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1. 发明专利

JP2011122495A Intermediate product of gas turbine blade, gas turbine blade, gas turbine, method of manufacturing intermediate product of gas turbine blade, and method of manufacturing gas turbine blade 有权
标题翻译：气体涡轮叶片的中间产品，气体涡轮叶片，气体涡轮机，制造气体涡轮叶片中间产品的方法和制造气体涡轮叶片的方法
公开(公告)号：JP2011122495A
公开(公告)日：2011-06-23
申请号：JP2009279830
申请日：2009-12-09
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： HIRATA NORIFUMI , TAKAMURA KEITA , ARASE KENICHI , KOYABU TOSHIMICHI , HANEDA SATORU , SHODA JUNICHIRO , TSUKAGOSHI KEIZO
IPC分类号： F02C7/00 , F01D5/14
摘要： PROBLEM TO BE SOLVED: To provide an intermediate product of a gas turbine blade allowing performance of both external working and internal working while securing desired accuracy, a method of manufacturing the intermediate product, the gas turbine blade, a method of manufacturing the gas turbine blade, and a gas turbine.
SOLUTION: The intermediate product 20 of the gas turbine blade includes: a first reference point group provided on the external face and constituted of a plurality of first reference points 21 for performing positioning when machining the shape of the external face; and a second reference point group provided on the external face and constituted of a plurality of second reference points 22 for performing positioning when machining holes, among which at least one place is provided at a position different from the first reference points 21.
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种允许外部加工和内部工作同时确保期望精度的燃气轮机叶片的中间产品，制造中间产品的方法，燃气轮机叶片，制造方法燃气轮机叶片和燃气轮机。燃气轮机叶片的中间产品20包括：第一参考点组，设置在外表面上并且由多个第一参考点21构成，用于在加工外表面的形状时进行定位; 以及设置在外表面上并由多个第二参考点22构成的第二参考点组，用于在加工孔时进行定位，其中至少一个位置设置在与第一参考点21不同的位置。版权所有（C）2011，JPO＆INPIT

2. 发明专利

JP2010276010A Turbine vane, method for manufacturing turbine vane, and gas turbine 有权
标题翻译：涡轮风扇，制造涡轮风扇的方法和气体涡轮
公开(公告)号：JP2010276010A
公开(公告)日：2010-12-09
申请号：JP2009268850
申请日：2009-11-26
申请人： Mitsubishi Heavy Ind Ltd , Tohoku Electric Power Co Inc , 三菱重工業株式会社 , 東北電力株式会社
发明人： MIZUKAMI SATOSHI , ISHIGURO TATSUO , SHODA JUNICHIRO , TAKADA KAZUMASA , TORII SHUNSUKE , FUKUNAGA YUYA , NISHIMURA YOSHIAKI , ONDA TOKUO , SATO MAKI
IPC分类号： F01D5/18 , F01D9/02 , F02C7/00 , F02C7/18
摘要： PROBLEM TO BE SOLVED: To provide a turbine vane, which is configured so that a cooling flow passage can be easily and accurately formed in the inner part, and thermal stress in operation can be suppressed, a method for manufacturing the turbine vane, and a gas turbine. SOLUTION: The turbine stator vane 10 includes an outer frame 20 formed in a cylindrical shape along the vane height direction to form an outer sheath, a support part 21 provided within the outer frame 20 and supported by the outer frame 20, and an insert member 22 inserted into the outer frame 20 while securing a gap that forms a cooling flow passage 11b with the inner circumferential surface of the outer frame 20, and fixed to the support part 21 at only one of both ends in the vane height direction thereof. COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种涡轮叶片，其构造成能够在内部容易且精确地形成冷却流路，并且可以抑制运转中的热应力，制造涡轮叶片的方法，和燃气轮机。解决方案：涡轮机定子叶片10包括沿着叶片高度方向形成为圆柱形的外框架20以形成外护套，设置在外框架20内并由外框20支撑的支撑部21，以及插入构件22，同时固定与外框架20的内周面形成冷却流路11b的间隙，并且仅在叶片高度方向的两端中的一端固定到支撑部21 它们。版权所有（C）2011，JPO＆INPIT

