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1. 发明授权

EP2354276B1 GAS TURBINE SHROUD WITH CERAMIC ABRADABLE COATINGS 有权转让
标题翻译：与环绕耐磨陶瓷涂层燃气轮机
公开(公告)号：EP2354276B1
公开(公告)日：2016-10-12
申请号：EP11151974.0
申请日：2011-01-25
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Kojima, Yoshitaka , Arikawa, Hideyuki , Mebata, Akira , Kasuya, Tadashi , Doi, Hiroyuki , Ichikawa, Kunihiro
IPC分类号： C23C28/00 , F01D11/08
CPC分类号： C23C28/00 , F01D11/122 , F05D2230/90 , F05D2240/11 , F05D2250/181 , F05D2300/21

2. 发明公开

EP2813671A1 Gas turbine with honeycomb seal 审中-公开
标题翻译： Gasturbine mit Wabendichtung
公开(公告)号：EP2813671A1
公开(公告)日：2014-12-17
申请号：EP14170172.2
申请日：2014-05-28
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Arikawa, Hideyuki , Kasuya, Tadashi , Kojima, Yoshitaka , Watanabe, Yasuyuki , Murakata, Tadashi , Ichikawa, Kunihiro , Konrai, Takumi
IPC分类号： F01D11/12
CPC分类号： F01D11/127 , F05D2250/283
摘要： A gas turbine 100 includes a compressor 10, a combustor 20, and a turbine 30 with a honeycomb seal 7 disposed so as to be secured to a casing side in a clearance between the casing 1 and turbine blades 5A-5C rotating around a rotating shaft 4 extending in a longitudinal direction of the casing 1 and a seal fin 6 provided on an end face of each of the turbine blades 5A - 5C facing the honeycomb seal 7, the seal fin 6 extending in a direction perpendicular to the rotating shaft 4. The honeycomb seal 7 is formed by a plurality of corrugated thin metal sheets 71 overlapped with each other at walls of node 71a thereof and the walls of node 71 brazed with each other, each of the corrugated thin metal sheets 71 having trapezoids alternately continued. A longer direction (Y1 direction) of the wall of node 71a of the honeycomb seal 7 is tilted with respect to the rotational direction (Z direction) of the turbine blades 5A - 5C.
摘要翻译：燃气轮机100包括压缩机10，燃烧器20和具有蜂窝密封件7的涡轮机30，蜂窝密封件7被设置成在壳体1和围绕旋转轴线旋转的涡轮机叶片5A-5C之间的间隙中固定到壳体侧 4和设置在面对蜂窝密封件7的涡轮机叶片5A-5C的端面上的密封翅片6，密封翅片6沿垂直于旋转轴4的方向延伸。蜂窝状密封件7由在其节点71a的壁处彼此重叠的多个波纹状薄金属片71和彼此钎焊的节点71的壁形成，每个具有梯形的波纹状薄金属片71交替连续。蜂窝密封件7的节点71a的壁的长方向（Y1方向）相对于涡轮叶片5A-5C的旋转方向（Z方向）倾斜。

3. 发明授权

EP2434102B1 Gas turbine shroud with ceramic abradable layer 有权转让
标题翻译：燃气涡轮护罩与陶瓷可磨耗层
公开(公告)号：EP2434102B1
公开(公告)日：2016-10-26
申请号：EP11183071.7
申请日：2011-09-28
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Kojima, Yoshitaka , Arikawa, Hideyuki , Mebata, Akira , Kasuya, Tadashi , Doi, Hiroyuki , Ichikawa, Kunihiro , Endo, Takao , Mikazuki, Kazuto , Kuroki, Hidetoshi
IPC分类号： F01D11/12
CPC分类号： F01D11/122 , F05D2230/311 , F05D2240/11 , F05D2300/514 , F05D2300/522 , Y10T29/49323

