Patents by Inventor Takashi Ikeguchi

Takashi Ikeguchi 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: 7028487
    Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.
    Type: Grant
    Filed: February 23, 2004
    Date of Patent: April 18, 2006
    Assignee: Hitachi, Ltd.
    Inventors: Shinya Marushima, Manabu Matsumoto, Kazuhiko Kawaike, Takashi Ikeguchi, Takashi Machida, Masaru Sekihara
  • Patent number: 7028486
    Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.
    Type: Grant
    Filed: February 23, 2004
    Date of Patent: April 18, 2006
    Assignee: Hitachi, Ltd.
    Inventors: Shinya Marushima, Manabu Matsumoto, Kazuhiko Kawaike, Takashi Ikeguchi, Takashi Machida, Masaru Sekihara
  • Publication number: 20040163394
    Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.
    Type: Application
    Filed: February 23, 2004
    Publication date: August 26, 2004
    Applicant: Hitachi, Ltd.
    Inventors: Shinya Marushima, Manabu Matsumoto, Kazuhiko Kawaike, Takashi Ikeguchi, Takashi Machida, Masaru Sekibara
  • Publication number: 20040161335
    Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.
    Type: Application
    Filed: February 23, 2004
    Publication date: August 19, 2004
    Applicant: Hitachi, Ltd.
    Inventors: Shinya Marushima, Manabu Matsumoto, Kazuhiko Kawaike, Takashi Ikeguchi, Takashi Machida, Masaru Sekihara
  • Patent number: 6735957
    Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.
    Type: Grant
    Filed: April 1, 2003
    Date of Patent: May 18, 2004
    Assignee: Hitachi, Ltd.
    Inventors: Shinya Marushima, Manabu Matsumoto, Kazuhiko Kawaike, Takashi Ikeguchi, Takashi Machida, Masaru Sekihara
  • Publication number: 20030167777
    Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.
    Type: Application
    Filed: April 1, 2003
    Publication date: September 11, 2003
    Applicant: Hitachi, Ltd.
    Inventors: Shinya Marushima, Manabu Matsumoto, Kazuhiko Kawaike, Takashi Ikeguchi, Takashi Machida, Masaru Sekihara
  • Patent number: 6568191
    Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.
    Type: Grant
    Filed: February 26, 2002
    Date of Patent: May 27, 2003
    Assignee: Hitachi, Ltd.
    Inventors: Shinya Marushima, Manabu Matsumoto, Kazuhiko Kawaike, Takashi Ikeguchi, Takashi Machida, Masaru Sekihara
  • Publication number: 20020085911
    Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.
    Type: Application
    Filed: February 26, 2002
    Publication date: July 4, 2002
    Inventors: Shinya Marushima, Manabu Matsumoto, Kazuhiko Kawaike, Takashi Ikeguchi, Takashi Machida, Masaru Sekihara
  • Patent number: 6393829
    Abstract: A gas turbine has a rotor shaft which includes a plurality of discs, each having a plurality of moving blades driven by combustion gas and arranged annularly on the peripheral portion and having spaces arranged between the discs. The respective discs and spacers are arranged in the axial direction. Gap portions are formed between the rotor axis side regions of the discs facing the spacers and adjacent spacers. Contact surfaces contacting each other on both rotor peripheral side regions of the discs facing the spaces and adjacent spacers are formed. A first flow path for supplying a coolant into the moving blades and a second flow path for recovering the coolant heated by the moving blades from the moving blade are provided. A third flow path for introducing fluid into the gap portions is formed in the discs with the third flow path being independent from the first and second flow paths.
    Type: Grant
    Filed: May 28, 1999
    Date of Patent: May 28, 2002
    Assignee: Hitachi, Ltd.
    Inventors: Shinya Marushima, Manabu Matsumoto, Kazuhiko Kawaike, Takashi Ikeguchi, Takashi Machida, Masaru Sekihara
  • Patent number: 6370866
    Abstract: Operational reliability of a gas turbine is improved by suppressing the thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs. Gap portions are formed between a region on the rotor shaft center portion side of the discs facing the spacers and spacers adjacent thereof. Contact surfaces are formed which contact on both a region on the rotor peripheral side of the discs facing the spacers and adjacent spacers thereto. Furthermore, a third flow path leading fluid to the above-mentioned gap portions is provided.
