Patents by Inventor Satoshi Hada

Satoshi Hada 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).

  • Patent number: 11913341
    Abstract: In a clearance control system for a gas turbine, a control device operates an adjustment device such that a first flow rate is greater than a second flow rate when a load stable state is entered in which a fluctuation range of a load shifts within a preset range, and operates the adjustment device such that the second flow rate is greater than the first flow rate when a load fluctuation state is entered in which the load falls outside the range.
    Type: Grant
    Filed: September 7, 2021
    Date of Patent: February 27, 2024
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Yuya Fukunaga, Susumu Wakazono, Satoshi Hada
  • Patent number: 11891920
    Abstract: A turbine stator vane includes: a vane body which includes: an airfoil portion which has a serpentine flow passage inside thereof, the serpentine flow passage including a plurality of cooling flow passages and a plurality of turn-back flow passages; a shroud disposed on at least one of a tip end side or a root end side, in the vane height direction, of the airfoil portion; and a lid portion fixed to the airfoil portion. The lid portion forming the turn-back flow passage and being provided as a separate member from the airfoil portion. The lid portion has an inner wall surface width formed to be greater than the flow-passage width of the cooling passage formed in the airfoil portion, and a minimum value of a thickness of the lid portion is smaller than a thickness of a part of the shroud to which the lid portion is mounted.
    Type: Grant
    Filed: March 30, 2020
    Date of Patent: February 6, 2024
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Hidemichi Koyabu, Satoshi Hada
  • Patent number: 11867085
    Abstract: A turbine blade is provided with an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface which extend between the leading edge and the trailing edge, the airfoil portion internally forming a cooling passage. The cooling passage includes: a first cooling passage located closer to the pressure surface than the suction surface; and a second cooling passage located closer to the suction surface than the pressure surface. The first cooling passage and the second cooling passage are separated by a partition member disposed in the airfoil portion. At least one communication space connecting the first cooling passage and the second cooling passage is formed in the partition member.
    Type: Grant
    Filed: March 23, 2021
    Date of Patent: January 9, 2024
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Satoshi Mizukami, Masamitsu Kuwabara, Satoshi Hada, Saki Matsuo, Yoshitaka Uemura, Ryozo Tamura, Yasumasa Kunisada
  • Publication number: 20230407752
    Abstract: A turbine stationary blade includes: a blade body; and a shroud formed in an end portion of the blade body in a blade height direction. The shroud includes: a bottom plate in contact with a combustion gas flow passage; a peripheral wall formed in the blade height direction and along a peripheral edge of the bottom plate; a recess forming a space surrounded by the peripheral wall and the bottom plate; partition ribs connecting the blade body and the peripheral wall, dividing the recess into a plurality of spaces, and forming a plurality of cavities; and an impingement plate dividing the space into an outer cavity formed on an outer side in the blade height direction and an inner cavity formed on an inner side of the outer cavity, and having a plurality of through holes via which the outer cavity and the inner cavity communicate with each other.
    Type: Application
    Filed: October 15, 2021
    Publication date: December 21, 2023
    Inventors: Takuya OKAMOTO, Tomoko MORIKAWA, Satoshi HADA
  • Patent number: 11834962
    Abstract: A turbine stator vane includes; an airfoil portion; a shroud disposed on at least one of the side of a tip end portion or the side of a root end portion of the airfoil portion; and a protruding portion protruding toward the opposite side to the airfoil portion across a gas path surface in a radial direction. The shroud includes: a circumferential-direction passage disposed at the side of a trailing edge and extending in a circumferential direction; and a plurality of trailing edge end portion passages arranged in the circumferential direction at the side of the trailing edge, each trailing edge end portion passage having a first end portion connected to the circumferential-direction passage and a second end portion having an opening on a trailing edge end surface of the shroud.
    Type: Grant
    Filed: April 8, 2020
    Date of Patent: December 5, 2023
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Satoshi Hada, Yoshifumi Okajima, Kunihiko Waki
  • Patent number: 11834994
    Abstract: 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: Grant
    Filed: August 6, 2020
    Date of Patent: December 5, 2023
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Saki Matsuo, Satoshi Hada, Tomoko Morikawa, Hiroyuki Otomo
  • Publication number: 20230340882
    Abstract: This stator vane is at least provided with a blade body disposed in a combustion gas flow channel through which a combustion gas flows, a shroud that defines a part of the combustion gas flow channel, and an impingement plate attached to the shroud. A partition rib extends from a blade body end to an inner wall surface of a peripheral wall, and a shelf is provided at a rib-less part of the inner wall surface of the peripheral wall excluding at least a part in which the partition rib extends to the inner wall surface of the peripheral wall.
