Patents by Inventor Shohei Numata

Shohei Numata 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: 11879359
    Abstract: Provided is a transition piece including a first flow path group formed by arraying a plurality of in-wall flow paths that extend inside a plate material forming the transition piece and a second flow path group that is positioned on a side closer to a combustor liner than the first flow path group is. Each in-wall flow path in the first flow path group and the second flow path group has an inlet that is located at one end section in a flow direction of a combustion gas and that faces a compressed air main flow path, and an outlet that is located at the other end section in the flow direction of the combustion gas and that faces a combustion gas flow path.
    Type: Grant
    Filed: September 2, 2022
    Date of Patent: January 23, 2024
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Hiroaki Nagahashi, Yoshitaka Terada, Shohei Numata
  • Patent number: 11719108
    Abstract: A transition piece includes a first flow passage group formed by arranging a plurality of intra-wall flow passages, a second flow passage group, and a plurality of dilution holes that penetrate a plate, and establish communication between a compressed air main flow passage and a combustion gas flow passage, each intra-wall flow passage of the first flow passage group and the second flow passage group having an inlet facing the compressed air main flow passage at an end portion on a side near the gas turbine, and having an outlet facing the combustion gas flow passage at an end portion on a side near the combustor liner, a dilution hole being located nearer to the inlet of an intra-wall flow passage of the second flow passage group than to the outlet of the intra-wall flow passage of the second flow passage group.
    Type: Grant
    Filed: September 16, 2022
    Date of Patent: August 8, 2023
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Naoto Fujiwara, Shohei Numata, Yasuhiro Wada, Shota Igarashi, Yoshitaka Hirata
  • Publication number: 20230167747
    Abstract: Provided is a transition piece including a first flow path group formed by arraying a plurality of in-wall flow paths that extend inside a plate material forming the transition piece and a second flow path group that is positioned on a side closer to a combustor liner than the first flow path group is. Each in-wall flow path in the first flow path group and the second flow path group has an inlet that is located at one end section in a flow direction of a combustion gas and that faces a compressed air main flow path, and an outlet that is located at the other end section in the flow direction of the combustion gas and that faces a combustion gas flow path.
    Type: Application
    Filed: September 2, 2022
    Publication date: June 1, 2023
    Applicant: Mitsubishi Heavy Industries, LTD.
    Inventors: Hiroaki Nagahashi, Yoshitaka Terada, Shohei Numata
  • Publication number: 20230094510
    Abstract: Provided is a transition piece including: a first flow passage group formed by arranging a plurality of intra-wall flow passages extending within a plate constituting the transition piece from a side near a gas turbine to a side near a combustor liner; a second flow passage group located on a side near the combustor liner with respect to the first flow passage group; and a plurality of dilution holes that penetrate the plate, and establish communication between a compressed air main flow passage and a combustion gas flow passage, each intra-wall flow passage of the first flow passage group and the second flow passage group having an inlet facing the compressed air main flow passage at an end portion on a side near the gas turbine, and having an outlet facing the combustion gas flow passage at an end portion on a side near the combustor liner, a dilution hole being located nearer to the inlet of an intra-wall flow passage of the second flow passage group than to the outlet of the intra-wall flow passage of the
    Type: Application
    Filed: September 16, 2022
    Publication date: March 30, 2023
    Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Naoto Fujiwara, Shohei Numata, Yasuhiro Wada, Shota Igarashi, Yoshitaka Hirata
  • Publication number: 20220082260
    Abstract: A fuel nozzle including a plurality of fuel lines is provided, which has low thermal stress caused by a temperature difference between fuel and combustion air which are passed through the fuel nozzle, and also a gas turbine combustor using the fuel nozzle is provided. The fuel nozzle includes a plurality of channels including a first channel through which either fuel or combustion air is passed, and a second channel through which either fuel or combustion air is passed and which is distinct from the first channel. Of components of the fuel nozzle, a single-piece component makes up at least a region where the first channel and the second channel are placed.
