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1.发明公开
公开(公告)号：EP3077724A1
公开(公告)日：2016-10-12
申请号：EP14868343.6
申请日：2014-12-04
CPC分类号： F23R3/002 , F02C7/12 , F02C7/18 , F02C7/24 , F02K1/822 , F05D2220/30 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/231 , F23R3/04 , F23R3/06 , F23R2900/03044 , Y02T50/675
摘要： An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell, a heat shield and an annular body engaged with the shell and the heat shield. The annular body extends through the combustor wall. The annular body at least partially defines a quench aperture along a centerline through the combustor wall. The annular body also at least partially defines a cooling aperture in fluid communication with the quench aperture. At least a portion of the cooling aperture extends radially outward from the quench aperture relative to the centerline.
摘要翻译： 为涡轮发动机提供组件。 涡轮发动机组件的燃烧器壁包括壳体，隔热罩和与壳体和隔热罩接合的环形体。 环形体延伸穿过燃烧器壁。 环形主体至少部分地限定沿着通过燃烧器壁的中心线的淬火孔。 环形本体还至少部分地限定与骤冷孔流体连通的冷却孔。 冷却孔的至少一部分相对于中心线从淬火孔径向向外延伸。
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公开(公告)号：EP3102884B1
公开(公告)日：2020-04-01
申请号：EP15743262.6
申请日：2015-02-03
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3.发明公开GAS TURBINE ENGINE WALL ASSEMBLY WITH CIRCUMFERENTIAL RAIL STUD ARCHITECTURE 审中-公开具有电流下轨螺栓架构燃气涡轮发动机壁布置
公开(公告)号：EP3084310A1
公开(公告)日：2016-10-26
申请号：EP14871741.6
申请日：2014-08-29
CPC分类号： F23R3/002 , F01D25/12 , F02C7/18 , F05D2220/323 , F05D2230/60 , F05D2240/35 , F05D2260/201 , F05D2260/31 , F16B33/004 , F23R3/005 , F23R3/007 , F23R3/50 , F23R3/60 , F23R2900/00017 , F23R2900/03041 , F23R2900/03044 , Y02T50/675
摘要： A liner panel for use in a gas turbine engine. The liner panel has a hot side and a cold side. The liner panel includes a rail extending from the cold side and a multiple of studs extending from the cold side. At least one of the multiple of studs extends from, in part, the rail.
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公开(公告)号：EP3058201B1
公开(公告)日：2018-07-18
申请号：EP14854071.9
申请日：2014-05-23
CPC分类号： F23R3/002 , F02C7/18 , F23R3/005 , F23R3/007 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044 , F23R2900/03045
摘要： A combustor wall is provided for a turbine engine. The combustor wall includes a shell, a heat shield and a cooling element. The shell defined a first set of apertures. The heat shield defines a second set of apertures. The cooling element extends between the shell and the heat shield within a tapered cooling cavity defined between the shell and the heat shield. The tapered cavity is fluidly coupled with the first and the second sets of apertures. The cooling element is thermally coupled to one of the shell and the heat shield.
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公开(公告)号：EP3071887A1
公开(公告)日：2016-09-28
申请号：EP14864817.3
申请日：2014-11-21
摘要： A multi-walled structure is provided for a turbine engine. This structure includes a shell with a textured first surface, and a heat shield with a second surface. The heat shield is attached to the shell. The first and the second surfaces vertically define a cooling cavity between the shell and the heat shield. The cooling cavity fluidly couples a plurality of cooling apertures defined in the shell with a plurality of cooling apertures defined in the heat shield.
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6.发明公开COOLING A MULTI-WALLED STRUCTURE OF A TURBINE ENGINE 有权KÜHLUNGEINER MEHRWANDIGEN STRUKTUR EINES TURBINENMOTORS
公开(公告)号：EP3071816A1
公开(公告)日：2016-09-28
申请号：EP14863469.4
申请日：2014-11-21
CPC分类号： F23R3/002 , F05D2240/15 , F05D2260/201 , F23R3/005 , F23R3/06 , F23R3/10 , F23R2900/03044
摘要： An assembly is provided for a turbine engine. This turbine engine assembly includes a body, a shell and a heat shield panel. The panel is attached to the shell with a tapered cooling cavity between the shell and the panel. The panel defines a cooling aperture configured to direct air out of the cooling cavity to impinge against the body.
摘要翻译： 提供了一种用于涡轮发动机的组件。 该涡轮发动机组件包括主体，壳体和隔热板。 面板在外壳和面板之间具有锥形冷却腔连接到外壳。 面板限定了一个冷却孔，该冷却孔构造成将空气引导出冷却腔以撞击身体。
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公开(公告)号：EP3071887B1
公开(公告)日：2020-03-11
申请号：EP14864817.3
申请日：2014-11-21
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公开(公告)号：EP3077727B1
公开(公告)日：2019-10-09
申请号：EP14868497.0
申请日：2014-12-03
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公开(公告)号：EP3102884A1
公开(公告)日：2016-12-14
申请号：EP15743262.6
申请日：2015-02-03
CPC分类号： F23R3/002 , F02C7/24 , F05D2220/32 , F05D2240/35 , F05D2260/201 , F23R3/06 , F23R2900/03042 , F23R2900/03044
摘要： An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall with a shell and a heat shield. The combustor wall defines a quench aperture therethrough. The combustor wall also defines a cavity between the shell and the heat shield. The shell defines a first aperture through which air is directed into the cavity. The heat shield includes a rail that at least partially defines a second aperture configured to direct at least some of the air within the cavity out of the combustor wall and towards the quench aperture.
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10.发明公开
公开(公告)号：EP3077727A1
公开(公告)日：2016-10-12
申请号：EP14868497.0
申请日：2014-12-03
IPC分类号： F23R3/06
CPC分类号： F23R3/005 , F05D2240/35 , F23R3/002 , F23R3/04 , F23R3/06 , F23R3/50 , F23R2900/00017 , F23R2900/03042 , F23R2900/03044
摘要： An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell, a heat shield and an annular body. The annular body extends through the combustor wall. The annular body at least partially defines a quench aperture along a centerline through the combustor wall. The annular body defines a first cooling aperture fluidly coupled between a cooling cavity and the quench aperture. The cooling cavity is between the shell and the heat shield.
摘要翻译： 为涡轮发动机提供组件。 涡轮发动机组件的燃烧器壁包括壳体，隔热罩和环形体。 环形体延伸穿过燃烧器壁。 环形主体至少部分地限定沿着通过燃烧器壁的中心线的淬火孔。 环形主体限定流体联接在冷却腔和骤冷孔之间的第一冷却孔。 冷却腔位于壳体和隔热罩之间。
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