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41. 发明专利

JP2010025006A Exhaust diffuser of gas turbine 有权
标题翻译：气体涡轮排气歧管
公开(公告)号：JP2010025006A
公开(公告)日：2010-02-04
申请号：JP2008188343
申请日：2008-07-22
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： ENDO TAKAO , ICHIKAWA KUNIHIRO , NAGANO HIKARU
IPC分类号： F02C7/00 , F01D25/00 , F01D25/30
摘要： PROBLEM TO BE SOLVED: To provide an exhaust diffuser of a gas turbine for lengthening the service life by restraining thermal stress with an economical and simple structure, without requiring study of a design change in a gas turbine facility. SOLUTION: The exhaust diffuser of the gas turbine is arranged in an exhaust flue part for exhausting exhaust gas 2 of the gas turbine to an external part, and is composed of an outside cylinder body 1, an inside cylinder body 4A and a strut 5 arranged between these cylinder bodies. The strut 5 is a hollow cylindrical body having a cooling passage for connecting the outside cylinder body 1 and the inside cylinder body 4A. Joining members 6B and 6A having the peripheral edge joined to the outside cylinder body 1 and/or the inside cylinder body 4A, are arranged on the opening end of the strut 5. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：为了提供燃气轮机的排气扩散器，通过以经济和简单的结构抑制热应力来延长使用寿命，而不需要研究燃气轮机设备的设计变化。解决方案：燃气轮机的排气扩散器布置在用于将燃气轮机的废气2排出到外部的排气烟道部分中，并且由外筒体1，内筒体4A和支柱5布置在这些缸体之间。支柱5是具有用于连接外筒体1和内筒体4A的冷却通道的中空圆筒体。具有连接到外筒体1和/或内筒体4A的周缘的接合件6B和6A布置在支柱5的开口端。（C）2010，JPO＆INPIT

42. 发明专利

JP2009235476A Coating for high-temperature seal 审中-公开
标题翻译：涂层用于高温密封
公开(公告)号：JP2009235476A
公开(公告)日：2009-10-15
申请号：JP2008082355
申请日：2008-03-27
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： C23C4/04 , C23C4/10 , F01D5/28 , F01D11/08 , F01D25/00 , F02C7/00 , F02C7/28
摘要： PROBLEM TO BE SOLVED: To provide a coating which exhibits excellent machinability and heat-shielding property as a coating for a high-temperature seal of a gas turbine or the like and has both functions of abradable coating and TBC (Thermal Barrier Coating). SOLUTION: As an abradable coating for a high temperature seal, a mixed coating composed of a partially stabilized zirconia and a Ni- or Co-based alloy is used. The ratio of the Ni- or Co-based alloy in the mixed coating is 10-50% by area ratio in the cross sectional constitution of the coating. Further, the composition of the Ni- or Co-based alloy is preferably composed of at least one of Ni and Co. The composition of the Ni- or Co-based alloy contains Ni and Co in an amount of 50-75 wt.% in total, Cr in an amount of 5-40 wt.% and Al in an amount of 1-30 wt.%. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种作为燃气轮机等的高温密封的涂层具有优异的机械加工性和隔热性的涂层，并且具有耐磨涂层和TBC（热障涂层）。解决方案：作为用于高温密封的耐磨涂层，使用由部分稳定的氧化锆和Ni-或Co-基合金组成的混合涂层。混合涂层中Ni-或Co基合金的比例在涂层的横截面构造中为10-50％（面积）。此外，Ni基或Co基合金的组成优选由Ni和Co中的至少一种构成。Ni-或Co基合金的组成含有50-75重量％的Ni和Co，总共为5-40重量％的Cr和1-30重量％的Al。版权所有（C）2010，JPO＆INPIT

43. 发明专利

JP2009068032A Heat-resistant member and its manufacturing method 审中-公开
标题翻译：耐热构件及其制造方法
公开(公告)号：JP2009068032A
公开(公告)日：2009-04-02
申请号：JP2007234860
申请日：2007-09-11
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 , C23C26/00
摘要： PROBLEM TO BE SOLVED: To provide a manufacturing method for a heat-resistant member which has excellent durability and is obtained by laminating a heat-resistant alloy of different kind from a base body on a heat-resistant alloy base body.
SOLUTION: The manufacturing method includes (a) a step of laminating heat-resistant alloy powder particles 3 of different kind from a base body 1 on a heat-resistant alloy base body with its relative density of 53 to
摘要翻译：解决的问题：提供一种耐热构件的制造方法，该耐热构件具有优异的耐久性，并且通过将耐热合金基体上的与基体不同种类的耐热合金层压而获得。解决方案：制造方法包括（a）将耐热合金基体上与基体1不同种类的耐热合金粉末颗粒3层压在其相对密度为53至<97％的步骤，（b）在第一阶段之后的真空中密封层叠耐热合金层的表面附近的孔4的步骤，（c）对所述构件进行HIP（热等静压）处理的步骤第二步后的惰性气氛，以消除叠层耐热合金层2中的气孔致密。版权所有（C）2009，JPO＆INPIT

