Patents by Inventor Takaaki HASE
Takaaki HASE 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: 11339676Abstract: This aircraft gas turbine is provided with a rotor, a rotor blade (24), a casing, a stationary blade (26), and a guide member (53). The rotor blade (24) has fins (43) projecting from the outer peripheral surface (42a) of a rotor blade shroud (42). A stationary blade shroud (51) of the stationary blade (26) forms a cavity (Ct) with at least the rotor blade shroud (42) and the fins (43). The guide member (53) is provided inside the cavity (Ct) and extends inward from the radial outer side, and an inner-side end part (53a) on the radial inner side faces the outer peripheral surface (42a) of the rotor blade shroud (42) with a gap therebetween.Type: GrantFiled: December 4, 2018Date of Patent: May 24, 2022Assignee: MITSUBISHI HEAVY INDUSTRIES AERO ENGINES, LTD.Inventors: Daigo Fujimura, Takaaki Hase, Hirokazu Hagiwara
-
Patent number: 11118476Abstract: Provided is a transition duct that forms an annular gas flow channel through which a main flow gas flows from a high-pressure turbine to a low-pressure turbine, wherein the gas flow channel has an inner peripheral flow channel surface and an outer peripheral flow channel surface, the inner peripheral flow channel surface and the outer peripheral flow channel surface extend radially outward while angles of inclination relative to an axial direction of a rotating shaft change from the high-pressure turbine (first turbine) toward the low-pressure turbine (second turbine), and an inner peripheral maximum inclined part is provided in a range A2 that extends in the axial direction from a position of alignment with an outer peripheral maximum inclined part to a position advanced toward the low-pressure turbine by a length no more than 20% of the duct length.Type: GrantFiled: December 8, 2017Date of Patent: September 14, 2021Assignee: MITSUBISHI HEAVY INDUSTRIES AERO ENGINES, LTD.Inventors: Takaaki Hase, Daigo Fujimura, Tadayuki Hanada
-
Patent number: 11111820Abstract: A gas turbine for an aircraft includes: blades each including a blade body extending outward from a rotor rotating about an axis in a radial direction of the rotor and a fin protruding from an outer peripheral surface of a blade shroud formed on a distal end of the blade body; a casing installed to form gaps between the casing and the fins; and vanes each including a vane shroud formed such that at least a leading end portion of the vane shroud formed upstream in an axial direction is located outside with respect to an extended line of an inner peripheral surface of the casing in the radial direction.Type: GrantFiled: December 26, 2018Date of Patent: September 7, 2021Assignee: MITSUBISHI HEAVY INDUSTRIES AERO ENGINES, LTD.Inventors: Daigo Fujimura, Hiroshi Watanabe, Tadayuki Hanada, Takaaki Hase
-
Publication number: 20210180464Abstract: This aircraft gas turbine is provided with a rotor, a rotor blade (24), a casing, a stationary blade (26), and a guide member (53). The rotor blade (24) has fins (43) projecting from the outer peripheral surface (42a) of a rotor blade shroud (42). A stationary blade shroud (51) of the stationary blade (26) forms a cavity (Ct) with at least the rotor blade shroud (42) and the fins (43). The guide member (53) is provided inside the cavity (Ct) and extends inward from the radial outer side, and an inner-side end part (53a) on the radial inner side faces the outer peripheral surface (42a) of the rotor blade shroud (42) with a gap therebetween.Type: ApplicationFiled: December 4, 2018Publication date: June 17, 2021Inventors: Daigo FUJIMURA, Takaaki HASE, Hirokazu HAGIWARA
-
Publication number: 20210079811Abstract: A gas turbine for an aircraft includes: blades each including a blade body extending outward from a rotor rotating about an axis in a radial direction of the rotor and a fin protruding from an outer peripheral surface of a blade shroud formed on a distal end of the blade body; a casing installed to form gaps between the casing and the fins; and vanes each including a vane shroud formed such that at least a leading end portion of the vane shroud formed upstream in an axial direction is located outside with respect to an extended line of an inner peripheral surface of the casing in the radial direction.Type: ApplicationFiled: December 26, 2018Publication date: March 18, 2021Inventors: Daigo FUJIMURA, Hiroshi WATANABE, Tadayuki HANADA, Takaaki HASE
-