    Type: Application
    Filed: November 20, 2020
    Publication date: October 26, 2023
    Inventors: Saki MATSUO, Yusuke IZUMI, Satoshi HADA, Takuya OKAMOTO
  • Publication number: 20230340881
    Abstract: This gas turbine blade comprises a platform part having a cooling passage formed inside, and a wing body part protruding from the upper surface of the platform part. A plurality of first ejection ports that eject a gas supplied from the cooling passage are formed in an inner chordal region of the upper surface, which is positioned further toward the wing-body side than a wing chord connecting the leading edge and the trailing edge of the wing body part. A plurality of second ejection ports that eject the gas supplied from the cooling passage are formed in an outer chordal region of the upper surface, which is positioned on the side opposite the inner chordal region with respect to the wing chord. The outer chordal region has an outer chordal leading edge region positioned on the leading-edge side and an outer chordal trailing edge region positioned on the trailing-edge side, more second ejection ports being formed in the outer chordal leading edge region than in the outer chordal trailing edge region.
    Type: Application
    Filed: September 21, 2021
    Publication date: October 26, 2023
    Inventors: Keita TAKAMURA, Satoshi HADA
  • Patent number: 11788417
    Abstract: A turbine blade and a gas turbine are provided with: an airfoil portion (41) internally including a cooling air passage (60); a platform (42) provided in a blade base end portion (55) in a blade height direction (Dh) of the airfoil portion (41); and a fillet portion (80) provided around the entire perimeter of a connecting portion of the airfoil portion (41) and the platform (42). The fillet portion (80) includes a first fillet portion (81) which is provided on a rear side blade surface (53) side of the airfoil portion (41), on the trailing edge (52) side of a position at which the distance between the rear side blade surface (53) of the airfoil portion (41) and a rear side edge portion (44) of the platform (42) is shortest, and which has a fillet width (W) that is greater than the fillet width W of other regions of the fillet portion (80).
    Type: Grant
    Filed: March 2, 2020
    Date of Patent: October 17, 2023
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Susumu Wakazono, Yasuo Miyahisa, Satoshi Hada
  • Publication number: 20230296030
    Abstract: In a clearance control system for a gas turbine, a control device operates an adjustment device such that a first flow rate is greater than a second flow rate when a load stable state is entered in which a fluctuation range of a load shifts within a preset range, and operates the adjustment device such that the second flow rate is greater than the first flow rate when a load fluctuation state is entered in which the load falls outside the range.
    Type: Application
    Filed: September 7, 2021
    Publication date: September 21, 2023
    Inventors: Yuya FUKUNAGA, Susumu WAKAZONO, Satoshi HADA
  • Publication number: 20230287796
    Abstract: A method of cooling a vane of a turbine is provided. The turbine includes an airfoil, an outer shroud disposed at an outer radial end of the airfoil and an inner shroud, the airfoil including a plurality of air channels extending along the radial direction of the turbine, the air channels comprising a first air channel and a second air channel. A cooling air is caused to flow inside the first air channel to cool the first air channel, then cool one of the outer shroud and the inner shroud. A cooling air is caused to flow inside the second air channel to cool the second air channel, then cool the other one of the outer shroud and the inner shroud.
    Type: Application
    Filed: March 11, 2022
    Publication date: September 14, 2023
    Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Satoshi Mizukami, David Allen Flodman, Satoshi Hada
  • Patent number: 11713683
    Abstract: A turbine blade including an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface extending between the leading edge and the trailing edge. The airfoil portion internally forming a cooling passage, which includes first and second cooling passages, and a plurality of outflow passages each having one end which opens to a merging portion formed by connecting an end portion of the first cooling passage on a side of the trailing edge and an end portion of the second cooling passage on the side of the trailing edge, and another end which opens to the trailing edge. The first cooling passage and the second cooling passage are divided by a partition member disposed in the airfoil portion. The cooling passage includes pressure side pin fins in the first cooling passage, and suction side pin fins in the second cooling passage.
    Type: Grant
    Filed: March 23, 2021
    Date of Patent: August 1, 2023
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Satoshi Mizukami, Masamitsu Kuwabara, Satoshi Hada, Saki Matsuo, Yoshitaka Uemura, Ryozo Tamura, Yasumasa Kunisada
  • Publication number: 20230175404
    Abstract: A turbine stator vane includes; an airfoil portion; a shroud disposed on at least one of the side of a tip end portion or the side of a root end portion of the airfoil portion; and a protruding portion protruding toward the opposite side to the airfoil portion across a gas path surface in a radial direction. The shroud includes: a circumferential-direction passage disposed at the side of a trailing edge and extending in a circumferential direction; and a plurality of trailing edge end portion passages arranged in the circumferential direction at the side of the trailing edge, each trailing edge end portion passage having a first end portion connected to the circumferential-direction passage and a second end portion having an opening on a trailing edge end surface of the shroud.
