Patents by Inventor Yoshitaka Kojima
Yoshitaka Kojima 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: 20240046694Abstract: According to an aspect, a detection device includes: a plurality of optical sensors that are arranged in a detection area and each of which is configured to output a signal corresponding to light irradiating the optical sensor; a detection circuit configured to be supplied with the signals from the optical sensors; and a control circuit configured to output first data and second data for which detection conditions for acquiring the signals differ from each other. The control circuit is configured to output detection information data in which the detection conditions for the first data and the detection conditions for the second data are added as attribute information to a head of a data string in which the first data and the second data are sequentially arranged.Type: ApplicationFiled: October 10, 2023Publication date: February 8, 2024Inventors: Hirofumi KATO, Yoshitaka KOJIMA
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Publication number: 20230301125Abstract: According to an aspect, a detection device includes: a light source configured to emit light to an object to be detected; a plurality of photodiodes arranged in a detection area; one or more detection circuits; and a coupling switching circuit configured to switch coupling of one or more of the photodiodes to one or more of the detection circuits. The coupling switching circuit is configured to change the number of the detection circuits coupled to one or more of the photodiodes based on an output value from one or more of the photodiodes.Type: ApplicationFiled: March 14, 2023Publication date: September 21, 2023Inventors: Makoto HAYASHI, Hirofumi KATO, Yoshitaka KOJIMA, Yuta HAGA, Ayato KITAMURA, Yoshiyuki TERADA
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Publication number: 20220338352Abstract: A detection device includes a sensor substrate provided with a plurality of photosensors, a control board provided with a control circuit configured to control the photosensors, and a flexible printed circuit board provided with wiring configured to electrically couple the sensor substrate to the control board. The flexible printed circuit board is provided with a plurality of cutting indication lines for changing a length between the sensor substrate and the flexible printed circuit board.Type: ApplicationFiled: April 12, 2022Publication date: October 20, 2022Inventors: Hirofumi KATO, Yoshitaka KOJIMA
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Patent number: 9822659Abstract: A gas turbine includes a compressor, a combustor, and a turbine. The turbine includes a honeycomb seal disposed so as to be secured to a casing side in a clearance between the casing and turbine blades rotating around a rotating shaft and a seal fin that is provided on an end face of each of the turbine blades facing the honeycomb seal. The seal fin extends in a direction perpendicular to the rotating shaft. The honeycomb seal is formed by a plurality of corrugated sheet metals overlapped with each other at walls of nodes thereof and the walls of the nodes are blazed with each other. Each of the corrugated sheet metals has trapezoids formed in alternating fashion. A longer direction of each wall of the nodes of the honeycomb seal is angled with respect to the rotational direction of the turbine blades.Type: GrantFiled: May 28, 2014Date of Patent: November 21, 2017Assignee: Mitsubishi Hitachi Power Systems, Ltd.Inventors: Hideyuki Arikawa, Tadashi Kasuya, Yoshitaka Kojima, Yasuyuki Watanabe, Tadashi Murakata, Kunihiro Ichikawa, Takumi Konrai
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Patent number: 9732411Abstract: This method is a method for manufacturing a gas turbine blade, including: producing a gas turbine blade having a cooling pass inside thereof; and partially coating an inner surface of the cooling pass with Al. The step of partially coating an inner surface of the cooling pass with Al further including: a first step of specifying a temperature range which satisfies both of oxidation resistance and fatigue strength and the temperature distribution of the inner surface of the cooling pass based on an examination result or result of a numerical analysis; a second step of setting an Al-coating-applying portion of the inner surface of the cooling pass as the temperature range specified at the first step; and a third step of applying Al coating only into the set Al-coating-applying portion.Type: GrantFiled: May 28, 2014Date of Patent: August 15, 2017Assignee: Mitsubishi Hitachi Power Systems, Ltd.Inventors: Takeshi Izumi, Hideyuki Arikawa, Yoshitaka Kojima, Akira Mebata, Tadashi Kasuya, Shinya Imano, Koji Miyamoto
