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1. 发明专利

JP2009299192A Heat resistant member having thermal barrier coating and gas turbine 有权
标题翻译：具有热障涂层和气体涡轮的耐热构件
公开(公告)号：JP2009299192A
公开(公告)日：2009-12-24
申请号：JP2009218458
申请日：2009-09-24
申请人： Central Res Inst Of Electric Power Ind , Hitachi Ltd , 株式会社日立製作所 , 財団法人電力中央研究所
发明人： ARIKAWA HIDEYUKI , MEHATA TERU , KOJIMA YOSHIYUKI , ICHIKAWA KUNIHIRO , YOSHIOKA TAKAYUKI , OKADA MITSUTOSHI , HISAMATSU NOBORU
IPC分类号： C23C4/06 , C23C4/10 , C23C28/00 , F01D5/28 , F01D25/00 , F02C7/00
CPC分类号： Y02T50/67
摘要： PROBLEM TO BE SOLVED: To provide a heat resistant member provided with a thermal barrier coating which has excellent durability and usable, e.g. for a gas turbine and an aircraft engine having extremely high driving temperature. SOLUTION: In the heat resistant member, a thermal barrier layer 3 composed of ceramics via a bonding layer 2 of an alloy substantially consisting of at least one selected from Ni and Co, Cr and Al is provided on the surface of a heat resistant alloy base material 1 essentially consisting of at least one selected from Ni and Co. The alloy in the bonding layer can comprise at least one selected from the group consisting Ta, W, Si, Pt, Mn and B in the range of 0 to 20 wt.%. In the heat resistant member, the durability of the thermal barrier ceramic layer is extremely excellent, and its peeling damage is hard to occur. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种耐热构件，其设置有耐热性优异的耐热性涂层，例如耐热性。对于具有极高驱动温度的燃气轮机和飞机发动机。解决方案：在耐热构件中，通过基本上由选自Ni和Co，Cr和Al中的至少一种的合金的接合层2的陶瓷构成的热障层3设置在热表面上基本上由选自Ni和Co中的至少一种的耐碱合金基材1组成。接合层中的合金可以包括选自Ta，W，Si，Pt，Mn和B中的至少一种，其范围为0至 20重量％。在耐热构件中，热障陶瓷层的耐久性极好，难以发生剥离损伤。版权所有（C）2010，JPO＆INPIT

2. 发明专利

JP2006097042A Heat resistant member having thermal barrier coating and gas turbine 有权
标题翻译：具有热障涂层和气体涡轮的耐热构件
公开(公告)号：JP2006097042A
公开(公告)日：2006-04-13
申请号：JP2004281377
申请日：2004-09-28
申请人： Central Res Inst Of Electric Power Ind , Hitachi Ltd , 株式会社日立製作所 , 財団法人電力中央研究所
发明人： ARIKAWA HIDEYUKI , MEHATA TERU , KOJIMA YOSHIYUKI , ICHIKAWA KUNIHIRO , YOSHIOKA TAKAYUKI , OKADA MITSUTOSHI , HISAMATSU NOBORU
IPC分类号： C23C4/06 , C22C19/00 , C23C4/10 , C23C28/00 , F01D5/28 , F02C7/00
CPC分类号： C23C28/321 , C23C28/3215 , C23C28/345 , C23C28/3455 , F01D5/288 , F05D2230/90 , F05D2300/611 , Y02T50/67 , Y02T50/671 , Y10T428/12611 , Y10T428/12618 , Y10T428/12847 , Y10T428/12931 , Y10T428/12937 , Y10T428/12944
摘要： PROBLEM TO BE SOLVED: To provide a heat resistant member provided with a thermal barrier coating which has excellent durability and usable, e.g., for a gas turbine and an aircraft engine having extremely high driving temperature. SOLUTION: In the heat resistant member, the surface of a heat resistant alloy base material 1 essentially consisting of at least one selected from Ni and Co is provided with a thermal barrier layer 3 composed of ceramics via a bonding layer of an alloy substantially consisting of at least one selected from Ni and Co, Cr and Al. The alloy in the bonding layer can comprise at least one kind selected from the group consisting of Ta, Cs, W, Si, Pt, Mn and B in the range of 0 to 20 wt.%. In the heat resistant member, the durability of the thermal barrier ceramic layer is extremely excellent, and its peeling damage is hard to occur. COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供一种耐热构件，该耐热构件具有优异的耐久性和可用的热障涂层，例如用于具有极高驱动温度的燃气轮机和飞机发动机。解决方案：在耐热构件中，基本上由选自Ni和Co中的至少一种的耐热合金基材1的表面设置有由陶瓷经由合金的接合层构成的热障层3 基本上由选自Ni和Co，Cr和Al中的至少一种组成。接合层中的合金可以包含0至20重量％范围内的选自Ta，Cs，W，Si，Pt，Mn和B中的至少一种。在耐热构件中，隔热陶瓷层的耐久性非常优异，并且难以发生剥离损伤。版权所有（C）2006，JPO＆NCIPI

