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公开(公告)号：EP3537046A1
公开(公告)日：2019-09-11
申请号：EP19156495.4
申请日：2019-02-11
发明人： CLUM, Carey , MOURA, Dennis M.
摘要： A dual wall liner (300; 400) for a gas turbine engine (20) may comprise a shell (310) having a first side (312) and a second side (314), a panel (320) contacting the shell (310), the panel (320) at least partially defining a hot gas path through which a hot gas flows, wherein the first side (312) of the shell (310) faces the panel (320), wherein the shell (310) includes a thermal barrier coating (TBC) (334) disposed on the first side of the shell (310). The TBC (334) may thermally protect the shell (310) from heat from a hot gas path.
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公开(公告)号：EP2959111B1
公开(公告)日：2019-06-12
申请号：EP13818916.2
申请日：2013-12-18
发明人： THOMAS, David J. , FREEMAN, Ted J.
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公开(公告)号：EP3315719B1
公开(公告)日：2019-06-05
申请号：EP17196197.2
申请日：2017-10-12
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公开(公告)号：EP2971691B1
公开(公告)日：2019-05-08
申请号：EP14807870.2
申请日：2014-03-11
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公开(公告)号：EP2971660B1
公开(公告)日：2019-05-01
申请号：EP14807640.9
申请日：2014-03-12
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公开(公告)号：EP2834498B1
公开(公告)日：2019-05-01
申请号：EP13772338.3
申请日：2013-03-25
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公开(公告)号：EP3473812A1
公开(公告)日：2019-04-24
申请号：EP18199069.8
申请日：2018-10-08
摘要： An aft frame assembly (92) for a gas turbine transition piece (72) has a main body (100) with an upstream facing surface (110) and downstream facing surface (112). Feed hole inlets (120) are located on the upstream facing surface, and each feed hole inlet is coupled to a cooling channel (122) that passes through the main body towards the downstream facing surface. Plenums (124) are located in or near the downstream facing surface. Each cooling channel is connected to and terminates in a plenum. Microchannels (126) are formed in or near the downstream facing surface, and each microchannel is connected to a plenum. The cooling channels are configured as inputs and the microchannels are configured as outputs of the plenums. Two or more of the cooling channels and two or more of the microchannels are connected to one plenum. Exit channels (130) are connected to the microchannels, and exhaust flow out of an upstream facing surface (107) of a seal slot (103).
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公开(公告)号：EP3141705B1
公开(公告)日：2018-12-26
申请号：EP15184277.0
申请日：2015-09-08
CPC分类号： F01D25/08 , F01D11/18 , F01D25/145 , F01D25/24 , F02C3/04 , F05D2220/32 , F05D2240/35 , F05D2260/231
摘要： A gas turbine rotor cover (10) is described, comprising a body (20), the body comprising an inner side (22) facing towards a central axis (50) and an outer side (24) facing away from the central axis, wherein the gas turbine rotor cover is configured and arranged to extend in an axial direction (52) and a circumferential direction (54) relative to the central axis. An inner layer of insulation (30) is attached to the inner side of the body and extends along at least part of the length of the body in the axial direction and/or an outer layer of insulation (40) is attached to the outer side of the body, and extends along at least part of the length of the body in the axial direction. A gas turbine (60) containing the gas turbine rotor cover (10) is also described.
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公开(公告)号：EP3167164B1
公开(公告)日：2018-10-31
申请号：EP15774541.5
申请日：2015-09-23
CPC分类号： F01D9/023 , B23K26/21 , F01D25/08 , F01D25/12 , F01D25/14 , F01D25/24 , F02K1/82 , F02K1/822 , F05D2230/22 , F05D2230/54 , F05D2250/292 , F05D2260/20 , F05D2260/202 , F05D2260/203 , F23R3/002 , F23R3/005 , F23R2900/03041 , F23R2900/03042 , Y02T50/675
摘要： The invention is directed to a turbomachine component (10), particularly a gas turbine engine component, comprising at least one part (2) built in parts from a curved or planar panel (11), particularly a sheet metal, the part (2) comprising a plurality of cooling channels (3) via which a cooling fluid (5), particularly air, is guidable, wherein at least one of the plurality of cooling channels (3) has a continuously tapered section (8). The invention furthermore is directed to a gas turbine engine equipped with such a component and a method of manufacturing.
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公开(公告)号：EP2735708B1
公开(公告)日：2018-05-23
申请号：EP13193015.8
申请日：2013-11-15
发明人： Todorovic, Predrag
CPC分类号： F01D11/005 , F01D9/042 , F01D25/08 , F05D2240/15 , Y02T50/671 , Y02T50/673 , Y02T50/675
摘要： A bifurcation aerofoil having a leading edge portion and flanks where the leading edge portion is mounted to an inner wall of the bypass duct using a floating seal which permits circumferential movement of the leading edge. A cowl has a wall that provides the flanks of the aerofoil. On closing of the cowl into its flight position any contact between the flanks and the leading edge portion enables realignment of the leading edge portion to the inner wall of the bypass duct.
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