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31. 发明专利

JP2008266698A Heat resistant member with thermal barrier coating 有权
标题翻译：具有热障涂层的耐热构件
公开(公告)号：JP2008266698A
公开(公告)日：2008-11-06
申请号：JP2007108801
申请日：2007-04-18
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： C22C19/05 , C23C4/06 , C23C4/10 , C23C28/00 , F01D5/28 , F01D25/00 , F02C7/00
CPC分类号： F01D5/288 , C22C19/05 , C23C4/073 , C23C4/11 , C23C4/18 , C23C28/3215 , C23C28/325 , C23C28/3455 , C23C30/00 , F05C2201/0466 , F05D2300/12 , F05D2300/132 , F05D2300/21 , Y02T50/67 , Y02T50/671 , Y10T428/12535 , Y10T428/12611
摘要： PROBLEM TO BE SOLVED: To provide a heat resistant member which has a thermal barrier coating excellent in durability and reliability and can be used as a heat resistant member for a gas turbine, an aircraft engine, etc., having extremely high operating temperature. SOLUTION: The surface of a base material of heat resistant alloy composed mainly of Ni is provided with a thermal barrier layer composed of ceramics via a bond coat of alloy composed essentially of Ni as a principal component and also containing Cr and Al. The alloy as the bond coat can contain 0 to 10 wt.% Si. By this method, the peeling damage of the thermal barrier ceramic layer can be minimized during long-term operation, and also deterioration in the mechanical properties of the base material can be minimized. COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：提供一种耐热性构件，该耐热构件具有耐久性和可靠性优异的隔热涂层，并且可以用作具有极高操作性的燃气轮机，飞机发动机等的耐热构件温度。解决方案：以Ni为主要成分的耐热合金基材的表面，由以Ni为主要成分并且还含有Cr和Al的合金的粘结层由陶瓷形成的隔热层。作为粘合涂层的合金可以含有0〜10重量％的Si。通过这种方法，可以在长期运行期间使热障陶瓷层的剥离损伤最小化，并且可以使基材的机械性能的劣化最小化。版权所有（C）2009，JPO＆INPIT

32. 发明专利

JP2006200962A Damage evaluation method of gas turbine part 有权
标题翻译：燃气涡轮机损伤评估方法
公开(公告)号：JP2006200962A
公开(公告)日：2006-08-03
申请号：JP2005011141
申请日：2005-01-19
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： ICHIKAWA KUNIHIRO , KONNO SHINYA , DOI HIROYUKI , KANETANI AKIHIRO , NAGAE MASATAKA
IPC分类号： G01N33/20 , G01M99/00
摘要： PROBLEM TO BE SOLVED: To provide a damage evaluation method of a gas turbine part which enables a reduction of the estimate error of life.
SOLUTION: The damage of the gas turbine part is evaluated on the basis of FEM temperature analyzing results by performing a step (a) for transferring the metal texture of the surface of the gas turbine part to a replica using an electrolytic etching method, a step (b) for observing the replica, on which a conductive substance is vapor-deposited by a scanning electron microscope to measure the mean particle size of a precipitate, a step (c) for estimating a metal temperature from the measured mean particle size of the precipitate and a step (d) for analyzing an FEM temperature using the estimate result of the metal temperature and an inverse problem analyzing technique.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供能够降低生命估计误差的燃气轮机部件的损伤评估方法。解决方案：通过执行使用电解蚀刻方法将燃气轮机部件的表面的金属质感转印到副本的步骤（a），基于FEM温度分析结果来评价燃气轮机部件的损坏，用于观察复制品的步骤（b），通过扫描电子显微镜气相沉积导电物质以测量沉淀物的平均粒度;步骤（c），用于从测量的平均粒子估计金属温度沉淀物的尺寸和使用金属温度的估计结果和逆问题分析技术来分析FEM温度的步骤（d）。版权所有（C）2006，JPO＆NCIPI

