公开(公告)号：US20210123349A1

公开(公告)日：2021-04-29

申请号：US16617266

申请日：2018-07-04

申请人： Mitsubishi Hitachi Power Systems, Ltd.

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

公开(公告)号：US20170241289A1

公开(公告)日：2017-08-24

申请号：US15519363

申请日：2014-11-19

申请人： MITSUBISHI HITACHI POWER SYSTEMS, LTD.

发明人： Kohei HIDAKA ,  Susumu WAKAZONO ,  Toshihiro TAKEDA ,  Scott CLOYD ,  Santo SCIMECA

IPC分类号： F01D25/16 ,  F16J15/3268 ,  F16C17/03 ,  F16J15/3288 ,  F01D11/00 ,  F01D21/00

CPC分类号： F01D25/162 ,  F01D11/003 ,  F01D21/003 ,  F01D25/16 ,  F05D2220/32 ,  F05D2230/72 ,  F05D2240/20 ,  F05D2240/50 ,  F05D2240/55 ,  F16C17/03 ,  F16C2237/00 ,  F16C2360/23 ,  F16J15/3268 ,  F16J15/3288 ,  Y10T29/49318 ,  Y10T29/49718 ,  Y10T29/49719 ,  Y10T29/49721 ,  Y10T29/49723 ,  Y10T29/49725

摘要： An exhaust-side journal bearing for supporting a gas turbine rotor is disposed inside a bearing box. The bearing box is supported by a strut which extends inward from an exhaust casing, and a seal ring having an annular inner peripheral end is disposed on the bearing box. Executed during a maintenance work are: a bearing adjustment step of displacing a bearing surface of the journal bearing relative to the bearing box in a perpendicular direction perpendicular to the axial direction; and a seal ring adjustment step of displacing the inner peripheral end of the seal ring relative to the bearing box in accordance with the direction of displacement and the amount of displacement of the bearing surface.

公开(公告)号：US20200263554A1

公开(公告)日：2020-08-20

申请号：US16651559

申请日：2018-10-15

申请人： Mitsubishi Hitachi Power Systems, Ltd.

发明人： Yasuo MIYAHISA ,  Susumu WAKAZONO ,  Satoshi HADA

IPC分类号： F01D5/18 ,  F01D9/06

摘要： A turbine blade includes an airfoil body, and a plurality of cooling passages extending along a blade height direction inside the airfoil body and communicating with each other to form a serpentine flow passage. The cooling passages include first turbulators disposed on an inner wall surface of an upstream side passage of the plurality of cooling passages, and second turbulators disposed on an inner wall surface of a downstream side passage of the plurality of cooling passages, the second turbulators being arranged on a downstream side of the upstream side passage. A second angle formed by the second turbulators with respect to a flow direction of a cooling fluid in the most downstream passage is smaller than a first angle formed by the first turbulators with respect to the flow direction of the cooling fluid in the upstream side passage.

公开(公告)号：US20200056540A1

公开(公告)日：2020-02-20

申请号：US16486603

申请日：2018-02-23

申请人： Mitsubishi Hitachi Power Systems, Ltd.

发明人： Takashi HIYAMA ,  Kazuya NISHIMURA ,  Keita TAKAMURA ,  Susumu WAKAZONO ,  Daigo FUJIMURA

IPC分类号： F02C3/04 ,  F01D5/14 ,  F23R3/26

摘要： A turbine blade includes a blade body in which a suction side (51) facing one side in a circumferential direction and a pressure side (52) facing the other side in the circumferential direction are connected at a leading edge and a trailing edge; and a shroud provided at a tip which is a radially outer end portion of the blade body. The shroud includes a shroud body having an outer circumferential surface facing radially outward, a front end surface extending to both sides in the circumferential direction with a leading edge side of the blade body as a reference point (P1), a rear end surface extending to both sides in the circumferential direction with a trailing edge side of the blade body as a reference point (P2), and a contact surface provided on both sides in the circumferential direction, and a reinforcing portion which protrudes from the outer circumferential surface.