-
1.发明授权
-
公开(公告)号：EP3988763B1
公开(公告)日：2024-05-01
申请号：EP21203969.7
申请日：2021-10-21
-
-
4.发明公开
公开(公告)号：EP3502563A2
公开(公告)日：2019-06-26
申请号：EP18214255.4
申请日：2018-12-19
发明人： MOURA, Dennis M. , CLUM, Carey
CPC分类号： F23R3/002 , F01D5/189 , F01D9/065 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/607 , F23M5/08 , F23R3/005 , F23R3/06 , F23R2900/00004 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044
摘要： A gas turbine engine component assembly is provided. The gas turbine engine component assembly (100), comprising: a first component (600) having a first surface (610), a second surface (620) opposite the first surface, and a cooling hole (307) extending from the second surface to the first surface through the first component; a second component (400) having a first surface (410) and a second surface (420), the first surface of the first component and the second surface of the second component defining a cooling channel (390) therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a particulate capture device (500, 800) attached to at least one of the first component and the second component, the particulate capture device configured to aerodynamically separate the airflow (590) from the particulate (592).
-
公开(公告)号：EP3418638A1
公开(公告)日：2018-12-26
申请号：EP17177065.4
申请日：2017-06-21
CPC分类号： F23R3/346 , F23C2201/401 , F23R3/005 , F23R3/14 , F23R3/18 , F23R2900/03341
摘要： A combustor (16) for a turbomachine includes a rich combustion zone (41) and a low temperature zone (43) downstream of the rich combustion zone. A heat exchanger (100) is positioned downstream of the rich combustion zone and upstream of the low temperature zone. The heat exchanger includes a plurality of air passages, a plurality of air inlets in fluid communication with the plurality of air passages, and a plurality of combustion gas passages. Each of the combustion gas passages extends between a combustion gas inlet in fluid communication with the rich combustion zone and a combustion gas outlet in fluid communication with the low temperature zone. The plurality of combustion gas passages are in thermal communication with the plurality of air passages.
-
公开(公告)号：EP3009636B1
公开(公告)日：2018-12-05
申请号：EP15179517.6
申请日：2015-08-03
发明人： Suzuki, Kenji
CPC分类号： F23R3/40 , C01B3/384 , F02C3/20 , F02C3/205 , F02C7/22 , F02C7/224 , F05D2250/25 , F23C2900/03002 , F23K5/08 , F23K5/20 , F23R3/005 , F23R3/28 , F23R2900/00017 , F23R2900/00018 , Y02T50/675
摘要： A fuel supply system (1) includes a fuel reformer (30) disposed to contact at least one of a combustion chamber (20) or a wall of the combustion chamber (20). The fuel reformer includes a reformer chamber wall enclosing a fuel reformer chamber (50), and a reforming catalyst support sheet (32) disposed in the fuel reformer chamber.
-
公开(公告)号：EP2189721B1
公开(公告)日：2018-11-07
申请号：EP09170135.9
申请日：2009-09-11
发明人： YANKOWICH, Paul , XU, Fang
CPC分类号： F23R3/005 , F23R3/045 , F23R3/06 , F23R2900/03041 , F23R2900/03044 , Y02T50/675
摘要： A combustor includes a first liner; and a second liner forming a combustion chamber with the first liner. The combustion chamber is configured to receive an air-fuel mixture for combustion therein, and the first liner is a first dual wall liner having a first hot wall facing the combustion chamber and a first cold wall. The first cold wall has a first cold wall orifice and the first hot wall has a first hot wall orifice. A first insert is mounted in the first hot wall orifice and is configured to receive a first air jet of pressured air from the first cold wall orifice, and guide the first jet through the first hot wall orifice and into the combustion chamber.
-
8.发明公开
公开(公告)号：EP3382278A1
公开(公告)日：2018-10-03
申请号：EP18162531.0
申请日：2018-03-19
IPC分类号： F23R3/00
CPC分类号： F23R3/005 , B23P15/26 , F23R3/002 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045 , Y02T50/675
摘要： A combustor panel (108) may include a combustion facing surface, a cooling surface opposite the combustion facing surface, a first heat transfer pin (151) extending from the cooling surface having a first geometric specification, and a second heat transfer pin (152) extending from the cooling surface having a second geometric specification. The first geometric specification may be different than the second geometric specification. The first geometric specification may be a first height of the first pin (151) and the second geometric specification may be a second height of the second pin (152)
-
公开(公告)号：EP3379149A1
公开(公告)日：2018-09-26
申请号：EP18162933.8
申请日：2018-03-20
CPC分类号： F23R3/005 , F02C3/04 , F23R3/002 , F23R3/06 , F23R2900/00018 , F23R2900/03041 , F23R2900/03044
摘要： Components for gas turbine engines having a hot side surface, a cold side surface, the cold side surface receiving cooling impingement at one or more cold locations, and at least one thermal transfer feature (352; 452a-e; 552', 552"; 652'; 752'; 852', 852"; 952) located between the hot side surface and the cold side surface within the component and arranged such that a condenser section of the thermal transfer feature is located proximate at least one of the cold locations and an evaporator section of the thermal transfer feature is located away from the cold location.
-
10.发明公开
公开(公告)号：EP3372795A1
公开(公告)日：2018-09-12
申请号：EP18160305.1
申请日：2018-03-06
CPC分类号： F01D25/12 , F01D9/023 , F01D11/003 , F01D11/005 , F01D25/08 , F01D25/243 , F01D25/28 , F01D25/30 , F04D29/545 , F05D2220/32 , F05D2240/35 , F05D2240/55 , F05D2260/201 , F23R3/002 , F23R3/005 , F23R3/60 , F23R2900/00012
摘要： A system includes a web plate (36) axially disposed between a transition piece (32) and a turbine nozzle (34). The web plate (36) includes a radial arm (114) extending in a radial direction between an inner surface (112) and an outer surface (110) of the web plate (36). The radial arm (114), the inner surface (112), and the outer surface (110) are disposed about an axial passage (82) configured to facilitate a flow of combustion products (61) from the transition piece (32) to the turbine nozzle (34). The transition piece (32) is disposed within a compressor discharge cavity (28) configured to receive an oxidant (60). The radial arm (114) includes an upstream face (134) in fluid communication with the compressor discharge cavity (28). The radial arm (114) also includes an arm passage (172, 173, 174, 175) that extends an axial length (182) in an axial direction (72) from the upstream face (134) through at least an axial depth (180) of the radial arm (114). The arm passage (172, 173, 174, 175) is configured to receive a portion of the oxidant (60) through the upstream face (134).
-
-
-
-
-
-
-
-
-
搜索结果
503 条记录 (耗时 0.021 秒)
