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公开(公告)号：US11867085B2
公开(公告)日：2024-01-09
申请号：US17778974
申请日：2021-03-23
发明人： Satoshi Mizukami , Masamitsu Kuwabara , Satoshi Hada , Saki Matsuo , Yoshitaka Uemura , Ryozo Tamura , Yasumasa Kunisada
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2220/32
摘要： A turbine blade is provided with an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface which extend between the leading edge and the trailing edge, the airfoil portion internally forming a cooling passage. The cooling passage includes: a first cooling passage located closer to the pressure surface than the suction surface; and a second cooling passage located closer to the suction surface than the pressure surface. The first cooling passage and the second cooling passage are separated by a partition member disposed in the airfoil portion. At least one communication space connecting the first cooling passage and the second cooling passage is formed in the partition member.
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公开(公告)号：US11536149B1
公开(公告)日：2022-12-27
申请号：US17692667
申请日：2022-03-11
摘要： A method of cooling a vane of a turbine is provided. The turbine includes an airfoil, a shroud disposed at an end of the airfoil, the end being a radial end along a radial direction of the turbine, the shroud comprising a shroud main body and a shroud edge disposed on a circumference of the shroud main body to surround the shroud main body, the shroud edge comprising a shroud edge passage therein. A cooling air is caused to flow inside the shroud edge passage to cool the shroud edge, and after cooling the shroud edge, the shroud main body is cooled by using the cooling air which has flowed inside the shroud edge passage.
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公开(公告)号：US10247030B2
公开(公告)日：2019-04-02
申请号：US14843672
申请日：2015-09-02
发明人： Satoshi Mizukami , Tatsuo Ishiguro , Junichiro Masada , Kazumasa Takata , Yuya Fukunaga , Hiroki Takahashi , Masaki Satoh , Yoshiaki Nishimura , Norio Oogai , Souji Hasegawa , Masato Hayashi
摘要： Provided is a gas turbine capable of achieving high-speed startup of the gas turbine through quick operation control of an ACC system during startup of the gas turbine, improving the cooling efficiency of turbine stationary components, and quickly carrying out an operation required for cat back prevention during shutdown of the gas turbine. Included are a pressurizing device (40) connected to a branching channel (42) branching from the discharge side of a compressor (11) and capable of carrying out an operation for introducing and pressurizing air independently from the compressor (11); a temperature-control-medium supply channel (43) that guides compressed air pressurized at the pressuring device (40) to a turbine-cooling-medium channel (50) provided in stationary components of a turbine (13); and a temperature-control-medium return channel (44) that guides the compressed air that has passed through the turbine-cooling-medium channel (50) to the discharge side of the compressor (11) such that the flows are combined, and the pressurizing device (40) is operated at startup of the gas turbine and in preparation immediately before startup to carry out temperature-raising and cooling by letting the compressed air flow in the turbine-cooling-medium channel (50). The pressurizing device (40) is operated during shutdown of the gas turbine to exhaust the high-temperature gas remaining in the turbine (13).
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公开(公告)号：US10352243B2
公开(公告)日：2019-07-16
申请号：US15022966
申请日：2014-09-19
IPC分类号： F02C6/08 , F02C7/08 , F02C7/12 , F02C7/14 , F02C7/18 , F01D25/10 , F02C7/224 , F02C7/141 , F02C9/18 , F02C3/13
摘要： A gas turbine equipped with a compressor, a combustion chamber and a turbine is further equipped with: a pressurizing device for taking a portion of the compressed air compressed by the compressor, and pressurizing the compressed air; a combustion chamber cooling line for cooling the combustion chamber using the pressurized compressed air; a temperature regulating line for regulating the temperature of a stationary member of a blade ring or the like of a turbine by using the pressurized compressed air; a combustion chamber supply line through which the compressed air flows from the pressurizing device to the combustion chamber cooling line; a turbine supply line through which the compressed air flows from the pressurizing device to the temperature regulating line; a heater for heating the compressed air, provided in the turbine supply line; and a control device capable of controlling the heater.
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公开(公告)号：US09249977B2
公开(公告)日：2016-02-02
申请号：US13683754
申请日：2012-11-21
发明人： Yuichiro Kimura , Satoshi Takiguchi , Keisuke Matsuyama , Satoshi Mizukami , Shinji Akamatsu , Kenji Sato , Hikaru Katano , Shigemi Mandai
CPC分类号： F23R3/002 , F01D9/023 , F02C7/12 , F23R3/06 , F23R2900/00014 , F23R2900/03042
摘要： A combustor includes a combustion chamber and an acoustic liner, wherein through-holes through are formed in a wall of the combustion chamber, a plurality of rows of the through-holes is arranged in a lengthwise direction of the combustor, the through-holes of a first through-hole row are shifted with respect to the through-holes of a second through-hole row so that centers of the through-holes of the first and second through-hole rows adjacent each other are staggered in the circumferential direction, cooling grooves are formed so as to avoid the through-holes inside that is sandwiched between the outer peripheral surface and the inner peripheral surface of the combustion chamber, and the cooling grooves include transverse cooling grooves extending in the circumferential direction between rows of the through-holes, and longitudinal cooling grooves extending in the lengthwise direction between the through-holes and connecting the transverse cooling grooves adjacent to each other.
