专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US07334993B2 Gas turbine rotor blade, gas turbine using the rotor blade, and power plant using the gas turbine 有权
标题翻译：燃气轮机转子叶片，使用转子叶片的燃气轮机，以及使用燃气轮机的发电厂
公开(公告)号：US07334993B2
公开(公告)日：2008-02-26
申请号：US11433497
申请日：2006-05-15
申请人： Masaru Sekihara , Yasushi Hayasaka , Kunihiro Ichikawa
发明人： Masaru Sekihara , Yasushi Hayasaka , Kunihiro Ichikawa
IPC分类号： F01D5/18 , F01D5/26
CPC分类号： F01D5/225 , F01D5/3007
摘要： A gas turbine rotor blade capable of effectively reducing creep damage by forming a cooling through hole to cool a target area in which significant creep damage of a shroud cover is predicted based on analysis of stress and temperature acting on the gas turbine rotor blade. A gas turbine using the rotor blade, and a power plant using the gas turbine are also provided. The gas turbine rotor blade includes a blade section provided with a shroud cover at an outer peripheral end thereof, and a platform, a shank and a dovetail which are formed in integral structure to successively continue from the blade section. An inner cooling hole is formed to penetrate through the gas turbine rotor blade from the dovetail to the shroud cover. The shroud cover has a cooling through hole formed to open in an outer surface of the shroud cover and extend in communication with the inner cooling hole.
摘要翻译：一种燃气轮机转子叶片，其能够通过形成冷却通孔来冷却目标区域，从而通过基于作用在燃气轮机转子叶片上的应力和温度的分析来预测护罩盖的显着的蠕变损伤，来有效地减少蠕变损伤。还提供了使用转子叶片的燃气轮机和使用燃气轮机的动力装置。燃气轮机转子叶片包括在其外周端处设置有护罩盖的叶片部分，以及形成为一体结构的平台，柄部和燕尾榫，从叶片部分连续延伸。形成内部冷却孔，以从燕尾槽穿过燃气轮机转子叶片到罩盖。护罩罩具有形成为在护罩罩的外表面上开口并与内部冷却孔连通延伸的冷却通孔。

2. 发明申请

US20070065283A1 Gas turbine rotor blade, gas turbine using the rotor blade, and power plant using the gas turbine 有权
标题翻译：燃气轮机转子叶片，使用转子叶片的燃气轮机，以及使用燃气轮机的发电厂
公开(公告)号：US20070065283A1
公开(公告)日：2007-03-22
申请号：US11433497
申请日：2006-05-15
申请人： Masaru Sekihara , Yasushi Hayasaka , Kunihiro Ichikawa
发明人： Masaru Sekihara , Yasushi Hayasaka , Kunihiro Ichikawa
IPC分类号： F01D5/18
CPC分类号： F01D5/225 , F01D5/3007
摘要： A gas turbine rotor blade capable of effectively reducing creep damage by forming a cooling through hole to cool a target area in which significant creep damage of a shroud cover is predicted based on analysis of stress and temperature acting on the gas turbine rotor blade. A gas turbine using the rotor blade, and a power plant using the gas turbine are also provided. The gas turbine rotor blade includes a blade section provided with a shroud cover at an outer peripheral end thereof, and a platform, a shank and a dovetail which are formed in integral structure to successively continue from the blade section. An inner cooling hole is formed to penetrate through the gas turbine rotor blade from the dovetail to the shroud cover. The shroud cover has a cooling through hole formed to open in an outer surface of the shroud cover and extend in communication with the inner cooling hole.
摘要翻译：一种燃气轮机转子叶片，其能够通过形成冷却通孔来冷却目标区域，从而通过基于作用在燃气轮机转子叶片上的应力和温度的分析来预测护罩盖的显着的蠕变损伤，来有效地减少蠕变损伤。还提供了使用转子叶片的燃气轮机和使用燃气轮机的动力装置。燃气轮机转子叶片包括在其外周端处设置有护罩盖的叶片部分，以及形成为一体结构的平台，柄部和燕尾榫，从叶片部分连续延伸。形成内部冷却孔，以从燕尾槽穿过燃气轮机转子叶片到罩盖。护罩罩具有形成为在护罩罩的外表面上开口并与内部冷却孔连通延伸的冷却通孔。