Patent number: 10663169Abstract: A cylinder for a combustor includes a cylindrical member, a first cooling passage defined in the cylindrical member and a second cooling passage defined in the cylindrical member, and a supply port extender. The first cooling passage includes a supply port that opens to an outer peripheral surface of the cylindrical member. The second cooling passage includes a discharge port that opens to the outer peripheral surface of the cylindrical member downstream of the supply port. The supply port extender includes a first wall that is disposed between the supply port and the discharge port and extends away from the outer peripheral surface of the cylindrical member and a second wall that is disposed upstream of the supply port and extends away from the outer peripheral surface of the cylindrical member.Type: GrantFiled: July 22, 2015Date of Patent: May 26, 2020Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.Inventors: Satoshi Mizukami, Satoshi Tanimura, Tetsu Konishi, Masaki Mitani, Taiki Kinoshita, Yoshiaki Yamaguchi, Takaaki Hase, Hiroshi Makigano, Hikaru Kurosaki
-
Publication number: 20190226359Abstract: Provided is a transition duct that forms an annular gas flow channel through which a main flow gas flows from a high-pressure turbine to a low-pressure turbine, wherein the gas flow channel has an inner peripheral flow channel surface and an outer peripheral flow channel surface, the inner peripheral flow channel surface and the outer peripheral flow channel surface extend radially outward while angles of inclination relative to an axial direction of a rotating shaft change from the high-pressure turbine (first turbine) toward the low-pressure turbine (second turbine), and an inner peripheral maximum inclined part is provided in a range A2 that extends in the axial direction from a position of alignment with an outer peripheral maximum inclined part to a position advanced toward the low-pressure turbine by a length no more than 20% of the duct length.Type: ApplicationFiled: December 8, 2017Publication date: July 25, 2019Inventors: Takaaki HASE, Daigo FUJIMURA, Tadayuki HANADA
-
Publication number: 20170108221Abstract: A cylinder for a combustor provided with a cylindrical member, a first cooling passage and a second cooling passage formed in the cylindrical member, and a supply port extended portion. The first cooling passage includes a supply port that opens to an outer peripheral surface of the cylindrical member. The second cooling passage includes a discharge port that opens to the outer peripheral surface of the cylindrical member downstream of the supply port. The supply port extended portion includes a first wall portion disposed between the supply port and the discharge port extending away from the outer peripheral surface of the cylindrical member and a second wall portion disposed upstream of the supply port extending away from the outer peripheral surface of the cylindrical member.Type: ApplicationFiled: July 22, 2015Publication date: April 20, 2017Inventors: Satoshi MIZUKAMI, Satoshi TANIMURA, Tetsu KONISHI, Masaki MITANI, Taiki KINOSHITA, Yoshiaki YAMAGUCHI, Takaaki HASE, Hiroshi MAKIGANO, Hikaru KUROSAKI
-
Patent number: 9360216Abstract: A gas turbine includes downstream side members that face a passage and have guide faces arranged in the passage side as it goes toward the upstream side. In a cross section including an axis center of a rotor shaft extending in a flow direction of a gas main stream, extension sections of the guide faces continuing to the upstream end portion of the guide faces are arranged downstream from the cavity inner wall portion of the upstream side member facing the cavities.Type: GrantFiled: May 29, 2013Date of Patent: June 7, 2016Assignee: Mitsubishi Heavy Industries Aero Engines, Ltd.Inventors: Takaaki Hase, Yoshihiro Kuwamura, Osamu Morii, Tadayuki Hanada, Hirokazu Hagiwara
-
Publication number: 20140020392Abstract: A gas turbine includes downstream side members that face a passage and have guide faces arranged in the passage side as it goes toward the upstream side. In a cross section including an axis center of a rotor shaft extending in a flow direction of a gas main stream, extension sections of the guide faces continuing to the upstream end portion of the guide faces are arranged downstream from the cavity inner wall portion of the upstream side member facing the cavities.Type: ApplicationFiled: May 29, 2013Publication date: January 23, 2014Inventors: Takaaki HASE, Yoshihiro KUWAMURA, Osamu MORII, Tadayuki HANADA, Hirokazu HAGIWARA