    Type: Application
    Filed: August 18, 2021
    Publication date: March 17, 2022
    Inventors: Hiroaki NAGAHASHI, Yoshitaka TERADA, Shohei NUMATA, Shota IGARASHI, Yasuhiro WADA
  • Publication number: 20220025773
    Abstract: There are provided transition piece cooling holes which make NOx reduction and combustion performance improvement possible while effectively cooling the transition piece end frame and the first-stage stator vane end wall. The transition piece cooling holes include a transition piece which guides combustion gas from a combustor to a turbine, a transition piece end frame which is installed on a turbine-side outlet of the transition piece and is disposed so as to face a first-stage stator vane end wall of the turbine with a predetermined gap being interposed, and a seal member which is fitted on the transition piece end frame and is fitted into the first-stage stator vane end wall so as to seal cooling air which is supplied into the gap. The cooling holes are made in the transition piece end frame so as to directly supply the cooling air to the first-stage stator vane end wall.
    Type: Application
    Filed: July 19, 2021
    Publication date: January 27, 2022
    Inventors: Yasuhiro WADA, Shota IGARASHI, Shohei NUMATA, Tomomi KOGANEZAWA, Hiroaki NAGAHASHI
  • Patent number: 11215364
    Abstract: A combustor includes: a first cylindrical body which is configured to hold a fuel nozzle extending in an axial line direction and through which air flows toward a downstream side thereof; a second cylindrical body that is connected to a downstream side of the first cylindrical body; and an outer shell that has an inner peripheral surface configured to define an air introduction channel through which air is introduced such that the air reverses course at an upstream end of the first cylindrical body and flows toward the downstream side together with an outer peripheral surface of the first cylindrical body. The inner peripheral surface has an outside narrowing surface that is formed to extend inward in a radial direction toward the upstream end of the first cylindrical body.
    Type: Grant
    Filed: February 27, 2017
    Date of Patent: January 4, 2022
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Kenji Miyamoto, Satoshi Takiguchi, Koichi Nishida, Yoshitaka Hirata, Shohei Numata, Keita Yunoki, Yasuhiro Akiyama, Tomoki Uruno
  • Publication number: 20210108797
    Abstract: The present invention provides a gas turbine combustor configured to form a film-like airflow around a region of a combustion liner, where pressure dynamics damping holes are formed for efficiently cooling the region where the pressure dynamics damping holes are formed without increasing concentration of discharged nitrogen oxides. The gas turbine combustor includes the combustion liner that forms a combustion chamber for receiving supply of fuel and air to generate combustion gas, a liner attached to an outer circumferential surface of the combustion liner for forming space from the outer circumferential surface, and the pressure dynamics damping hole formed in the combustion liner provided with the liner for communication between the space and the combustion chamber. The gas turbine combustor includes a cooling air guide lip disposed on an inner circumferential surface of the combustion liner for forming a film-like airflow around a region where the pressure dynamics damping hole is formed.
    Type: Application
    Filed: October 14, 2020
    Publication date: April 15, 2021
    Inventors: Yasuhiro WADA, Shohei YOSHIDA, Akinori HAYASHI, Yoshitaka HIRATA, Hirokazu TAKAHASHI, Satoshi DODO, Shohei NUMATA, Tetsuma TATSUMI, Kazuki ABE
  • Patent number: 10480789
    Abstract: Disclosed is a heat-transfer device adapted to enhance uniformity of cooling characteristics to be given to a heat transfer object, and thereby to extend a life of the heat transfer object.
    Type: Grant
    Filed: June 18, 2015
    Date of Patent: November 19, 2019
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Osami Yokota, Shohei Numata, Tomomi Koganezawa, Tetsuma Tatsumi
  • Patent number: 10443845
    Abstract: A gas turbine combustor includes a combustor liner, a flow sleeve in which the combustor liner is provided and an annular flow passage formed between the combustor liner and the flow sleeve, through which compressed air flows. The flow sleeve includes an internal-diameter changing portion diagonally connected to the flow sleeve and an internal-diameter reducing portion connected to the internal-diameter changing portion and extending along the flow direction of the compressed air. The combustor liner includes an annular protruding portion annularly formed on an outer wall of the combustor liner and protruding toward the flow sleeve. The annular protruding portion is located at a position on the outer wall of the combustion liner, the position facing a connection position between the flow sleeve and the internal-diameter changing portion or being at an upstream side of the position facing the connection position in the flow direction of the compressed air.
