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公开(公告)号：US20170002662A1
公开(公告)日：2017-01-05
申请号：US14789356
申请日：2015-07-01
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D9/065 , F05D2250/313 , F05D2250/75 , F05D2260/20 , Y02T50/676
摘要： An airfoil for a gas turbine engine includes a body that extends in a radial direction that provides an exterior airfoil surface. The body includes pressure and suction side walls that extend from a leading edge to a trailing edge in a chord-wise direction. A core cooling passage is provided between the pressure and suction side walls and extends in the radial direction. A skin passage is arranged in one of the pressure and suction side walls between the core cooling passage and the exterior airfoil surface. The skin passage includes a first passageway that extends in the radial direction. The first passageway turns to a second passageway that extends in the chord-wise direction to terminate at an exit arranged near the trailing edge.
摘要翻译： 用于燃气涡轮发动机的翼型件包括沿径向延伸的主体，其提供外部翼型表面。 主体包括压力和吸力侧壁，其沿着弦向方向从前缘延伸到后缘。 核心冷却通道设置在压力侧和吸力侧壁之间，并沿径向方向延伸。 皮芯通道设置在芯冷却通道和外部翼型件表面之间的压力和吸力侧壁之一中。 皮肤通道包括沿径向方向延伸的第一通道。 第一通道转向第二通道，该第二通道沿顺时针方向延伸以终止在靠近后缘的出口处。
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公开(公告)号：US20160252049A1
公开(公告)日：2016-09-01
申请号：US15030848
申请日：2014-10-23
发明人： Christophe Maerky , Emmanuel Baudin , Lucien Donce
CPC分类号： F02K1/763 , F02K1/766 , F05D2250/313 , F05D2250/41 , F05D2260/52 , F05D2260/56 , F16H25/2204 , F16H25/2454 , F16H2025/2084
摘要： The invention relates to an actuator device (8) for moving a movable cowl of a thrust reverser, including: an actuator (12) including a screw (14) and a nut (15) capable of engaging with the screw (14) such that a rotation of the screw relative to the nut translates the nut relative to the screw; a locking device (30) including a locking part (31, 57) which is movable relative to the screw (14) between a locked position in which the locking part (31, 57) prevents the rotation of the screw (14) and an unlocked position in which the locking part (31, 57) allows the rotation of the screw (14), in which the screw (14) includes a body (17) and a lock-inhibiting device (38), the lock-inhibiting device (38) including an inhibiting part (47, 48) which is movable relative to the body (17) between a first position in which the part (47, 48) allows the locking part (31, 47) to move between the locked position and the unlocked position, and a second position in which the inhibiting part (47, 48) prevents the locking part (31, 57) from moving into the locked position.
摘要翻译： 本发明涉及一种用于移动推力反向器的可移动整流罩的致动器装置（8），其包括：致动器（12），其包括螺钉（14）和能够与螺钉（14）接合的螺母（15），使得 螺杆相对于螺母的旋转使螺母相对于螺钉转动; 锁定装置（30），其包括锁定部分（31,57），所述锁定部分在所述锁定部分（31,57）防止所述螺钉（14）的旋转的锁定位置之间相对于所述螺钉（14）移动， 解锁位置，其中锁定部分（31,57）允许螺钉（14）的旋转，螺钉（14）包括主体（17）和锁定禁止装置（38），锁定装置 （38）包括禁止部分（47,48），所述禁止部分能够在所述部分（47,48）允许所述锁定部分（31,47）在所述锁定位置（31,47）之间移动的第一位置之间相对于所述主体（17）移动 和解锁位置，以及第二位置，其中禁止部分（47,48）防止锁定部分（31,57）进入锁定位置。
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公开(公告)号：US20160245114A1
公开(公告)日：2016-08-25
申请号：US14607102
申请日：2015-01-28
发明人： Cheng-Zhang Wang
CPC分类号： F01D25/14 , F01D9/041 , F01D25/12 , F01D25/162 , F02C7/18 , F05D2220/3213 , F05D2240/126 , F05D2240/128 , F05D2240/14 , F05D2250/313 , F05D2260/201 , Y02T50/676
摘要： A turbine engine includes a frame assembly including an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A baffle within the outer cavity includes a plurality of openings for directing cooling airflow into the outer cavity for preventing impingement on a radially inner wall of the outer cavity for maintaining a desired temperature of the cooling air within the outer cavity.