44. 发明专利

JP2009024631A Gas turbine facility 审中-公开
标题翻译：气体涡轮机设施
公开(公告)号：JP2009024631A
公开(公告)日：2009-02-05
申请号：JP2007189576
申请日：2007-07-20
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： ENDO TAKAO , ICHIKAWA KUNIHIRO , SAKURAI HIROSHI
IPC分类号： F02C7/00 , F01D25/30
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine facility having an economical exhaust diffuser capable of preventing generation of crack due to thermal deformation by approximating thermal capacities of flanges and cylindrical bodies.
SOLUTION: In this invention, the exhaust diffuser 5 is structured by separating the cylindrical bodies 14N, 15N, 16N, 14S, 15S, 16S into a plurality of sections in an exhaust gas flow-out direction, forming the flanges 15Fs, 16Fs, 15Fn, 16Fs at separated parts of the cylindrical bodies and inserting bolts 19 to the flanges and fastening them with nuts 20. In the exhaust diffuser 5, the wall thickness of the flanges is formed to be as thin as that of the cylindrical bodies and washers 18, 20, 21 thicker than the wall thickness of the flanges are brought into face contact with the fastening part of the flange of the adjacent cylindrical body in a surface-to-surface manner by using the bolts and the nuts.
COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供一种具有经济的排气扩散器的燃气轮机设备，其能够通过近似法兰和圆柱体的热容量来防止由于热变形而产生裂纹。解决方案：在本发明中，排气扩散器5通过将圆筒体14N，15N，16N，14S，15S，16S分成排气流出方向的多个部分而构成，形成凸缘15F， 16F，15Fn，16F在圆柱体的分离部分处，并将螺栓19插入凸缘并用螺母20紧固。在排气扩散器5中，凸缘的壁厚形成为与圆柱体相同的壁厚并且比凸缘的壁厚更厚的垫圈18,20,21通过使用螺栓和螺母以表面到表面方式与相邻圆柱体的凸缘的紧固部分面接触。版权所有（C）2009，JPO＆INPIT

45. 发明专利

JP2008274314A Gas turbine blade and manufacturing method thereof 有权
标题翻译：气体涡轮叶片及其制造方法
公开(公告)号：JP2008274314A
公开(公告)日：2008-11-13
申请号：JP2007115650
申请日：2007-04-25
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： KONNO SHINYA , ICHIKAWA KUNIHIRO , DOI HIROYUKI , TANAKA KATSUMI
IPC分类号： C22C19/05 , B23K9/00 , B23K9/04 , B23K9/167 , B23K31/00 , B23K35/30 , B23K103/08 , C22F1/00 , C22F1/10
CPC分类号： C22C19/051 , C22C19/05 , F01D5/005 , F05D2230/235 , F05D2230/80
摘要： PROBLEM TO BE SOLVED: To obtain a gas turbine blade excellent in fatigue characteristic and crack resistance by restraining an inter-granular linearity of a welded metal in the gas turbine blade containing the welded part.
SOLUTION: In the part of the gas turbine blade, in which a part of γ' phase precipitating strengthened type Ni based ultra-alloy base material is constituted with the welded metal, the welded metal is the Ni-based alloy containing 4.8-5.3 wt.% Ta, 18-23 wt.% Cr, 12-17 wt.% Co, 14-18 wt.% W, 0.03-0.1 wt.% C, 1-2 wt.% Mo, ≤1 wt.% Al and 0-30ppm oxygen content, 0-0.1 wt.% Ti content, 0-0.5 Re content. The blade-base material is manufactured with: the step of stripping; the step of solution heat treatment, in which γ' phase is dissolved again; the step of welding in the inert gas chamber by TIG method with a welding wire, in which the above weld metal can be obtained; the step of HIP treatment at 1,100-1,150°C; and the step of aging treatment at 835-855°C.
COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：解决方案：通过抑制包含焊接部件的燃气轮机叶片中的焊接金属的粒间线性，获得疲劳特性和抗裂性优异的燃气轮机叶片。解决方案：在一部分γ'相析出强化型Ni基超合金基体的燃气轮机叶片部分中，焊接金属为Ni基合金，含有4.8 -5.3重量％的Ta，18-23重量％的Cr，12-17重量％的Co，14-18重量％的W，0.03-0.1重量％的C，1-2重量％的Mo，≤1重量％。％Al和0-30ppm氧含量，0-0.1重量％Ti含量，0-0.5 Re含量。刀片基材料制成：剥离步骤; 固溶热处理步骤，其中γ'相再次溶解; 通过TIG法在惰性气体室中用焊丝焊接上述焊接金属的步骤; 在1100-1,150℃下进行HIP处理的步骤; 和835-855℃的老化处理步骤。版权所有（C）2009，JPO＆INPIT