3. 发明专利

JP2017116272A 溶融塩浸透試験装置、および、溶融塩浸透試験方法审中-公开
公开(公告)号：JP2017116272A
公开(公告)日：2017-06-29
申请号：JP2015248507
申请日：2015-12-21
申请人：三菱重工業株式会社 , Mitsubishi Heavy Ind Ltd
发明人： KUDO DAISUKE , TORIGOE TAIJI , SHODA JUNICHIRO , TAKAHASHI KOJI , KAMIMURA YOSHIHISA , OKAJIMA YOSHIFUMI , OKAYA NAOTOSHI , ITO EISAKU , MEGA MASAHIKO , HORIE SHIGENARI , TANIGAWA HIDETSUGU , TSURU YASUHIKO , TSUKAGOSHI KEIZO , KUWABARA MASAMITSU , MITSUI HIROYUKI
IPC分类号： G01N17/00
CPC分类号： G01N17/00
摘要：【課題】装置の大型化を抑制しつつ、遮熱コーティングに対する溶融塩の浸透状態を正しく評価することが可能な溶融塩浸透試験装置、および、溶融塩浸透試験方法を提供する。【解決手段】溶融塩浸透試験装置20は、圧縮空気と燃料とを混合して燃焼させることで燃焼ガスを得る燃焼器21と、前記燃焼ガスに塩を供給する塩供給部30と、遮熱コーティングにより表面が被覆された試験片1を収容して支持する収容支持部23と、前記塩が供給された前記燃焼ガスを加速させて前記試験片に衝突させる加速器24と、を備える。【選択図】図2

4. 发明专利

JP2014034720A Ni-BASED SINGLE CRYSTAL SUPERALLOY 有权
标题翻译：镍基单晶超级合金
公开(公告)号：JP2014034720A
公开(公告)日：2014-02-24
申请号：JP2012177573
申请日：2012-08-09
申请人： National Institute For Materials Science , 独立行政法人物質・材料研究機構 , Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： KAWAGISHI KYOKO , HARADA KOJI , YOKOGAWA TADAHARU , KOIZUMI YUTAKA , KOBAYASHI TOSHIHARU , SAKAMOTO MASAO , YUYAMA MICHIYA , TANEIKE MASAKI , OKADA IKUO , SHIMOHATA SACHIO , OGUMA HIDETAKA , OKIMOTO RYOTA , TSUKAGOSHI KEIZO , KAMIMURA YOSHIHISA , SHODA JUNICHIRO , TORII SHUNSUKE
IPC分类号： C22C19/05 , C22F1/00 , C22F1/10 , F01D5/28 , F01D25/00 , F02C7/00
CPC分类号： C22C19/057 , C22C19/056 , C22F1/10 , C30B11/00 , C30B29/52 , C30B33/02 , F01D5/28 , F05D2300/132 , F05D2300/175 , F05D2300/607 , Y02T50/671
摘要： PROBLEM TO BE SOLVED: To provide Ni-based single crystal superalloy excellent in TMF characteristics, creep characteristics and environment-resistant characteristics, having small direction dependance of creep characteristics, and excellent in cost performance in practical use.SOLUTION: The Ni-based single crystal superalloy contains Cr:6 mass% to 12 mass%, Mo:0.4 mass% to 3.0 mass%, W:6 mass% to 10 mass%, Al:4.0 mass% to 6.5 mass%, Nb:0 mass% to 1 mass%, Ta:8 mass% to 12 mass%, Hf:0 mass% to 0.15 mass%, Si:0.01 mass% to 0.2 mass% and Zr:0 mass% to 0.04 mass%, may contain at least one element of B, C, Y, La, Ce or V and contains the balance Ni with inevitable impurities.
摘要翻译：要解决的问题：提供优异的TMF特性，蠕变特性和耐环境特性的Ni基单晶超合金，具有蠕变特性小的方向依赖性，并且在实际应用中具有优异的成本性能。解决方案：Ni基单结晶超合金含有Cr：6质量％〜12质量％，Mo：0.4质量％〜3.0质量％，W：6质量％〜10质量％，Al：4.0质量％〜6.5质量％，Nb：0质量％〜1 质量％，Ta：8质量％〜12质量％，Hf：0质量％〜0.15质量％，Si：0.01质量％〜0.2质量％，Zr：0质量％〜0.04质量％ B，C，Y，La，Ce或V，并且余量为Ni和不可避免的杂质。