3. 发明专利

JP2012137073A Gas turbine component having thermal barrier coating and gas turbine using the component 有权
标题翻译：使用组件的具有热障涂层和气体涡轮的气体涡轮机组件
公开(公告)号：JP2012137073A
公开(公告)日：2012-07-19
申请号：JP2010291548
申请日：2010-12-28
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： ARIKAWA HIDEYUKI , MEHATA TERU , KOJIMA YOSHIYUKI , ICHIKAWA KUNIHIRO , HARUYAMA HIROSHI
IPC分类号： F01D5/28 , C23C26/00 , F01D25/24 , F02C3/24 , F02C7/00 , F23R3/42
CPC分类号： C23C28/04 , C23C28/042 , C23C28/046 , C23C28/048 , F01D5/288 , Y02T50/67 , Y02T50/671
摘要： PROBLEM TO BE SOLVED: To provide gas turbine components having durability and reliability for use in a corrosive environment such as a turbine employing a low grade fuel, and also to provide a gas turbine equipped with the components.SOLUTION: A gas turbine rotor/stator vane includes: a substrate made from an alloy containing Ni, Co, or Fe; a bonding layer made from an alloy and disposed over the substrate; and a thermal barrier coating disposed over the bonding layer. The thermal barrier coating includes: a thermal barrier layer of porous ceramics; an environmental barrier layer containing silica; and an impregnation layer having a silica-containing material in the pores of the porous ceramics.
摘要翻译：要解决的问题：提供具有耐久性和可靠性的燃气轮机部件，其用于腐蚀性环境，例如使用低等级燃料的涡轮机，并且还提供配备有部件的燃气轮机。燃气轮机转子/定子叶片包括：由含有Ni，Co或Fe的合金制成的基体; 由合金制成并设置在所述基板上的接合层; 以及设置在结合层上的热障涂层。热障涂层包括：多孔陶瓷的热障层; 含有二氧化硅的环境阻挡层; 以及在多孔陶瓷的孔中具有含二氧化硅的材料的浸渍层。版权所有（C）2012，JPO＆INPIT

4. 发明专利

JP2012073126A Evaluation method and device for crack evolution velocity of metallic material 有权
标题翻译：金属材料裂纹演化速度的评估方法和装置
公开(公告)号：JP2012073126A
公开(公告)日：2012-04-12
申请号：JP2010218447
申请日：2010-09-29
申请人： Hitachi Ltd , Kyushu Electric Power Co Inc , 九州電力株式会社 , 株式会社日立製作所
发明人： KONNO SHINYA , ICHIKAWA KUNIHIRO , SATO JUN , KANETANI AKIHIRO , WATANABE HAJIME , KUSUMOTO JUNICHI
IPC分类号： G01N23/20 , G01N17/00
摘要： PROBLEM TO BE SOLVED: To evaluate crack evolution velocity of metallic material with high accuracy and to evaluate remaining life as well.SOLUTION: The evaluation method for crack evolution velocity of metallic material of the present invention comprises: a measurement step (S2) for measuring crystal orientation at multiple measurement points in a region including a tip of crack in a sample formed of metallic material by an EBSP method; an analysis step (S3) for analyzing a misorientation function value indicating deviation of the crystal orientation at each measurement point to acquire an evaluation parameter of the sample; and evaluation steps (S4, S5) for evaluating the crack evolution velocity of the sample based on the evaluation parameter of the sample acquired by the analysis at the analysis step, by referring to correlation between a crack evolution velocity and an evaluation parameter acquired from another sample which is formed of the same kind of metallic material as the sample and whose crack evolution velocity is known since a crack evolution test is performed in advance.
摘要翻译：要解决的问题：以高精度评估金属材料的裂纹演化速度，并评估剩余寿命。解决方案：本发明的金属材料的裂纹扩展速度的评价方法包括：测量步骤（S2），用于测量由金属材料形成的样品中的包括裂纹尖端的区域中的多个测量点处的晶体取向通过EBSP方法; 分析步骤（S3），用于分析指示每个测量点处的晶体取向的偏差的取向函数值，以获取样本的评估参数; 以及评估步骤（S4，S5），用于基于通过分析步骤中的分析获得的样本的评估参数，通过参考裂纹演化速度和从另一个获取的评估参数之间的相关性来评估样品的裂纹演变速度样品由与样品相同种类的金属材料形成，并且由于进行裂纹扩展试验，所以其已知的裂纹扩展速度是已知的。版权所有（C）2012，JPO＆INPIT

