Patents by Inventor Hiroyuki Otomo
Hiroyuki Otomo 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: 11939882Abstract: A turbine rotor blade includes a leading edge portion having a plurality of cooling holes. The plurality of cooling holes includes: m cooling holes arranged in a first range in the blade height direction, where m is an integer of 2 or more; and n cooling holes arranged in a second range on the blade tip side of the first range in the blade height direction, where n is an integer of 2 or more, and n/b<m/a is satisfied, where a is the dimension of the first range in the blade height direction, and b is the dimension of the second range in the blade height direction.Type: GrantFiled: November 12, 2019Date of Patent: March 26, 2024Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Hiroki Kitada, Hiroyuki Otomo
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Patent number: 11905848Abstract: To provide a turbine blade, a manufacturing method for a turbine blade, and a gas turbine. In the turbine blade including a cooling passage provided along a blade height direction, the cooling passage includes: a first cooling hole including one end opening toward a front end, and having an inner diameter that is constant along the blade height direction; and a second cooling hole including one end communicating with the other end of the first cooling hole without a level difference, and having an inner diameter that is increased toward a base end. A length from the one end of the first cooling hole to a position where the first cooling hole and the second cooling hole are communicated with is 40% to 60% of a length from the one end of the first cooling hole to a gas path surface on the base end.Type: GrantFiled: June 1, 2020Date of Patent: February 20, 2024Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Masayoshi Hatta, Keita Takamura, Susumu Wakazono, Takashi Fujii, Hiroyuki Otomo, Yosuke Mukai, Kazuhisa Tamura, Takaaki Oda, Hiroshi Kawasaki, Hiroyuki Kishihara
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Patent number: 11834994Abstract: A turbine vane includes a blade body and a shroud. The shroud includes a gas path surface, a front end surface, a front end corner portion which is a corner portion between the gas path surface and the front end surface, a cavity defining surface which defines a cavity allowing cooling air to flow thereinto, a first air passage in which the cooling air flows, and a second air passage in which the cooling air flows. The first air passage includes a first inlet opened at the cavity defining surface and a first outlet opened at the front end corner portion. The second air passage includes a second inlet opened at the cavity defining surface and a second outlet opened at the front end surface.Type: GrantFiled: August 6, 2020Date of Patent: December 5, 2023Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Saki Matsuo, Satoshi Hada, Tomoko Morikawa, Hiroyuki Otomo
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Patent number: 11560802Abstract: A blade and gas turbine include a stationary blade main body provided internally with cavities, and an inner shroud linked to an end portion, in the longitudinal direction, of the stationary blade main body, and which is internally provided with an inner shroud cooling passage with which a first cavity is in fluid communication. The inner shroud is provided, in front edge corner portions, with a first chamfered portion intersecting a front surface, a side surface, and an upper surface, and first cooling holes in fluid communication with the inner shroud cooling passage are provided in the first chamfered portion.Type: GrantFiled: June 5, 2019Date of Patent: January 24, 2023Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Hiroyuki Otomo, Shogo Furukawa
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Patent number: 11499430Abstract: A turbine rotor blade includes: a root portion fixed to a rotor shaft; and an airfoil portion including a pressure surface, a suction surface, and a top surface connecting the pressure surface and the suction surface, with a cooling passage formed inside the airfoil portion. The top surface of the turbine rotor blade includes a leading edge region located on the leading edge side and formed parallel to the rotor shaft, and a trailing edge region adjacent to the leading edge region. The trailing edge region has an inclined surface inclined radially inward toward a trailing edge.Type: GrantFiled: November 20, 2019Date of Patent: November 15, 2022Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Hiroki Kitada, Satoshi Hada, Hiroyuki Otomo, Yasumasa Kunisada
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Publication number: 20220268211Abstract: A turbine vane includes a blade body and a shroud. The shroud includes a gas path surface, a front end surface, a front end corner portion which is a corner portion between the gas path surface and the front end surface, a cavity defining surface which defines a cavity allowing cooling air to flow thereinto, a first air passage in which the cooling air flows, and a second air passage in which the cooling air flows. The first air passage includes a first inlet opened at the cavity defining surface and a first outlet opened at the front end corner portion. The second air passage includes a second inlet opened at the cavity defining surface and a second outlet opened at the front end surface.Type: ApplicationFiled: August 6, 2020Publication date: August 25, 2022Inventors: Saki MATSUO, Satoshi HADA, Tomoko MORIKAWA, Hiroyuki OTOMO
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Publication number: 20220220856Abstract: A turbine rotor blade includes a leading edge portion having a plurality of cooling holes. The plurality of cooling holes includes: m cooling holes arranged in a first range in the blade height direction, where m is an integer of 2 or more; and n cooling holes arranged in a second range on the blade tip side of the first range in the blade height direction, where n is an integer of 2 or more, and n/b<m/a is satisfied, where a is the dimension of the first range in the blade height direction, and b is the dimension of the second range in the blade height direction.Type: ApplicationFiled: November 12, 2019Publication date: July 14, 2022Inventors: Hiroki KITADA, Hiroyuki OTOMO