    Type: Application
    Filed: April 8, 2020
    Publication date: June 8, 2023
    Inventors: Satoshi HADA, Yoshifumi OKAJIMA, Kunihiko WAKI
  • Patent number: 11643935
    Abstract: A turbine blade includes an airfoil body, and a plurality of cooling passages extending along a blade height direction inside the airfoil body and being in communication with each other to define a serpentine flow passage. The plurality of cooling passages include first turbulators on an inner wall surface of an upstream cooling passage of the plurality of cooling passages, and second turbulators on an inner wall surface of a downstream cooling passage of the plurality of cooling passages. A second angle formed by the second turbulators with respect to a flow direction of a cooling fluid in the downstream cooling passage is smaller than a first angle formed by the first turbulators with respect to the flow direction of the cooling fluid in the upstream cooling passage.
    Type: Grant
    Filed: October 15, 2018
    Date of Patent: May 9, 2023
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Yasuo Miyahisa, Susumu Wakazono, Satoshi Hada
  • Publication number: 20220412220
    Abstract: A turbine blade is provided with an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface which extend between the leading edge and the trailing edge, the airfoil portion internally forming a cooling passage. The cooling passage includes: a first cooling passage located closer to the pressure surface than the suction surface; and a second cooling passage located closer to the suction surface than the pressure surface. The first cooling passage and the second cooling passage are separated by a partition member disposed in the airfoil portion. At least one communication space connecting the first cooling passage and the second cooling passage is formed in the partition member.
    Type: Application
    Filed: March 23, 2021
    Publication date: December 29, 2022
    Inventors: Satoshi MIZUKAMI, Masamitsu KUWABARA, Satoshi HADA, Saki MATSUO, Yoshitaka UEMURA, Ryozo TAMURA, Yasumasa KUNISADA
  • Patent number: 11536149
    Abstract: A method of cooling a vane of a turbine is provided. The turbine includes an airfoil, a shroud disposed at an end of the airfoil, the end being a radial end along a radial direction of the turbine, the shroud comprising a shroud main body and a shroud edge disposed on a circumference of the shroud main body to surround the shroud main body, the shroud edge comprising a shroud edge passage therein. A cooling air is caused to flow inside the shroud edge passage to cool the shroud edge, and after cooling the shroud edge, the shroud main body is cooled by using the cooling air which has flowed inside the shroud edge passage.
    Type: Grant
    Filed: March 11, 2022
    Date of Patent: December 27, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Satoshi Mizukami, David Allen Flodman, Satoshi Hada
  • Publication number: 20220403744
    Abstract: A turbine blade including an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface extending between the leading edge and the trailing edge. The airfoil portion internally forming a cooling passage, which includes first and second cooling passages, and a plurality of outflow passages each having one end which opens to a merging portion formed by connecting an end portion of the first cooling passage on a side of the trailing edge and an end portion of the second cooling passage on the side of the trailing edge, and another end which opens to the trailing edge. The first cooling passage and the second cooling passage are divided by a partition member disposed in the airfoil portion. The cooling passage includes pressure side pin fins in the first cooling passage, and suction side pin fins in the second cooling passage.
    Type: Application
    Filed: March 23, 2021
    Publication date: December 22, 2022
    Inventors: Satoshi MIZUKAMI, Masamitsu KUWABARA, Satoshi HADA, Saki MATSUO, Yoshitaka UEMURA, Ryozo TAMURA, Yasumasa KUNISADA
  • Patent number: 11499430
    Abstract: 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: Grant
    Filed: November 20, 2019
    Date of Patent: November 15, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Hiroki Kitada, Satoshi Hada, Hiroyuki Otomo, Yasumasa Kunisada
  • Publication number: 20220268211
    Abstract: 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: Application
    Filed: August 6, 2020
    Publication date: August 25, 2022
    Inventors: Saki MATSUO, Satoshi HADA, Tomoko MORIKAWA, Hiroyuki OTOMO
  • Patent number: 11414998
    Abstract: A turbine blade includes an airfoil portion having a hollow portion extending along the blade height direction and film cooling holes arranged along the blade height direction, and an insert disposed in the hollow portion along the blade height direction and having impingement cooling holes. The insert includes a first high-density opening region having a higher density of the impingement cooling holes than in other surface regions of the insert. The geometric center of the first high-density opening region is positioned on the suction side of the airfoil portion in the leading-edge-to-trailing-edge direction and on the outer side of the midpoint of the airfoil portion in the blade height direction. The film cooling holes includes upstream film cooling holes disposed in the suction surface of the airfoil portion at a position corresponding to the first high-density opening region or at a position closer to a leading edge than the position.
    Type: Grant
    Filed: April 17, 2018
    Date of Patent: August 16, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Takashi Fujii, Hidemichi Koyabu, Shunsuke Torii, Satoshi Hada