摘要翻译： 涡轮发动机包括框架组件，该框架组件包括外部空腔和内部空腔，其中外部空腔包括构造并适于将冷却空气与涡轮机壳体通信的至少一个开口。 外腔内的挡板包括用于将冷却气流引导到外腔中的多个开口，用于防止碰撞在外腔的径向内壁上，以保持外腔内的冷却空气的期望温度。
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公开(公告)号：US09194282B2
公开(公告)日：2015-11-24
申请号：US13989629
申请日：2011-12-19
IPC分类号： F02D23/00 , F02F1/42 , F02B33/44 , F02B37/02 , F01D9/02 , F01D17/10 , F01D25/14 , F01D25/16 , F01D25/24 , F01D25/26 , F01D25/28 , F01N3/04 , F01N13/10 , F02B39/00 , F02B67/10 , F02F1/24
CPC分类号： F02B37/02 , F01D9/02 , F01D9/026 , F01D17/105 , F01D25/14 , F01D25/16 , F01D25/162 , F01D25/24 , F01D25/265 , F01D25/28 , F01N3/046 , F01N13/105 , F02B39/005 , F02B67/10 , F02F1/24 , F02F1/243 , F05D2230/53 , F05D2250/313 , Y02T10/144 , Y02T10/20
摘要： An engine cylinder head and turbocharger assembly includes a turbocharger having a turbine housing, wherein part of the turbine housing is integrated into a casting of the engine cylinder head. The turbocharger is arranged with respect to the engine cylinder head such that the rotational axis of the turbocharger is transverse to the engine axis along which the engine cylinders are spaced. A compressor housing of the turbocharger is oriented toward an air intake side of the engine cylinder head, and the turbine housing is oriented toward an exhaust side of the engine cylinder head.
摘要翻译： 发动机气缸盖和涡轮增压器组件包括具有涡轮壳体的涡轮增压器，其中涡轮机壳体的一部分集成到发动机气缸盖的铸件中。 涡轮增压器相对于发动机气缸盖布置，使得涡轮增压器的旋转轴线横向于发动机气缸间隔开的发动机轴线。 涡轮增压器的压缩机壳体朝向发动机气缸盖的进气侧，并且涡轮机壳体朝向发动机气缸盖的排气侧。
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公开(公告)号：US20130318999A1
公开(公告)日：2013-12-05
申请号：US13485035
申请日：2012-05-31
申请人： James L. Lucas
发明人： James L. Lucas
IPC分类号： F02C3/067
CPC分类号： F02C3/067 , F02C3/107 , F02C7/36 , F02K3/072 , F05D2250/313 , F05D2260/532
摘要： An exemplary gas turbine engine includes a fan, a compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The fan includes a first plurality of fan blades supported on a first fan support and a second plurality of fan blades supported on a second fan support. The first and second fan supports are rotatable about a fan axis independently of each other. A geared architecture includes at least one gear driven by the turbine section for rotating about a gear axis that is transverse to the fan axis. The gear drives the fan supports for rotating the respective pluralities of fan blades in opposite directions.
摘要翻译： 示例性的燃气涡轮发动机包括风扇，压缩机部分，与压缩机部分流体连通的燃烧器和与燃烧器流体连通的涡轮部分。 风扇包括支撑在第一风扇支撑件上的第一多个风扇叶片和支撑在第二风扇支架上的第二多个风扇叶片。 第一和第二风扇支撑件能够相对于彼此独立地围绕风扇轴线旋转。 齿轮架构包括由涡轮机部分驱动的至少一个齿轮，用于围绕横向于风扇轴线的齿轮轴线旋转。 齿轮驱动风扇支撑件，以相反方向旋转相应的多个风扇叶片。
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公开(公告)号：US20130152543A1
公开(公告)日：2013-06-20
申请号：US13326392
申请日：2011-12-15
申请人： David J. Wiebe
发明人： David J. Wiebe
IPC分类号： F02C3/14
CPC分类号： F02C3/14 , F01D1/08 , F01D9/023 , F05D2250/313
摘要： A gas turbine engine (10), including: a turbine having radial inflow impellor blades (38); and an array of advanced transition combustor assemblies arranged circumferentially about the radial inflow impellor blades (38) and having inner surfaces (34) that are adjacent to combustion gases (40). The inner surfaces (34) of the array are configured to accelerate and orient, for delivery directly onto the radial inflow impellor blades (38), a plurality of discrete flows of the combustion gases (40). The array inner surfaces (34) define respective combustion gas flow axes (20). Each combustion gas flow axis (20) is straight from a point of ignition until no longer bound by the array inner surfaces (34), and each combustion gas flow axis (20) intersects a unique location on a circumference defined by a sweep of the radial inflow impellor blades (38).
摘要翻译： 一种燃气涡轮发动机（10），包括：具有径向流入叶轮叶片（38）的涡轮机; 以及一组先进的过渡燃烧器组件，其围绕径向流入叶轮（38）周向布置并具有与燃烧气体（40）相邻的内表面（34）。 阵列的内表面（34）构造成加速和定向，以直接输送到径向流入叶轮（38）上，燃烧气体（40）的多个离散流。 阵列内表面（34）限定相应的燃烧气体流动轴线（20）。 每个燃烧气体流动轴线（20）从点火直线直到不再受阵列内表面（34）的约束，并且每个燃烧气体流动轴线（20）与由扫描线 径向流入叶轮叶片（38）。
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公开(公告)号：US20120317991A1
公开(公告)日：2012-12-20
申请号：US13160380
申请日：2011-06-14
申请人： Cristopher Frost , Mary Eileen Richardson , Michael Stephen Crestin , James Laffan , Mingfong Hwang , Doug Hollingshead , Marc Schmittenberg
发明人： Cristopher Frost , Mary Eileen Richardson , Michael Stephen Crestin , James Laffan , Mingfong Hwang , Doug Hollingshead , Marc Schmittenberg
IPC分类号： F02C6/04
CPC分类号： F02C7/32 , F02C7/36 , F05D2250/312 , F05D2250/313 , F05D2260/53 , Y02T50/671
摘要： A gas turbine engine and an accessory gear box (AGB) are provided for. The gas turbine engine comprises a drive shaft, a compressor, a combustor and an exhaust turbine, where the exhaust turbine and the compressor are coaxially connected by the drive shaft. The gas turbine engine further comprises an engine casing of varying diameters circumferentially enveloping the compressor, the combustor and the exhaust turbine with a waist located between the compressor and the combustor. The gas turbine engine also includes an accessory gear box (AGB) attached to the engine casing at the waist, the AGB comprising a gear rotating on an axis extending in a transverse direction relative to that of the drive shaft.
