Patents by Inventor Ryou Akiyama

Ryou Akiyama 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).

  • Publication number: 20170159562
    Abstract: A two-shaft gas turbine having a steam injection mechanism, comprising: a compressor having an inlet guide vane, a combustor, turbines, a heat recovery steam generator, a steam valve to control a flow rate of steam to be supplied to the combustor, a fuel valve to control a flow rate of fuel to be supplied to the combustor, characterized in that, the two-shaft gas turbine further comprising: a rotational frequency meter, a flow rate meter to measure the flow rate of the steam to be supplied to the combustor from the heat recovery steam generator, an inlet guide vane position gauge provided to the compressor, a steam valve position gauge, and a control system calculates and outputs command signals to operate openings of the fuel valve, the steam valve, and the inlet guide vane based on measurement signals obtained by the rotational frequency meter, the inlet guide vane position gauge, or the steam valve position gauge, and an output increase command value to the gas turbine.
    Type: Application
    Filed: December 1, 2016
    Publication date: June 8, 2017
    Inventors: Kazuo TAKAHASHI, Shinichi HIGUCHI, Chihiro MYOREN, Ryou AKIYAMA, Takuya TAKEDA
  • Patent number: 9127569
    Abstract: There is provided a shroud structure for gas turbines capable of suppressing a drop in the amount of cooling air for cooling the inner shroud by reducing the amount of cooling air leakage that occurs along the cooling air path when feeding cooling air from the one-piece outer shroud to the inner shroud of the gas turbine and ensure more reliable cooling of the inner shroud. The gas turbine shroud structure contains a one-piece outer shroud, and an inner shroud retained on the inner circumferential side of the outer shroud in a structure divided into multiple inner shrouds along the periphery. An inner seal plate groove is formed on the outer circumference of the hook formed on the inner shroud, a seal plate is inserted in the inner seal plate groove, and the seal plate is mounted so that a section of the seal plate protrudes in the gap between the hook mechanism of the outer shroud and the inner shroud.
    Type: Grant
    Filed: August 4, 2011
    Date of Patent: September 8, 2015
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Ryou Akiyama, Yasuo Takahashi, Tetsuro Morisaki, Yasuhiro Horiuchi
  • Patent number: 9109461
    Abstract: There is provided an axial flow compressor that improves reliability on an increase in a blade loading on a last-stage stator vane of the axial flow compressor due to a partial load operation of a gas turbine. An annular flow passage is formed by a rotor having multiple rotor blades fitted thereto and a casing having multiple stator vanes fitted thereto, two or more of the stator vanes are disposed downstream of a last-stage rotor blade that is the rotor blade disposed at the most downstream side in a flow direction of the annular flow passage, a blade loading on a first stator vane disposed at the most upstream side is set to be smaller than a blade loading of a second stator vane disposed downstream of the first stator vane by one row.
    Type: Grant
    Filed: August 4, 2011
    Date of Patent: August 18, 2015
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Yasuo Takahashi, Chihiro Myoren, Ryou Akiyama, Ichiro Miyoshi
  • Publication number: 20120163965
    Abstract: When a gas turbine is operated with inlet guide vanes (IGVs) closed during part load operation or the like, the degradation of aerodynamic performance and of reliability may potentially occur since the load on rear stage side vanes of a compressor increases. An object of the present invention is to suppress the degradation of the aerodynamic performance and of reliability of an axial compressor. The axial compressor includes a rotor; a plurality of rotor blade rows installed on the rotor; a casing located outside of the rotor blade rows; a plurality of stator vane rows installed on the casing; and exit guide vanes installed on the downstream side of a final stage stator vane row among the stator vane rows. An incidence angle of a flow toward the final stage stator vane row is equal to or below a limit line of an incidence operating range.
    Type: Application
    Filed: December 23, 2011
    Publication date: June 28, 2012
    Applicant: Hitachi, Ltd.