33. 发明专利

JP2006063837A Gas turbine 有权
标题翻译：燃气轮机
公开(公告)号：JP2006063837A
公开(公告)日：2006-03-09
申请号：JP2004245435
申请日：2004-08-25
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： ICHIKAWA KUNIHIRO , MOMOZAKI HISATAKA , ENDO TAKAO
IPC分类号： F01D11/08 , F01D5/20 , F01D5/22 , F02C7/28 , F16J15/44
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine capable of improving gas turbine performance by minimizing gaps between turbine moving blade and a stationary body and of preventing fracture of shroud covers. SOLUTION: The gas turbine driving a turbine 3 by combustion gas obtained by burning compressed air together with fuel is provided with the shroud covers 12 out of which the shroud covers 12 adjacent to each other in the blade rotational direction contact with each other to enhance rigidity of the turbine moving blades 6; honeycomb seals 14 provided in shroud blocks 10 so as to oppose to diametrical direction outside of the shroud covers 12; shroud fins 13 which are protruded on diametrical direction outside faces of the shroud covers 12 so as to oppose to the honeycomb seals 14 and are approximately parallel with the blade rotational direction; and cut parts 15 defined by projecting parts 16 projecting outwardly from rotation loci R of contours of linear parts of the shroud fins 13 and weight adjustment parts 17 inclined so as to enter into inside of the rotation loci R toward the blade rotational direction forward side. COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供一种能够通过使涡轮机动叶片与固定体之间的间隙最小化并防止护罩盖的断裂来提高燃气轮机性能的燃气轮机。解决方案：通过燃烧压缩空气与燃料一起燃烧得到的燃烧气体来驱动涡轮机3的燃气轮机设置有护罩罩12，其中叶片旋转方向上彼此相邻的护罩罩12彼此接触以提高涡轮机动叶片6的刚性; 蜂窝密封件14设置在护罩块10中，以便与护罩罩12外侧的直径方向相反; 护罩翅片13，其在护罩罩12的径向外侧突出，以与蜂窝状密封件14相对，并且与刀片旋转方向大致平行; 以及从罩体翅片13的直线部分和重量调节部分17的轮廓线的旋转轨迹R向外突出的突出部分16所限定的切割部分15，其倾斜以朝向叶片旋转方向前侧进入旋转轨迹R的内部。版权所有（C）2006，JPO＆NCIPI

34. 发明专利

JP2004136301A Welding material, welded structure, blade of gas turbine, and method for repairing rotary blade or stationary blade of gas turbine 有权
公开(公告)号：JP2004136301A
公开(公告)日：2004-05-13
申请号：JP2002301549
申请日：2002-10-16
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： KONNO SHINYA , DOI HIROYUKI , ICHIKAWA KUNIHIRO , ISHII HIDEAKI
IPC分类号： F01D5/12 , B23K31/00 , B23K35/30 , C22C19/05 , F01D5/28 , F02C7/00
CPC分类号： C22C19/056 , B23K35/3033 , B23K35/304 , Y10T29/49318 , Y10T428/12944
摘要： PROBLEM TO BE SOLVED: To provide a welded structure and a welding material, which are used in the environment of a temperature above 1000°C. SOLUTION: The welding material is the Ni radical super-alloy which contains 18-25 wt% Co, 15-20 wt% Cr, 1.5-5.5 wt% Al, 5-14 wt% W, 0.05-0.15 wt% C, 0-0.02 wt% B, at least one of 0-1 wt% Ta, Nb, Ti, Mo, Re, and Fe, at least one of 0-0.5 wt% V, Zr, rare earth elements, and Y, and has precipitated γ' phase and Cr carbide including 0-1 wt% Mn, and 0-0.5 wt% Si. The amounts of Al, W, and Co (wt%) of the welding material satisfy the relationship, (GP×0.139+11) COPYRIGHT: (C)2004,JPO

35. 发明专利

JP2004037035A Gas turbine combustor 审中-公开
公开(公告)号：JP2004037035A
公开(公告)日：2004-02-05
申请号：JP2002197599
申请日：2002-07-05
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： ICHIKAWA KUNIHIRO , OKIHARA TOMIO , HAYASAKA YASUSHI , SHIBASHITA NAOAKI , HIROSE FUMIYUKI
IPC分类号： F23R3/42
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine combustor capable of preventing an abnormal stop of a gas turbine plant and damage thereof to improve reliability and profitability of the whole of the gas turbine plant by preventing the generation of a crack in a tie piece. SOLUTION: A transition piece 11 of the gas turbine combustor for burning the air-fuel mixture of the compressed air and the fuel in a combustor liner 24 is provided with a transition piece main body 20 connected to a downstream side of the combustion liner 24, an impingement cover 25 provided to cover a peripheral side of the transition piece main body 20 through a clearance space, a zipper plate 27 for coupling split parts of the impingement cover 25, a connection ring 26 fixed to an upstream side of the impingement cover 25 and divided into a several number in the circumferential direction, and a nearly plate-like tie piece 28 having at least one open tip and for tying the split parts of the connection ring. COPYRIGHT: (C)2004,JPO

