Patents by Inventor Hisato Tagawa
Hisato Tagawa has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 10655488Abstract: In a gas turbine in which a seal member seals a gap between a transition piece and a nozzle end wall in a turbine first stage, the transition piece and the nozzle end wall has a seal groove. The seal member includes a hook portion that slides in the turbine radial direction with respect to the flange and a seal plate portion inserted in the groove. The groove and the portion are configured to include a surface contact region in which a surface of the groove and the portion are in surface contact with each other, a non-contact region disposed on a side closer to the transition piece than the region, and a hole provided at the portion so as to face the surface in the groove across a gap in the region.Type: GrantFiled: August 16, 2017Date of Patent: May 19, 2020Assignee: Mitsubishi Hitachi Power Systems, Ltd.Inventors: Yasuhiro Horiuchi, Shinichi Higuchi, Hisato Tagawa, Kenji Shingai, Takemitsu Miura
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Patent number: 10006368Abstract: The invention provides a gas turbine blade that is capable of reducing the temperature difference between the pressure side and the suction side even if the trailing-edge cooling channel is narrow, thereby lessening thermal stress as well. A gas turbine blade 1 comprises: an internal trailing-edge cooling channel formed by a suction-side cooling target surface 6a and a pressure-side cooling target surface 6b that face each other; and multiple vortex-generator-shaped fins 10 disposed between the two cooling target surfaces 6a and 6b such that the fins 10 connect the two cooling target surfaces 6a and 6b. Each of the vortex-generator-shaped fins 10 includes an oblique surface 33 located on the downstream side of the flow direction of a cooling medium. A normal line 34 to the oblique surface 33 intersects with one of the two cooling target surfaces 6a and 6b.Type: GrantFiled: November 19, 2014Date of Patent: June 26, 2018Assignee: Mitsubishi Hitachi Power Systems, Ltd.Inventors: Yasuhiro Horiuchi, Hisato Tagawa, Tetsuro Morisaki
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Publication number: 20180058234Abstract: In a gas turbine in which a seal member seals a gap between a transition piece and a nozzle end wall in a turbine first stage, the transition piece and the nozzle end wall has a seal groove. The seal member includes a hook portion that slides in the turbine radial direction with respect to the flange and a seal plate portion inserted in the groove. The groove and the portion are configured to include a surface contact region in which a surface of the groove and the portion are in surface contact with each other, a non-contact region disposed on a side closer to the transition piece than the region, and a hole provided at the portion so as to face the surface in the groove across a gap in the region.Type: ApplicationFiled: August 16, 2017Publication date: March 1, 2018Inventors: Yasuhiro HORIUCHI, Shinichi HIGUCHI, Hisato TAGAWA, Kenji SHINGAI, Takemitsu MIURA
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Patent number: 9790799Abstract: A gas turbine airfoil is provided that is superior in the cooling performance of an end wall and in the thermal efficiency of a gas turbine. A gas turbine airfoil includes an airfoil portion having a cooling passage therein; and an end wall portion located at an inner band end portion of the airfoil portion in the turbine-radial direction. Cooling holes are disposed in the leading edge side hook portion of the end wall portion. The plurality of cooling holes are arranged at different distance of intervals in the circumferential direction of the gas turbine. Cooling air that has flowed in the cooling passage is configured to flow from the cooling holes toward the leading edge of the end wall portion.Type: GrantFiled: November 4, 2014Date of Patent: October 17, 2017Assignee: Mitsubishi Hitachi Power Systems, Ltd.Inventors: Hisato Tagawa, Yasuhiro Horiuchi
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Patent number: 9587494Abstract: A gas turbine blade includes a hollow-blade-form portion formed by a leading edge on an upstream side of an working fluid of a gas turbine in a flow direction, a trailing edge on a downstream side of the working fluid in the flow direction, and a suction surface and a pressure surface reaching the trailing edge from the leading edge, and a shank portion for supporting the blade form portion. The blade also includes a partition for connecting the suction surface and the pressure surface in a hollow region of the blade-form portion, coolant paths formed by the partition, the suction surface, and the pressure surface, an impingement cooling hole formed in the partition for dividing the first path that is a flow path nearest to the leading edge side among the coolant paths and the second path adjacent to the first path, and first and second converter portions.Type: GrantFiled: August 22, 2013Date of Patent: March 7, 2017Assignee: Mitsubishi Hitachi Power Systems, Ltd.Inventors: Tetsuro Morisaki, Hisato Tagawa, Manabu Yagi, Yasuhiro Horiuchi, Shinichi Higuchi