5. 发明专利

JP2010001841A Moving blade and gas turbine 审中-公开
标题翻译：移动叶片和气体涡轮机
公开(公告)号：JP2010001841A
公开(公告)日：2010-01-07
申请号：JP2008162166
申请日：2008-06-20
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： WAKAZONO SUSUMU , YURI MASANORI , SHODA JUNICHIRO
IPC分类号： F01D5/14 , F01D5/18 , F01D11/02 , F01D25/00 , F02C7/28
摘要： PROBLEM TO BE SOLVED: To provide a moving blade having a reliability improved by reducing the concentration of gas bending stress and thermal stress and also provide a gas turbine.
SOLUTION: This moving blade comprises: a blade attaching section 21 and a shank 22 detachable from a rotor; a platform 23 extending from the outer end of the shank 22 in the axial and circumferential directions of the rotor; an aerofoil section 24 extending from the outer peripheral surface of the platform 23 radially outward; a side wall section 61 which extends from the inner peripheral surface of the connection section of the platform 23 with the leading edge 51 of the aerofoil section 24 radially inward and circumferentially and which is disposed detachably from the platform 23; a moving blade side projecting section 62 extending from the surface of the side plate section 61 on the leading edge 51 side in the axial direction of the rotor and extending from the trailing edge to the leading edge of the aerofoil section 24 circumferentially.
COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：解决的问题：提供通过降低气体弯曲应力和热应力的浓度而提高可靠性的动叶片，并且还提供燃气轮机。解决方案：该动叶片包括：叶片安装部分21和可从转子上拆卸的柄部22; 从柄22的外端沿转子的轴向和圆周方向延伸的平台23; 从平台23的外周面径向向外延伸的机翼部24; 从平台23的连接部的内周面延伸的侧壁部61与翼面部24的前缘51径向向内且周向延伸，并且与台架23可拆卸地配置; 从侧板部61的表面沿着转子的轴向的前缘51侧延伸并沿着圆周方向从机翼部24的后缘延伸到前缘的动叶片侧突出部62。版权所有（C）2010，JPO＆INPIT

6. 发明专利

JP2004044572A Turbine blade and gas turbine equipped with its turbine blade 有权
公开(公告)号：JP2004044572A
公开(公告)日：2004-02-12
申请号：JP2003016736
申请日：2003-01-24
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： HANEDA SATORU , KUWABARA MASAMITSU , TOMITA YASUOKI , SOECHTING FRIEDRICH , SHODA JUNICHIRO
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/186 , F01D5/189 , F05D2250/70 , F05D2260/202
摘要： PROBLEM TO BE SOLVED: To provide a turbine blade and a gas turbine equipped with this turbine blade for reducing the amount of a cooling air, improving performance of the whole gas turbine, and minimizing a temperature difference over the whole gas turbine blade body.
SOLUTION: This turbine blade 100 has the turbine blade body 120 provided with a plurality of film cooling holes 121 and forming at least two cavities C1 and C2 inside by at least one rib 122 and a hollow insert 30 arranged in the respective cavities C1 and C2 so as to form cooling spaces C and S between an outer peripheral surface 32 of itself and an inner peripheral surface 125 of the turbine blade body 120 and provided with a plurality of impingement holes 31. The rib 122 is provided with a communicating means 140 for communicating the cavity C1 positioned on the front edge L.E. side to the rib 122 with the cavity C2 positioned on the rear edge T.E. side.
COPYRIGHT: (C)2004,JPO

