Patents by Inventor Shunsuke Torii
Shunsuke Torii 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).
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Publication number: 20180306037Abstract: Provided are a turbine blade, a gas turbine, an intermediate product of the turbine blade, and a method of manufacturing the turbine blade. This turbine blade has a blade body having hollow shape, cavities provided inside the blade body, and a cooling passage that opens from the cavities to the rear end portion of the blade body. The cooling passage includes: a first passage provided on the third cavity side and having a width that becomes narrower from the third cavity side toward the rear end portion of the blade body; and a second passage provided on the rear end portion side of the blade body and having a width that is constant from the third cavity side toward the rear end portion of the blade body.Type: ApplicationFiled: November 4, 2016Publication date: October 25, 2018Inventors: Yoshimasa TAKAOKA, Shunsuke TORII, Hidemichi KOYABU, Saki MATSUO, Yasuoki TOMITA, Satoshi HADA, Yoshifumi OKAJIMA
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Publication number: 20180209282Abstract: A gas turbine combustor and a gas turbine; wherein inclined surfaces are provided on inner surfaces of side walls neighboring in a circumferential direction at downstream end portions of transition pieces of combustors, the inclined surfaces being configured to increase a passage area of the transition pieces, a ratio (S/P) is from 0 to 0.2, where (P) is a pitch dimension of first stage vanes, and (S) is a circumferential dimension from an intermediate point between neighboring transition pieces to an upstream end of a first stage vane closest in the circumferential direction; and a ratio (L/P) is from 0.3 to 0.55, where (P) is the pitch dimension, and (L) is an axial dimension from a downstream end of the transition piece to the upstream end of the first stage vane.Type: ApplicationFiled: August 19, 2015Publication date: July 26, 2018Inventors: Yasuro SAKAMOTO, Satoshi MIZUKAMI, Keisuke MATSUYAMA, Satoshi TANIMURA, Masanori YURI, Shunsuke TORII, Hiroaki KISHIDA
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Patent number: 9816161Abstract: Provided is a Ni-based single crystal superalloy containing 6% by mass or more and 12% by mass or less of Cr, 0.4% by mass or more and 3.0% by mass or less of Mo, 6% by mass or more and 10% by mass or less of W, 4.0% by mass or more and 6.5% by mass or less of Al, 0% by mass or more and 1% by mass or less of Nb, 8% by mass or more and 12% by mass or less of Ta, 0% by mass or more and 0.15% by mass or less of Hf, 0.01% by mass or more and 0.2% by mass or less of Si, and 0% by mass or more and 0.04% by mass or less of Zr, and optionally containing at least one element selected from B, C, Y, La, Ce, and V, with a balance being Ni and inevitable impurities.Type: GrantFiled: July 30, 2013Date of Patent: November 14, 2017Assignees: MITSUBISHI HITACHI POWER SYSTEMS, LTD., NATIONAL INSTITUTE FOR MATERIALS SCIENCEInventors: Kyoko Kawagishi, Hiroshi Harada, Tadaharu Yokokawa, Yutaka Koizumi, Toshiharu Kobayashi, Masao Sakamoto, Michinari Yuyama, Masaki Taneike, Ikuo Okada, Sachio Shimohata, Hidetaka Oguma, Ryota Okimoto, Keizo Tsukagoshi, Yoshitaka Uemura, Junichiro Masada, Shunsuke Torii
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Publication number: 20170198594Abstract: A turbine vane (3) includes: a vane body (21); a plate-like inner shroud (22) provided at a radially inner end of the vane body (21); and a plate-like outer shroud (23) provided at a radially outer end of the vane body (21). The vane body (21) includes a serpentine channel (30) which is formed so as to meander inside the vane body (21) in the radial direction and through which a cooling medium flows. The inner shroud (22) includes a cooling path (40) which has one end open at the downstream end side of the serpentine channel (30) and the other end open at a trailing edge (22D) of the inner shroud (22) and through which the serpentine channel (30) communicates with the outside of the inner shroud (22).Type: ApplicationFiled: June 24, 2015Publication date: July 13, 2017Applicant: MITSUBISHI HITACHI POWER SYSTEMS, LTD.Inventors: Keita TAKAMURA, Shunsuke TORII, Masanori YURI