    Type: Grant
    Filed: January 5, 2001
    Date of Patent: April 16, 2002
    Assignee: Hitachi, Ltd.
    Inventors: Shinya Marushima, Manabu Matsumoto, Kazuhiko Kawaike, Takashi Ikeguchi, Takashi Machida, Masaru Sekihara
  • Publication number: 20020018710
    Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.
    Type: Application
    Filed: May 28, 1999
    Publication date: February 14, 2002
    Inventors: SHINYA MARUSHIMA, MANABU MATSUMOTO, KAZUHIKO KAWAIKE, TAKASHI IKEGUCHI, TAKASHI MACHIDA, MASARU SEKIHARA
  • Publication number: 20010000846
    Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.
    Type: Application
    Filed: January 5, 2001
    Publication date: May 10, 2001
    Inventors: Shinya Marushima, Manabu Matsumoto, Kazuhiko Kawaike, Takashi Ikeguchi, Takashi Machida, Masaru Sekihara
  • Patent number: 6202400
    Abstract: To improve the thermal efficiency when an exhaust heat recovery type combined cycle plant having a gas turbine and a steam turbine in combination is operated at a partial load, the gas turbine exhaust is recirculated and returned to the compressor, and the combustion temperature is prevented from being lowered at the partial load. Preferably, the temperature is maintained constant. In this way, the thermal efficiency during operation at partial load can be improved.
    Type: Grant
    Filed: March 9, 2000
    Date of Patent: March 20, 2001
    Assignee: Hitachi, Ltd.
    Inventors: Motoaki Utamura, Shinichi Hoizumi, Yasushi Takeda, Toshihiko Sasaki, Hideaki Komatsu, Seiichi Kirikami, Takeshi Suzumura, Tetsuo Sasada, Takashi Ikeguchi, Shigehisa Sugita
  • Patent number: 6185924
    Abstract: A high efficiency coolant collection type gas turbine is obtained by forming coolant supply and collection flow paths for moving blades in a more outer peripheral side of a gas turbine rotor than a hub, supplying the coolant supplied from a shaft end into the moving blades through the supply flow path, collecting the coolant after cooling into a combustion chamber side, supplying air extracted from a compressor to cool moving blades of a downstream side stage or a rotor outer wall through slits formed from a turbine rotor central portion to the hub, reducing rotor thermal stress and a pressure loss of the coolant flow paths and cooling a high stage side of a compressor rotor.
    Type: Grant
    Filed: October 15, 1998
    Date of Patent: February 13, 2001
    Assignee: Hitachi, Ltd.
    Inventors: Manabu Matsumoto, Shinya Marushima, Takashi Ikeguchi, Kazuhiko Kawaike
  • Patent number: 6173562
    Abstract: To improve the thermal efficiency when an exhaust heat recovery type combined cycle plant having a gas turbine and a steam turbine in combination is operated at a partial load, the gas turbine exhaust is recirculated and returned to the compressor, and the combustion temperature is prevented from being lowered at the partial load. Preferably, the temperature is maintained constant. In this way, the thermal efficiency during operation at partial load can be improved.
    Type: Grant
    Filed: February 12, 1998
    Date of Patent: January 16, 2001
    Assignee: Hitachi, Ltd.
    Inventors: Motoaki Utamura, Shinichi Hoizumi, Yasushi Takeda, Toshihiko Sasaki, Hideaki Komatsu, Seiichi Kirikami, Takeshi Suzumura, Tetsuo Sasada, Takashi Ikeguchi, Shigehisa Sugita
  • Patent number: 5794431
    Abstract: To improve the thermal efficiency when an exhaust heat recovery type combined cycle plant having a gas turbine and a steam turbine in combination is operated at a partial load, the gas turbine exhaust is recirculated and returned to the compressor, and the combustion temperature is prevented from being lowered at the partial load. Preferably, the temperature is maintained constant. In this way, the thermal efficiency during operation at partial load can be improved.