4. 发明公开

EP2808418A2 Method for manufacturing gas turbine blade, and gas turbine blade 有权转让
标题翻译：一种用于制造涡轮机叶片和燃气涡轮叶片的过程
公开(公告)号：EP2808418A2
公开(公告)日：2014-12-03
申请号：EP14170194.6
申请日：2014-05-28
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Izumi, Takeshi , Arikawa, Hideyuki , Kojima, Yoshitaka , Mebata, Akira , Kasuya, Tadashi , Imano, Shinya , Miyamoto, Koji
IPC分类号： C23C10/48 , C23C10/36 , F01D5/18 , F01D5/28
CPC分类号： C23C10/04 , B22D21/025 , B23P15/02 , C23C10/48 , C23C10/60 , F01D5/18 , F01D5/187 , F01D5/288 , F05D2230/211 , Y10T29/49337 , Y10T29/49341
摘要： This method is a method for manufacturing a gas turbine blade, including:
producing a gas turbine blade having a cooling pass inside thereof (S1); and
partially coating an inner surface S of the cooling pass P with Al.
The step of partially coating an inner surface S of the cooling pass P with Al further including:
a first step (S4) of specifying a temperature range which satisfies both of oxidation resistance and fatigue strength and the temperature distribution of the inner surface of the cooling pass based on an examination result or result of a numerical analysis;
a second step (S5) of setting an Al-coating-applying portion of the inner surface of the cooling pass P as the temperature range specified at the first step; and
a third step of applying Al coating only into the set Al-coating-applying portion (S6).

5. 发明公开

EP2684976A3 Thermal barrier coating for industrial gas turbine blade, and Industrial gas turbine using the same 有权转让
标题翻译：热障涂层的工业燃气涡轮叶片，和工业燃气轮机顺序
公开(公告)号：EP2684976A3
公开(公告)日：2014-11-26
申请号：EP13175928.4
申请日：2013-07-10
申请人： Mitsubishi Hitachi Power Systems, Ltd. , National University Corporation Hokkaido University
发明人： Izumi, Takeshi , Arikawa, Hideyuki , Kojima, Yoshitaka , Mebata, Akira , Kasuya, Tadashi , Narita, Toshio
IPC分类号： C23C10/00 , C23C28/00 , C23C10/02 , C23C10/38 , C23C10/60 , F01D5/28
CPC分类号： F01D5/288 , C23C10/00 , C23C10/02 , C23C10/38 , C23C10/60 , C23C28/00 , C23C28/321 , C23C28/3215 , C23C28/325 , C23C28/3455 , C23C28/42 , F05D2300/10 , Y02T50/672 , Y10T428/12618
摘要： Disclosed is a turbine blade for an industrial gas turbine including a blade substrate; a multilayer alloy coating containing a diffusion barrier layer; a bond coat; and a top coat, the blade substrate being formed of a single crystal alloy which consists essentially of 0.06 to 0.08% of C, 0.016 to 0.035% of B, 0.2 to 0.3% of Hf, 6.9 to 7.3% of Cr, 0.7 to 1.0% of Mo, 7.0 to 9.0% of W, 1.2 to 1.6% of Re, 8.5 to 9.5% of Ta, 0.6 to 1.0% of Nb, 4.9 to 5.2% of Al, 0.8 to 1.2% of Co, and the balance being Ni and incidental impurities by weight, the multilayer alloy coating, the bond coat and the top coat being directly and sequentially laminated on a surface of the blade substrate, in which the diffusion barrier layer is a multilayer and a discontinuous layer. Thus, the thermal barrier coating structure including a diffusion barrier layer can be provided for the single-crystal turbine blade for the industrial gas turbine formed of a single crystal alloy. The thermal barrier coating structure can suppress growth of a secondary reaction zone caused by element diffusion into the substrate, and can provide durability against thermal fatigue due to thermal cycles and durability against mechanical fatigue.

6. 发明授权

EP2354276B8 GAS TURBINE SHROUD WITH CERAMIC ABRADABLE COATINGS 有权转让
标题翻译：与环绕耐磨陶瓷涂层燃气轮机
公开(公告)号：EP2354276B8
公开(公告)日：2017-04-19
申请号：EP11151974.0
申请日：2011-01-25
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Kojima, Yoshitaka , Arikawa, Hideyuki , Mebata, Akira , Kasuya, Tadashi , Doi, Hiroyuki , Ichikawa, Kunihiro
IPC分类号： C23C28/00 , F01D11/08
CPC分类号： C23C28/00 , F01D11/122 , F05D2230/90 , F05D2240/11 , F05D2250/181 , F05D2300/21

7. 发明授权

EP2725120B1 High temperature components with thermal barrier coatings for gas turbine 有权转让
标题翻译：热障涂层用于燃气轮机的高温部件
公开(公告)号：EP2725120B1
公开(公告)日：2016-07-27
申请号：EP13189647.4
申请日：2013-10-22
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Arikawa, Hideyuki , Kojima, Yoshitaka , Kasuya, Tadashi , Mebata, Akira , Ichikawa, Kunihiro , Endo, Hiroyuki , Endo, Takao
IPC分类号： C23C24/08 , C23C28/00 , F01D5/28 , F01D5/18 , C23C4/08
CPC分类号： F01D5/288 , C23C4/073 , C23C4/08 , C23C24/04 , C23C28/3215 , C23C28/3455 , F01D5/183 , F01D5/186

