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. 发明专利

JP2015038358A ガスタービン有权
标题翻译：燃气轮机
公开(公告)号：JP2015038358A
公开(公告)日：2015-02-26
申请号：JP2014238277
申请日：2014-11-25
申请人：三菱重工業株式会社 , Mitsubishi Heavy Ind Ltd
发明人： MIZUKAMI SATOSHI , ISHIGURO TATSUO , YAGI KATSUKI , HANEDA SATORU , KUWABARA MASAMITSU , FUKUI YOSHIO , MORIKAWA TOMOKO
IPC分类号： F01D9/02 , F01D25/00 , F02C7/18
摘要：【課題】翼内に入り込んだゴミによって冷却孔が塞がれてしまうことを効率良く抑制することができるガスタービンを提供する。【解決手段】本発明は、断面翼形状で内部に空気流入口14aから冷却孔まで冷却空気が流れる冷却流路が形成された翼体と、前記翼体が取り付けられると共に、空気供給口7aから供給された前記冷却空気を前記冷却流路の空気流入口14aに供給する供給流路を有するケーシング7と、を備え、前記供給流路の空気供給口7aに配置され、上流側に開口すると共に流入する冷却空気を下流側に流通させる空気放出孔17aと、底部にゴミを貯留する貯留部17bと、を有するゴミ受部17を備えていることを特徴とする。【選択図】図4
摘要翻译：要解决的问题：提供一种有效地阻止冷却孔被灰尘进入叶片的燃气轮机。解决方案：本发明包括：具有翼型形状的叶片体，每个叶片体具有形成在其中的冷却通道，其中冷却空气从空气流入口14a流到冷却孔; 以及安装有叶片体的壳体7，壳体7具有用于将从空气供给口7a供给的冷却空气供给到冷却通路的空气流入口14a的供给通路。本发明还包括设置在供给通道的供气口7a处的污物接收部分17，并且包括在上游侧开口并使流入其下游侧的冷却空气循环的空气释放孔17a和存储部17b 其在底部存储污物。

2. 发明专利

JP2013144994A Turbine blade and method for cooling the same 有权
标题翻译：涡轮叶片及其冷却方法
公开(公告)号：JP2013144994A
公开(公告)日：2013-07-25
申请号：JP2013095137
申请日：2013-04-30
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： TAKAMURA KEITA , ITO EISAKU , SHODA JUNICHIRO , HANEDA SATORU
IPC分类号： F01D5/18 , F01D5/20 , F01D9/02 , F01D25/12 , F01D25/24
CPC分类号： F01D5/225
摘要： PROBLEM TO BE SOLVED: To provide a turbine blade that can reduce the supply pressure of a cooling medium supplied to a blade root and can reduce a seal leakage air volume from a cavity formed at the blade root to improvement the performance of a gas turbine.SOLUTION: In a turbine blade 1, a plurality of first cooling passages 4 project along a blade shaft direction. A first tapered part 15 is formed to be a folding fan toward a blade edge at an end of an outlet side of the first cooling passage 4.
摘要翻译：要解决的问题：提供一种涡轮叶片，其能够降低供给到叶片根部的冷却介质的供给压力，并且可以减少从形成在叶根处的空腔的密封泄漏空气量，从而改善燃气轮机的性能。解决方案：在涡轮叶片1中，多个第一冷却通道4沿叶片轴方向突出。第一锥形部15形成为朝向第一冷却通道4的出口侧的端部处的叶片边缘的折叠风扇。

