公开(公告)号：EP2690197A1

公开(公告)日：2014-01-29

申请号：EP13169377.2

申请日：2013-05-27

申请人： Hitachi 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

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.

摘要翻译： 使用工业燃气轮机的涡轮叶片，其包括由C：0.06〜0.08％，B：0.016〜0.035％，Hf：0.2〜0.3％，Cr：6.9〜 7.3％，Mo：0.7〜1.0％，W：7.0〜9.0％，Re：1.2〜1.6％，Ta：8.5〜9.5％，Nb：0.6〜1.0％，Al：4.9〜5.2％，Co：0.8〜1.2 ％，余量基本上由质量的Ni组成，并且包括扩散阻挡层，金属层，粘合涂层和顶涂层，这些层和涂层依次层叠在刮板基板的表面上 ，金属层的厚度为5〜30μm。 因此，可以提供涡轮叶片，其具有在不丧失扩散阻挡层的功能的情况下形成的热障涂层。

公开(公告)号：EP2725120A1

公开(公告)日：2014-04-30

申请号：EP13189647.4

申请日：2013-10-22

申请人： Hitachi 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

摘要： The most principal feature of the present invention is as follows: Namely, in the gas-turbine-use high-temperature component including the thermal barrier coating and a cooling structure, micro passages are provided inside an alloy bond-coat layer (2) and a thermal-barrier ceramic top-coat layer (3) of the thermal barrier coating, the micro passages being in communication from the substrate side to the surface side. Moreover, a partial amount of coolant of a coolant (8) for cooling the high-temperature component is caused to flow out to the outside of the high-temperature component via these micro passages. The employment of the structure like this makes it possible to expect the implementation of a high-temperature component's heat-resistant-temperature enhancement effect based on the transpiration cooling effect.

摘要翻译： 本发明的主要特征如下：即，在具有隔热涂层和冷却结构的燃气轮机用高温部件中，在合金接合涂层（2）的内部设置微通道， 所述热障涂层的热障陶瓷顶涂层（3），所述微通道从所述基板侧至所述表面侧连通。 此外，使用于冷却高温部件的冷却剂（8）的一部分冷却剂通过这些微通道流出到高温部件的外部。 使用这样的结构使得可以期望基于蒸腾冷却效果实现高温部件的耐热温度增强效果。

公开(公告)号：EP2434102A2

公开(公告)日：2012-03-28

申请号：EP11183071.7

申请日：2011-09-28

申请人： Hitachi 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

摘要： A gas turbine shroud includes a ceramic abradable coating superior in abradable property and durability. The gas turbine ceramic abradable coating of the present invention is configured by an abradable metal layer and a porous ceramic abradable layer (3) (hardness RC15Y: 80±3), the porous ceramic abradable layer (3) is provided with slit grooves (4) by machining work, and a slit groove width (5) is 0.5 to 5 mm. Thereby, the abradable property, and durability against a thermal cycle and high-temperature oxidation are improved.

摘要翻译： 燃气轮机罩包括耐磨性和耐久性优异的陶瓷耐磨涂层。 本发明的燃气轮机陶瓷耐磨涂层由耐磨金属层和多孔陶瓷耐磨层（3）（硬度RC15Y：80±3）构成，多孔陶瓷耐磨层（3）设有狭槽（4） ），切槽宽度（5）为0.5〜5mm。 由此，耐热性，耐热循环性和耐高温氧化性提高。

公开(公告)号：EP2354276A1

公开(公告)日：2011-08-10

申请号：EP11151974.0

申请日：2011-01-25

申请人： Hitachi 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

摘要： There is provided a gas turbine shroud including a ceramic abradable coating used as a gap adjusting component that can reduce a fluid leakage from a gap and increase turbine efficiency. A gas turbine ceramic abradable coating includes a bond layer (2), a thermal barrier ceramic layer (3), and a porous ceramic abradable layer (4) (hardness may be RC15Y: 80±3). A slit groove (5) is provided in the porous ceramic abradable layer (4) by machining. A width of a rectangular section of the ceramic abradable layer (4) divided by the slit groove (5) may be set to a range of 2 to 7 mm.

摘要翻译： 提供了一种燃气轮机罩，其包括用作间隙调节部件的陶瓷耐磨涂层，其可以减少从间隙泄漏的液体并提高涡轮机效率。 燃气轮机陶瓷耐磨涂层包括粘合层（2），热障陶瓷层（3）和多孔陶瓷耐磨层（4）（硬度可以是RC15Y：80±3）。 通过机加工在多孔陶瓷耐磨层（4）中设置狭槽（5）。 由狭缝槽（5）分割的陶瓷耐磨层（4）的矩形截面的宽度可以设定在2〜7mm的范围内。

公开(公告)号：EP2434102A3

公开(公告)日：2014-03-19

申请号：EP11183071.7

申请日：2011-09-28

申请人： Hitachi 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

摘要： A gas turbine shroud includes a ceramic abradable coating superior in abradable property and durability. The gas turbine ceramic abradable coating of the present invention is configured by an abradable metal layer and a porous ceramic abradable layer (3) (hardness RC15Y: 80±3), the porous ceramic abradable layer (3) is provided with slit grooves (4) by machining work, and a slit groove width (5) is 0.5 to 5 mm. Thereby, the abradable property, and durability against a thermal cycle and high-temperature oxidation are improved.

摘要翻译： 燃气轮机罩包括耐磨性和耐久性优异的陶瓷耐磨涂层。 本发明的燃气轮机陶瓷耐磨涂层由耐磨金属层和多孔陶瓷耐磨层（3）（硬度RC15Y：80±3）构成，多孔陶瓷耐磨层（3）设有狭槽（4） ），切槽宽度（5）为0.5〜5mm。 由此，耐热性，耐热循环性和耐高温氧化性提高。

公开(公告)号：EP2684976A2

公开(公告)日：2014-01-15

申请号：EP13175928.4

申请日：2013-07-10

申请人： Hitachi 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

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.

摘要翻译： 公开了一种用于工业燃气轮机的涡轮叶片，其包括叶片基板; 含有扩散阻挡层的多层合金涂层; 粘合外套; 和顶涂层，所述刀片基材由单晶合金形成，所述单晶合金基本上由C：0.06〜0.08％，B：0.016〜0.035％，Hf：0.2〜0.3％，Cr：6.9〜7.3％，0.7〜1.0 Mo为7.0〜9.0％，Re为1.2〜1.6％，Ta为8.5〜9.5％，Nb为0.6〜1.0％，Al为4.9〜5.2％，Co为0.8〜1.2％，余量为 Ni和重量杂质，多层合金涂层，粘结涂层和顶涂层直接依次层压在其中扩散阻挡层为多层和不连续层的叶片基板的表面上。 因此，对于由单晶合金形成的工业燃气轮机的单晶涡轮叶片，能够提供包括扩散阻挡层的热障涂覆结构。 热障涂层结构可以抑制由元件扩散到基板中引起的二次反应区的生长，并且可以提供耐热循环和对机械疲劳的耐久性的热疲劳的耐久性。