Patents by Inventor Chihiro MYOREN

Chihiro MYOREN 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: 9638050
    Abstract: An axial compressor includes: a rotor as a rotational shaft, rotor blades mounted on the rotor, a compressor casing that covers the rotor and the rotor blades, and stator vanes mounted on the compressor casing. The rotor blades and the stator vanes are each disposed in a circumferential direction of the rotational shaft to form a rotor-blade cascade and a stator-vane cascade, respectively. The rotor-blade cascade and the stator-vane cascade are arranged in plural rows, respectively, in an axial direction of the rotational shaft. The stator vane has a dovetail, and the compressor casing has a dovetail groove that extends in the circumferential direction of the rotational shaft to receive the dovetail inserted therein to fix the stator vanes. Two or more stator vanes, the stator vanes belonging to stator-vane cascades different from each other, are fixed in the dovetail groove.
    Type: Grant
    Filed: July 28, 2014
    Date of Patent: May 2, 2017
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Hiroki Takeda, Yasuo Takahashi, Chihiro Myoren
  • Publication number: 20170030375
    Abstract: An axial flow compressor includes multiple rotor blade rows configured to include multiple rotor blades and multiple stator blade rows configured to include multiple stator blades, the multiple rotor blades and the multiple stator blades being arranged in an annular channel through which a working fluid flows. A portion of at least one wall surface on an inner peripheral side and an outer peripheral side of the annular channel, the portion being at an arrangement portion where at least any one blade row of the rotor blade rows and the stator blade rows is located, has a protruding portion such that downstream side part of the portion is curved so as to further protrude to the annular channel than upstream side part of the portion.
    Type: Application
    Filed: July 27, 2016
    Publication date: February 2, 2017
    Inventors: Takanori SHIBATA, Naoto OMURA, Chihiro MYOREN, Yasuo TAKAHASHI
  • Publication number: 20160245172
    Abstract: A two-shaft gas turbine of the present invention, in which a mass flow of an air into a compressor is regulated by controlling a set angle of an inlet guide vane (IGV) on an air intake side of the compressor, comprises, as a device to control the set angle of the IGV, a first controller to control the set angle of the IGV based on a corrected speed of the gas generator shaft during low speed rotation of the gas generator shaft, the corrected speed having been corrected according to an ambient temperature; a second controller to control the set angle of the IGV to maintain a constant actual speed of the gas generator shaft during high speed rotation of the gas generator shaft; and an ambient temperature correction part to increase the actual speed maintained constant by the second controller if the ambient temperature is equal to or more than a threshold value.
    Type: Application
    Filed: February 22, 2016
    Publication date: August 25, 2016
    Inventors: Chihiro MYOREN, Kenji NANATAKI, Yasuo TAKAHASHI, Kota KAWAMURA
  • Publication number: 20160245300
    Abstract: An axial compressor includes a plurality of stator vanes attached to an inner surface of a casing defining an annular flow path and a plurality of rotor blades attached to a rotating rotor defining the annular flow path. A flow path is defined between a pressure surface of a stator vane and a suction surface of a stator vane, the vanes being circumferentially adjacent to each other, or between a pressure surface of a rotor blade and a suction surface of a rotor blade, the blades being circumferentially adjacent to each other. The flow path is formed so that a throat portion at which a flow path width is minimized is provided on the upstream side of 50% of an axial chord length.
    Type: Application
    Filed: February 25, 2016
    Publication date: August 25, 2016
    Inventors: Yasuo TAKAHASHI, Chihiro MYOREN
  • Patent number: 9303656
    Abstract: An axial compressor includes a plurality of stator vanes attached to an inner surface of a casing defining an annular flow path and a plurality of rotor blades attached to a rotating rotor defining the annular flow path. A flow path is defined between a pressure surface of a stator vane and a suction surface of a stator vane, the vanes being circumferentially adjacent to each other, or between a pressure surface of a rotor blade and a suction surface of a rotor blade, the blades being circumferentially adjacent to each other. The flow path is formed so that a throat portion at which a flow path width is minimized is provided on the upstream side of 50% of an axial chord length.
    Type: Grant
    Filed: October 13, 2011
    Date of Patent: April 5, 2016
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Yasuo Takahashi, Chihiro Myoren
  • Patent number: 9279329
    Abstract: The present invention provides a transonic blade that concurrently achieves reduction in shock loss at a design point and improvement in stall margin in blades operating in a flow field of transonic speed or higher in an axial-flow rotating machine. A cross-sectional surface at each of spanwise positions of the blade is shifted parallel to a stagger line connecting a leading edge with a trailing edge of the blade. A stacking line is shifted toward an upstream side of working fluid. The stacking line connects together respective gravity center positions of blade cross-sectional surfaces at spanwise positions in a range from a hub cross-sectional surface joined to a rotating shaft or an outer circumferential side casing of a rotating machine to a tip cross-sectional surface lying at a position most remote from the hub cross-sectional surface in a spanwise direction.
