Tsukagoshi

IPC分类号： F01D5/18

CPC分类号： F01D5/189 ,  F05D2240/12 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/30

摘要： An airfoil part includes a plurality of cooling chambers that are spaces into which the inside of the airfoil part is partitioned, from a leading edge side to a trailing edge side, by a partition wall, that extend in a vane-longitudinal-section direction, and that include division parts on inner walls of a body; insert cylinders that are disposed in the cooling chambers and that have a plurality of impingement holes; and film holes that are provided in the body. The insert cylinders include partitioning parts that extend from the leading edge side to the trailing edge side and that extend in the vane-longitudinal-section direction. The insides of the insert cylinders are partitioned into pressure-surface-side insert spaces close to a pressure surface and suction-surface-side insert spaces close to a suction surface.

摘要翻译： 机翼部包括多个冷却室，所述多个冷却室是通过沿着叶片纵向方向延伸的分隔壁将翼型部的内部从前缘侧到后缘侧隔开的空间， 并且包括在身体的内壁上的分隔部分; 插入设置在冷却室中并具有多个冲击孔的圆柱体; 以及设置在身体中的胶片孔。 插入圆筒包括从前缘侧延伸到后缘侧并且沿叶片纵向方向延伸的分隔部。 插入圆筒的内部被分隔成靠近压力表面的压力表面侧插入空间和靠近抽吸表面的吸入表面侧插入空间。

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。

公开(公告)号：US08662844B2

公开(公告)日：2014-03-04

申请号：US12644633

申请日：2009-12-22

申请人： Satoshi Hada ,  Keizo Tsukagoshi

发明人： Satoshi Hada ,  Keizo Tsukagoshi

IPC分类号： F01D5/18

CPC分类号： F01D5/189 ,  F05D2240/12 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/30

摘要： An airfoil part includes a plurality of cooling chambers that are spaces into which the inside of the airfoil part is partitioned, from a leading edge side to a trailing edge side, by a partition wall, that extend in a vane-longitudinal-section direction, and that include division parts on inner walls of a body; insert cylinders that are disposed in the cooling chambers and that have a plurality of impingement holes; and film holes that are provided in the body. The insert cylinders include partitioning parts that extend from the leading edge side to the trailing edge side and that extend in the vane-longitudinal-section direction. The insides of the insert cylinders are partitioned into pressure-surface-side insert spaces close to a pressure surface and suction-surface-side insert spaces close to a suction surface.

摘要翻译： 机翼部包括多个冷却室，所述多个冷却室是通过沿着叶片纵向方向延伸的分隔壁将翼型部的内部从前缘侧到后缘侧隔开的空间， 并且包括在身体的内壁上的分隔部分; 插入设置在冷却室中并具有多个冲击孔的圆柱体; 以及设置在身体中的胶片孔。 插入圆筒包括从前缘侧延伸到后缘侧并且沿叶片纵向方向延伸的分隔部。 插入圆筒的内部被分隔成靠近压力表面的压力表面侧插入空间和靠近抽吸表面的吸入表面侧插入空间。

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％。

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。

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。

公开(公告)号：US6141957A

公开(公告)日：2000-11-07

申请号：US214928

申请日：1999-09-17

申请人： Keizo Tsukagoshi ,  Satoshi Tanimura ,  Katsuhiko Abe

发明人： Keizo Tsukagoshi ,  Satoshi Tanimura ,  Katsuhiko Abe

IPC分类号： F02C7/26 ,  F02C7/00 ,  F02C9/00 ,  F23M11/04 ,  F23N5/08 ,  F23R3/00 ,  F02G1/00

CPC分类号： F23N5/08 ,  F23M11/045 ,  F23N2029/18

摘要： In a starter combustor of a pressurized fluidized bed combined cycle power system, disorder of a flame detecting device due to ash accumulation is prevented. A fuel nozzle (33) of the starter combustor is provided so as to be directed to an inner cylinder (32) and a pipe (38) of a fitting pipe (36), which is connected to the inner cylinder (32). A valve body (1), having a valve body passage (1a), is provided so as to be connected to one end of the fitting pipe (36) and a valve component (3). The valve component (3) has a recess portion 3a and is connected to a shaft (1a) . When the combustor is started, the shaft (2), which is engaged rotatably with shaft fitting portion (3a') of the valve component (3) and is in threaded engagement with a threaded portion of the valve body (1), is moved by handle (4) so that the valve component is moved and the passage (1a) is opened. While the combustor is stopped, the passage (1a) is closed by the valve component (3). In ordinary operation time, ash is collected in the recess portion (3a) of the valve component (3), and therefore ash does not accumulate on a glass plate (37) and disorder of the flame detecting device due to ash accumulation does not occur.