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Publication number: 20160024637Abstract: There is provided a method for forming an aluminide coating on a surface of a heat resistant superalloy substrate, comprising the steps of: exposing a base metal of the substrate in a selective area; forming a aluminum or an aluminum alloy film on the exposed base metal, by a non-aqueous electroplating; and conducting a heat treatment to the substrate on which the film is formed, in order to make a diffusion reaction between an aluminum component in the film and the base metal, and form the aluminide coating, wherein: there is used, as a plating liquid, a non-aqueous plating liquid containing a halide of the metal to be plated and an organic compound which forms an ion pair with the metal halide; and the electroplating is conducted by immersing the selective area into the plating liquid through the use of predetermined means for shielding the plating liquid from the atmosphere.Type: ApplicationFiled: March 7, 2013Publication date: January 28, 2016Inventors: Hiroshi NAKANO, Yoshinori NEGISHI, Haruo AKAHOSHI, Takeshi IZUMI, Yoshitaka KOJIMA, Hideyuki ARIKAWA
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Publication number: 20140356186Abstract: This method is a method for manufacturing a gas turbine blade, including: producing a gas turbine blade having a cooling pass inside thereof; and partially coating an inner surface of the cooling pass with Al. The step of partially coating an inner surface of the cooling pass with Al further including: a first step of specifying a temperature range which satisfies both of oxidation resistance and fatigue strength and the temperature distribution of the inner surface of the cooling pass based on an examination result or result of a numerical analysis; a second step of setting an Al-coating-applying portion of the inner surface of the cooling pass as the temperature range specified at the first step; and a third step of applying Al coating only into the set Al-coating-applying portion.Type: ApplicationFiled: May 28, 2014Publication date: December 4, 2014Applicant: Mitsubishi Hitachi Power Systems, Ltd.Inventors: Takeshi IZUMI, Hideyuki ARIKAWA, Yoshitaka KOJIMA, Akira MEBATA, Tadashi KASUYA, Shinya IMANO, Koji MIYAMOTO
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Publication number: 20140356142Abstract: Provided is a gas turbine that can solve a problem in which a seal fin of a turbine blade is abraded by a brazed place of a honeycomb seal. A gas turbine 100 includes a compressor 10, a combustor 20, and a turbine 30. The turbine 30 includes: a honeycomb seal 7 disposed so as to be secured to a casing side in a clearance between the casing 1 and turbine blades 5A-5C rotating around a rotating shaft 4 extending in a longitudinal direction of the casing 1 and a seal fin 6 provided on an end face of each of the turbine blades 5A-5C facing the honeycomb seal 7, the seal fin 6 extending in a direction perpendicular to the rotating shaft 4. The honeycomb seal 7 is formed by a plurality of corrugated thin sheet metals 71 overlapped with each other at walls of node 71a thereof and the walls of node 71 blazed with each other, each of the corrugated thin sheet metals 71 having trapezoids alternately continued.Type: ApplicationFiled: May 28, 2014Publication date: December 4, 2014Applicant: Mitsubishi Hitachi Power Systems, Ltd.Inventors: Hideyuki ARIKAWA, Tadashi KASUYA, Yoshitaka KOJIMA, Yasuyuki WATANABE, Tadashi MURAKATA, Kunihiro ICHIKAWA, Takumi KONRAI
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Patent number: 8801373Abstract: A metal sealing material used in a sealing device which can reduce a gap between a stator and a rotor of a turbine. The metal sealing material used in a sealing device for a stator and a rotor of a turbine includes a surface layer and a lower layer composed of a porous metal layer, wherein the porosity of the surface layer is smaller than the porosity of the lower layer; the porosity of the surface layer is 60 to 65% and the porosity of the lower layer is 67 to 75% or less; and the porous metal layer has a thickness of 0.3 to 3.0 mm and may include, as a main component, an MCrAlY alloy where M is either one of Ni and Co or both thereof, and h-BN as a solid lubricant.Type: GrantFiled: June 29, 2010Date of Patent: August 12, 2014Assignee: Hitachi Ltd.Inventors: Yoshitaka Kojima, Hideyuki Arikawa, Akira Mebata, Hiroyuki Doi, Hajime Toriya, Kenjiro Narita
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Publication number: 20140112758Abstract: The most principal feature of the present invention is as follows: Namely, in the gas-turbine-use high-temperature component including the thermal barrier coating and a cooling structure, micro passages are provided inside an alloy bond-coat layer and a thermal-barrier ceramic top-coat layer of the thermal barrier coating, the micro passages being in communication from the substrate side to the surface side. Moreover, a partial amount of coolant of a coolant for cooling the high-temperature component is caused to flow out to the outside of the high-temperature component via these micro passages. The employment of the structure like this makes it possible to expect the implementation of a high-temperature component's heat-resistant-temperature enhancement effect based on the transpiration cooling effect.Type: ApplicationFiled: October 23, 2013Publication date: April 24, 2014Applicant: Hitachi, Ltd.Inventors: Hideyuki ARIKAWA, Yoshitaka KOJIMA, Tadashi KASUYA, Akira MEBATA, Kunihiro ICHIKAWA, Hiroyuki ENDO, Takao ENDO