    Type: Grant
    Filed: October 18, 2010
    Date of Patent: March 8, 2016
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Chihiro Myoren, Yasuo Takahashi, Shinya Marushima
  • Patent number: 9217368
    Abstract: A method of modifying a gas turbine plant which is provided with a one-shaft gas turbine having a compressor for compressing air, a combustor for generating a combustion gas from the air compressed by the compressor and a fuel, and a one-shaft turbine driven by the combustion gas generated by the combustor and supported by a rotational axis common to the compressor, and an electric generator for generating electric power by driving force of the one-shaft turbine, wherein: the one-shaft turbine is replaced with a two-shaft gas turbine including a compressor for compressing air, a combustor for generating a combustion gas from the air compressed by the compressor and a fuel, and a high-pressure turbine driven by the combustion gas generated by the combustor and supported by a first rotational axis common to the compressor, and a low-pressure turbine driven by the combustion gas used to drive the high-pressure turbine and supported by a second rotational axis, which is different from the axis for the high-pressu
    Type: Grant
    Filed: December 30, 2010
    Date of Patent: December 22, 2015
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Chihiro Myoren, Ryo Akiyama, Shinya Marushima
  • 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: 20150030438
    Abstract: An axial compressor includes: a spray nozzle (32) that supplies droplets to a working fluid before compression or being compressed; a variable stator vane (56) having a stem section (94) inserted in an insertion hole (73) in a casing (54), the variable stator vane (56) having an angle of attack varied through sliding motion relative to the casing caused by rotation of the stem section; a sealing groove (93) provided in a sliding portion between a thrust washer (82) slid relative to the casing during rotation of the stem section and the casing; and a sealing member (92) housed in the sealing groove.
    Type: Application
    Filed: July 22, 2014
    Publication date: January 29, 2015
    Inventors: Yasuo TAKAHASHI, Chihiro MYOREN, Kohta KAWAMURA
  • Publication number: 20150027131
    Abstract: An axial compressor includes: a rotor as a rotational shaft; a plurality of rotor blades mounted on the rotor; a compressor casing that covers the rotor and the rotor blades; a plurality of stator vanes mounted on the compressor casing. The rotor blades and the stator vanes are each disposed in a circumferential direction of the rotational shaft to form a rotor-blade cascade and a stator-vane cascade, respectively. The rotor-blade cascade and the stator-vane cascade are arranged in plural rows, respectively, in an axial direction of the rotational shaft. The stator vane has a dovetail as a base for supporting a vane section. The compressor casing has a dovetail groove formed therein. The dovetail groove extends in the circumferential direction of the rotational shaft to receive the dovetail inserted therein to fix the stator vanes. Two or more stator vanes, the stator vanes belonging to stator-vane cascades different from each other, are fixed in the dovetail groove.
    Type: Application
    Filed: July 28, 2014
    Publication date: January 29, 2015
    Inventors: Hiroki TAKEDA, Yasuo TAKAHASHI, Chihiro MYOREN
  • Publication number: 20140178176
    Abstract: An axial compressor comprising liquid drop feed means for feeding liquid drops to an operating fluid of the compressor, a casing for forming a flow path through which the operating fluid flows down and a plurality of stages, each of which is composed of one continuous rotor blade row and one continuous stator vane row, the axial compressor being structured so that the liquid drops evaporate inside the compressor, characterized in that: the casing is provided with a cavity therein, and the cavity is formed by an outer casing and an inner casing which is enclosing a periphery of the rotor blade rows at the plurality of stages and forming internally a flow path of the operating fluid, and a flow path is provided for feeding the operating fluid to the cavity on a downstream side of a region forming the cavity of the inner casing.
    Type: Application
    Filed: November 5, 2013
    Publication date: June 26, 2014
    Applicant: Hitachi, Ltd.
    Inventors: Yasuo TAKAHASHI, Tetsuro MORISAKI, Chihiro MYOREN, Kohta KAWAMURA
  • Publication number: 20140034752
    Abstract: In an atomizer constructed to cool inlet air for a gas turbine by spraying fine droplets of water into the inlet air, a spray nozzle is disposed to spray the finely atomized droplets of water from an outer edge of an atomized airstream into a high-speed zone thereof, towards a central region of the airstream. The atomized airstream meets an airstream of a low-speed zone formed at a downstream side, and after the two kinds of airstreams have been mixed and unified, this mixture is supplied to an axisymmetric compressor. Devices such as a feed water pipe and spray nozzle are placed in the low-speed zone so as not to obstruct the airstream.
    Type: Application
    Filed: July 29, 2013
    Publication date: February 6, 2014
    Applicant: Hitachi, Ltd.
