Patents by Inventor Norifumi Hirata
Norifumi Hirata 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: 11959394Abstract: A suction side fillet portion of a turbine rotor blade includes a central fillet portion located at the center of a length of the suction side fillet portion along an extension direction of the suction side fillet portion, an upstream intermediate fillet portion which is located between the central fillet portion and a front edge that is an upstream end of the suction side fillet portion, and in which a fillet height from an upper surface of a platform portion is higher than a fillet height of the central fillet portion, and a downstream intermediate fillet portion which is located between the central fillet portion and a rear edge that is a downstream end of the suction side fillet portion, and in which a fillet height from the upper surface of the platform portion is higher than the fillet height of the central fillet portion.Type: GrantFiled: January 26, 2021Date of Patent: April 16, 2024Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventor: Norifumi Hirata
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Patent number: 11814986Abstract: One of spacing between the base-side first tooth and the base-side second tooth or spacing between the base-side second tooth and the base-side third tooth is greater than spacing between the tip-side first tooth and the tip-side second tooth.Type: GrantFiled: March 7, 2023Date of Patent: November 14, 2023Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventor: Norifumi Hirata
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Publication number: 20230323778Abstract: One of spacing between the base-side first tooth and the base-side second tooth or spacing between the base-side second tooth and the base-side third tooth is greater than spacing between the tip-side first tooth and the tip-side second tooth.Type: ApplicationFiled: March 7, 2023Publication date: October 12, 2023Inventor: Norifumi HIRATA
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Publication number: 20230037206Abstract: A suction side fillet portion of a turbine rotor blade includes a central fillet portion located at the center of a length of the suction side fillet portion along an extension direction of the suction side fillet portion, an upstream intermediate fillet portion which is located between the central fillet portion and a front edge that is an upstream end of the suction side fillet portion, and in which a fillet height from an upper surface of a platform portion is higher than a fillet height of the central fillet portion, and a downstream intermediate fillet portion which is located between the central fillet portion and a rear edge that is a downstream end of the suction side fillet portion, and in which a fillet height from the upper surface of the platform portion is higher than the fillet height of the central fillet portion.Type: ApplicationFiled: January 26, 2021Publication date: February 2, 2023Inventor: Norifumi HIRATA
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Patent number: 11286785Abstract: A turbine rotor blade includes: a blade body including a pressure surface and a suction surface; and a tip shroud on a tip portion of the blade body, the tip shroud being inclined outward in a radial direction from the pressure surface to the suction surface in an axial direction. The tip shroud includes a fin at a center portion in a circumferential direction, the fin extending radially outward, a pressure-side tip shroud on the pressure surface side, and a suction-side tip shroud. The suction-side tip shroud includes a suction-side contact block at a front edge end of the tip shroud. The pressure-side tip shroud includes a pressure-side contact block at a rear edge end of the tip shroud, the suction-side contact block includes a first surface facing in the circumferential direction, and the pressure-side contact block includes a second surface facing in a direction opposite to the circumferential direction.Type: GrantFiled: June 18, 2019Date of Patent: March 29, 2022Assignee: MITSUBISHI POWER, LTD.Inventors: Norifumi Hirata, Tetsuya Shimmyo, Satoshi Hada, Masamitsu Kuwabara, Shunsuke Torii
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Publication number: 20210115800Abstract: A turbine rotor blade includes: a blade body including a pressure surface and a suction surface; and a tip shroud on a tip portion of the blade body, the tip shroud being inclined outward in a radial direction from the pressure surface to the suction surface in an axial direction. The tip shroud includes a fin at a center portion in a circumferential direction, the fin extending radially outward, a pressure-side tip shroud on the pressure surface side, and a suction-side tip shroud. The suction-side tip shroud includes a suction-side contact block at a front edge end of the tip shroud. The pressure-side tip shroud includes a pressure-side contact block at a rear edge end of the tip shroud, the suction-side contact block includes a first surface facing in the circumferential direction, and the pressure-side contact block includes a second surface facing in a direction opposite to the circumferential direction.Type: ApplicationFiled: June 18, 2019Publication date: April 22, 2021Inventors: Norifumi HIRATA, Tetsuya SHIMMYO, Satoshi HADA, Masamitsu KUWABARA, Shunsuke TORII
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Patent number: 10975700Abstract: A turbine blade designing method is for designing a turbine blade formed using a metal material in which creep including diffusion creep and dislocation creep occurs by heating. The turbine blade designing method includes: acquiring temperature distribution data relating to temperature distribution in the turbine blade to be heated; acquiring creep strength distribution data relating to distribution of the creep strength required for the turbine blade to be heated; from the correlation data, based on the temperature distribution data and the creep strength distribution data, setting the crystal grain size of a high-temperature portion that is the diffusion creep temperature range of the turbine blade to a size coarser than the reference crystal grain size, and setting the crystal grain size of a low-temperature portion that is the dislocation creep temperature range of the turbine blade to a size finer than the reference crystal grain size.Type: GrantFiled: August 22, 2016Date of Patent: April 13, 2021Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Hideaki Kaneko, Kenji Yamamoto, Takanori Karato, Norifumi Hirata, Naoya Fujita
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Patent number: 10655471Abstract: A flow path width at a hub endwall of a blade main body decreases toward a minimum width from a leading edge, and increases toward a trailing edge from the minimum width, the flow path width at a reference blade height aparted toward a tip side from the hub endwall of the blade main body gradually decreases toward the trailing edge from the leading edge, and an axial chord length position of the minimum flow path widths at respective blade height shift toward a transition to the trailing edge side from the hub endwall toward the tip side of the blade main body and coincides with the trailing edge at the reference blade height.Type: GrantFiled: February 10, 2016Date of Patent: May 19, 2020Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.Inventors: Koichiro Iida, Norifumi Hirata