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Publication number: 20140064939Abstract: A metal sealing material used in a sealing device which can reduce a gap between a stator and a rotor of a turbine. The metal sealing material used in a sealing device for a stator and a rotor of a turbine includes a surface layer and a lower layer composed of a porous metal layer, wherein the porosity of the surface layer is smaller than the porosity of the lower layer; the porosity of the surface layer is 60 to 65% and the porosity of the lower layer is 67 to 75% or less; and the porous metal layer has a thickness of 0.3 to 3.0 mm and may include, as a main component, an MCrAlY alloy where M is either one of Ni and Co or both thereof, and h-BN as a solid lubricant.Type: ApplicationFiled: August 28, 2013Publication date: March 6, 2014Applicant: HITACHI, LTD.Inventors: Yoshitaka KOJIMA, Hideyuki ARIKAWA, Akira MEBATA, Hiroyuki DOI, Hajime TORIYA, Kenjiro NARITA
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Patent number: 8656723Abstract: An operation control method for a gas turbine includes making a molten salt map of molten salt for causing high-temperature corrosion on high-temperature components of the turbine due to impurities using a thermodynamic equilibrium calculation on the basis of the impurities contained in low-quality fuel and operation data of the gas turbine, indicating a surface temperature and a pressure of the high-temperature components of the turbine on the molten salt map , predicting a lifetime of the high-temperature components of the gas turbine by estimating a corrosion rate thereof, and controlling the flow rate of the low-quality fuel supplied to a combustor so that an area of surface temperature and pressure regions of the high-temperature components superposing on the region of molten salt in the liquid phase on the molten salt map is reduced.Type: GrantFiled: July 7, 2009Date of Patent: February 25, 2014Assignee: Hitachi, Ltd.Inventors: Hiroshi Haruyama, Hideki Tamaki, Yoshitaka Kojima, Hironori Kamoshida
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Publication number: 20140017511Abstract: Disclosed is a turbine blade for an industrial gas turbine including a blade substrate; a multilayer alloy coating containing a diffusion barrier layer; a bond coat; and a top coat. The blade substrate being formed of a single crystal alloy which consists essentially of 0.06 to 0.08% of C, 0.016 to 0.035% of B, 0.2 to 0.3% of Hf, 6.9 to 7.3% of Cr, 0.7 to 1.0% of Mo, 7.0 to 9.0% of W, 1.2 to 1.6% of Re, 8.5 to 9.5% of Ta, 0.6 to 1.0% of Nb, 4.9 to 5.2% of Al, 0.8 to 1.2% of Co, and the balance being Ni and incidental impurities by weight. The multilayer alloy coating, the bond coat and the top coat being directly and sequentially laminated on a surface of the blade substrate, in which the diffusion barrier layer is a multilayer and a discontinuous layer.Type: ApplicationFiled: July 9, 2013Publication date: January 16, 2014Inventors: Takeshi IZUMI, Hideyuki ARIKAWA, Yoshitaka KOJIMA, Akira MEBATA, Tadashi KASUYA, Toshio NARITA
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Publication number: 20130323069Abstract: A turbine blade for industrial gas turbine is used which includes a blade substrate formed of a single-crystal heat-resistant alloy containing C: 0.06 to 0.08%, B: 0.016 to 0.035%, Hf: 0.2 to 0.3%, Cr: 6.9 to 7.3%, Mo: 0.7 to 1.0%, W: 7.0 to 9.0%, Re: 1.2 to 1.6%, Ta: 8.5 to 9.5%, Nb: 0.6 to 1.0%, Al: 4.9 to 5.2%, Co: 0.8 to 1.2%, and the remainder substantially consisting of Ni with reference to mass, and includes a diffusion barrier layer, a metal layer, a bond coat, and a top coat, these layers and coats being stacked in this order on a surface of the blade substrate, the metal layer having a thickness of 5 to 30 ?m. Thus, the turbine blade can be provided which has a thermal barrier coating formed without loss of a function of the diffusion barrier layer.Type: ApplicationFiled: May 29, 2013Publication date: December 5, 2013Applicants: National University Corporation Hokkaido University, Hitachi, Ltd.Inventors: Takeshi IZUMI, Hideyuki ARIKAWA, Yoshitaka KOJIMA, Akira MEBATA, Tadashi KASUYA, Toshio NARITA
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Patent number: 8485788Abstract: A steam turbine rotor shaft and method of manufacturing the same are provided wherein the sliding characteristics of a journal are improved, and the journal is free from welding cracks and does not need a post heat treatment. The low alloy steel coating layer having better sliding characteristics than 9 to 13% Cr heat resisting steel and an area rate of defects including pores and oxides in a range of 3 to 15% is formed by a high velocity flame spray coating method on a sliding surface of the journal.Type: GrantFiled: June 9, 2006Date of Patent: July 16, 2013Assignee: Hitachi, Ltd.Inventors: Hideyuki Arikawa, Akira Mebata, Masahiko Arai, Yoshitaka Kojima, Haijime Toriya