3. 发明专利

JP2013072316A Transition piece of combustor, gas turbine having the same, and method for manufacturing transition piece 有权
标题翻译：燃气轮机的过渡部件，具有其的燃气轮机，以及制造过渡部件的方法
公开(公告)号：JP2013072316A
公开(公告)日：2013-04-22
申请号：JP2011210710
申请日：2011-09-27
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： HANEDA SATORU , NAKAMURA SOSUKE , TANAKA KATSUNORI , AKAGI KOICHI , KONISHI SATORU , SHIBATA HIROKI
IPC分类号： F02C7/18 , F01D25/12 , F02C7/00 , F23R3/42
CPC分类号： F01D9/023 , F23R3/002 , F23R3/005 , F23R3/60 , F23R2900/00017 , F23R2900/00018 , F23R2900/03043
摘要： PROBLEM TO BE SOLVED: To provide a transition piece of combustor capable of enduring conditions with a more severe thermal environment.SOLUTION: The transition piece 20 of combustor includes: a tubular trunk body 21; a tubular outlet trunk 32 which is joined to the downstream end of the trunk body and which forms a trunk B in cooperation with the trunk body; and an inner flange 36 which extends from the downstream end of the outlet trunk toward the outer peripheral side of the outlet trunk. The outlet trunk 32 and the inner flange 36 are formed as an integrated member. In the outlet trunk 32, a groove 35 is formed on the upstream side of the inner flange at a position along the inner flange, being recessed from the outer peripheral side to the inner peripheral side and extending in the circumferential direction. Further, in the outlet trunk 32, a cooling fluid path 33 is formed, extending along an axis Ac of the trunk B, and opening to the groove.
摘要翻译：要解决的问题：提供一种能够具有更严格的热环境的耐久条件的燃烧器的过渡片。解决方案：燃烧器的过渡件20包括：管状主体21; 管状出口主干32，其与躯干主体的下游端连接并与躯干主体配合形成躯干B. 以及从出口主干的下游端向出口主干的外周侧延伸的内凸缘36。出口主干32和内凸缘36形成为一体的构件。在出口主干32中，在内凸缘的上游侧，沿着内凸缘的位置，在外周侧向内周侧凹陷并沿圆周方向延伸形成有槽35。此外，在出口主干32中，形成有沿着树干B的轴线Ac延伸并且向槽开口的冷却流体路径33。版权所有（C）2013，JPO＆INPIT

4. 发明专利

JP2012237292A Turbine stator vane 有权
标题翻译：涡轮定子槽
公开(公告)号：JP2012237292A
公开(公告)日：2012-12-06
申请号：JP2011108399
申请日：2011-05-13
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： UECHI HIDEYUKI , MORIKAWA TOMOKO , HANEDA SATORU
IPC分类号： F01D9/02 , F02C7/18
CPC分类号： F01D9/023 , F01D5/18 , F01D5/187 , F01D5/188 , F01D5/189 , F01D9/041 , F05D2240/81 , F05D2260/201 , F05D2260/202
摘要： PROBLEM TO BE SOLVED: To suppress the occurrence of deformation or damage by evenly cooling a vane structure part or an end wall structure part in a turbine stator vane and a gas turbine.SOLUTION: An outer shroud 45 is fixed to one end of a vane body 44 forming a hollow shape, an inner shroud 46 is fixed to the other end, and a cavity 61 that is continuous between a vane body 44, the outer shroud 45, the inner shroud 46, and a partition plate 55 is formed by fixing the partition plate 55 to the vane body 44, the outer shroud 45, and the inside of the inner shroud 46. Many cooling holes 52 are formed in the vane body 44, the outer shroud 45, and the inner shroud 46, and many through-holes 65 are formed in the partition plate 55.
摘要翻译：要解决的问题：通过均匀地冷却涡轮机定子叶片和燃气轮机中的叶片结构部件或端壁结构部件来抑制变形或损坏的发生。解决方案：外护罩45固定到形成中空形状的叶片体44的一端，内护罩46固定到另一端，空腔61连接在叶片体44，外侧护罩45，内护罩46和隔板55通过将分隔板55固定到叶片体44，外护罩45和内护罩46的内部而形成。许多冷却孔52形成在叶片主体44，外护罩45和内护罩46，以及许多通孔65形成在隔板55中。（C）版权所有（C）2013，JPO＆INPIT

5. 发明专利

JP2012177377A Gas turbine blade and gas turbine equipped therewith 有权
标题翻译：燃气涡轮叶片和燃气涡轮机
公开(公告)号：JP2012177377A
公开(公告)日：2012-09-13
申请号：JP2012137010
申请日：2012-06-18
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： HANEDA SATORU , YURI MASANORI
IPC分类号： F01D5/18 , F01D9/02 , F01D25/12 , F02C7/18
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine blade capable of improving the heat transfer performance of a serpentine flow path.SOLUTION: The serpentine flow path is formed of second-fourth cooling flow paths 12B, 12C, 12D so that the second cooling flow path 12B is situated at the most downstream side. A first wall 22A and a third wall 22C are disposed so that a space therebetween is gradually wider from the belly side toward the back side of the blade. A second wall 24B extends approximately parallel to the first wall 22A. A second flow path 12B having an approximately square cross section is formed of the first wall 22A, a back sidewall 4B of the blade, the second wall 24B and a belly sidewall 4A of the blade. A third flow path 12C having an approximately triangular cross section is formed of the second wall 24B, the belly sidewall 4A of the blade and the third wall 22C.
摘要翻译：要解决的问题：提供一种能够提高蛇形流路的传热性能的燃气轮机叶片。解决方案：蛇形流动路径由第二第四冷却流路12B，12C，12D形成，使得第二冷却流路12B位于最下游侧。第一壁22A和第三壁22C被设置成使得它们之间的空间从叶片的腹侧向后侧逐渐变宽。第二壁24B大致平行于第一壁22A延伸。具有大致正方形横截面的第二流路12B由叶片的第一壁22A，叶的后侧壁4B，第二壁24B和叶片的腹部侧壁4A形成。具有大致三角形横截面的第三流路12C由第二壁24B，叶片的腹部侧壁4A和第三壁22C形成。版权所有（C）2012，JPO＆INPIT