    Type: Grant
    Filed: December 6, 1995
    Date of Patent: August 18, 1998
    Assignee: Hitachi, Ltd.
    Inventors: Motoaki Utamura, Shinichi Hoizumi, Yasushi Takeda, Toshihiko Sasaki, Hideaki Komatsu, Seiichi Kirikami, Takeshi Suzumura, Tetsuo Sasada, Takashi Ikeguchi, Shigehisa Sugita
  • Patent number: 5695319
    Abstract: A vapor cooled gas turbine has a cooling system including a vapor supply port and a vapor recovery port, and the cooling system is formed so that vapor from the supply port is supplied to blades through a central supply passage in a rotor and the vapor having cooled the blades is recovered from the recovery port through a recovery passage spaced outwardly from the supply passage.
    Type: Grant
    Filed: April 4, 1996
    Date of Patent: December 9, 1997
    Assignee: Hitachi, Ltd.
    Inventors: Manabu Matsumoto, Kazuhiko Kawaike, Takashi Ikeguchi, Shunichi Anzai, Masami Noda, Nobuaki Kizuka, Shin'ichi Higuchi, Shinya Marushima, Masaru Sekihara
  • Patent number: 5393198
    Abstract: A blade for a gas turbine has a leading edge portion which has an arc-shaped cross-section, and a maximum thickness portion of the blade is located within this arc. With this blade configuration, an abrupt acceleration of hot gas at the leading edge portion of the blade is restrained, so that the velocity of the hot gas at the blade surface can be made low. Therefore, the heat transfer coefficient from the hot gas to the blade wall is lowered, so that the amount of cooling air required to be passed through the interior of the blade can be reduced.
    Type: Grant
    Filed: September 14, 1993
    Date of Patent: February 28, 1995
    Assignee: Hitachi, Ltd.
    Inventors: Masami Noda, Takashi Ikeguchi, Shunichi Anzai, Kazuhiko Kawaike, Isao Takehara
  • Patent number: 5177448
    Abstract: An industrial compact synchrotron radiation source includes, for the purpose of prolonging lifetime of a charged particle beam, beam absorbers made of a material having a low photodesorption yield and disposed inside a bending section/vacuum chamber at at least positions upon which the synchrotron radiation is irradiated, and electrically conductive beam stabilizers disposed at positions inside the bending section/vacuum chamber which are distant by a predetermined distance from an orbit of the charged particle beam toward the outer circumferential wall of the bending section/vacuum chamber.
    Type: Grant
    Filed: November 21, 1990
    Date of Patent: January 5, 1993
    Assignees: Hitachi, Ltd., Nippon Telegraph and Telephone Corporation, Hitachi Service Engineering Co., Ltd.
    Inventors: Takashi Ikeguchi, Manabu Matsumoto, Shinjiroo Ueda, Tadasi Sonobe, Toru Murashita, Satoshi Ido, Kazuo Kuroichi, Akinori Shibayama
  • Patent number: 5100293
    Abstract: A cooling structure for a turbine blade. Comprising a hollow-structured main body and a cooling medium discharging device located in the inner cavity of the hollow-structured main body and formed to discharge a cooling medium from the surface thereof, so that the cooling medium discharged from the cooling medium discharging device impinges against the inner surface of the main body to remove the heat from the same. The turbine blade further includes a projection formed on the inner surface of the leading edge of the main body, extending along the spanwise direction of the blade, and the cooling medium discharging device is formed to allow at least part of the cooling medium to directly impinge against proximal portions of the projection. With this arrangement, a turbine blade is provided which allows a small amount of cooling air to cool the turbine blade and its leading edge in particular with great effectiveness.
    Type: Grant
    Filed: August 28, 1990
    Date of Patent: March 31, 1992
    Assignee: Hitachi, Ltd.
    Inventors: Shunichi Anzai, Kazuhiko Kawaike, Takashi Ikeguchi, Masami Noda, Tetsuo Sasada, Isao Takehara, Haruo Urushidani