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公开(公告)号：US20190032499A1
公开(公告)日：2019-01-31
申请号：US16074943
申请日：2017-03-03
发明人： Saki MATSUO , Satoshi HADA , Tomoko MORIKAWA , Kunihiko WAKI , Kenichi ARASE
摘要： Provided is a flow path forming plate having a gas path surface that comes in contact with combustion gas, end surfaces formed at peripheral edges of the gas path surface, a first side passage, and a plurality of end surface blow-out passages. The first side passage extends in a direction along a first end surface that is one of the end surfaces, and cooling air flows through the first side passage. A plurality of passage forming surfaces forming the first side passage includes a first forming surface that faces an opposite-flow-path side and extends gradually farther away from the gas path surface while extending toward the first end surface. The end surface blow-out passages open in the first forming surface of the first side passage and in the first end surface.
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2.发明申请公开(公告)号：US20180306037A1
公开(公告)日：2018-10-25
申请号：US15771257
申请日：2016-11-04
发明人： Yoshimasa TAKAOKA , Shunsuke TORII , Hidemichi KOYABU , Saki MATSUO , Yasuoki TOMITA , Satoshi HADA , Yoshifumi OKAJIMA
CPC分类号： F01D5/187 , F01D5/18 , F01D5/181 , F01D9/02 , F02C7/00 , F02C7/18 , F05D2230/21 , F05D2240/12 , F05D2240/122 , F05D2240/301 , F05D2240/304 , F05D2260/201
摘要： 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.
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公开(公告)号：US20210062678A1
公开(公告)日：2021-03-04
申请号：US16644629
申请日：2018-09-12
发明人： Takaharu HIROE , Satoshi HADA , Kazunari IDE , Koki TATEISHI , Ryuji TAKENAKA , Koshiro FUKUMOTO , Shinichi YOSHIOKA
摘要： A control device controls a temperature of a shaft seal portion provided around a rotating shaft of a rotating machine to an appropriate temperature by adjusting an amount of the cooling air to be supplied to the shaft seal portion. The control device calculates a sensitivity indicated using the temperature of the shaft seal portion with respect to a flow rate of the cooling air supplied to the shaft seal portion and controls the flow rate of the cooling air so that the sensitivity has a predetermined target value on the basis of the calculated sensitivity. When the sensitivity is calculated, the flow rate is varied in a predetermined range having a certain flow rate as a center. The sensitivity of the temperature at the flow rate as a center is calculated from the variation in the temperature of the shaft seal portion with respect to the variation in the flow rate.
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公开(公告)号：US20170138211A1
公开(公告)日：2017-05-18
申请号：US15127446
申请日：2015-03-20
发明人： Yoshio FUKUI , Masamitsu KUWABARA , Satoshi HADA
摘要： A ring segment cooling structure including: a cavity surrounded by main bodies of segment bodies; and cooling passages arranged inside the main body of the segment body in a circumferential direction, and having one ends communicating with the cavity and the other ends open at lateral ends of the segment body on the front side and the rear side in a rotation direction, wherein the cooling passages include first cooling passages formed in a first region of the segment body located on the front side in the rotation direction and through which cooling air is discharged from the rear side toward the front side in the rotation direction, and second cooling passages formed in a second region of the segment body located on the rear side in the rotation direction and through which the cooling air is discharged from the front side toward the rear side in the rotation direction.
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公开(公告)号：US20210123349A1
公开(公告)日：2021-04-29
申请号：US16617266
申请日：2018-07-04
发明人： Yoshifumi TSUJI , Ryuta ITO , Hiroyuki OTOMO , Satoshi HADA , Susumu WAKAZONO
IPC分类号： F01D5/18
摘要： A turbine blade includes an airfoil portion, a cooling passage inside the airfoil portion, and a plurality of cooling holes formed in a trailing edge part of the airfoil portion. The cooling holes communicating with the cooling passage and opening in a surface of the trailing edge part. A relation of d_up
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公开(公告)号：US20190040747A1
公开(公告)日：2019-02-07
申请号：US15759687
申请日：2016-09-14
发明人： Yusuke IZUMI , Kazuki MORIMOTO , Satoshi HADA
IPC分类号： F01D5/18
摘要： A blade includes a blade body in which a cooling flow passage through which a cooling medium flows is formed. The blade body includes a top plate, and a thinning which is formed on a top surface of the top plate, closer to a suction side than a camber line, and which protrudes and extends along the camber line. A top plate flow passage is formed inside the top plate. The top plate flow passage includes an inlet flow passage which is formed closer to the suction side than the camber line and into which the cooling medium flows, a main flow passage which extends in a direction intersecting the camber line along the top surface, and an outlet flow passage through which the cooling medium is discharged to an outside of the blade body from a position closer to a pressure side than the camber line.