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Patent number: 9512781Abstract: In a cooling structure for a recovery-type air-cooled gas turbine combustor having a recovery-type air-cooling structure that bleeds, upstream of the combustor, and pressurizes compressed air supplied from a compressor, that uses the bled and pressurized air to cool a wall, and that recovers and reuses the bled and pressurized air as combustion air for burning fuel in the combustor together with a main flow of the compressed air, wall cooling in which cooling air is supplied to cooling air passages formed in the wall of the combustor to perform cooling involves a downstream wall region, closer to a turbine, that is cooled using the bled and pressurized air as the cooling air and an upstream wall region, closer to a burner, that is cooled using, as the cooling air, bled compressed air bled from a main flow of the compressed air through a housing inner space.Type: GrantFiled: August 10, 2011Date of Patent: December 6, 2016Assignees: MITSUBISHI HITACHI POWER SYSTEMS, LTD., TOHOKU ELECTRIC POWER CO., INC.Inventors: Satoshi Mizukami, Tatsuo Ishiguro, Junichiro Masada, Kazumasa Takata, Shunsuke Torii, Yuya Fukunaga, Tetsu Konishi, Yoshiaki Nishimura, Yoshiaki Igarashi, Shinya Ishikawa
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Publication number: 20150197833Abstract: Provided is a Ni-based single crystal superalloy containing 6% by mass or more and 12% by mass or less of Cr, 0.4% by mass or more and 3.0% by mass or less of Mo, 6% by mass or more and 10% by mass or less of W, 4.0% by mass or more and 6.5% by mass or less of Al, 0% by mass or more and 1% by mass or less of Nb, 8% by mass or more and 12% by mass or less of Ta, 0% by mass or more and 0.15% by mass or less of Hf, 0.01% by mass or more and 0.2% by mass or less of Si, and 0% by mass or more and 0.04% by mass or less of Zr, and optionally containing at least one element selected from B, C, Y, La, Ce, and V, with a balance being Ni and inevitable impurities.Type: ApplicationFiled: July 30, 2013Publication date: July 16, 2015Inventors: Kyoko Kawagishi, Hiroshi Harada, Tadaharu Yokokawa, Yutaka Koizumi, Toshiharu Kobayashi, Masao Sakamoto, Michinari Yuyama, Masaki Taneike, Ikuo Okada, Sachio Shimohata, Hidetaka Oguma, Ryota Okimoto, Keizo Tsukagoshi, Yoshitaka Uemura, Junichiro Masada, Shunsuke Torii
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Publication number: 20140216055Abstract: In this gas turbine, at a downstream portion of a transition piece of a combustor, inner surfaces of a pair of lateral walls facing each other in a circumferential direction of a turbine rotor form inclination surfaces that incline down to a downstream end of the transition piece in a direction approaching the transition piece of another adjacent combustor that gradually draws closer as it goes to the downstream side of the transition piece in an axis direction.Type: ApplicationFiled: September 12, 2012Publication date: August 7, 2014Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Yasuro Sakamoto, Keisuke Matsuyama, Keizo Tsukagoshi, Masanori Yuri, Hiroaki Kishida, Shunsuke Torii
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Patent number: 8556583Abstract: A blade cooling structure of a gas turbine, which can reduce the pressure loss of a cooling medium without decreasing the heat transfer coefficient, is provided. The blade cooling structure comprises a cooling passage (15) for flowing cooling air (A) from a proximal end portion (12) toward a blade portion (14) of a moving blade (11), a plurality of turbulators (21) arranged, on both wall surfaces of the cooling passage (15) opposing each other, in such a manner as to be inclined with respect to the flowing direction of the cooling air (A), and a plurality of dimples (22) formed in a downstream region (N) downstream of a center position (O) in the flowing direction of the cooling air (A) on the wall surface of the cooling passage (15) between the adjacent turbulators (21).Type: GrantFiled: August 30, 2007Date of Patent: October 15, 2013Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Daigo Fujimura, Hideaki Sugishita, Masaaki Matsuura, Hiroyuki Yamamoto, Shunsuke Torii, Satoshi Hada, Kiyoshi Suenaga, Yuko Suenaga