6. 发明专利

JP2012087809A High-temperature member for gas turbine 有权
标题翻译：用于气体涡轮机的高温部件
公开(公告)号：JP2012087809A
公开(公告)日：2012-05-10
申请号：JP2012023393
申请日：2012-02-06
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： UECHI HIDEYUKI , KAWADA YUTAKA , MATSUURA MASAAKI , SUENAGA KIYOSHI , SUGISHITA HIDEAKI , YAMAMOTO HIROYUKI , HANEDA SATORU
IPC分类号： F01D5/18 , F01D9/02 , F02C7/18
CPC分类号： F01D5/186 , F01D9/065 , F05D2240/11 , F05D2240/81 , F05D2250/711 , F05D2250/712 , F05D2250/713 , F05D2250/75 , F05D2260/202 , F05D2260/204 , F23R3/002 , F23R2900/03042
摘要： PROBLEM TO BE SOLVED: To provide a high-temperature member for a gas turbine which can uniformize a thickness of a membrane of a coolant formed on a surface of the high-temperature member for a gas turbine in the crosswise direction, and is equipped with film cooling holes which can exclude unevenness of film cooling.SOLUTION: In the high-temperature member 170 for a gas turbine, the membrane of the coolant is formed on a surface 10a by the coolant blown off from a plurality of film cooling holes 174 in which heat transfer from a high-temperature gas is suppressed. The high-temperature member is configured so that two flow paths serving as the inflow part 175 of the film cooling holes 174 are provided at separate positions, an angle formed by central axes of these flow paths and a central axis of the flow path in the outflow part 176 of the film cooling holes 174 becomes an obtuse angle, and an angle formed by the central axis of the flow path in the outflow part 176 of the film cooling holes 174 and the surface 10a becomes an acute angle.
摘要翻译：要解决的问题：提供一种用于燃气轮机的高温部件，该高温部件能够使形成在燃气轮机的高温部件的表面上的冷却剂的膜的横向厚度均匀化，以及配有可以排除薄膜冷却不均匀的薄膜冷却孔。解决方案：在用于燃气轮机的高温构件170中，通过从多个膜冷却孔174吹出的冷却剂在表面10a上形成冷却剂膜，其中从多个膜冷却孔174中传递高温气体被压制高温部件被构造为使得用作薄膜冷却孔174的流入部分175的两个流动路径设置在分开的位置，由这些流动路径的中心轴线形成的角度和流动路径的中心轴线薄膜冷却孔174的流出部分176变成钝角，并且由薄膜冷却孔174的流出部分176中的流动路径的中心轴线和表面10a形成的角度成为锐角。版权所有（C）2012，JPO＆INPIT

7. 发明专利

JP2009287511A Turbine blade 有权
标题翻译：涡轮叶片
公开(公告)号：JP2009287511A
公开(公告)日：2009-12-10
申请号：JP2008142926
申请日：2008-05-30
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： OKAJIMA YOSHIFUMI , HANEDA SATORU
IPC分类号： F01D9/02 , F01D5/18 , F02C7/18
摘要： PROBLEM TO BE SOLVED: To even out the temperature of metal forming a blade trailing edge portion and to reduce the flow rate of a cooling medium. SOLUTION: In this turbine blade 10, the cooling medium is passed through a passage 16c formed in the trailing edge portion of a blade body 11 and the cooling medium is blown off from an outlet 32 formed in the trailing edge of the blade body 11, thereby the trailing edge portion of the blade body 11 is cooled. A plurality of pin fins 26 projecting in the passage 16c are arranged in order to keep the flow velocity of the cooling medium substantially constant. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：为了均匀地形成形成刀片后缘部分的金属的温度并且降低冷却介质的流量。解决方案：在该涡轮叶片10中，冷却介质通过形成在叶片主体11的后缘部分中的通道16c，并且冷却介质从形成在叶片后缘中的出口32吹出主体11，从而叶片主体11的后缘部分被冷却。布置在通道16c中的多个销散热片26，以便使冷却介质的流速基本保持不变。版权所有（C）2010，JPO＆INPIT