3. 发明授权

US06636813B1 Service life management system for high-temperature part of gas turbine 有权
标题翻译：燃气轮机高温部分使用寿命管理系统
公开(公告)号：US06636813B1
公开(公告)日：2003-10-21
申请号：US09913957
申请日：2001-11-15
申请人： Nobuhiro Isobe , Yasushi Hayasaka , Shigeo Sakurai , Kunihiro Ichikawa
发明人： Nobuhiro Isobe , Yasushi Hayasaka , Shigeo Sakurai , Kunihiro Ichikawa
IPC分类号： F01D902
CPC分类号： G06Q10/06 , F01D21/003 , F02C9/00 , G05B23/0283
摘要： A life management system for high-temperature parts of a gas turbine has one server system 3 and a plurality of client systems 5a, 5b, 5c, and 5d, all of which are connected via an Intranet. Further, the server system 3 manages a program for performing evaluation of the remaining life and the life management, and each of the client systems 5a, 5b, 5c, and 5d has a subprogram for accessing the database 4 and for entering data respectively. The clients are dedicated to different objects and share respective element data such as real component damage, design, materials, etc. which are necessary for the evaluation of the remaining life. Further, this system enables the operation of the gas turbine to be optimized based on the damage of the evaluated parts, hence contributing to operational cost reduction of the gas turbine.
摘要翻译：燃气轮机的高温部件的生命管理系统具有一个服务器系统3和多个客户端系统5a，5b，5c和5d，所有客户端系统都通过内联网连接。此外，服务器系统3管理用于执行剩余寿命和寿命管理的评估的程序，并且每个客户端系统5a，5b，5c和5d具有用于访问数据库4并分别输入数据的子程序。客户专用于不同的对象，并分享对剩余寿命进行评估所需的各个元素数据，例如实际元件损坏，设计，材料等。此外，该系统能够基于评估部件的损坏来优化燃气轮机的运行，从而有助于燃气轮机的运行成本降低。

4. 发明授权

US07165325B2 Welding material, gas turbine blade or nozzle and a method of repairing a gas turbine blade or nozzle 有权
标题翻译：焊接材料，燃气轮机叶片或喷嘴以及修理燃气轮机叶片或喷嘴的方法
公开(公告)号：US07165325B2
公开(公告)日：2007-01-23
申请号：US10635548
申请日：2003-08-07
申请人： Shinya Imano , Hiroyuki Doi , Kunihiro Ichikawa , Hideaki Ishii
发明人： Shinya Imano , Hiroyuki Doi , Kunihiro Ichikawa , Hideaki Ishii
IPC分类号： B23P6/00
CPC分类号： C22C19/056 , B23K35/3033 , B23K35/304 , Y10T29/49318 , Y10T428/12944
摘要： A welding material composition, which is a nickel based super alloy having γ′ phase and chromium carbides precipitated. The composition comprising 18 to 25% by weight of Co, 15 to 20% by weight of Cr, 1.5 to 5.5% by weight of Al, 5 to 14% by weight of W, 0.05 to 0.15% by weight of C, 0 to 0.02% by weight of B, 0 to 1% by weight of at least one of Ta, Nb, Ti, Mo, Re and Fe, 0 to 0.5% by weight of at least one of V, Zr, rare earth elements and Y, 0 to 1% by weight of Mn, 0 to 0.5% by weight of Si, and the balance being Ni.
摘要翻译：一种焊接材料组合物，其是具有γ'相和铬碳化物的镍基超级合金。该组合物包含18至25重量％的Co，15至20重量％的Cr，1.5至5.5重量％的Al，5至14重量％的W，0.05至0.15重量％的C，0至 0.02重量％的B，0〜1重量％的Ta，Nb，Ti，Mo，Re和Fe中的至少一种，0〜0.5重量％的V，Zr，稀土元素中的至少一种，Y ，0〜1重量％的Mn，0〜0.5重量％的Si，余量为Ni。