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Publication number: 20130098063Abstract: In a cooling structure for a recovery-type air-cooled gas turbine combustor having a recovery-type air-cooling structure that bleeds, upstream of the combustor, and pressurizes compressed air supplied from a compressor, that uses the bled and pressurized air to cool a wall, and that recovers and reuses the bled and pressurized air as combustion air for burning fuel in the combustor together with a main flow of the compressed air, wall cooling in which cooling air is supplied to cooling air passages formed in the wall of the combustor to perform cooling involves a downstream wall region, closer to a turbine, that is cooled using the bled and pressurized air as the cooling air and an upstream wall region, closer to a burner, that is cooled using, as the cooling air, bled compressed air bled from a main flow of the compressed air through a housing inner space.Type: ApplicationFiled: August 10, 2011Publication date: April 25, 2013Applicants: TOHOKU ELECTRIC POWER CO., LTD., MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Satoshi Mizukami, Tatsuo Ishiguro, Junichiro Masada, Kazumasa Takata, Shunsuke Torii, Yuya Fukunaga, Tetsu Konishi, Yoshiaki Nishimura, Yoshiaki Igarashi, Shinya Ishikawa
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Patent number: 8231348Abstract: A platform cooling structure for a gas turbine moving blade is provided which is capable of improving cooling performance of a platform and of improving reliability of a moving blade in such a manner that a portion in the vicinity of a side edge of the platform which is away from moving blade cooling passageways and is easily influenced by thermal stress caused by high-temperature combustion gas, that is, an upper surface of the side edge is effectively cooled by guiding high-pressure cooling air, flowing to the moving blade cooling passageways, to a discharge opening formed in a surface of the platform in the vicinity of the side edge of the platform without particularly attaching an additional member such as a cover plate to the platform. A moving blade cooling passageway 17c is formed in the inside of the gas turbine moving blade.Type: GrantFiled: November 27, 2007Date of Patent: July 31, 2012Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Shunsuke Torii, Masamitsu Kuwabara, Eisaku Ito
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Publication number: 20100226791Abstract: A blade cooling structure of a gas turbine, which can reduce the pressure loss of a cooling medium without decreasing the heat transfer coefficient, is provided. The blade cooling structure comprises a cooling passage (15) for flowing cooling air (A) from a proximal end portion (12) toward a blade portion (14) of a moving blade (11), a plurality of turbulators (21) arranged, on both wall surfaces of the cooling passage (15) opposing each other, in such a manner as to be inclined with respect to the flowing direction of the cooling air (A), and a plurality of dimples (22) formed in a downstream region (N) downstream of a center position (O) in the flowing direction of the cooling air (A) on the wall surface of the cooling passage (15) between the adjacent turbulators (21).Type: ApplicationFiled: August 30, 2007Publication date: September 9, 2010Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Daigo Fujimura, Hideaki Sugishita, Masaaki Matsuura, Hiroyuki Yamamoto, Shunsuke Torii, Satoshi Hada, Kiyoshi Suenaga, Yuko Suenaga
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Publication number: 20090202339Abstract: A platform cooling structure for a gas turbine moving blade is provided which is capable of improving cooling performance of a platform and of improving reliability of a moving blade in such a manner that a portion in the vicinity of a side edge of the platform which is away from moving blade cooling passageways and is easily influenced by thermal stress caused by high-temperature combustion gas, that is, an upper surface of the side edge is effectively cooled by guiding high-pressure cooling air, flowing to the moving blade cooling passageways, to a discharge opening formed in a surface of the platform in the vicinity of the side edge of the platform without particularly attaching an additional member such as a cover plate to the platform. A moving blade cooling passageway 17c is formed in the inside of the gas turbine moving blade.Type: ApplicationFiled: November 27, 2007Publication date: August 13, 2009Applicant: Mitsubishi Heavy Industries, Ltd.Inventors: Shunsuke Torii, Masamitsu Kuwabara, Eisaku Ito