8. 发明专利

JP2009091911A Gas turbine blade 有权
标题翻译：气体涡轮叶片
公开(公告)号：JP2009091911A
公开(公告)日：2009-04-30
申请号：JP2007260847
申请日：2007-10-04
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： UECHI HIDEYUKI , HANEDA SATORU
IPC分类号： F01D5/18
摘要： PROBLEM TO BE SOLVED: To increase efficiency in cooling at the both of base side and an end side of a turbine blade.
SOLUTION: A turbine blade 10 includes a blade main body 11 having flow passages 31 to 33 internally formed, and a first structure 41 extending in the base to end direction of the blade main body 11. The flow passages 31 to 33 include a first flow passage part 31a extending in the base to end direction from the base 13 to the end 12 of the blade main body 11. The blade main body 11 is tapered from the base 13 to the end 12. The first flow passage part 31a is composed of only a first flow passage base side part 31w at the base 13 side, and a first flow passage end side part 31v at the end 12 side. The first structure 41 is provided in the first flow passage base side part 31w, but is not provided in the first flow passage end side part 31v.
COPYRIGHT: (C)2009,JPO&INPIT
摘要翻译：要解决的问题：为了提高涡轮叶片的基部侧和端部侧的冷却效率。解决方案：涡轮机叶片10包括具有内部形成有流动通道31至33的叶片主体11和沿着叶片主体11的底部方向延伸的第一结构41.流动通道31至33包括从基座13延伸到叶片主体11的端部12的端部方向上延伸的第一流路部31a。叶片主体11从基部13向端部12成锥形。第一流路部31a 仅由底座13侧的第一流路基部侧部31w，端部12侧的第一流路端侧部31v构成。第一结构41设置在第一流路基部侧部31w中，但不设置在第一流路端侧部31v中。版权所有（C）2009，JPO＆INPIT

9. 发明专利

JP2007231876A Blade cooling structure for gas turbine 有权
标题翻译：气体涡轮叶片冷却结构
公开(公告)号：JP2007231876A
公开(公告)日：2007-09-13
申请号：JP2006056449
申请日：2006-03-02
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： FUJIMURA DAIGO , SUGISHITA HIDEAKI , MATSUURA MASAAKI , SUENAGA KIYOSHI , YAMAMOTO HIROYUKI , TORII SHUNSUKE , HANEDA SATORU
IPC分类号： F01D5/18
摘要： PROBLEM TO BE SOLVED: To provide a blade cooling structure for a gas turbine capable of reducing pressure loss of cooling medium without dropping heat transfer coefficient.
SOLUTION: This structure is provided with a cooling channel 15 making cooling air A flow from a base end part 12 of the moving blade 11 and a plurality of turbulator 21 arranged obliquely to a flow direction of cooling air A on both wall surfaces facing to the cooling passage 15, and a plurality of dimples formed in a downstream area N in a downstream of a center position O in a flow direction of cooling air A on the wall surface of a cooling channel 15 between adjoining turbulators 21 are provided.
COPYRIGHT: (C)2007,JPO&INPIT

10. 发明专利

JP2004084604A Platform repair method for turbine rotor blade and turbine rotor blade 审中-公开
标题翻译：涡轮转子叶片和涡轮转子叶片平台维修方法
公开(公告)号：JP2004084604A
公开(公告)日：2004-03-18
申请号：JP2002248957
申请日：2002-08-28
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： HANEDA SATORU , TOMITA YASUOKI , OTOMO HIROYUKI , KANEKO HIDEAKI
IPC分类号： F01D5/14 , B23K26/00 , B23K26/20 , F02C7/00
CPC分类号： B23P6/005
摘要： PROBLEM TO BE SOLVED: To provide a method for appropriately repairing damages generated in the platform of a uni-directional solidified turbine rotor blade. SOLUTION: The platform repair method comprises a damaged parts removing process for completely piercing a crack part and forming a thorough-hole 4 tapered towards a centrifugal direction, an insert material fitting process for fitting an insert material 5 into the hole 4, and a welding process for conducting laser welding at the point of contact. The turbine rotor blade repaired by the method is adopted. COPYRIGHT: (C)2004,JPO

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