7. 发明专利

JP2014058979A Gas turbine and its rated operational method 有权
标题翻译：燃气轮机及其额定运行方法
公开(公告)号：JP2014058979A
公开(公告)日：2014-04-03
申请号：JP2013245017
申请日：2013-11-27
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： MIZUKAMI SATOSHI , ISHIGURO TATSUO , SHODA JUNICHIRO , TAKADA KAZUMASA , FUKUNAGA YUYA , NISHIMURA YOSHIAKI , TAKAHASHI HIROKI
IPC分类号： F01D11/08 , F01D25/12 , F01D25/14 , F01D25/16 , F02C7/00 , F02C7/141 , F02C7/18 , F02C7/28 , F02C9/00
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine that can achieve the improvement of cooling efficiency of a turbine static system component in an active clearance control (ACC) system during rated operation of the gas turbine.SOLUTION: The gas turbine comprises a pressure rise device 40 that is connected to a branch flow passage 42, which is branched from a discharge side of a compressor 11, and capable of operating independently of the compressor 11 which boosts introduced air; a temperature control medium supply flow channel 43 that introduces compressed air boosted by the pressure rise device 40 to a turbine cooling medium flow passage 50 disposed in the static system component of a turbine 13; and a temperature control medium return flow passage 44 in which the compressed air which passes through the turbine cooling medium flow passage 50 is introduced and merged on the discharge side. The pressure rise device 40 operates during gas turbine rated operation and makes the compressed air flow into a blade ring of the turbine 13 via the inside of the turbine cooling medium flow passage 50 for cooling it.
摘要翻译：要解决的问题：提供一种燃气轮机，其能够在燃气轮机的额定运行期间实现主动间隙控制（ACC）系统中的涡轮机静态系统部件的冷却效率的提高。解决方案：燃气涡轮机包括压力升高装置40，其连接到从压缩机11的排出侧分支的分支流路42，并且能够独立于压缩机11运行，该压缩机11增强引入的空气; 温度控制介质供给流路43，其将由升压装置40升压的压缩空气引导到设置在涡轮13的静止系统部件中的涡轮冷却介质流路50; 以及温度控制介质返回流路44，通过涡轮冷却介质流路50的压缩空气在排出侧导入并合流。压力升高装置40在燃气轮机额定运行期间运行，并且使得压缩空气经由涡轮机冷却介质流动通道50的内部流入涡轮机13的叶片环，用于对其进行冷却。

8. 发明专利

JP2012177420A Shaft sealing mechanism 有权
标题翻译：轴封密封机构
公开(公告)号：JP2012177420A
公开(公告)日：2012-09-13
申请号：JP2011040372
申请日：2011-02-25
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： MORIMOTO HITOSHI , TSUKAGOSHI KEIZO , SHODA JUNICHIRO , TAKAHASHI TATSUJI , ARAKI KATSUTO , SHINOHARA TANEHIRO , UEHARA HIDEKAZU
IPC分类号： F16J15/447 , F01D11/00 , F02C7/28 , F16J15/22
CPC分类号： F01D11/02 , F04D29/10 , F04D29/102 , F05D2240/57 , F05D2250/75 , F16J15/3288
摘要： PROBLEM TO BE SOLVED: To prevent a thin plate from being worn due to the failure of pressure distribution around the thin plate, by keeping the pressure distribution around the thin plate in a good state even if the thin plate is tilted in an axial direction of a rotating shaft due to error in manufacturing or assembly of each component.SOLUTION: An inner wall surface 18c of a side plate 18 adjacent to a low pressure area, the inner wall surface facing a side surface of a thin plate 12, is formed along a direction across the axial direction of the rotating shaft such that a clearance between the inner wall surface 18c and the thin plate 12 decreases gradually from the radially inward direction to the radially outward direction of the side plate 18 adjacent to the low pressure area.
摘要翻译：要解决的问题：为了防止由于薄板周围的压力分布的故障而使薄板磨损，通过将薄板周围的压力分布保持在良好状态，即使薄板倾斜在由于每个部件的制造或组装错误，旋转轴的轴向方向。解决方案：沿着旋转轴的轴向的方向，形成与低压区域相邻的侧板18的内壁面18c，内壁面与薄板12的侧面相对，内壁面18c和薄板12之间的间隙从与低压区域相邻的侧板18的径向向内的方向逐渐减小。版权所有（C）2012，JPO＆INPIT