5. 发明申请

US20060251916A1 High temperature component with thermal barrier coating and gas turbine using the same 有权
标题翻译：高温部件采用隔热涂层和燃气轮机使用
公开(公告)号：US20060251916A1
公开(公告)日：2006-11-09
申请号：US11233379
申请日：2005-09-23
申请人： Hideyuki Arikawa , Akira Mebata , Yoshitaka Kojima , Kunihiro Ichikawa , Takayuki Yoshioka , Mitsutoshi Okada , Tohru Hisamatsu
发明人： Hideyuki Arikawa , Akira Mebata , Yoshitaka Kojima , Kunihiro Ichikawa , Takayuki Yoshioka , Mitsutoshi Okada , Tohru Hisamatsu
IPC分类号： F03B3/12 , C03C27/00 , C25D5/10 , B32B15/00
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： There is provided a high temperature component with a thermal barrier coating, which can be used as a high temperature component for a gas turbine, an aircraft gas turbine engine, or the like. A top coat is formed of a ceramic on a bond coat, the bond coat being formed on a heat resistant alloy substrate composed mainly of at least one element of nickel and cobalt, wherein the bond coat contains at least one of nickel and cobalt, chromium and aluminum, and further contains at least one selected from a group consisting of tantalum, cesium, tungsten, silicon, platinum, manganese and boron in a range of 0 to 20 wt %. The high temperature component according to the present invention has very high durability of a thermal-insulating ceramic layer, and is less susceptible to spalling damage.
摘要翻译：提供了具有热障涂层的高温部件，其可以用作燃气轮机，飞机燃气轮机等的高温部件。顶涂层由粘结涂层上的陶瓷形成，粘合涂层形成在主要由至少一种镍和钴元素组成的耐热合金基底上，其中粘合涂层含有镍和钴中的至少一种，铬，铝，还含有选自钽，铯，钨，硅，铂，锰和硼中的至少一种为0〜20重量％。根据本发明的高温部件具有非常高的绝热陶瓷层的耐久性，并且不易受剥落损伤。

6. 发明授权

US07901790B2 High temperature component with thermal barrier coating and gas turbine using the same 有权
标题翻译：高温部件采用隔热涂层和燃气轮机使用
公开(公告)号：US07901790B2
公开(公告)日：2011-03-08
申请号：US11233379
申请日：2005-09-23
申请人： Hideyuki Arikawa , Akira Mebata , Yoshitaka Kojima , Kunihiro Ichikawa , Takayuki Yoshioka , Mitsutoshi Okada , Tohru Hisamatsu
发明人： Hideyuki Arikawa , Akira Mebata , Yoshitaka Kojima , Kunihiro Ichikawa , Takayuki Yoshioka , Mitsutoshi Okada , Tohru Hisamatsu
IPC分类号： B32B15/00
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： There is provided a high temperature component with a thermal barrier coating, which can be used as a high temperature component for a gas turbine, an aircraft gas turbine engine, or the like. A top coat is formed of a ceramic on a bond coat, the bond coat being formed on a heat resistant alloy substrate composed mainly of at least one element of nickel and cobalt, wherein the bond coat contains at least one of nickel and cobalt, chromium and aluminum, and further contains at least one selected from a group consisting of tantalum, cesium, tungsten, silicon, platinum, manganese and boron in a range of 0 to 20 wt %. The high temperature component according to the present invention has very high durability of a thermal-insulating ceramic layer, and is less susceptible to spalling damage.
摘要翻译：提供了具有热障涂层的高温部件，其可以用作燃气轮机，飞机燃气轮机等的高温部件。顶涂层由粘结涂层上的陶瓷形成，粘合涂层形成在主要由至少一种镍和钴元素组成的耐热合金基底上，其中粘合涂层含有镍和钴中的至少一种，铬，铝，还含有选自钽，铯，钨，硅，铂，锰和硼中的至少一种为0〜20重量％。根据本发明的高温部件具有非常高的绝热陶瓷层的耐久性，并且不易受剥落损伤。