5. 发明专利

JP2011163184A Outlet blade cascade of gas turbine compressor 审中-公开
标题翻译：气体涡轮压缩机出口叶片
公开(公告)号：JP2011163184A
公开(公告)日：2011-08-25
申请号：JP2010025741
申请日：2010-02-08
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： ENDO TAKAO , ICHIKAWA KUNIHIRO , MOMOZAKI HISATAKA , AKUTSU HIROYUKI
IPC分类号： F04D29/52
摘要： PROBLEM TO BE SOLVED: To provide an outlet blade cascade of a gas turbine compressor capable of suppressing the wear of a fitting portion of a stator blade cascade in the compressor.
SOLUTION: The outlet blade cascade 3 of the gas turbine compressor 57 includes an outer ring 5 inserted in a turbine circumferential direction and fitted in the inner peripheral part of a turbine casing 1, an inner ring 7 inserted in the turbine circumferential direction and fitted in a recessed groove 11 of an inner barrel 4 enclosing a turbine rotating shaft, a plurality of stator blades 6 connected at a tip side to the outer ring 5 and at a root side to the inner ring 7, and a spacer 14 provided between the turbine casing 1 and the outer ring 5 and formed of a material higher in the coefficient of thermal expansion than the outer ring 5.
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供能够抑制压缩机中定子叶片级联的装配部分的磨损的燃气轮机压缩机的出口叶片级联。解决方案：燃气轮机压缩机57的出口叶片级联3包括以涡轮机圆周方向插入并装配在涡轮机壳体1的内周部分中的外环5，插入涡轮机圆周方向的内环7 并且装配在封装有涡轮机转轴的内筒4的凹槽11中，多个定子叶片6在前端侧连接到外圈5并且在根部侧连接到内圈7，并且设置有间隔件14 在涡轮壳体1和外环5之间并且由比外环5更高的热膨胀系数的材料形成。版权所有（C）2011，JPO＆INPIT

6. 发明专利

JP2011132565A Heat-resistant alloy coating film forming method, and composite powder for use in the same 有权
标题翻译：耐热合金涂膜成型方法及其使用的复合粉末
公开(公告)号：JP2011132565A
公开(公告)日：2011-07-07
申请号：JP2009291701
申请日：2009-12-24
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： ARIKAWA HIDEYUKI , MEHATA TERU , KOJIMA YOSHIYUKI , ICHIKAWA KUNIHIRO
IPC分类号： C23C24/04 , B22F1/00 , B22F1/02 , F01D5/28 , F01D9/02 , F01D25/00 , F02C7/00 , F23R3/42
摘要： PROBLEM TO BE SOLVED: To provide a low-heat input and inexpensive method for manufacturing and repairing a heat-resistant member by enabling the film of a nickel and cobalt-based heat-resistant alloy to be inexpensively and highly efficiently deposited by the cold spray.
SOLUTION: A heat-resistant alloy coating film is deposited by a method including a step of selecting a plurality of kinds of metal powder having the composition to be selected from among elements constituting a heat-resistant alloy, and selected so that its total becomes the composition of the heat-resistant alloy, a step of forming a mixed coating film of the plurality of kinds of metal powder on a metal base body by forming a supersonic gas flow kept at the temperature at which particles of the plurality of kinds of metal powder are not melt, charging the plural kinds of metal powder in the supersonic gas flow, and colliding the powder particles with the base body at the supersonic speed, and a heat treatment step of applying heat treatment to the metal base body on which the mixed coating film comprising the plural kinds of metal powder is formed, obtaining a targeted deposit layer of the heat-resistant alloy by homogenizing and alloying the deposit layer, and firmly bonding the metal base body and the coating film to each other by generating the dispersion therebetween.
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：为了通过使镍和钴基耐热合金的膜能够通过以下方式廉价且高效地沉积，提供低热输入和廉价的制造和修复耐热构件的方法：冷喷。解决方案：通过包括选择多种金属粉末的方法来沉积耐热合金涂膜，所述金属粉末具有从构成耐热合金的元素中选择的组成，并选择为总计成为耐热合金的组成，通过形成保持在多种颗粒的温度的超音速气流，在金属基体上形成多种金属粉末的混合涂膜的步骤的金属粉末不熔化，在超音速气流中填充多种金属粉末，并以超音速与粉末颗粒物质碰撞，以及对金属基体进行热处理的热处理工序，形成包含多种金属粉末的混合涂膜，通过使沉积层均质化和合金化，获得耐热合金的靶向沉积层，并将金属基体和涂膜彼此之间产生分散。版权所有（C）2011，JPO＆INPIT