    Inventors: Fumio TAKAHASHI, Kazuhito KOYAMA, Shigeo HATAMIYA, Naohiro KUSUMI, Chihiro MYOREN, Go AGATA, Takaaki SEKIAI
  • Publication number: 20130318973
    Abstract: An axial compressor that can remove an attachment within a groove of a casing and recover an effect of suppressing stall on rotor blades, and a gas turbine provided with the axial compressor, are provided. The axial compressor includes a compressor body 6 and a sprayer 9 for spraying droplets in suction gas of the compressor body 6 so that the droplets are introduced into the compressor body 6 and evaporate. The compressor body 6 includes a casing 11, a rotor 12, rotor blades 13, and stator vanes 14. A groove 21 is formed in an inner circumferential surface of the casing 11 so as to be positioned around rotor blades 13 arranged on a front stage side. A purge system 23 is provided that supplies high-pressure air to the groove 21 through communication holes 22.
    Type: Application
    Filed: May 30, 2013
    Publication date: December 5, 2013
    Applicant: Hitachi, Ltd.
    Inventors: Yasuo TAKAHASHI, Chihiro MYOREN, Kohta KAWAMURA
  • Publication number: 20130259668
    Abstract: The present invention provides a transonic blade that concurrently achieves reduction in shock loss at a design point and improvement in stall margin in blades operating in a flow field of transonic speed or higher in an axial-flow rotating machine. A cross-sectional surface at each of spanwise positions of the blade is shifted parallel to a stagger line connecting a leading edge with a trailing edge of the blade. A stacking line is shifted toward an upstream side of working fluid. The stacking line connects together respective gravity center positions of blade cross-sectional surfaces at spanwise positions in a range from a hub cross-sectional surface joined to a rotating shaft or an outer circumferential side casing of a rotating machine to a tip cross-sectional surface lying at a position most remote from the hub cross-sectional surface in a spanwise direction.
    Type: Application
    Filed: October 18, 2010
    Publication date: October 3, 2013
    Applicant: HITACHI, LTD.
    Inventors: Chihiro Myoren, Yasuo Takahashi, Shinya Marushima
  • Patent number: 8425185
    Abstract: A transonic blade is provided that operates in a flow field where flow has a transonic speed or higher in an axial-flow rotating machine and that concurrently achieves a reduction in shock loss and in the local stress of the blade. The transonic blade includes a hub cross-sectional surface joined to a rotating shaft or an outer circumferential side casing of a rotating machine; a tip cross-sectional surface located furthest from the hub cross-sectional surface in a spanwise direction which is a vertical direction of the rotating shaft; a leading edge located on an upstream side; and a trailing edge located on a downstream side. At least a part of a passing working fluid flow has a transonic speed or higher. A portion of a stacking line which is a line connecting together respective gravity centers of cross-sectional surfaces located from the hub cross-sectional surface to the tip cross-sectional surface is located on a downstream side of a stacking center in a flow direction of a working fluid main flow.
    Type: Grant
    Filed: February 17, 2010
    Date of Patent: April 23, 2013
    Assignee: Hitachi, Ltd.
    Inventors: Chihiro Myoren, Yasuo Takahashi
  • 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: 20120093637
    Abstract: An axial compressor includes a plurality of stator vanes attached to an inner surface of a casing defining an annular flow path and a plurality of rotor blades attached to a rotating rotor defining the annular flow path. A flow path is defined between a pressure surface of a stator vane and a suction surface of a stator vane, the vanes being circumferentially adjacent to each other, or between a pressure surface of a rotor blade and a suction surface of a rotor blade, the blades being circumferentially adjacent to each other. The flow path is formed so that a throat portion at which a flow path width is minimized is provided on the upstream side of 50% of an axial chord length.
    Type: Application
    Filed: October 13, 2011
    Publication date: April 19, 2012
    Applicant: Hitachi, Ltd.
    Inventors: Yasuo TAKAHASHI, Chihiro Myoren
  • 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: 20110162369
    Abstract: A method of modifying a gas turbine plant which is provided with a one-shaft gas turbine having a compressor for compressing air, a combustor for generating a combustion gas from the air compressed by the compressor and a fuel, and a one-shaft turbine driven by the combustion gas generated by the combustor and supported by a rotational axis common to the compressor, and an electric generator for generating electric power by driving force of the one-shaft turbine, wherein: the one-shaft turbine is replaced with a two-shaft gas turbine including a compressor for compressing air, a combustor for generating a combustion gas from the air compressed by the compressor and a fuel, and a high-pressure turbine driven by the combustion gas generated by the combustor and supported by a first rotational axis common to the compressor, and a low-pressure turbine driven by the combustion gas used to drive the high-pressure turbine and supported by a second rotational axis, which is different from the axis for the high-pressu
    Type: Application
    Filed: December 30, 2010
    Publication date: July 7, 2011
    Applicant: Hitachi, Ltd.
    Inventors: Chihiro MYOREN, Ryo AKIYAMA, Shinya MARUSHIMA