7. 发明申请

US20100266418A1 Gas Turbine Blade and Manufacturing Method Thereof 审中-公开
标题翻译：燃气轮机叶片及其制造方法
公开(公告)号：US20100266418A1
公开(公告)日：2010-10-21
申请号：US12107796
申请日：2008-04-23
申请人： Shinya IMANO , Kunihiro Ichikawa , Hiroyuki Doi , Katsumi Tanaka
发明人： Shinya IMANO , Kunihiro Ichikawa , Hiroyuki Doi , Katsumi Tanaka
IPC分类号： F01D5/14 , B23P15/02
CPC分类号： C22C19/051 , C22C19/05 , F01D5/005 , F05D2230/235 , F05D2230/80
摘要： In a gas turbine blade where a part of the γ′ phase precipitation strengthened type Ni-based alloy base material is composed of a weld metal, the weld metal is a Ni-based alloy containing Ta from 4.8 to 5.3 wt. %, Cr from 18 to 23 wt. %, Co from 12 to 17 wt. %, W from 14 to 18 wt. %, C from 0.03 to 0.1 wt. %, Mo from 1 to 2 wt. %, and Al of 1 wt. % or less, in which the oxygen content is 0 to 30 ppm, the Ti content from 0 to 0.1 wt. %, and the Re content from 0 to 0.5 wt. %. A blade base metal is manufactured by the step of stripping, the step of solution heat treatment where the γ′ phase is dissolved again, the step of welding in an inert gas chamber by a TIG method using a welding wire where the weld metal can be obtained, the step of HIP treatment at 1100° C. to 1150° C., and the step of an aging treatment at 835° C. to 855° C.
摘要翻译：在γ相析出强化型Ni基合金基材的一部分由焊接金属构成的燃气轮机叶片中，焊接金属为含有4.8〜5.3重量％的Ta的Ni系合金。％，Cr为18〜23wt。％，Co为12〜17wt。％，W为14〜18wt。％，C为0.03〜0.1wt。％，Mo为1〜2wt。％，Al为1重量％。％以下，氧含量为0〜30ppm，Ti含量为0〜0.1重量％。％，Re含量为0〜0.5wt。％。通过剥离步骤，再次溶解γ'相的固溶热处理步骤，通过TIG法使用焊丝在焊接金属可以焊接的焊丝的惰性气体室中进行焊接的工序来制造刀片母材在1100℃至1150℃下进行HIP处理的步骤，以及在835℃至855℃的时效处理步骤。

8. 发明申请

US20050136249A1 Heat resistant article having thermal barrier coatinging 有权
标题翻译：耐热制品具有隔热涂层
公开(公告)号：US20050136249A1
公开(公告)日：2005-06-23
申请号：US11006763
申请日：2004-12-08
申请人： Hideyuki Arikawa , Akira Mebata , Yoshitaka Kojima , Kunihiro Ichikawa
发明人： Hideyuki Arikawa , Akira Mebata , Yoshitaka Kojima , Kunihiro Ichikawa
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： A thermal barrier coating comprises a bond coating 12 made of high temperature corrosion resistance superior to a substrate 11 and a thermal barrier coating 13 made of ZrO2 series ceramics formed on the bond coating. The thermal barrier coating has cracks extending in the direction of the thickness of the barrier coat. Substantially all of the tips of the cracks have a distance between the tips and the boundary at the substrate side.
摘要翻译：热障涂层包括由耐热性高于基材11的粘结涂层12和形成在粘结涂层上的ZrO 2系陶瓷制成的热障涂层13。隔热涂层具有在阻挡涂层的厚度方向上延伸的裂纹。基本上所有的裂纹的尖端在顶端和衬底侧的边界之间具有一定距离。