    Inventors: Yasuo TAKAHASHI, Chihiro Myoren, Ryou Akiyama
  • Publication number: 20120076650
    Abstract: There is provided a shroud structure for gas turbines capable of suppressing a drop in the amount of cooling air for cooling the inner shroud by reducing the amount of cooling air leakage that occurs along the cooling air path when feeding cooling air from the one-piece outer shroud to the inner shroud of the gas turbine and ensure more reliable cooling of the inner shroud. The gas turbine shroud structure contains a one-piece outer shroud, and an inner shroud retained on the inner circumferential side of the outer shroud in a structure divided into multiple inner shrouds along the periphery. An inner seal plate groove is formed on the outer circumference of the hook formed on the inner shroud, a seal plate is inserted in the inner seal plate groove, and the seal plate is mounted so that a section of the seal plate protrudes in the gap between the hook mechanism of the outer shroud and the inner shroud.
    Type: Application
    Filed: August 4, 2011
    Publication date: March 29, 2012
    Applicant: Hitachi, Ltd.
    Inventors: Ryou AKIYAMA, Yasuo Takahashi, Tetsuro Morisaki, Yasuhiro Horiuchi
  • Publication number: 20120070267
    Abstract: There is provided an axial flow compressor that improves reliability on an increase in a blade loading on a last-stage stator vane of the axial flow compressor due to a partial load operation of a gas turbine. An annular flow passage is formed by a rotor having multiple rotor blades fitted thereto and a casing having multiple stator vanes fitted thereto, two or more of the stator vanes are disposed downstream of a last-stage rotor blade that is the rotor blade disposed. at the most downstream side in a flow direction of the annular flow passage, a blade loading on a first stator vane disposed at the most upstream side is set to be smaller than a blade loading of a second stator vane disposed downstream of the first stator vane by one row.
    Type: Application
    Filed: August 4, 2011
    Publication date: March 22, 2012
    Applicant: Hitachi, Ltd.
    Inventors: Yasuo TAKAHASHI, Chihiro Myoren, Ryou Akiyama, Ichiro Miyoshi
  • Publication number: 20120060509
    Abstract: An inner bleed structure of the 2-shaft gas turbine includes a slit for leading part of compressed air to a cavity is formed between a wall surface of a rotor wheel of the compressor equipped with a last stage rotor of the compressor which is connected to a first rotating shaft and end of an inner casing, and a bleed hole for leading part of compressed air after flowing down the last stage of the compressor to a cavity formed in the inner side of the inner casing at the downstream side of the last stage of the compressor.
    Type: Application
    Filed: August 5, 2011
    Publication date: March 15, 2012
    Applicant: Hitachi, Ltd.
    Inventors: Chihiro MYOREN, Ryou Akiyama, Shinya Marushima, Yasuo Takahashi, Shinichi Higuchi
  • Publication number: 20100293963
    Abstract: On a two-shaft gas turbine, on at least one of an inner peripheral side or an outer peripheral side of a main flow passage, an outlet of a high-pressure turbine is lower than an inlet of a low-pressure turbine, an outer periphery of a flow channel that connects the outlet of the high-pressure turbine and the inlet of the low-pressure turbine includes a first casing shroud that is supported by a casing and located on an outer peripheral side of a final-stage rotor vane of the high-pressure turbine, and an initial-stage stator vane of the low-pressure turbine, and a connection position of the first casing shroud and the initial-stage stator vane of the low-pressure turbine is closer to the inlet of the initial-stage stator vane of the low-pressure turbine than the outlet of the final-stage rotor vane of the high-pressure turbine.
    Type: Application
    Filed: May 14, 2010
    Publication date: November 25, 2010
    Applicant: Hitachi, Ltd.
    Inventors: Chihiro Myoren, Ryou Akiyama
  • Patent number: 7320175
    Abstract: The invention provides a production process of a gas turbine capable of being applied to various cycles. A principal part of a gas turbine is set in advance based on roughly set conditions, and the number of stages of a compressor and the number of stages of a turbine, which can provide conditions suitable for a desired cycle, are set based on the set principal part. The compressor and the turbine each having the set number of stages and included in the principal part are combined with each other to construct the gas turbine. When the set number of stages of the compressor or the turbine differs among a plurality of desired cycles, a substantially disk-shaped member having an outer periphery, which forms an inner peripheral wall of a substantially annular flow passage of the compressor or the turbine, is assembled into the cycle having a smaller number of stages so that the bearing-to-bearing distance is kept constant in the gas turbine operated in the plurality of desired cycles.
