公开(公告)号：EP2820269B1

公开(公告)日：2018-07-11

申请号：EP13706543.9

申请日：2013-02-28

申请人： Ansaldo Energia Switzerland AG

发明人： BENZ, Eribert ,  HELLAT, Jaan ,  WETTSTEIN, Hans ,  PAYNE, Robin

IPC分类号： F02C7/04 ,  F01K13/02 ,  F01K23/10 ,  F02C3/34 ,  F02C6/18 ,  F02C1/00 ,  F02C1/08 ,  F02C7/042 ,  F02C7/057

CPC分类号： F02C3/34 ,  F01K13/02 ,  F01K23/10 ,  F01K23/101 ,  F02C1/005 ,  F02C1/08 ,  F02C6/18 ,  F02C7/04 ,  F02C7/042 ,  F02C7/057 ,  F05D2220/60 ,  F05D2270/20

摘要： A method for operating a gas turbine power plant, and a gas turbine power plant in which fresh air is delivered to a compressor inlet and is accelerated in the compressor inlet and a recirculated first exhaust gas substream is delivered into a region of the compressor inlet in which the fresh air is accelerated to an extent such that the difference between total pressure and static pressure in the fresh air is greater than or equal to a pressure difference which is required in order to suck a target mass flow of the recirculated first exhaust gas substream into the compressor inlet.

公开(公告)号：EP2694878B1

公开(公告)日：2018-12-12

申请号：EP12717070.2

申请日：2012-04-05

申请人： Ansaldo Energia Switzerland AG

发明人： MARMILIC, Robert ,  HELLAT, Jaan ,  FREITAG, Ewald ,  EROGLU, Adnan

IPC分类号： F23C6/04 ,  F02C7/141 ,  F02C7/228

CPC分类号： F02C3/00 ,  F02C7/141 ,  F02C7/228 ,  F05D2220/722 ,  F23R3/346 ,  F23R2900/03341 ,  Y02E20/16 ,  Y02E20/18 ,  Y02T50/671 ,  Y02T50/675

公开(公告)号：EP2912381B1

公开(公告)日：2018-06-13

申请号：EP13721300.5

申请日：2013-04-25

申请人： Ansaldo Energia Switzerland AG

发明人： DUESING, Michael ,  TAY WO CHONG HILARES, Luis ,  BOTHIEN, Mirko Ruben ,  HELLAT, Jaan ,  SCHUERMANS, Bruno

IPC分类号： F23R3/34 ,  F23R3/06

CPC分类号： F23R3/06 ,  F02C6/02 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/964 ,  F23M20/005 ,  F23R3/002 ,  F23R2900/00014 ,  F23R2900/03341 ,  Y02E20/16

摘要： The invention concerns a damper arrangement (112) for reducing combustion-chamber pulsation arising inside a gas turbine (100), wherein the gas turbine (100) essentially comprises at least one compressor (103), a primary combustor (101) which is connected downstream to the compressor (103), and the hot gases of the primary combustor (101) are admitted at least to an intermediate turbine or directly or indirectly to a secondary combustor (102). The hot gases of the secondary combustor (102) are admitted to a further turbine (105) or directly or indirectly to an energy recovery, wherein at least one combustor is arranged in a can-architecture. At least one combustor liner comprising air passages (114), wherein at least one of the air passages (114) is formed as a damper neck (113). The damper neck (113) being actively connected to a damper volume (112), and the damper volume (112) is part of a connecting duct extending between a compressor air plenum and the combustor.