    Type: Grant
    Filed: September 4, 2015
    Date of Patent: October 15, 2019
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Shohei Numata, Osami Yokota, Tetsuma Tatsumi
  • Publication number: 20190056111
    Abstract: A combustor includes: a first cylindrical body which is configured to hold a fuel nozzle extending in an axial line direction and through which air flows toward a downstream side thereof; a second cylindrical body that is connected to a downstream side of the first cylindrical body; and an outer shell that has an inner peripheral surface configured to define an air introduction channel through which air is introduced such that the air reverses course at an upstream end of the first cylindrical body and flows toward the downstream side together with an outer peripheral surface of the first cylindrical body. The inner peripheral surface has an outside narrowing surface that is formed to extend inward in a radial direction toward the upstream end of the first cylindrical body.
    Type: Application
    Filed: February 27, 2017
    Publication date: February 21, 2019
    Applicant: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Kenji MIYAMOTO, Satoshi TAKIGUCHI, Koichi NISHIDA, Yoshitaka HIRATA, Shohei NUMATA, Keita YUNOKI, Yasuhiro AKIYAMA, Tomoki URUNO
  • Patent number: 10184662
    Abstract: A gas turbine combustor achieves improved product reliability and a reduced increase in pressure loss through improvements made on a cooling characteristic and structural intensity. The structure of the gas turbine combustor includes a plurality of circularity recesses formed on a side of an annular passage on a partial area of a combustion liner that requires cooling. Each of the circularity recesses has a rectangular surface forming a convex at a right angle with respect to a flowing direction of combustion air. The circularity recesses form a rectangular triangle having an oblique surface facing upstream of the flowing direction of the combustion air.
    Type: Grant
    Filed: November 3, 2014
    Date of Patent: January 22, 2019
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Osami Yokota, Masataka Hidaka, Shohei Numata, Tetsuma Tatsumi
  • Patent number: 10163005
    Abstract: A mail processing apparatus includes a data retrieving section for retrieving sample data from e-mail and/or a network NW, a signalizing section for converting the sample data form the data retrieving section into n-value, a sample storage section for storing n-value data converted by the signalizing section, a signal processing section for comparing the n-value sample data stored in the sample storage section with an inputted e-mail to judge whether or not the e-mail is spam mail based on the degree of similarity, and a spam storing section for storing the spam mail based on the judgment result.
    Type: Grant
    Filed: June 1, 2018
    Date of Patent: December 25, 2018
    Assignee: IMatrix Corp.
    Inventors: Mitsuo Kojima, Atsushi Yokoyama, Tatsuo Suzuki, Shohei Numata
  • Publication number: 20180276459
    Abstract: A mail processing apparatus includes a data retrieving section for retrieving sample data from e-mail and/or a network NW, a signalizing section for converting the sample data form the data retrieving section into n-value, a sample storage section for storing n-value data converted by the signalizing section, a signal processing section for comparing the n-value sample data stored in the sample storage section with an inputted e-mail to judge whether or not the e-mail is spam mail based on the degree of similarity, and a spam storing section for storing the spam mail based on the judgment result.
    Type: Application
    Filed: June 1, 2018
    Publication date: September 27, 2018
    Inventors: Mitsuo Kojima, Atsushi Yokoyama, Tatsuo Suzuki, Shohei Numata
  • Patent number: 9958163
    Abstract: A gas turbine combustor is provided in which product reliability and heat transfer promotion are compatible while suppressing an increase in pressure loss. In a gas turbine combustor comprising a combustor liner, an outer tube provided around an outer periphery of the combustor liner, and an annular flow passage in which a cooling medium (cooling air) flows and which is formed between an outer surface of the combustor liner and an inner surface of the outer tube, the outer tube includes an inner diameter reduced portion and a taper portion smoothly connecting the inner diameter reduced portion and an inner peripheral portion on an upstream side, and is provided at an inner surface of the taper portion with longitudinal vortex generating means generating a vortex that has a central rotation axis in a flowing direction of the cooling medium (cooling air).