46. 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

47. 发明专利

JP2004340044A Repairing method for gas turbine moving blade, and gas turbine moving blade structure 有权
公开(公告)号：JP2004340044A
公开(公告)日：2004-12-02
申请号：JP2003138180
申请日：2003-05-16
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： SEKIHARA TAKASHI , ICHIKAWA KUNIHIRO
IPC分类号： F01D5/22 , F01D25/00 , F02C7/00
CPC分类号： B23P6/002
摘要： PROBLEM TO BE SOLVED: To provide a repair method for a gas turbine moving blade facilitating repair of a damaged part such as a crack, in the gas turbine moving blade.
SOLUTION: The gas turbine moving blade is constituted of a blade part 4 and a fir three part 5 fitted into an embedment groove worked in an outer periphery of a turbine wheel. The gas turbine moving blade has a shroud cover 7 with an uneven part 8 formed at an outer periphery thereof, the uneven parts 8 are mutually fitted to neighboring moving blades, so that the gas turbine moving blades are engaged. Since a part near the crack 9 generated in the recesses part 6 of the uneven part 8 of the shroud cover 7 is removed in a circular arc shape (circular shape) from above, along a height direction of the gas turbine moving blade, the repair is facilitated.
COPYRIGHT: (C)2005,JPO&NCIPI

48. 发明专利

JP2004156860A Gas turbine combustor 有权
公开(公告)号：JP2004156860A
公开(公告)日：2004-06-03
申请号：JP2002323784
申请日：2002-11-07
申请人： Chubu Electric Power Co Inc , Hitachi Ltd , 中部電力株式会社 , 株式会社日立製作所
发明人： TAKEHARA ISAO , ICHIKAWA KUNIHIRO , ITO KAZUYUKI , HIRANO RYUICHI , KIDA RYOSUKE
IPC分类号： F23R3/08 , F23R3/48
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustor reducing cooling air flow rate while maintaining metal temperature of a combustion chamber liner within an appropriate range.
SOLUTION: This gas turbine combustor is constituted by connecting a plurality of can type combustors with cross fire pipes. The can type combustor has the combustion chamber liner 20 on which a connection part of the cross fire pipe is arranged. A plurality of combustion holes 30a, 30b and cooling holes 40a, 40b, 40c for cooling the combustion chamber liner are arranged on the combustion chamber liner 20, and the combustion holes 30a, 30b are circumferentially dispersedly arranged thereon at axial positions approximately at the same position as the cross fire pipe connection parts 101. In addition to the cooling holes 40a, 40b, 40c, cooling hole columns 50a, 50b are also provided, and the cooling holes are more densely arranged on the axial area in the vicinity of the cross fire pipe connection part 101 of the combustion chamber liner 20 than other portions.
COPYRIGHT: (C)2004,JPO

49. 发明专利

JP2000130103A GAS TURBINE STATIONARY BLADE STRUCTURE AND LIFE CONTROLLING METHOD THEREFOR 失效
公开(公告)号：JP2000130103A
公开(公告)日：2000-05-09
申请号：JP30501898
申请日：1998-10-27
申请人： HITACHI LTD
发明人： ISOBE NOBUHIRO , HAYASAKA YASUSHI , SAKURAI SHIGEO , ICHIKAWA KUNIHIRO
IPC分类号： F01D9/02 , F02C7/18
摘要： PROBLEM TO BE SOLVED: To suppress maximum crack growth of a gas turbine stationary blade and to attain long lives of parts by preliminarily providing cooling holes on paths of cracks for a portion in which growth of the cracks is estimated and making a structure in which stress strength at tips of the cracks is reduced at a point of time when the cracks reach the cooling holes. SOLUTION: When thermal fatigue cracks 3 are detected in a gas turbine stationary blade, development of the cracks 3 is suppressed by working holes 4 in the growth directions of the cracks 3 and reducing specific stress field at tips of the cracks 3 when the cracks 3 reach the holes 4. Because the shapes of the holes 4 reduce stress concentration in the growth directions of the cracks 3, the holes 4 are made elliptical or race track type holes in which the growth directions of the cracks 3 become a minor axis. Because there are many cases where portions generating these thermal fatigue cracks 3 can be estimated from a structural analysis or analysis of trends of past damage data, sometimes these holes 4 are preliminarily worked at a portion where the cracks 3 are estimated to be generated when manufactured.

50. 发明专利

JPH10238777A GAS TURBINE COMBUSTOR 失效
公开(公告)号：JPH10238777A
公开(公告)日：1998-09-08
申请号：JP4519297
申请日：1997-02-28
申请人： HITACHI LTD
发明人： HAYASAKA YASUSHI , SAKURAI SHIGEO , ICHIKAWA KUNIHIRO , NAKAHARA SHINICHI , SASADA TETSUO
IPC分类号： F02C7/20 , F23R3/42
摘要： PROBLEM TO BE SOLVED: To provide a combustor for a gas turbine in which the natural frequency of a liner can be easily separated apart from the frequency of combustion vibration and damage to the liner due to the resonance with the combustion vibration can be sufficiently avoided. SOLUTION: In the gas turbine combustor in which a combustor liner 1 in which fuel and air is burned and a tail cylinder which is disposed on the downstream side end of the liner 1 to guide combustion gas to a turbine are provided and the liner 1 includes a sleeve 16 and a lip ring 12 projecting inside the inner wall of the sleeve toward the downstream side, a part of the protruding end of the ring 12 is fixed to the inner wall of the sleeve 16 by, for example, welding.

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