-
公开(公告)号：US20170268355A1
公开(公告)日：2017-09-21
申请号：US15531762
申请日：2014-12-11
发明人： Manish Kumar , Joseph L. Evins , Khamhou Sayavong , Matthias Hase , Miguel Bascones , Adam J. Weaver , Robert H. Bartley , Lashanda N. Williams
IPC分类号： F01D9/02
CPC分类号： F01D9/023 , F01D25/04 , F02C3/00 , F05D2260/96 , F23R3/60
摘要： A transition duct support apparatus and a method to support an exit frame in a transition duct in a gas turbine engine are provided. A stiffener (24) may be arranged to provide support to an outer edge (27) of an exit frame (12) in a transition duct (14). Stiffener (24) may be configured to circumferentially extend between mutually opposed corners (30) of the exit frame of the transition duct. A brace (26) may be connected to a centrally-disposed section (20) and may extend to support respective end portions (32) of the stiffener. The support apparatus is effective to provide a respective tuned level of stiffness support with respect to one or more axes of the exit frame in the transition duct. The apparatus and method may be effective for distributing mechanical stresses on the exit frame of the transition duct and/or neighboring regions in the transition duct.
-
公开(公告)号：US10443855B2
公开(公告)日：2019-10-15
申请号：US15515294
申请日：2014-10-23
摘要： A fuel burner system (10) configured to inject a liquid fuel and a gas fuel into a combustor (12) of a turbine engine (14) such that the engine (14) may operate on the combustion of both fuel sources (20, 24) is disclosed. The fuel burner system (10) may be formed from a nozzle cap (16) including one or more first fuel injection ports (18) in fluid communication with a first fuel source (20) of syngas and one or more second fuel injection ports (22) in fluid communication with a second fuel source (24) of natural gas. The fuel burner system (10) may also include an oil lance (26) with one or more oil injection passages (28) that is in fluid communication with at least one oil source (30) and is configured to emit oil into the combustor (12). The oil lance (26) may include one or more fluid injection passages (32) configured to emit air to break up the oil spray and water to cool the combustor (12), or both.
-
公开(公告)号：US11066941B2
公开(公告)日：2021-07-20
申请号：US15531762
申请日：2014-12-11
发明人： Manish Kumar , Joseph L. Evins , Khamhou Sayavong , Matthias Hase , Miguel Bascones , Adam J. Weaver , Robert H. Bartley , Lashanda N. Williams
摘要： A transition duct support apparatus and a method to support an exit frame in a transition duct in a gas turbine engine are provided. A stiffener (24) may be arranged to provide support to an outer edge (27) of an exit frame (12) in a transition duct (14). Stiffener (24) may be configured to circumferentially extend between mutually opposed corners (30) of the exit frame of the transition duct. A brace (26) may be connected to a centrally-disposed section (20) and may extend to support respective end portions (32) of the stiffener. The support apparatus is effective to provide a respective tuned level of stiffness support with respect to one or more axes of the exit frame in the transition duct. The apparatus and method may be effective for distributing mechanical stresses on the exit frame of the transition duct and/or neighboring regions in the transition duct.
-
公开(公告)号：US20210054751A1
公开(公告)日：2021-02-25
申请号：US16982866
申请日：2018-03-27
摘要： A sealing arrangement in a gas turbine engine to seal a gap between first and second turbine components is provided. The sealing arrangement includes a first arcuate feather seal connected to an anchoring assembly of the sealing arrangement affixed to the first turbine component. A second arcuate feather seal is affixed to the second turbine component. The first arcuate feather seal and the second arcuate feather seal are responsive to a pressure differential that develops across the gap to form a pressure-loaded sealing joint between respective sealing surfaces of the first arcuate feather seal and the second arcuate feather seal. The sealing arrangement provides substantial design flexibility since it can reliably provide appropriate sealing functionality while enabling multiple degrees of freedom, such as to accommodate radial and/or axial displacements that can develop between the first turbine component and the second turbine component.
-
公开(公告)号：US20170234542A1
公开(公告)日：2017-08-17
申请号：US15515294
申请日：2014-10-23
摘要： A fuel burner system (10) configured to inject a liquid fuel and a gas fuel into a combustor (12) of a turbine engine (14) such that the engine (14) may operate on the combustion of both fuel sources (20, 24) is disclosed. The fuel burner system (10) may be formed from a nozzle cap (16) including one or more first fuel injection ports (18) in fluid communication with a first fuel source (20) of syngas and one or more second fuel injection ports (22) in fluid communication with a second fuel source (24) of natural gas. The fuel burner system (10) may also include an oil lance (26) with one or more oil injection passages (28) that is in fluid communication with at least one oil source (30) and is configured to emit oil into the combustor (12). The oil lance (26) may include one or more fluid injection passages (32) configured to emit air to break up the oil spray and water to cool the combustor (12), or both.
-
-
-
-
搜索结果
5 条记录 (耗时 0.013 秒)