7. 发明专利

JP2006214671A Gas turbine combustor 有权
标题翻译：气体涡轮搅拌机
公开(公告)号：JP2006214671A
公开(公告)日：2006-08-17
申请号：JP2005029145
申请日：2005-02-04
申请人： Chugoku Electric Power Co Inc:The , Hitachi Ltd , 中国電力株式会社 , 株式会社日立製作所
发明人： KOJIMA YOSHIYUKI , ICHIKAWA KUNIHIRO , CHIYONOBU KYOTA , SHINTANI SHIZUMA , NISHIDA HIDETAKA , WADA YASUTAKA , NITTA TSUTOMU , NAGAHISA TAKAYA
IPC分类号： F23R3/42 , C23C4/10 , F02C7/00 , F02C7/28
CPC分类号： F01D9/023 , F01D11/003 , F05D2230/90 , F05D2240/57 , F05D2300/2118
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustor free from separation and dropping of an abrasion-proof material, and keeping sealing effect for a long period. SOLUTION: A spring seal material 4 and floating seal materials 9A, 9B are mounted in a state of being respectively engaged with connecting portions of a combustor liner 1, a transition piece 2 and a stator vane 11 of a gas turbine, the seal materials and counterpart members 2 slid to the seal materials are composed of cobalt alloy material, ZrO 2 sprayed coatings are formed on sliding faces of the seal materials and the counterpart members made of the cobalt alloy material as foundation layers 18, and an Al oxide sprayed coating is formed as a surface layer 19 on the foundation layer. Further, coating layers 17 of sprayed coating composed of NiCr alloy or MCrAlY (M is Co or Ni) alloy are respectively formed between the seal material and the opposition-side member, and the foundation layer. COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供一种没有耐磨材料分离和滴落的燃气轮机燃烧器，并且长时间保持密封效果。解决方案：弹簧密封材料4和浮动密封材料9A，9B以与燃气轮机的燃烧器衬套1，过渡件2和定子叶片11的连接部分分别接合的状态安装，密封材料和对应构件2滑动到密封材料由钴合金材料组成，ZrO 2 喷涂涂层形成在密封材料的滑动面和由钴合金材料制成的对应构件的基础上层18，并且在基底层上形成作为表面层19的Al氧化物喷涂涂层。此外，分别在密封材料和对置侧构件之间分别形成由NiCr合金或MCrAlY（M为Co或Ni）合金构成的喷涂层的涂层17和基础层。版权所有（C）2006，JPO＆NCIPI