摘要翻译： 提供燃气涡轮发动机和附件齿轮箱（AGB）。 燃气涡轮发动机包括驱动轴，压缩机，燃烧器和排气涡轮机，其中排气涡轮机和压缩机通过驱动轴同轴连接。 燃气涡轮发动机还包括具有不同直径的发动机壳体，其周向包围压缩机，燃烧器和排气涡轮机，腰部位于压缩机和燃烧器之间。 燃气涡轮发动机还包括在腰部附接到发动机壳体的附件齿轮箱（AGB），AGB包括沿相对于驱动轴的横向方向延伸的轴线旋转的齿轮。
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公开(公告)号：US20090104035A1
公开(公告)日：2009-04-23
申请号：US12344776
申请日：2008-12-29
申请人： William Abdel-Messeh , Frank Cunha
发明人： William Abdel-Messeh , Frank Cunha
CPC分类号： F01D5/187 , F05D2250/313 , F05D2250/70 , F05D2260/2212 , F05D2260/22141 , Y10T137/2087
摘要： A passageway is provided through which a cooling fluid flows in a first direction. The passageway has a plurality of trip strips positioned within the passageway. Adjacent one of the trip strips are oriented to converge towards each other at a first end to form an apex portion and to form a region in which turbulence is created. The apex portion is oriented at an angle with respect to the first direction.
摘要翻译： 提供通道，冷却流体沿第一方向流过该通道。 通道具有定位在通道内的多个跳闸条。 相邻的一个行程带在第一端处朝向彼此会聚以形成顶点部分并形成其中产生湍流的区域。 顶点部分相对于第一方向成一角度定向。
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公开(公告)号：US20080222874A1
公开(公告)日：2008-09-18
申请号：US11685503
申请日：2007-03-13
IPC分类号： B23P25/00
CPC分类号： F01D9/023 , F01D9/047 , F02C3/14 , F05D2230/80 , F05D2250/313 , F05D2250/35 , Y10T29/4973 , Y10T29/49885
摘要： A hot gas duct, such as a combustion casing in a gas turbine engine, includes a duct splitter held within the hot gas duct in at least three, preferably four, locations spaced around a peripheral edge of the duct splitter. At least one, preferably two, of the holding locations each comprise a generally cylindrical mounting that projects through a wall of the hot gas duct to engage an edge portion of the duct splitter by means of a slot formed in a circular face of the mounting. Mutually contacting surfaces of the slot and the duct splitter comprise hard face coatings to combat wear due to vibration and differential thermal expansion and contraction. The mountings have cooling holes that penetrate the mounting, so that coolant can flow through the mountings and into the interior of the hot gas duct to cool the mountings and the hard face coatings.
摘要翻译： 诸如燃气涡轮发动机中的燃烧壳体的热气体管道包括保持在热气体管道内的至少三个，优选四个位置的管道分配器，其围绕管道分流器的周边边缘间隔开。 至少一个，优选两个保持位置各自包括大致圆柱形的安装件，其突出通过热气体管道的壁，以通过形成在安装件的圆形面中的狭槽接合管道分流器的边缘部分。 狭槽和管道分离器的相互接触的表面包括硬面涂层，以抵抗由于振动和不同的热膨胀和收缩导致的磨损。 安装件具有穿透安装件的冷却孔，使得冷却剂可以流过安装件并进入热气管道的内部，以冷却安装件和硬面涂层。
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公开(公告)号：US20070224048A1
公开(公告)日：2007-09-27
申请号：US11388815
申请日：2006-03-24
申请人： William Abdel-Messeh , Frank Cunha
发明人： William Abdel-Messeh , Frank Cunha
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/313 , F05D2250/70 , F05D2260/2212 , F05D2260/22141 , Y10T137/2087
摘要： A passageway is provided through which a cooling fluid flows in a first direction. The passageway has a plurality of trip strips positioned within the passageway. Adjacent one of the trip strips are oriented to converge towards each other at a first end to form an apex portion and to form a region in which turbulence is created. The apex portion is oriented at an angle with respect to the first direction.
摘要翻译： 提供通道，冷却流体沿第一方向流过该通道。 通道具有定位在通道内的多个跳闸条。 相邻的一个行程带在第一端处朝向彼此会聚以形成顶点部分并形成其中产生湍流的区域。 顶点部分相对于第一方向成一角度定向。
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