摘要翻译： 燃烧器包括燃烧室和声衬，其中贯通的通孔形成在燃烧室的壁中，沿着燃烧室的长度方向排列有多列通孔，通孔为 第一通孔列相对于第二通孔列的通孔移位，使得相邻的第一和第二通孔列的通孔的中心在圆周方向上交错，冷却 形成槽，以避免其内部的通孔夹在燃烧室的外周表面和内周表面之间，并且冷却槽包括在圆周方向上延伸通过排的通孔之间的横向冷却槽 以及沿着长度方向在通孔之间延伸并且将横向冷却槽相互连接的纵向冷却槽。
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公开(公告)号：US20230287796A1
公开(公告)日：2023-09-14
申请号：US17692572
申请日：2022-03-11
CPC分类号： F02C7/18 , F01D9/041 , F05D2220/32 , F05D2260/232 , F05D2240/12
摘要： A method of cooling a vane of a turbine is provided. The turbine includes an airfoil, an outer shroud disposed at an outer radial end of the airfoil and an inner shroud, the airfoil including a plurality of air channels extending along the radial direction of the turbine, the air channels comprising a first air channel and a second air channel. A cooling air is caused to flow inside the first air channel to cool the first air channel, then cool one of the outer shroud and the inner shroud. A cooling air is caused to flow inside the second air channel to cool the second air channel, then cool the other one of the outer shroud and the inner shroud.
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公开(公告)号：US11713683B2
公开(公告)日：2023-08-01
申请号：US17778228
申请日：2021-03-23
发明人： Satoshi Mizukami , Masamitsu Kuwabara , Satoshi Hada , Saki Matsuo , Yoshitaka Uemura , Ryozo Tamura , Yasumasa Kunisada
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2220/32 , F05D2230/10 , F05D2240/30 , F05D2260/202 , F05D2260/221
摘要： A turbine blade including an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface extending between the leading edge and the trailing edge. The airfoil portion internally forming a cooling passage, which includes first and second cooling passages, and a plurality of outflow passages each having one end which opens to a merging portion formed by connecting an end portion of the first cooling passage on a side of the trailing edge and an end portion of the second cooling passage on the side of the trailing edge, and another end which opens to the trailing edge. The first cooling passage and the second cooling passage are divided by a partition member disposed in the airfoil portion. The cooling passage includes pressure side pin fins in the first cooling passage, and suction side pin fins in the second cooling passage.
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公开(公告)号：US20180038388A1
公开(公告)日：2018-02-08
申请号：US15555022
申请日：2015-11-18
发明人： Satoshi Mizukami
CPC分类号： F04D29/5806 , F04D25/0686 , F04D25/082 , F04D29/642 , H02K5/12 , H02K5/128 , H02K7/14 , H02K9/06 , H02K9/19 , H02K9/197 , H02K2005/1287
摘要： A compressor system including a motor including: a rotor that rotates around an axis and a stator disposed on an outer circumferential side of the rotor with a gap from the rotor; a compressor that rotates together with the rotor to generate a compressed fluid; and a partitioning member that is disposed in the gap formed between the rotor and the stator to partition the gap in the radial direction, and forms a rotor-side flow passage through which a cooling fluid can flow along the axis with the rotor, and a stator-side flow passage through which the cooling fluid can flow along the axis with the stator. The partitioning member has a cylindrical shape with the axis as a center and has a shape in which a thickness dimension in a radial direction of the rotor increases from one side to the other side of the axis.
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公开(公告)号：US20150377054A1
公开(公告)日：2015-12-31
申请号：US14843585
申请日：2015-09-02
发明人： Satoshi Mizukami , Tatsuo Ishiguro , Junichiro Masada , Kazumasa Takata , Yuya Fukunaga , Hiroki Takahashi , Masaki Satoh , Yoshiaki Nishimura , Norio Oogai , Souji Hasegawa , Masato Hayashi
CPC分类号： F01D11/24 , F01D21/00 , F01D21/12 , F02C7/08 , F02C7/12 , F02C7/18 , F05D2260/205 , F05D2260/608
摘要： Provided is a gas turbine capable of achieving high-speed startup of the gas turbine through quick operation control of an ACC system during startup of the gas turbine, improving the cooling efficiency of turbine stationary components, and quickly carrying out an operation required for cat back prevention during shutdown of the gas turbine. Included are a pressurizing device (40) connected to a branching channel (42) branching from the discharge side of a compressor (11) and capable of carrying out an operation for introducing and pressurizing air independently from the compressor (11); a temperature-control-medium supply channel (43) that guides compressed air pressurized at the pressuring device (40) to a turbine-cooling-medium channel (50) provided in stationary components of a turbine (13); and a temperature-control-medium return channel (44) that guides the compressed air that has passed through the turbine-cooling-medium channel (50) to the discharge side of the compressor (11) such that the flows are combined, and the pressurizing device (40) is operated at startup of the gas turbine and in preparation immediately before startup to carry out temperature-raising and cooling by letting the compressed air flow in the turbine-cooling-medium channel (50). The pressurizing device (40) is operated during shutdown of the gas turbine to exhaust the high-temperature gas remaining in the turbine (13).
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公开(公告)号：US20240159158A1
公开(公告)日：2024-05-16
申请号：US17988518
申请日：2022-11-16
发明人： Satoshi Mizukami , David Allen Flodman , Satoshi Hada , Yasumasa Kunisada , Saki Matsuo , Ryo Tanaka , Takuro Kameda , Yusuke Akada
IPC分类号： F01D9/06
CPC分类号： F01D9/065 , F05D2240/11 , F05D2260/201
摘要： A shroud of a vane of a turbine is provided. The shroud includes a shroud main body comprising a first wall having a gas-passage face facing a hot gas passage of the turbine and a cooling face facing opposite to the hot gas passage, a shroud edge disposed on a circumference of the shroud main body to surround the shroud main body, the shroud edge comprising a shroud edge passage therein, and an impingement box disposed to face the cooling face of the first wall so as to be spaced apart from the cooling face of the first wall. The impingement box comprises a cooling air inlet to introduce a cooling air from the shroud edge passage into an inside of the impingement box, and an impingement air hole configured to jet the introduced cooling air to the cooling face of the first wall to cool the cooling face of the first wall.
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