9. 发明申请

US20110296685A1 Gas Turbine Blade and Manufacturing Method Thereof 有权
标题翻译：燃气轮机叶片及其制造方法
公开(公告)号：US20110296685A1
公开(公告)日：2011-12-08
申请号：US13211417
申请日：2011-08-17
申请人： Shinya Imano , Kunihiro Ichikawa , Hiroyuki Doi , Katsumi Tanaka
发明人： Shinya Imano , Kunihiro Ichikawa , Hiroyuki Doi , Katsumi Tanaka
IPC分类号： B23P6/00 , B23P15/02
CPC分类号： C22C19/051 , C22C19/05 , F01D5/005 , F05D2230/235 , F05D2230/80
摘要： In a gas turbine blade where a part of the γ′ phase precipitation strengthened type Ni-based alloy base material is composed of a weld metal, the weld metal is a Ni-based alloy containing Ta from 4.8 to 5.3 wt. %, Cr from 18 to 23 wt. %, Co from 12 to 17 wt. %, W from 14 to 18 wt. %, C from 0.03 to 0.1 wt. %, Mo from 1 to 2 wt. %, and Al of 1 wt. % or less, in which the oxygen content is 0 to 30 ppm, the Ti content from 0 to 0.1 wt. %, and the Re content from 0 to 0.5 wt. %. A blade base metal is manufactured by the step of stripping, the step of solution heat treatment where the γ′ phase is dissolved again, the step of welding in an inert gas chamber by a TIG method using a welding wire where the weld metal can be obtained, the step of HIP treatment at 1100° C. to 1150° C., and the step of an aging treatment at 835° C. to 855° C.
摘要翻译：在γ相析出强化型Ni基合金基材的一部分由焊接金属构成的燃气轮机叶片中，焊接金属为含有4.8〜5.3重量％的Ta的Ni系合金。％，Cr为18〜23wt。％，Co为12〜17wt。％，W为14〜18wt。％，C为0.03〜0.1wt。％，Mo为1〜2wt。％，Al为1重量％。％以下，氧含量为0〜30ppm，Ti含量为0〜0.1重量％。％，Re含量为0〜0.5wt。％。通过剥离步骤，再次溶解γ'相的固溶热处理步骤，通过TIG法使用焊丝在焊接金属可以焊接的焊丝的惰性气体室中进行焊接的工序来制造刀片母材在1100℃至1150℃下进行HIP处理的步骤，以及在835℃至855℃的时效处理步骤。

10. 发明申请

US20110182720A1 GAS TURBINE SHROUD WITH CERAMIC ABRADABLE COATINGS 审中-公开
标题翻译：气体涡轮机与陶瓷可磨损涂层
公开(公告)号：US20110182720A1
公开(公告)日：2011-07-28
申请号：US13012017
申请日：2011-01-24
申请人： Yoshitaka KOJIMA , Hideyuki Arikawa , Akira Mebata , Tadashi Kasuya , Hiroyuki Doi , Kunihiro Ichikawa
发明人： Yoshitaka KOJIMA , Hideyuki Arikawa , Akira Mebata , Tadashi Kasuya , Hiroyuki Doi , Kunihiro Ichikawa
IPC分类号： F01D11/12 , B05D3/12
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, a thermal barrier ceramic layer, and a porous ceramic abradable layer (hardness may be RC15Y: 80±3). A slit groove is provided in the porous ceramic abradable layer by machining. A width of a rectangular section of the ceramic abradable layer divided by the slit groove 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，热障陶瓷层和多孔陶瓷耐磨层（硬度可以是RC15Y：80±3）。通过机械加工在多孔陶瓷耐磨层中设置狭缝槽。由狭缝槽划分的陶瓷耐磨层的矩形截面的宽度可以设定在2〜7mm的范围内。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式