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Patent number: 8460799Abstract: A high-temperature resistant component for, e.g., a gas turbine hot part, includes an alloy substrate containing Ni, Co, or Fe as the principal component, and a thermal barrier coating formed over the surface of the substrate via a bond coat. The thermal barrier coating includes a porous thermal-barrier layer made of ceramic and an environmental barrier layer with corrosion resistance. An impregnated layer is provided between the environmental barrier layer and the thermal barrier layer. In the impregnated layer, the thermal barrier layer is impregnated with a part of the environmental barrier layer. The thermal barrier layer is made of a porous zirconia layer, and the environmental barrier layer includes silica as the principal component. The porous zirconia layer has pores impregnated with the part of the environmental barrier layer. As a result, the high-temperature resistant component has excellent corrosion resistance and excellent heat resistance.Type: GrantFiled: June 24, 2010Date of Patent: June 11, 2013Assignee: Hitachi, Ltd.Inventors: Hideyuki Arikawa, Akira Mebata, Yoshitaka Kojima, Kunihiro Ichikawa, Hiroshi Haruyama
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Publication number: 20120159952Abstract: The present invention provides gas turbine components having durability and reliability for use in a corrosive environment such as a turbine employing a low grade fuel, and also provides a gas turbine equipped with the components. One of the components is a gas turbine bucket/nozzle comprising a substrate made from an alloy containing Ni, Co, or Fe, a bonding layer made from an alloy and disposed over the substrate, and a thermal barrier coating disposed over the bonding layer. The thermal barrier coating includes a thermal barrier layer of porous ceramics, an environmental barrier layer containing silica, and an impregnation layer having a silica-containing material in the pores of the porous ceramics.Type: ApplicationFiled: December 21, 2011Publication date: June 28, 2012Inventors: Hideyuki ARIKAWA, Akira Mebata, Yoshitaka Kojima, Kunihiro Ichikawa, Hiroshi Haruyama
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Publication number: 20120102966Abstract: An operation control method for a gas turbine comprising the steps of: making a molten salt map in a liquid phase state by calculating a dew point and a solidus temperature of molten salt for causing high-temperature corrosion on high-temperature components of the turbine due to impurities using a thermodynamic equilibrium calculation on the basis of the impurities contained in low-quality fuel and operation data of the gas turbine, indicating a surface temperature and a pressure of the high-temperature components of the turbine on the molten salt map to determine a superposition state thereof on a region of molten salt in a liquid phase, predicting a lifetime of the high-temperature components of the gas turbine by estimating a corrosion rate thereof, and controlling the flow rate of the low-quality fuel supplied to a combustor on the basis of the prediction of the lifetime of the high-temperature components so that an area of surface temperature and pressure regions of the high-temperature components superpType: ApplicationFiled: July 7, 2009Publication date: May 3, 2012Inventors: Hiroshi Haruyama, Hideki Tamaki, Yoshitaka Kojima, Hironori Kamoshida
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Publication number: 20120107103Abstract: A gas turbine shroud includes a ceramic abradable coating superior in abradable property and durability. The gas turbine ceramic abradable coating of the present invention is configured by an abradable metal layer and a porous ceramic abradable layer (hardness RC15Y: 80±3), the porous ceramic abradable layer is provided with slit grooves by machining work, and a slit groove width is 0.5 to 5 mm. Thereby, the abradable property, and durability against a thermal cycle and high-temperature oxidation are improved.Type: ApplicationFiled: September 23, 2011Publication date: May 3, 2012Inventors: Yoshitaka Kojima, Hideyuki Arikawa, Akira Mebata, Tadashi Kasuya, Hiroyuki Doi, Kunihiro Ichikawa, Takao Endo, Kazuto Mikazuki, Hidetoshi Kuroki
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Publication number: 20120084981Abstract: In a method of working a film cooling hole which communicates with an internal cooling passage of a turbine blade from an outer surface, in the turbine blade which has a heat shield coating and the internal cooling passage, there is employed a method of working a cooling hole of a turbine including a step of executing a bond coat on a blade base material a step of piercing a cooling hole in accordance with an electric discharge machining, a step of executing a top coat, and a step of removing the top coat in accordance with a mechanical method with respect to a band-like region including a row of cooling holes, by using an abrasive blasting, a water jet method or the like. Accordingly, an occlusion of the cooling hole, and a damage of the TBC due to the piercing are hardly generated.Type: ApplicationFiled: October 5, 2011Publication date: April 12, 2012Inventors: Hideyuki Arikawa, Akira Mebata, Yoshitaka Kojima, Kunihiro Ichikawa, Takeshi Izumi