摘要翻译： PCT No.PCT / JP98 / 02114 Sec。 371 1999年9月17日第 102（e）1999年9月17日PCT PCT提交1998年5月13日PCT公布。 公开号WO98 / 53254 日期1998年11月26日在加压流化床联合循环动力系统的起动机燃烧器中，防止了由于灰分积聚引起的火焰检测装置的混乱。 起动器燃烧器的燃料喷嘴（33）设置成与内筒（32）和连接到内筒（32）的配管（36）的管（38）相连。 具有阀体通道（1a）的阀体（1）设置成连接到配管（36）的一端和阀部件（3）。 阀部件（3）具有凹部3a并与轴（1a）连接。 当燃烧器启动时，与阀部件（3）的轴嵌合部分（3a'）可旋转并与阀体（1）的螺纹部分螺纹接合的轴（2）被移动 通过手柄（4）使得阀部件移动并且通道（1a）打开。 当燃烧器停止时，通道（1a）被阀门部件（3）关闭。 在通常的运转时间内，灰分被收集在阀部件（3）的凹部（3a）中，因此灰尘不积聚在玻璃板（37）上，并且不会发生由于灰分积聚引起的火焰检测装置的混乱 。

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。

公开(公告)号：US20110142597A1

公开(公告)日：2011-06-16

申请号：US12596224

申请日：2009-04-23

申请人： Keizo Tsukagoshi ,  Tomoko Hashimoto ,  Satoshi Hada

发明人： Keizo Tsukagoshi ,  Tomoko Hashimoto ,  Satoshi Hada

IPC分类号： F01D9/02

CPC分类号： F01D5/16 ,  F01D5/188 ,  F05D2260/94 ,  F05D2260/941

摘要： Provided is a turbine blade structure that is capable of suppressing quality variations of cast products during the manufacturing of turbine blades. A turbine blade structure wherein the space inside an air foil is divided into a plurality of cavities, partitioned by rib members provided substantially perpendicular to the center line connecting a leading edge and a trailing edge, is provided with partition members that partition the inside of the cavities located in the central portion of the blade, excluding the blade leading-edge side and the blade trailing-edge side, into blade pressure side cavities and blade suction side cavities substantially along the center line, wherein blade leading-edge end portions and blade trailing-edge end portions of the partition members are inserted from one shroud surface side to the other shroud surface side along engagement grooves formed on the rib members.

摘要翻译： 提供一种涡轮叶片结构，其能够抑制在涡轮叶片的制造期间铸造产品的质量变化。 一种涡轮叶片结构，其中，空气箔内的空间被分成多个空腔，所述多个空腔由基本上垂直于连接前缘和后缘的中心线设置的肋构件分隔开，分隔构件分隔 位于叶片的中心部分的除了叶片前缘侧和叶片后缘侧之外的空腔基本上沿着中心线分成叶片压力侧空腔和叶片吸入侧空腔，其中叶片前缘端部和叶片 分隔构件的后缘端部沿着形成在肋构件上的接合槽从一个护罩表面侧插入另一个护罩表面侧。

公开(公告)号：US20100150734A1

公开(公告)日：2010-06-17

申请号：US12633842

申请日：2009-12-09

申请人： Satoshi Hada ,  Tomoko Hashimoto ,  Masanori Yuri ,  Keizo Tsukagoshi

发明人： Satoshi Hada ,  Tomoko Hashimoto ,  Masanori Yuri ,  Keizo Tsukagoshi

IPC分类号： F01D5/18

CPC分类号： F01D5/188 ,  F01D5/189 ,  F05D2240/126 ,  F05D2240/306 ,  F05D2260/201 ,  F05D2260/202

摘要： In a turbine blade in which a tabular rib partitioning the blade into a pressure side and a suction side is provided in substantially the midsection of the blade along a center line connecting a leading edge and a trailing edge, and at least two cavities of which a cavity at the suction side and a cavity at the pressure side do not communicate with each other are provided, a pressure adjustment member for cooling air flowing into and out of the cavity at the suction side reduces the amount of cooling air flowing into the suction side, relative to the pressure side.

摘要翻译： 在涡轮机叶片中，其中沿着连接前缘和后缘的中心线将叶片分隔成压力侧和吸力侧的片状肋在叶片的大致中央部分中设置，并且其中至少两个空腔 设置吸入侧的空腔和压力侧的空腔不相通，用于冷却在吸入侧流入和流出空气的空气的压力调节构件减少流入吸入侧的冷却空气量 ，相对于压力侧。