36. 发明专利

JP2014084791A High temperature member for gas turbine having thermal barrier coating 有权
标题翻译：具有热障涂层气体涡轮的高温部件
公开(公告)号：JP2014084791A
公开(公告)日：2014-05-12
申请号：JP2012234278
申请日：2012-10-24
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： ARIKAWA HIDEYUKI , KOJIMA YOSHIYUKI , KASUYA TADASHI , MEHATA TERU , ICHIKAWA KUNIHIRO , ENDO HIROYUKI , ENDO TAKAO
IPC分类号： F01D5/28 , F02C7/00 , F23R3/42
CPC分类号： F01D5/288 , C23C4/073 , C23C4/08 , C23C24/04 , C23C28/3215 , C23C28/3455 , F01D5/183 , F01D5/186
摘要： PROBLEM TO BE SOLVED: To provide a high temperature member for a gas turbine having a thermal barrier coating in which heat resistance property is improved.SOLUTION: In a high temperature for a gas turbine having a thermal barrier coating and a cooling structure, fine passages communicating from a base material side to a front face side are provided in the alloy substrate layer of the thermal barrier coating and in a thermal barrier ceramic layer, and a part of refrigerant cooling the member is flowed out to the outside of the member through the fine passages. Consequently, a heat resistant temperature improvement effect of the high temperature member, due to a leaching-out cooling effect, can be expected.
摘要翻译：要解决的问题：提供一种具有耐热性能提高的隔热涂层的燃气轮机的高温部件。解决方案：在具有隔热涂层和冷却结构的燃气轮机的高温下，精细通道在热障涂层的合金基材层和热障陶瓷层中设置从基材侧到正面侧的连通状态，冷却构件的制冷剂的一部分通过罚款。因此，可以预期由于浸出冷却效果而导致的高温部件的耐热温度改善效果。

37. 发明专利

JP2013194617A Gas turbine blade, combustor, shroud and gas turbine employing them 有权
标题翻译：气体涡轮叶片，燃烧器，喷雾器和使用它们的气体涡轮
公开(公告)号：JP2013194617A
公开(公告)日：2013-09-30
申请号：JP2012063007
申请日：2012-03-21
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 , KASUYA TADASHI
IPC分类号： F01D5/28 , C23C28/00 , F02C7/00
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine blade, a combustor and a shroud which have durability and reliability for use under a corrosive environment with the use of a low-grade fuel or the like, and to provide a gas turbine employing them.SOLUTION: A moving blade and a stationary blade for a gas turbine include: a substrate comprised of alloy containing Ni, Co or Fe; a coupling layer provided on the substrate and comprised of alloy; and thermal barrier coating provided on the coupling layer. The thermal barrier coating includes a ceramics thermal-barrier layer having longitudinal cracks and an environmental barrier layer containing silica, and at least a part of the longitudinal cracks in the thermal-barrier layer is impregnated with a substance containing the silica of the environmental barrier layer.
摘要翻译：要解决的问题：提供一种在使用低等级燃料等的腐蚀环境下具有耐久性和可靠性的燃气轮机叶片，燃烧器和护罩，并提供使用它们的燃气轮机。解决方案：用于燃气轮机的动叶片和固定叶片包括：由含有Ni，Co或Fe的合金构成的基底; 设置在基板上并由合金组成的耦合层; 以及设置在耦合层上的热障涂层。隔热涂层包括具有纵向裂纹的陶瓷热障层和含有二氧化硅的环境阻挡层，并且热障层中的纵向裂纹的至少一部分用含有环境阻挡层二氧化硅的物质浸渍。

38. 发明专利

JP2013130494A Long-term creep strength estimation method, residual service life estimation method and residual service life evaluation device for precipitation strengthening type heat resistant alloy 有权
标题翻译：长期侵蚀强度估算方法，残留服务寿命估算方法和残留服务寿命评估装置，用于降低强化类型耐热合金
公开(公告)号：JP2013130494A
公开(公告)日：2013-07-04
申请号：JP2011280799
申请日：2011-12-22
申请人： Hitachi Ltd , 株式会社日立製作所
发明人： KONNO SHINYA , ICHIKAWA KUNIHIRO
IPC分类号： G01N3/18 , C22C19/05 , C22F1/00 , C22F1/10 , G01N33/20
摘要： PROBLEM TO BE SOLVED: To improve prediction accuracy of creep rupture strength of a precipitation strengthening type Ni base superalloy and evaluation accuracy of a residual service life after actual machine use, and to secure long-term reliability of a high temperature component.SOLUTION: A creep rupture test in limited time is performed, rupture stress σ and creep rupture time twhich are the results thereof are used to determine a stress index n of a creep deformation speed and a constant Cin a following equation (5) from following equations (5)-(7) and (2), and long-term creep strength of a precipitation strengthening type heat resistant alloy is estimated using the following equations (5)-(7) and (2): lnσ=-(1/n)lnCMP+C...(5), CMP=((π/F)-2)(d-d)...(6), d=(kt+d)...(7), and k=(C/T)exp(-Q/RT)...(2).
摘要翻译：要解决的问题：提高析出强化型Ni基超级合金的蠕变断裂强度的预测精度，实际机器使用后剩余使用寿命的评价精度，确保高温部件的长期可靠性。解决方案：A 在有限时间内进行蠕变断裂试验，断裂应力＆和蠕变断裂时间，其结果用于确定蠕变变形速度的应力指数n和来自以下等式（5） - （7）和（2）的下式（5）的常数Cin，使用以下等式（5） - （7）和（2）估算沉淀强化型耐热合金的长期蠕变强度：ln＆sgr; = - （1 / n）lnCMP + C ...（5），CMP = （（＆pgr; / F）-2）（dd）...（6），d =（kt + d）...（7），k =（C / T）exp（-Q / RT）。（2）。

39. 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

40. 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

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