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公开(公告)号：US20190010809A1
公开(公告)日：2019-01-10
申请号：US16069260
申请日：2017-01-25
摘要： An insert assembly (79) includes an insert (80), a reinforcing member (85), and a retaining member (90). The insert (80) is fixed to an end of an airfoil body (51) on one side in a radial direction. The reinforcing member (85) is disposed adjacent to an end of the insert (80) on the other side in the radial direction and enhances the rigidity of the insert (80). The retaining member (90) is fixed to an end of the airfoil body (51) on the other side in the radial direction, and allows the insert (80) to be positioned relative to the airfoil body (51) in a direction orthogonal to the radial direction.
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公开(公告)号：US20180200783A1
公开(公告)日：2018-07-19
申请号：US15743909
申请日：2016-09-08
CPC分类号： B22C9/043 , B22C9/04 , B22C9/10 , B22D25/02 , B22D29/00 , B22D29/04 , B23H9/10 , B23H9/14 , F01D5/18 , F01D5/187 , F02C7/00 , F02C7/18 , F05D2230/21 , F05D2240/81
摘要： A blade (50) has a blade, passage (71) extending in a blade height direction (Dwh), a platform passage (81) formed inside a platform (60), and a communication passage (75) leading from an outer surface (93) of a shaft-mounted part (90) through the platform passage (81) to the blade passage (71). An inner surface defining an inflow passage portion (82) of the platform passage (81) includes a shaft-side inner surface (88) that faces a gas path side. The shaft-side inner surface (88) spreads in a direction having more of a component of a blade thickness direction (Dwt) than a component of the blade height direction (Dwh). An inner surface defining the communication passage (75) joins to the shaft-side inner surface (88).
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公开(公告)号：US20180149024A1
公开(公告)日：2018-05-31
申请号：US15576090
申请日：2016-08-23
发明人： Keita TAKAMURA , Satoshi HADA , Hidekatsu ATSUMI
CPC分类号： F01D5/187 , F01D5/186 , F01D5/225 , F02C7/18 , F05D2220/32 , F05D2240/81 , F05D2260/2212
摘要： A turbine blade (43a) is provided with a blade main body (51) and a tip shroud (52). The blade main body (51) is provided with a leading edge-side cooling passage (64), a trailing edge-side cooling passage (67), and a middle cooling passage (65). The tip shroud (52) is provided with a first discharge passage (72), a second discharge passage (73), and a third discharge passage (74). The first discharge passage (72) discharges a cooling medium flowing through the leading edge-side cooling passage (64). The second discharge passage (73) discharges a cooling medium flowing through the trailing edge-side cooling passage (67). The third discharge passage (74) discharges a cooling medium flowing through the middle cooling passage (65).
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公开(公告)号：US20180045060A1
公开(公告)日：2018-02-15
申请号：US15557670
申请日：2016-03-11
发明人： Saki MATSUO , Tomoko MORIKAWA , Satoshi HADA , Hiroyuki OTOMO
CPC分类号： F01D5/187 , F01D9/02 , F01D25/12 , F01D25/24 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/35 , F05D2240/60 , F05D2240/81 , F05D2260/201
摘要： A blade has a flow passage forming plate that defines a part of a combustion gas flow passage. The flow passage forming plate has a plurality of back channels that open in a back end surface. A density of openings of the plurality of back channels in a middle region of the back end surface is higher than the density of openings of the plurality of back channels in at least one side region of a suction-side region and a pressure-side region of the back end surface. The density of openings is a ratio of a length of wetted perimeter of the plurality of back channels to an interval of openings of the plurality of back channels.
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