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Publication number: 20150139814Abstract: The invention provides a gas turbine blade that is capable of reducing the temperature difference between the pressure side and the suction side even if the trailing-edge cooling channel is narrow, thereby lessening thermal stress as well. A gas turbine blade 1 comprises: an internal trailing-edge cooling channel formed by a suction-side cooling target surface 6a and a pressure-side cooling target surface 6b that face each other; and multiple vortex-generator-shaped fins 10 disposed between the two cooling target surfaces 6a and 6b such that the fins 10 connect the two cooling target surfaces 6a and 6b. Each of the vortex-generator-shaped fins 10 includes an oblique surface 33 located on the downstream side of the flow direction of a cooling medium. A normal line 34 to the oblique surface 33 intersects with one of the two cooling target surfaces 6a and 6b.Type: ApplicationFiled: November 19, 2014Publication date: May 21, 2015Inventors: Yasuhiro HORIUCHI, Hisato TAGAWA, Tetsuro MORISAKI
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Publication number: 20150125310Abstract: A gas turbine airfoil is provided that is superior in the cooling performance of an end wall and in the thermal efficiency of a gas turbine. A gas turbine airfoil includes an airfoil portion having a cooling passage therein; and an end wall portion located at an inner band end portion of the airfoil portion in the turbine-radial direction. Cooling holes are disposed in the leading edge side hook portion of the end wall portion. The plurality of cooling holes are arranged at different distance of intervals in the circumferential direction of the gas turbine. Cooling air that has flowed in the cooling passage is configured to flow from the cooling holes toward the leading edge of the end wall portion.Type: ApplicationFiled: November 4, 2014Publication date: May 7, 2015Inventors: Hisato TAGAWA, Yasuhiro HORIUCHI
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Publication number: 20140056719Abstract: A gas turbine blade includes a hollow-blade-form portion formed by a leading edge on an upstream side of an working fluid of a gas turbine in a flow direction, a trailing edge on a downstream side of the working fluid in the flow direction, and a suction surface and a pressure surface reaching the trailing edge from the leading edge, and a shank portion for supporting the blade form portion. The blade also includes a partition for connecting the suction surface and the pressure surface in a hollow region of the blade-form portion, coolant paths formed by the partition, the suction surface, and the pressure surface, an impingement cooling hole formed in the partition for dividing the first path that is a flow path nearest to the leading edge side among the coolant paths and the second path adjacent to the first path, and first and second converter portions.Type: ApplicationFiled: August 22, 2013Publication date: February 27, 2014Applicant: Hitachi, Ltd.Inventors: Tetsuro MORISAKI, Hisato TAGAWA, Manabu YAGI, Yasuhiro HORIUCHI, Shinichi HIGUCHI
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Patent number: 7619332Abstract: A permanent magnet type electric rotating machine comprises a stator having a distributed winding and a permanent magnet rotor, wherein the permanent magnet rotor is provided with a wind passage in an axial direction thereof.Type: GrantFiled: September 30, 2005Date of Patent: November 17, 2009Assignee: Hitachi, Ltd.Inventors: Mamoruo Kimura, Kazumasa Ide, Motonobu Iizuka, Shuji Mizutani, Tetsuo Fujigaki, Kengo Iwashige, Hisato Tagawa, Yusaku Maruno
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Publication number: 20060071568Abstract: A permanent magnet type electric rotating machine comprises a stator having a distributed winding and a permanent magnet rotor, wherein the permanent magnet rotor is provided with a wind passage in an axial direction thereof.Type: ApplicationFiled: September 30, 2005Publication date: April 6, 2006Inventors: Mamoruo Kimura, Kazumasa Ide, Motonobu Iizuka, Shuji Mizutani, Tetsuo Fujigaki, Kengo Iwashige, Hisato Tagawa, Yusaku Maruno