公开(公告)号：US20180058234A1

公开(公告)日：2018-03-01

申请号：US15678805

申请日：2017-08-16

申请人： Mitsubishi Hitachi Power Systems, Ltd.

发明人： Yasuhiro HORIUCHI ,  Shinichi HIGUCHI ,  Hisato TAGAWA ,  Kenji SHINGAI ,  Takemitsu MIURA

IPC分类号： F01D11/00 ,  F01D9/02 ,  F02C7/28

CPC分类号： F01D11/005 ,  F01D9/023 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/55 ,  F16J15/02

摘要： In a gas turbine in which a seal member seals a gap between a transition piece and a nozzle end wall in a turbine first stage, the transition piece and the nozzle end wall has a seal groove. The seal member includes a hook portion that slides in the turbine radial direction with respect to the flange and a seal plate portion inserted in the groove. The groove and the portion are configured to include a surface contact region in which a surface of the groove and the portion are in surface contact with each other, a non-contact region disposed on a side closer to the transition piece than the region, and a hole provided at the portion so as to face the surface in the groove across a gap in the region.

公开(公告)号：US20170248020A1

公开(公告)日：2017-08-31

申请号：US15417277

申请日：2017-01-27

申请人： Mitsubishi Hitachi Power Systems, Ltd.

发明人： Yasunori KIMURA ,  Shinichi HIGUCHI ,  Ichiro MIYOSHI ,  Takuya TAKEDA

IPC分类号： F01D5/18 ,  F01D5/28

摘要： A turbine blade includes cooling passages formed inside the blade and extending in a blade height direction, blade surfaces on a suction side and a pressure side being covered with thermal barrier coating, a design point on a suction side being set on the blade surface on the suction side of each blade section perpendicular to the blade height direction within a range from a position on a back side of and including a throat position, and to a position in front of and not including a tailing end of a final cooling passage. Thickness distribution of the thermal barrier coating on the suction side of each blade section is configured such that a thickness of the thermal barrier coating is uniform from a blade leading edge to the design point and gradually reduces from the design point toward the back side up to the blade trailing edge.

公开(公告)号：US20170159562A1

公开(公告)日：2017-06-08

申请号：US15366104

申请日：2016-12-01

申请人： Mitsubishi Hitachi Power Systems, Ltd.

发明人： Kazuo TAKAHASHI ,  Shinichi HIGUCHI ,  Chihiro MYOREN ,  Ryou AKIYAMA ,  Takuya TAKEDA

IPC分类号： F02C3/30 ,  F02C6/18 ,  F02C9/40 ,  F02C3/10

CPC分类号： F02C3/305 ,  F02C3/10 ,  F02C3/30 ,  F02C6/18 ,  F02C9/40 ,  F02C9/54 ,  F05D2220/32 ,  F05D2270/02 ,  F05D2270/061 ,  F05D2270/101 ,  F05D2270/16 ,  F05D2270/20 ,  F05D2270/304 ,  F05D2270/306 ,  F05D2270/3062

摘要： A two-shaft gas turbine having a steam injection mechanism, comprising: a compressor having an inlet guide vane, a combustor, turbines, a heat recovery steam generator, a steam valve to control a flow rate of steam to be supplied to the combustor, a fuel valve to control a flow rate of fuel to be supplied to the combustor, characterized in that, the two-shaft gas turbine further comprising: a rotational frequency meter, a flow rate meter to measure the flow rate of the steam to be supplied to the combustor from the heat recovery steam generator, an inlet guide vane position gauge provided to the compressor, a steam valve position gauge, and a control system calculates and outputs command signals to operate openings of the fuel valve, the steam valve, and the inlet guide vane based on measurement signals obtained by the rotational frequency meter, the inlet guide vane position gauge, or the steam valve position gauge, and an output increase command value to the gas turbine.