    Type: Grant
    Filed: January 29, 2004
    Date of Patent: January 22, 2008
    Assignee: Hitachi, Ltd.
    Inventors: Tomomi Koganezawa, Takanori Shibata, Nobuhiro Seiki, Shinya Marushima, Shinichi Higuchi, Nobuaki Kizuka, Ryou Akiyama, Masami Noda
  • Publication number: 20050076502
    Abstract: The invention provides a production process of a gas turbine capable of being applied to various cycles. A principal part of a gas turbine is set in advance based on roughly set conditions, and the number of stages of a compressor and the number of stages of a turbine, which can provide conditions suitable for a desired cycle, are set based on the set principal part. The compressor and the turbine each having the set number of stages and included in the principal part are combined with each other to construct the gas turbine. When the set number of stages of the compressor or the turbine differs among a plurality of desired cycles, a substantially disk-shaped member having an outer periphery, which forms an inner peripheral wall of a substantially annular flow passage of the compressor or the turbine, is assembled into the cycle having a smaller number of stages so that the bearing-to-bearing distance is kept constant in the gas turbine operated in the plurality of desired cycles.
    Type: Application
    Filed: January 29, 2004
    Publication date: April 14, 2005
    Inventors: Tomomi Koganezawa, Takanori Shibata, Nobuhiro Seiki, Shinya Marushima, Shinichi Higuchi, Nobuaki Kizuka, Ryou Akiyama, Masami Noda
  • Patent number: 6877324
    Abstract: A turbine rotor includes a plurality of moving blades having cooling paths through which a refrigerant flows inside, a plurality of wheels having the moving blades mounted in the outer periphery thereof and at least one spacer member installed between the wheels. The spacer member has a plurality of flow paths through which a refrigerant flows after cooling the moving blades. The plurality of flow paths have flow paths interconnecting to the cooling paths in the moving blades on a first wheel adjacent the spacer member and interconnecting to a space formed on a side wall surface with which a second wheel adjacent the spacer member and the spacer member are in contact.
    Type: Grant
    Filed: April 11, 2003
    Date of Patent: April 12, 2005
    Assignee: Hitachi, Ltd.
    Inventors: Ryou Akiyama, Shinya Marushima, Manabu Matsumoto, Tsuyoshi Takano
  • Patent number: 6865893
    Abstract: A production process of a gas turbine capable of being applied to various cycles. A principal part of a gas turbine is initially set based on roughly set conditions, and the number of stages of the compressor and of the turbine for a desired cycle are set for the principal part. The compressor and the turbine each having the set number of stages and included in the principal part are combined to construct the gas turbine. When the set number of stages of the compressor or the turbine differs for a different desired cycle, a disk-shaped member having an outer periphery, which forms an inner peripheral wall of the annular flow passage of the compressor or the turbine, is assembled into the principal part having a smaller number of stages so that the bearing-to-bearing distance is kept constant.
    Type: Grant
    Filed: June 25, 2003
    Date of Patent: March 15, 2005
    Assignee: Hitachi, Ltd.
    Inventors: Tomomi Koganezawa, Takanori Shibata, Nobuhiro Seiki, Shinya Marushima, Shinichi Higuchi, Nobuaki Kizuka, Ryou Akiyama, Masami Noda
  • Publication number: 20040060296
    Abstract: The invention provides a production process of a gas turbine capable of being applied to various cycles. A principal part of a gas turbine is set in advance based on roughly set conditions, and the number of stages of a compressor and the number of stages of a turbine, which can provide conditions suitable for a desired cycle, are set based on the set principal part. The compressor and the turbine each having the set number of stages and included in the principal part are combined with each other to construct the gas turbine. When the set number of stages of the compressor or the turbine differs among a plurality of desired cycles, a substantially disk-shaped member having an outer periphery, which forms an inner peripheral wall of a substantially annular flow passage of the compressor or the turbine, is assembled into the cycle having a smaller number of stages so that the bearing-to-bearing distance is kept constant in the gas turbine operated in the plurality of desired cycles.