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Publication number: 20220170376Abstract: To provide a turbine blade, a manufacturing method for a turbine blade, and a gas turbine. In the turbine blade including a cooling passage provided along a blade height direction, the cooling passage includes: a first cooling hole including one end opening toward a front end, and having an inner diameter that is constant along the blade height direction; and a second cooling hole including one end communicating with the other end of the first cooling hole without a level difference, and having an inner diameter that is increased toward a base end. A length from the one end of the first cooling hole to a position where the first cooling hole and the second cooling hole are communicated with is 40% to 60% of a length from the one end of the first cooling hole to a gas path surface on the base end.Type: ApplicationFiled: June 1, 2020Publication date: June 2, 2022Inventors: Masayoshi HATTA, Keita TAKAMURA, Susumu WAKAZONO, Takashi FUJII, Hiroyuki OTOMO, Yosuke MUKAI, Kazuhisa TAMURA, Takaaki ODA, Hiroshi KAWASAKI, Hiroyuki KISHIHARA
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Patent number: 11339669Abstract: A turbine blade includes an airfoil portion, a cooling passage inside the airfoil portion, and a plurality of cooling holes formed in a trailing edge part of the airfoil portion. The cooling holes communicating with the cooling passage and opening in a surface of the trailing edge part. A relation of d_up<d_mid<d_down is satisfied, where d_mid is an index indicating opening densities of the cooling holes in a center region including an intermediate position between a first end and a second end of the airfoil portion in the blade height direction, d_up is an index in a region positioned upstream of a flow of a cooling medium in the cooling passage from the center region in the blade height direction, and d_down is an index in a region positioned downstream of the flow of the cooling medium from the center region in the blade height direction.Type: GrantFiled: July 4, 2018Date of Patent: May 24, 2022Assignee: MITSUBISHI POWER, LTD.Inventors: Yoshifumi Tsuji, Ryuta Ito, Hiroyuki Otomo, Satoshi Hada, Susumu Wakazono
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Patent number: 11313232Abstract: A turbine blade includes a blade main body that includes a cooling flow path formed inside, through which a cooling medium flows; and a plurality of turbulators that are aligned in a flow direction of the cooling medium, project into the cooling flow path from an inner surface of the blade main body, and extend in a direction intersecting with the flow direction. At least one of the turbulators is a first turbulator. The first turbulator includes a first portion and a second portion. The first portion is connected to the first portion and has a projecting height from the inner surface that changes at a first change ratio along a direction intersecting with the flow direction. The second portion has a projecting height from the inner surface that changes at a second change ratio higher than the first change ratio along the direction intersecting with the flow direction.Type: GrantFiled: February 26, 2018Date of Patent: April 26, 2022Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventor: Hiroyuki Otomo
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Publication number: 20210340877Abstract: A turbine rotor blade includes: a root portion fixed to a rotor shaft; and an airfoil portion including a pressure surface, a suction surface, and a top surface connecting the pressure surface and the suction surface, with a cooling passage formed inside the airfoil portion. The top surface of the turbine rotor blade includes a leading edge region located on the leading edge side and formed parallel to the rotor shaft, and a trailing edge region adjacent to the leading edge region. The trailing edge region has an inclined surface inclined radially inward toward a trailing edge.Type: ApplicationFiled: November 20, 2019Publication date: November 4, 2021Inventors: Hiroki KITADA, Satoshi HADA, Hiroyuki OTOMO, Yasumasa KUNISADA
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Publication number: 20210310360Abstract: A blade and gas turbine include a stationary blade main body provided internally with cavities, and an inner shroud linked to an end portion, in the longitudinal direction, of the stationary blade main body, and which is internally provided with an inner shroud cooling passage with which a first cavity is in fluid communication. The inner shroud is provided, in front edge corner portions, with a first chamfered portion intersecting a front surface, a side surface, and an upper surface, and first cooling holes in fluid communication with the inner shroud cooling passage are provided in the first chamfered portion.Type: ApplicationFiled: June 5, 2019Publication date: October 7, 2021Inventors: Hiroyuki OTOMO, Shogo FURUKAWA
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Publication number: 20210123349Abstract: A turbine blade includes an airfoil portion, a cooling passage inside the airfoil portion, and a plurality of cooling holes formed in a trailing edge part of the airfoil portion. The cooling holes communicating with the cooling passage and opening in a surface of the trailing edge part. A relation of d_up<d_mid<d_down is satisfied, where d_mid is an index indicating opening densities of the cooling holes in a center region including an intermediate position between a first end and a second end of the airfoil portion in the blade height direction, d_up is an index in a region positioned upstream of a flow of a cooling medium in the cooling passage from the center region in the blade height direction, and d_down is an index in a region positioned downstream of the flow of the cooling medium from the center region in the blade height direction.Type: ApplicationFiled: July 4, 2018Publication date: April 29, 2021Inventors: Yoshifumi TSUJI, Ryuta ITO, Hiroyuki OTOMO, Satoshi HADA, Susumu WAKAZONO