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Publication number: 20060269409Abstract: A platform of a gas turbine moving blade suppresses the effects of thermal elongation and thus improves cooling performance. A structure is constituted by a peripheral edge of a platform of a gas turbine moving blade, a bottom of the platform, and a shank of the moving blade. A cavity is blocked by disposing a sealing plate so as to seal the recessed section, while a supply route is formed for supplying air from cooling passages through an interior of the shank to the cavity, each of the passages being for air-cooling the interior of the gas turbine moving blade with air blown out from the cavity to a surface of the platform. A method of appropriately installing the sealing plate is also disclosed.Type: ApplicationFiled: May 27, 2005Publication date: November 30, 2006Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Shunsuke Torii, Friedrich Soechting, Masanori Yuri
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Patent number: 6994514Abstract: Holes 38 and 39 have upstream opening portions 38b and 39b and downstream opening portions 38a and 39a which have a larger cross-sectional area than upstream opening portions 38b and 39b, and are formed at top portion TP of each moving blade. Holes 38 and 39 have tapered shapes T1 and T2 or step portions, and preferably, downstream opening portions 38a and 39a are eccentrically formed toward the moving direction. When tip squealer 37 is formed, hole 38 is formed so that its opening portion is provided at the side surface of tip squealer 37. Without covering the holes for cooling which are formed at the top portion of the turbine blade due to rubbing or the like, the turbine blade is accurately cooled and stably driven.Type: GrantFiled: November 20, 2002Date of Patent: February 7, 2006Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Friedrich Soechting, Yasuoki Tomita, Shunsuke Torii
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Patent number: 6988872Abstract: The object of the present invention is to provide a turbine moving blade that has high heat resistance and can be used for a long period of time by improving the cooling efficiency of the turbine moving blade, and to improve both the thermal efficiency and operating efficiency of a gas turbine through the use of this turbine moving blade. In order to achieve the object, the present invention provide a turbine moving blade arranged in a combustion gas flow path in which a plurality of blow-out openings for blowing out a cooling medium are formed in its outer surface, wherein among a plurality of cooling medium trailing edge blow-out openings arranged from the vicinity of a blade base to the vicinity of a blade tip along a blade trailing edge of turbine moving blade, the opening area of a blade tip trailing edge blow-out opening located in the vicinity of blade tip is set to be larger than the opening area of the other trailing edge blow-out openings.Type: GrantFiled: January 27, 2003Date of Patent: January 24, 2006Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Friedrich Soechting, Charles Ellis, Yasuoki Tomita, Shunsuke Torii
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Patent number: 6893215Abstract: The division wall is made up of a plurality of division wall sections forming a passage wall of high temperature gas which are connected in the direction of arrangement of blades to form a wall surface having a roughly circular cross section as a whole, a gas flow restricting structure for preventing high temperature gas from passing through a gap formed at a connecting portion between the division wall sections in the flow direction of the high temperature gas from the opening on the upstream side of the high temperature gas in the gap, or a gas flow restricting structure for preventing the high temperature gas from being embraced in the gap, for example, a sealing member formed into a prism having a T-shape cross section as a whole composed of a plane portion as a sealing portion and a projected portion for filling the gap is provided.Type: GrantFiled: December 26, 2001Date of Patent: May 17, 2005Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Masamitsu Kuwabara, Yoshiyuki Morii, Yasuoki Tomita, Shunsuke Torii, Shigehiro Shiozaki, Kotaro Ohshima, Tatsuaki Fujikawa, Ryotaro Magoshi, Shinichi Inoue