    Type: Application
    Filed: June 25, 2003
    Publication date: April 1, 2004
    Inventors: Tomomi Koganezawa, Takanori Shibata, Nobuhiro Seiki, Shinya Marushima, Shinichi Higuchi, Nobuaki Kizuka, Ryou Akiyama, Masami Noda
  • Publication number: 20030170114
    Abstract: In a gas turbine having a structure of collecting a refrigerant after cooling the moving blades, a plurality of wheels having a plurality of moving blades including cooling paths in the outer periphery and a plurality of spacer members are alternately arranged on the rotating axis. A plurality of flow paths through which a refrigerant after cooling the moving blades flows are installed in the spacer members, and the first flow paths interconnect the moving blades arranged on the wheels on the upstream side of gas flow to the downstream side of gas flow of the spacer members, and the second flow paths interconnect the moving blades arranged on the wheels on the downstream side of gas flow to the upstream side of gas flow of the spacer members. The flow paths may be provided with bent parts in the neighborhood of the center of the space members in the axial direction or may be in a linear shape.
    Type: Application
    Filed: April 11, 2003
    Publication date: September 11, 2003
    Applicant: Hitachi, Ltd.
    Inventors: Ryou Akiyama, Shinya Marushima, Manabu Matsumoto, Tsuyoshi Takano
  • Patent number: 6568192
    Abstract: A turbine rotor includes a plurality of moving blades having cooling paths through which a refrigerant flows inside, a plurality of wheels having the moving blades mounted in the outer periphery thereof and at least one spacer member installed between the wheels. The spacer member has a plurality of flow paths through which a refrigerant flows after cooling the moving blades. The plurality of flow paths have flow paths interconnecting to the cooling paths in the moving blades on a first wheel adjacent the spacer member and interconnecting to a space formed on a side wall surface with which a second wheel adjacent the spacer member and the spacer member are in contact.
    Type: Grant
    Filed: May 6, 2002
    Date of Patent: May 27, 2003
    Assignee: Hitachi, Ltd.
    Inventors: Ryou Akiyama, Shinya Marushima, Manabu Matsumoto, Tsuyoshi Takano
  • Publication number: 20020124570
    Abstract: In a gas turbine having a structure of collecting a refrigerant after cooling the moving blades, a plurality of wheels having a plurality of moving blades including cooling paths in the outer periphery and a plurality of spacer members are alternately arranged on the rotating axis. A plurality of flow paths through which a refrigerant after cooling the moving blades flows are installed in the spacer members, and the first flow paths interconnect the moving blades arranged on the wheels on the upstream side of gas flow to the downstream side of gas flow of the spacer members, and the second flow paths interconnect the moving blades arranged on the wheels on the downstream side of gas flow to the upstream side of gas flow of the spacer members. The flow paths may be provided with bent parts in the neighborhood of the center of the space members in the axial direction or may be in a linear shape.
    Type: Application
    Filed: May 6, 2002
    Publication date: September 12, 2002
    Inventors: Ryou Akiyama, Shinya Marushima, Manabu Matsumoto, Tsuyoshi Takano
  • Patent number: 6405538
    Abstract: A gas turbine having a structure for collecting a refrigerant after cooling the moving blades, has a plurality of wheels having a plurality of moving blades including cooling paths in the outer periphery and a plurality of spacer members alternately arranged on the rotating axis. A plurality of flow paths through which a refrigerant flows after cooling the moving blades are provided in the spacer members. First flow paths interconnect the moving blades arranged on the wheels on the upstream side of gas flow to the downstream side of gas flow of the spacer members, and second flow paths interconnect the moving blades arranged on the wheels on the downstream side of gas flow to the upstream side of gas flow of the spacer members. The flow paths may be provided with bent parts in the neighborhood of the center of the space members in the axial direction or may be in a linear shape.
    Type: Grant
    Filed: August 24, 2000
    Date of Patent: June 18, 2002
    Assignee: Hitachi, Ltd.
    Inventors: Ryou Akiyama, Shinya Marushima, Manabu Matsumoto, Tsuyoshi Takano