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Patent number: 10641116Abstract: A plurality of circumferential blowout passages that communicate with a cavity into which cooling air flows and that open in a circumferential end surface are formed in a shroud of a vane. Of a central region of the circumferential end surface, an upstream-side region of the circumferential end surface, and a downstream-side region of the circumferential end surface, at least the central region has openings of the plurality of circumferential blowout passages formed therein. A density that is the number of the openings of the circumferential blowout passages per unit length in an axial direction is highest in the central region.Type: GrantFiled: August 1, 2016Date of Patent: May 5, 2020Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.Inventors: Hiroyuki Otomo, Satoshi Hada
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Patent number: 10626732Abstract: A blade has a flow passage forming plate that defines a part of a combustion gas flow passage. The flow passage forming plate has a plurality of back channels that open in a back end surface. A density of openings of the plurality of back channels in a middle region of the back end surface is higher than the density of openings of the plurality of back channels in at least one side region of a suction-side region and a pressure-side region of the back end surface. The density of openings is a ratio of a length of wetted perimeter of the plurality of back channels to an interval of openings of the plurality of back channels.Type: GrantFiled: March 11, 2016Date of Patent: April 21, 2020Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.Inventors: Saki Matsuo, Tomoko Morikawa, Satoshi Hada, Hiroyuki Otomo
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Publication number: 20200018170Abstract: A turbine blade includes a blade main body that includes a cooling flow path formed inside, through which a cooling medium flows; and a plurality of turbulators that are aligned in a flow direction of the cooling medium, project into the cooling flow path from an inner surface of the blade main body, and extend in a direction intersecting with the flow direction. At least one of the turbulators is a first turbulator. The first turbulator includes a first portion and a second portion. The first portion is connected to the first portion and has a projecting height from the inner surface that changes at a first change ratio along a direction intersecting with the flow direction. The second portion has a projecting height from the inner surface that changes at a second change ratio higher than the first change ratio along the direction intersecting with the flow direction.Type: ApplicationFiled: February 26, 2018Publication date: January 16, 2020Inventor: Hiroyuki OTOMO
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Publication number: 20180202301Abstract: A plurality of circumferential blowout passages that communicate with a cavity into which cooling air flows and that open in a circumferential end surface are formed in a shroud of a vane. Of a central region of the circumferential end surface, an upstream-side region of the circumferential end surface, and a downstream-side region of the circumferential end surface, at least the central region has openings of the plurality of circumferential blowout passages formed therein. A density that is the number of the openings of the circumferential blowout passages per unit length in an axial direction is highest in the central region.Type: ApplicationFiled: August 1, 2016Publication date: July 19, 2018Inventors: Hiroyuki OTOMO, Satoshi HADA
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Publication number: 20180045060Abstract: A blade has a flow passage forming plate that defines a part of a combustion gas flow passage. The flow passage forming plate has a plurality of back channels that open in a back end surface. A density of openings of the plurality of back channels in a middle region of the back end surface is higher than the density of openings of the plurality of back channels in at least one side region of a suction-side region and a pressure-side region of the back end surface. The density of openings is a ratio of a length of wetted perimeter of the plurality of back channels to an interval of openings of the plurality of back channels.Type: ApplicationFiled: March 11, 2016Publication date: February 15, 2018Applicant: MITSUBISHI HITACHI POWER AYSTEMS,LTD.Inventors: Saki MATSUO, Tomoko MORIKAWA, Satoshi HADA, Hiroyuki OTOMO
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Patent number: 9644485Abstract: A blade is formed with blade air passages connecting the inside of a blade body of the blade and the inside of a platform of the blade. The platform is formed with pressure side passages that extend from the blade air passages toward a circumferential pressure side, are open at a pressure side end face, and are arranged in an axial direction. Further, the platform is formed with a suction side main passage into which cooling air flows, and a suction side passage that communicates with the suction side main passage and extends from the suction side main passage along a suction side end face.Type: GrantFiled: June 5, 2015Date of Patent: May 9, 2017Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.Inventors: Hiroyuki Otomo, Masamitsu Kuwabara
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Publication number: 20160177751Abstract: A blade is formed with blade air passages connecting the inside of a blade body of the blade and the inside of a platform of the blade. The platform is formed with a plurality of pressure side passages that extend from the blade air passages toward a circumferential pressure side, are open at a pressure side end face, and are arranged in an axial direction. Further, the platform is formed with a suction side main passage into which cooling air flows, and a suction side passage that communicates with the suction side main passage and extends from the suction side main passage along a suction side end face.Type: ApplicationFiled: June 5, 2015Publication date: June 23, 2016Inventors: Hiroyuki OTOMO, Masamitsu KUWABARA