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Publication number: 20190120060Abstract: A turbine blade designing method is for designing a turbine blade formed using a metal material in which creep including diffusion creep and dislocation creep occurs by heating. The turbine blade designing method includes: acquiring temperature distribution data relating to temperature distribution in the turbine blade to be heated; acquiring creep strength distribution data relating to distribution of the creep strength required for the turbine blade to be heated; from the correlation data, based on the temperature distribution data and the creep strength distribution data, setting the crystal grain size of a high-temperature portion that is the diffusion creep temperature range of the turbine blade to a size coarser than the reference crystal grain size, and setting the crystal grain size of a low-temperature portion that is the dislocation creep temperature range of the turbine blade to a size finer than the reference crystal grain size.Type: ApplicationFiled: August 22, 2016Publication date: April 25, 2019Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Hideaki KANEKO, Kenji YAMAMOTO, Takanori KARATO, Norifumi HIRATA, Naoya FUJITA
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Publication number: 20180030835Abstract: A flow path width at a hub endwall of a blade main body decreases toward a minimum width from a leading edge, and increases toward a trailing edge from the minimum width, the flow path width at a reference blade height aparted toward a tip side from the hub endwall of the blade main body gradually decreases toward the trailing edge from the leading edge, and an axial chord length position of the minimum flow path widths at respective blade height shift toward a transition to the trailing edge side from the hub endwall toward the tip side of the blade main body and coincides with the trailing edge at the reference blade height.Type: ApplicationFiled: February 10, 2016Publication date: February 1, 2018Applicant: Mitsubishi Hitachi Power Systems, Ltd.Inventors: Koichiro IIDA, Norifumi HIRATA
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Patent number: 8827646Abstract: Gas turbine blades which simplify the formation of cooling channels provided inside the turbine blades while simultaneously avoiding loss of turbine blade strength and rigidity due to forming of the cooling channels. Cooling channels provided in the interior of a gas turbine blade include a plurality of straight channel-like base-side elongated holes extending in a longitudinal direction at a base side of the turbine blade, a plurality of straight channel-like tip-side elongated holes extending in a longitudinal direction at a tip side of the turbine blade, and a plurality of communicating hollow portions interposed at connection portions between the two types of elongated holes to allow the two types of elongated holes to communicate with each other, and have larger cross-sectional areas than the channel cross-sectional areas of both elongated holes. The communicating hollow portions are formed to match the position of a platform portion of the turbine blade.Type: GrantFiled: March 15, 2013Date of Patent: September 9, 2014Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Satoshi Hada, Takahiko Imada, Tomofumi Shintani, Katsutoshi Ooe, Norifumi Hirata, Hiroshi Asano
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Patent number: 8506251Abstract: Gas turbine blades which simplify the formation of cooling channels provided inside the turbine blades while simultaneously avoiding loss of turbine blade strength and rigidity due to forming of the cooling channels. Cooling channels provided in the interior of a gas turbine blade include a plurality of straight channel-like base-side elongated holes extending in a longitudinal direction at a base side of the turbine blade, a plurality of straight channel-like tip-side elongated holes extending in a longitudinal direction at a tip side of the turbine blade, and a plurality of communicating hollow portions interposed at connection portions between the two types of elongated holes to allow the two types of elongated holes to communicate with each other, and have larger cross-sectional areas than the channel cross-sectional areas of both elongated holes. The communicating hollow portions are formed to match the position of a platform portion of the turbine blade.Type: GrantFiled: April 25, 2011Date of Patent: August 13, 2013Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Satoshi Hada, Takahiko Imada, Tomofumi Shintani, Katsutoshi Ooe, Norifumi Hirata, Hiroshi Asano
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Publication number: 20110217181Abstract: Provided are gas turbine blades in which it is possible to simplify the formation of cooling channels provided inside the turbine blades while simultaneously avoiding loss of turbine blade strength and rigidity due to forming of the cooling channels. In a gas turbine blade (41), cooling channels (410) provided in the interior thereof include a plurality of straight channel-like base-side elongated holes (401a) that extend in a longitudinal direction at a base side of the turbine blade (41), a plurality of straight channel-like tip-side elongated holes (410b) that extend in a longitudinal direction at a tip side of the turbine blade (41), and a plurality of communicating hollow portions (410c) that are interposed at connection portions between the two types of elongated holes (410a, 410b) to individually allow the two types of elongated holes (410a, 410b) to communicate with each other and that have larger cross-sectional areas than the channel cross-sectional areas of both elongated holes (410a, 410b).Type: ApplicationFiled: April 25, 2011Publication date: September 8, 2011Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Satoshi Hada, Takahiko Imada, Tomofumi Shintani, Katsutoshi Ooe, Norifumi Hirata, Hiroshi Asano
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Publication number: 20110217180Abstract: Provided are gas turbine blades in which it is possible to simplify the formation of cooling channels provided inside the turbine blades while simultaneously avoiding loss of turbine blade strength and rigidity due to forming of the cooling channels. In a gas turbine blade, cooling channels provided in the interior thereof include a plurality of straight channel-like base-side elongated holes that extend in a longitudinal direction at a base side of the turbine blade, a plurality of straight channel-like tip-side elongated holes that extend in a longitudinal direction at a tip side of the turbine blade, and a plurality of communicating hollow portions that are interposed at connection portions between the two types of elongated holes to individually allow the two types of elongated holes to communicate with each other and that have larger cross-sectional areas than the channel cross-sectional areas of both elongated holes.Type: ApplicationFiled: December 6, 2010Publication date: September 8, 2011Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Satoshi Hada, Takahiko Imada, Tomofumi Shintani, Katsutoshi Ooe, Norifumi Hirata, Hiroshi Asano