    Type: Grant
    Filed: October 10, 2014
    Date of Patent: May 1, 2018
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Shohei Numata, Osami Yokota, Tetsuma Tatsumi, Akinori Hayashi
  • Patent number: 9828882
    Abstract: A thermal power generation system includes a combustor burning oxygen and fuel with supercritical CO2, a turbine driven by the supercritical CO2 and water vapor fed from the combustor, a low-pressure supercritical CO2 storage storing low-pressure supercritical CO2 from the turbine, a compressor compressing the low-pressure supercritical CO2, a high-pressure supercritical CO2 storage storing high-pressure supercritical CO2 from the compressor, and a high-pressure supercritical CO2 feeder supplying between the high-pressure supercritical CO2 storage and the combustor, in which the high-pressure supercritical CO2 feeder supplies the high-pressure supercritical CO2 to the combustor at a constant pressure.
    Type: Grant
    Filed: November 15, 2013
    Date of Patent: November 28, 2017
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Shohei Numata, Susumu Nakano, Takanori Shibata, Hidefumi Araki
  • Patent number: 9435536
    Abstract: An object of the present invention is to provide a gas turbine combustor that can suppress an increase in pressure loss while improving product reliability. The gas turbine combustor includes a combustor liner, an air transfer casing installed on the outer circumference of the combustor liner, the combustor liner and the air transfer casing defining an annular passage therebetween adapted to allow a heat-transfer medium to flow therethrough, and a plurality of vortex generating devices disposed on an inside surface of the air transfer casing, the vortex generating devices generating longitudinal vortices each having a rotational axis extending in a flow direction of a heat-transfer medium. The plurality of vortex generating devices are arranged in paired manner, with each pair of devices generating vortices having rotational directions opposed to each other.
    Type: Grant
    Filed: November 1, 2013
    Date of Patent: September 6, 2016
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Osami Yokota, Tomomi Koganezawa, Shohei Numata, Shohei Yoshida
  • Publication number: 20160069566
    Abstract: A gas turbine combustor includes a combustor liner, a flow sleeve in which the combustor liner is provided and an annular flow passage formed between the combustor liner and the flow sleeve, through which compressed air flows. The flow sleeve includes an internal-diameter changing portion diagonally connected to the flow sleeve and an internal-diameter reducing portion connected to the internal-diameter changing portion and extending along the flow direction of the compressed air. The combustor liner includes an annular protruding portion annularly formed on an outer wall of the combustor liner and protruding toward the flow sleeve. The annular protruding portion is located at a position on the outer wall of the combustion liner, the position facing a connection position between the flow sleeve and the internal-diameter changing portion or being at an upstream side of the position facing the connection position in the flow direction of the compressed air.
    Type: Application
    Filed: September 4, 2015
    Publication date: March 10, 2016
    Inventors: Shohei NUMATA, Osami YOKOTA, Tetsuma TATSUMI
  • Publication number: 20150369486
    Abstract: Disclosed is a heat-transfer device adapted to enhance uniformity of cooling characteristics to be given to a heat transfer object, and thereby to extend a life of the heat transfer object.
    Type: Application
    Filed: June 18, 2015
    Publication date: December 24, 2015
    Inventors: Osami YOKOTA, Shohei NUMATA, Tomomi KOGANEZAWA, Tetsuma TATSUMI
  • Publication number: 20150121885
    Abstract: There is provided a gas turbine combustor that achieves improved product reliability and a reduced increase in pressure loss through improvements made on a cooling characteristic and structural intensity. A gas turbine combustor structure includes a plurality of circularity recesses 20 formed on a side of an annular passage 11 on a partial area of a combustion liner 8 that requires cooling. The circularity recesses 20 each have a rectangular surface 25 forming a convex at a right angle with respect to a flowing direction of combustion air 2. The circularity recesses 20 is a rectangular triangle having an oblique surface 26 facing upstream of the flowing direction of the combustion air 2.
    Type: Application
    Filed: November 3, 2014
    Publication date: May 7, 2015
    Inventors: Osami YOKOTA, Masataka HIDAKA, Shohei NUMATA, Tetsuma TATSUMI