9. 发明专利

JP2011153540A Split ring cooling structure and gas turbine 有权
标题翻译：分体式冷却结构和气体涡轮机
公开(公告)号：JP2011153540A
公开(公告)日：2011-08-11
申请号：JP2010014356
申请日：2010-01-26
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： KOYABU TOSHIMICHI , HANEDA SATORU , SHODA JUNICHIRO , TSUKAGOSHI KEIZO
IPC分类号： F02C7/18 , F01D11/00 , F01D25/00 , F02C7/28
CPC分类号： F01D25/246 , F01D9/04 , F01D11/005 , F01D11/24 , F01D25/12 , F05D2240/11 , F05D2260/205
摘要： PROBLEM TO BE SOLVED: To provide a split ring cooling structure improving the thermal efficiency of a whole gas turbine by reducing the amount of cooling air to cool the side ends of split bodies while preventing the oxidation and wastage of the split bodies, and to provide the gas turbine. SOLUTION: The split ring cooling structure for the gas turbine includes the plurality of split bodies arranged in a ring shape around a rotating shaft, and sealing plates for sealing clearances between the side ends of the adjacent split bodies, opposing each other along the direction of the rotating shaft. The split bodies each include a first cooling flow path arranged in the body of the split body in the axial direction of the rotating shaft and formed with a cooling flow path in a first region and a cooling flow path in a second region having a smaller flow path cross section than the cooling flow path in the first region, and a second cooling flow path arranged at one side end thereof in the direction approximately perpendicular to the first cooling flow path for blowing cooling air toward the side ends of the adjacent split bodies. The cooling flow path in the first region is arranged neighboring the second cooling flow paths of the adjacent split bodies. COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：为了提供一种分裂环冷却结构，通过减少冷却空气的量使整个燃气轮机的热效率提高，同时防止分裂体的氧化和浪费，并提供燃气轮机。解决方案：用于燃气轮机的开口环冷却结构包括围绕旋转轴布置成环形的多个分体，以及用于密封相邻分裂体的侧端之间的间隙的密封板，沿着旋转轴的方向。开口体各自包括沿着旋转轴的轴向布置在分体的主体中的第一冷却流路，并且在第一区域中形成有冷却流路，并且在具有较小流动的第二区域中形成冷却流路所述第二冷却流路沿与所述第一冷却流路大致垂直的方向配置在所述第一冷却流路的一侧，用于向相邻的分割体的侧端吹出冷却空气。第一区域中的冷却流路与相邻分割体的第二冷却流路相邻配置。版权所有（C）2011，JPO＆INPIT

10. 发明专利

JP2010090818A Gas turbine and its rated operating method 有权
标题翻译：燃气轮机及其额定工作方法
公开(公告)号：JP2010090818A
公开(公告)日：2010-04-22
申请号：JP2008262074
申请日：2008-10-08
申请人： Mitsubishi Heavy Ind Ltd , Tohoku Electric Power Co Inc , 三菱重工業株式会社 , 東北電力株式会社
发明人： MIZUKAMI SATOSHI , ISHIGURO TATSUO , SHODA JUNICHIRO , TAKADA KAZUMASA , FUKUNAGA YUYA , NISHIMURA YOSHIAKI , TAKAHASHI HIROKI
IPC分类号： F02C7/18 , F01D25/12 , F02C6/08 , F02C9/18
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine achieving the enhancement of cooling efficiency of a turbine static system component in an ACC system during gas turbine rated operation.
SOLUTION: A gas turbine is provided with: a booster 40 which is connected to a branch flow path 42 branching off from a discharge side of a compressor 11 and which can be operated independently from the compressor 11 for introducing and boosting air; a temperature adjusting medium supply flow path 43 which leads the boosted compressed air boosted by the booster 40 to a turbine cooling medium flow path 50 provided in a static system component of a turbine 13; and a temperature adjusting medium return flow path 44 which leads the compressed air passing through the turbine cooling medium flow path 50 to the discharge side to merge therewith, and carries out cooling by operating the booster 40 to flow compressed air in the turbine cooling medium flow path 50 when the gas turbine is under gas turbine rated operation.
COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种在燃气轮机额定运行期间实现ACC系统中的涡轮机静态系统部件的冷却效率的燃气轮机。解决方案：燃气轮机设置有：增压器40，其连接到从压缩机11的排出侧分支的分支流路42，并且能够独立于压缩机11运行，用于引入和增压空气; 温度调节介质供应流路43，其将由增压器40升压的增压压缩空气引导到设置在涡轮13的静态系统部件中的涡轮冷却介质流路50; 以及温度调节介质回流路径44，其将通过涡轮机冷却介质流路50的压缩空气引导到排出侧与其并入，并通过操作增压器40来进行冷却，以使涡轮机冷却介质流中的压缩空气流动当燃气轮机处于燃气轮机额定运行时的路径50。版权所有（C）2010，JPO＆INPIT

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