8. 发明专利

JP2005180257A Heat resistant member including heat shield coating 有权
标题翻译：耐热构件，包括热风涂层
公开(公告)号：JP2005180257A
公开(公告)日：2005-07-07
申请号：JP2003420281
申请日：2003-12-18
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： ARIKAWA HIDEYUKI , MEHATA TERU , KOJIMA YOSHIYUKI , ICHIKAWA KUNIHIRO
IPC分类号： F01D5/28 , B05D1/08 , B32B15/04 , C23C4/02 , C23C4/08 , C23C4/10 , C23C28/00 , F02C7/00 , H05H1/26
CPC分类号： C23C28/3215 , C23C4/02 , C23C28/3455 , Y02T50/67 , Y10T428/12611 , Y10T428/12861 , Y10T428/12944 , Y10T428/24997 , Y10T428/26 , Y10T428/263
摘要： PROBLEM TO BE SOLVED: To provide heat shield coating and a heat resistant member provided with the heat shield coating excellent in heat resistance and durability at a time of long time operation capable of being used for a heat resistant member of a gas turbine or an aircraft engine of which operation temperature is very high. SOLUTION: This heat shield coating is composed of a bonding layer 12 made of alloy excellent in high temperature corrosion and oxidation resistance as compared with base material on a surface of heat resistant alloy base material 11 containing Ni and Co as principle component and a heat shield layer 13 made of ZrO 2 based ceramics formed on the bonding layer 12. The heat shield layer includes a plurality of cracks 14 extending in a direction of coating thickness toward base material side from a coating surface. Distance L between base material side tips of all cracks extending in the thickness direction and a base material side boundary of the coating is in a range 10-100μm. COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：提供隔热涂层和耐热构件，该耐热构件设置有能够被用于燃气轮机的耐热构件的长时间操作时耐热性和耐久性优异的隔热涂层或工作温度非常高的飞机发动机。解决方案：该隔热涂层由与Ni和Co作为主要成分的耐热合金基材11表面的基材相比，由耐高温腐蚀和耐氧化性优异的合金制成的接合层12组成，形成在接合层12上的由ZrO 2 SBS系陶瓷制成的隔热层13.隔热层包括多个裂纹14，沿着涂层厚度方向从基材侧向涂层表面延伸。在厚度方向上延伸的所有裂缝的基材侧尖端和涂层的基材侧边界之间的距离L在10-100μm的范围内。版权所有（C）2005，JPO＆NCIPI

9. 发明专利

JP2004185334A Components managing device, its method, its recording medium, and its program 审中-公开
公开(公告)号：JP2004185334A
公开(公告)日：2004-07-02
申请号：JP2002351896
申请日：2002-12-04
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： SHIROYAMA KOJI , MINAMI SHUNSUKE , ISHIDA TOMOTOSHI , KOJIMA YOSHIYUKI , ICHIKAWA KUNIHIRO
IPC分类号： G05B19/418 , G06Q50/00 , G06Q50/04 , G06F17/60
CPC分类号： Y02P90/30
摘要： PROBLEM TO BE SOLVED: To provide a components managing device capable of reducing the input man-hours of components arrival history data by managing a life cycle from the manufacturing of components to their abandonment. SOLUTION: This component managing device is provided with a product configuration compiling part for inputting and compiling product configurations expressing components configuring a product and a sub-assembly, an arrival history inputting part for inputting the arrival history of the product or the sub-assembly, and a component arrival history preparing part for preparing the component arrival history data expressing the arrival history of respective components configuring the product from the product configuration data inputted and compiled by the product configuration compiling part and the arrival history data inputted by the arrival history inputting part. COPYRIGHT: (C)2004,JPO&NCIPI

10. 发明专利

JP2004150700A Gas turbine facility 有权
标题翻译：气体涡轮机设施
公开(公告)号：JP2004150700A
公开(公告)日：2004-05-27
申请号：JP2002315926
申请日：2002-10-30
申请人： Hitachi Engineering & Services Co Ltd , Hitachi Ltd , 株式会社日立エンジニアリングサービス , 株式会社日立製作所
发明人： ENDO TAKAO , ICHIKAWA KUNIHIRO , MOMOZAKI HISATAKA
IPC分类号： F23R3/42
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine facility capable of preventing early wear of a seal member by easily repairing change of a gap between a combustion gas outlet of a transition piece and a combustion gas inlet of a turbine part.
SOLUTION: The gas turbine facility 1 is composed so that the gaps K and L are provided in an opposing part of the combustion gas outlet 13 of the transition piece 5B and the combustion gas inlet 14 of the turbine part 2, and the gaps K and L are sealed by the seal members 21 and 22. A displacement adjusting means 28 is provided for adjusting displacements of the gaps between the transition piece 5 and the turbine part 2.
COPYRIGHT: (C)2004,JPO
摘要翻译：解决的问题：提供一种能够通过容易地修复过渡件的燃烧气体出口与涡轮机部件的燃烧气体入口之间的间隙的变化来防止密封构件的早期磨损的燃气轮机设备。解决方案：燃气轮机设备1被构成为使得间隙K和L设置在过渡件5B的燃烧气体出口13和涡轮部分2的燃烧气体入口14的相对部分中，并且间隙K和L被密封构件21和22密封。设置位移调节装置28，用于调节过渡件5和涡轮部分2之间的间隙的位移。版权所有（C）2004，JPO

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