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Patent number: 6860108Abstract: In order to provide a gas turbine tail tube seal which can prevent an outer shroud and an inner shroud in a first row stationary blade from being damaged by heat and from being worn, and to provide a gas turbine having the above-mentioned gas turbine tail tube seal, in the gas turbine tail tube seal, the width of a combustion gas flow channel in the gas turbine tail tube seal is smaller than the width of a combustion gas flow channel made between an outer surface of the inner shroud and an inner surface of the outer shroud, and the combustion gas flow channel is provided with inclined surfaces having a gradually enlarging cross section toward the first row stationary blade in at least a downstream end section.Type: GrantFiled: January 22, 2003Date of Patent: March 1, 2005Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Friedrich Soechting, Yasuoki Tomita, Shunsuke Torii
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Publication number: 20040146402Abstract: The object of the present invention is to provide a turbine moving blade that has high heat resistance and can be used for a long period of time by improving the cooling efficiency of the turbine moving blade, and to improve both the thermal efficiency and operating efficiency of a gas turbine through the use of this turbine moving blade. In order to achieve the object, the present invention provide a turbine moving blade arranged in a combustion gas flow path in which a plurality of blow-out openings for blowing out a cooling medium are formed in its outer surface, wherein among a plurality of cooling medium trailing edge blow-out openings arranged from the vicinity of a blade base to the vicinity of a blade tip along a blade trailing edge of turbine moving blade, the opening area of a blade tip trailing edge blow-out opening located in the vicinity of blade tip is set to be larger than the opening area of the other trailing edge blow-out openings.Type: ApplicationFiled: January 27, 2003Publication date: July 29, 2004Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Friedrich Soechting, Charles Ellis, Yasuoki Tomita, Shunsuke Torii
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Publication number: 20040139746Abstract: In order to provide a gas turbine tail tube seal which can prevent an outer shroud and an inner shroud in a first row stationary blade from being damaged by heat and from being worn, and to provide a gas turbine having the above-mentioned gas turbine tail tube seal, in the gas turbine tail tube seal, the width of a combustion gas flow channel in the gas turbine tail tube seal is smaller than the width of a combustion gas flow channel made between an outer surface of the inner shroud and an inner surface of the outer shroud, and the combustion gas flow channel is provided with inclined surfaces having a gradually enlarging cross section toward the first row stationary blade in at least a downstream end section.Type: ApplicationFiled: January 22, 2003Publication date: July 22, 2004Applicant: MITSUBISHI HEAVY INDUSTRIES LTD.Inventors: Friedrich Soechting, Yasuoki Tomita, Shunsuke Torii
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Publication number: 20040096328Abstract: Holes 38 and 39 have upstream opening portions 38b and 39b and downstream opening portions 38a and 39a which have a larger cross-sectional area than upstream opening portions 38b and 39b, and are formed at top portion TP of each moving blade. Holes 38 and 39 have tapered shapes T1 and T2 or step portions, and preferably, downstream opening portions 38a and 39a are eccentrically formed toward the moving direction. When tip squealer 37 is formed, hole 38 is formed so that its opening portion is provided at the side surface of tip squealer 37. Without covering the holes for cooling which are formed at the top portion of the turbine blade due to rubbing or the like, the turbine blade is accurately cooled and stably driven.Type: ApplicationFiled: November 20, 2002Publication date: May 20, 2004Applicant: MITSUBISHI HEAVY INDUSTRIES LTD.Inventors: Friedrich Soechting, Yasuoki Tomita, Shunsuke Torii