8. 发明授权

EP2808418B1 Method for manufacturing gas turbine blade 有权转让
公开(公告)号：EP2808418B1
公开(公告)日：2019-07-10
申请号：EP14170194.6
申请日：2014-05-28
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Izumi, Takeshi , Arikawa, Hideyuki , Kojima, Yoshitaka , Mebata, Akira , Kasuya, Tadashi , Imano, Shinya , Miyamoto, Koji
IPC分类号： C23C10/48 , C23C10/04 , C23C10/36 , C23C10/60 , F01D5/28 , F01D5/18

9. 发明授权

EP2690197B1 Turbine blade for industrial gas turbine and industrial gas turbine 有权转让
公开(公告)号：EP2690197B1
公开(公告)日：2018-10-10
申请号：EP13169377.2
申请日：2013-05-27
申请人： Mitsubishi Hitachi Power Systems, Ltd. , National University Corporation Hokkaido University
发明人： Izumi, Takeshi , Arikawa, Hideyuki , Kojima, Yoshitaka , Mebata, Akira , Kasuya, Tadashi , Narita, Toshio
IPC分类号： C23C28/00 , F01D5/28
CPC分类号： F01D5/288 , C23C28/321 , C23C28/3215 , C23C28/3455 , C23C28/347 , Y02T50/6765
摘要： A turbine blade for industrial gas turbine is used which includes a blade substrate formed of a single-crystal heat-resistant alloy containing C: 0.06 to 0.08%, B: 0.016 to 0.035%, Hf: 0.2 to 0.3%, Cr: 6.9 to 7.3%, Mo: 0.7 to 1.0%, W: 7.0 to 9.0%, Re: 1.2 to 1.6%, Ta: 8.5 to 9.5%, Nb: 0.6 to 1.0%, Al: 4.9 to 5.2%, Co: 0.8 to 1.2%, and the remainder substantially consisting of Ni with reference to mass, and includes a diffusion barrier layer, a metal layer, a bond coat, and a top coat, these layers and coats being stacked in this order on a surface of the blade substrate, the metal layer having a thickness of 5 to 30 µm. Thus, the turbine blade can be provided which has a thermal barrier coating formed without loss of a function of the diffusion barrier layer.

10. 发明公开

EP2808418A3 Method for manufacturing gas turbine blade, and gas turbine blade 有权转让
标题翻译： Verfahren zur Herstellung einer Turbinenschaufel und Gasturbinenschaufel
公开(公告)号：EP2808418A3
公开(公告)日：2015-03-11
申请号：EP14170194.6
申请日：2014-05-28
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Izumi, Takeshi , Arikawa, Hideyuki , Kojima, Yoshitaka , Mebata, Akira , Kasuya, Tadashi , Imano, Shinya , Miyamoto, Koji
IPC分类号： C23C10/48 , C23C10/04 , C23C10/36 , C23C10/60 , F01D5/28 , F01D5/18
CPC分类号： C23C10/04 , B22D21/025 , B23P15/02 , C23C10/48 , C23C10/60 , F01D5/18 , F01D5/187 , F01D5/288 , F05D2230/211 , Y10T29/49337 , Y10T29/49341
摘要： This method is a method for manufacturing a gas turbine blade, including:
producing a gas turbine blade having a cooling pass inside thereof (S1); and
partially coating an inner surface S of the cooling pass P with Al.
The step of partially coating an inner surface S of the cooling pass P with Al further including:
a first step (S4) of specifying a temperature range which satisfies both of oxidation resistance and fatigue strength and the temperature distribution of the inner surface of the cooling pass based on an examination result or result of a numerical analysis;
a second step (S5) of setting an Al-coating-applying portion of the inner surface of the cooling pass P as the temperature range specified at the first step; and
a third step of applying Al coating only into the set Al-coating-applying portion (S6).
摘要翻译：该方法是一种制造燃气轮机叶片的方法，包括：在其内部制造具有冷却通道的燃气轮机叶片（S1）; 并且用Al部分地涂覆冷却通道P的内表面S. 用Al进一步包括冷却通道P的内表面S的步骤还包括：规定满足耐氧化性和疲劳强度两者的温度范围的第一步骤（S4）以及冷却的内表面的温度分布基于检验结果或数值分析结果; 将冷却通道P的内表面的涂覆涂层部分设定为第一步骤规定的温度范围的第二步骤（S5）以及仅将Al涂层施加到设定的Al涂布部分中的第三步骤（S6）。

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