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公开(公告)号：US20180230812A1
公开(公告)日：2018-08-16
申请号：US15405648
申请日：2017-01-13
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2220/323 , F05D2240/303 , F05D2250/10 , F05D2250/12 , F05D2250/18 , F05D2250/312 , F05D2250/324 , F05D2250/34 , F05D2250/38 , F05D2260/202 , Y02T50/676
摘要： An apparatus and method for an engine component for a turbine engine including an exterior wall separating a hot fluid flow exterior of the engine component from a cooling fluid flow interior of the engine component. A cooling circuit can be provided within the component having a cooling passage. At least two film holes can extend through the exterior wall for providing a cooling film along the exterior of the wall. The film holes can overlap one another relative to the hot fluid flow.
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公开(公告)号：US09957896B2
公开(公告)日：2018-05-01
申请号：US14361954
申请日：2012-12-04
申请人： SNECMA
CPC分类号： F02C7/20 , F01D11/122 , F01D25/246 , F01D25/28 , F02C7/28 , F05D2230/644 , F05D2240/11 , F05D2240/14 , F05D2250/312 , F05D2250/35 , F05D2250/70 , F05D2260/30
摘要： A device for axially arresting a sealing ring made of an abradable material in contact with a periphery of an aircraft turbomachine module rotor, the device having a first reference central axis, and including: a support including a support opening defining a circular track centered on a second axis at a distance from the axis; and an axial stop part including an extraction passage centered on a third axis at a distance from the axis, and defining a complementary circular track around its periphery, cooperating with the track to allow the part to rotate about the axis, between an axial stop position for the sealing ring, and a position to extract the ring through the extraction passage.
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公开(公告)号：US20180105278A1
公开(公告)日：2018-04-19
申请号：US15729504
申请日：2017-10-10
发明人： Nora EL GHANNAM , Matthieu Etienne ATTALI , Romain Jean-Claude FERRIER , Caroline Marie FRANTZ , Thomas Gerard Daniel RIVIERE , Nicolas Xavier TRAPPIER
CPC分类号： B64D27/26 , B64D27/12 , B64D29/08 , B64D2027/264 , F02C6/206 , F02C7/04 , F02C7/20 , F02C7/32 , F02C7/36 , F05D2220/323 , F05D2250/312 , F05D2260/15 , F05D2260/40 , F05D2260/4031 , Y02T50/671
摘要： The invention relates to an aircraft propulsion assembly comprising a cradle receiving a turbine engine comprising at least one propeller having a longitudinal axis of rotation, a gas turbine engine having a longitudinal axis of rotation offset from the axis, and a reduction gear by means of which said propeller receives drive power from said engine, wherein the propeller and the gas turbine engine are designed such that axes and are offset from one another within said cradle at least by a given value in a transverse direction, the axis of the gas turbine engine being transversely closer to a proximal lateral side of the cradle than to an opposite distal lateral side of the cradle in order to create a lateral space between said engine and said distal lateral side of the cradle, thereby forming at least one region for installing equipments, components or accessories of said turbine engine.
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公开(公告)号：US09879591B2
公开(公告)日：2018-01-30
申请号：US14806883
申请日：2015-07-23
发明人： Jean Thomassin , Sebastien Bolduc , Bruno Villeneuve , Stephane Berube , Mike Fontaine , David Gagnon-Martin , Andre Julien , Mark Cunningham , Serge Lafortune , Pierre-Yves Legare
IPC分类号： F02B29/04 , F02C6/12 , F02C7/047 , F02C7/052 , F02C7/055 , F02C7/14 , F02C7/36 , F02B37/12 , F02B53/08 , F02B53/14 , F01C11/00 , F02B39/04 , F01C21/18 , F02M31/04 , F02M31/10 , F01C1/22
CPC分类号： F02B29/0406 , F01C1/22 , F01C11/008 , F01C21/18 , F02B29/0412 , F02B33/40 , F02B37/12 , F02B39/04 , F02B53/08 , F02B53/14 , F02C6/12 , F02C7/047 , F02C7/052 , F02C7/055 , F02C7/14 , F02C7/36 , F02M31/042 , F02M31/10 , F02M31/107 , F05D2250/312 , F05D2260/40311 , F05D2260/98 , Y02T10/126 , Y02T10/17 , Y02T50/675
摘要： An intake assembly for a compressor providing compressed air to an internal combustion engine core, including an air conduit having at least one heat exchanger extending thereacross, an intake plenum for the compressor, a first intake conduit connected to the air conduit upstream of the heat exchanger(s), a second intake conduit connected to the air conduit downstream of the heat exchanger(s), and a selector valve configurable between a first configuration to allow a fluid communication between the intake plenum and the air conduit through the first intake conduit and a second configuration to prevent the fluid communication through the first intake conduit. Fluid communication between the intake plenum and the air conduit through the second intake conduit is allowed at least when the selector valve is in the second configuration. An engine assembly and method of supplying air to a compressor are also discussed.
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公开(公告)号：US20170234213A1
公开(公告)日：2017-08-17
申请号：US15518508
申请日：2014-11-17
发明人： Takaya FUTAE , Yosuke DANMOTO , Tadasuke NISHIOKA , Yoji AKIYAMA
IPC分类号： F02B39/14 , F01D25/18 , F04D29/063 , F01D25/16 , F04D29/051
CPC分类号： F02B39/14 , F01D25/166 , F01D25/18 , F02C6/12 , F04D29/051 , F04D29/063 , F05D2220/40 , F05D2250/312 , F16C17/04 , F16C33/1025 , F16C33/106 , F16C2360/24
摘要： A turbomachine includes: a rotational shaft; a pair of thrust collars disposed around the rotational shaft; a thrust bearing disposed around the rotational shaft at an axial directional position between the pair of thrust collars; and an oil-drain channel disposed around the rotational shaft, for draining lubricant oil after lubricating a sliding portion between the thrust bearing and the thrust collars. The oil-drain channel includes: an oil-drain port portion for discharging the lubricant oil inside the oil-drain channel downward; and an oil-guide channel portion disposed above the oil-drain port portion and configured to guide the lubricant oil from the sliding portion in a circumferential direction of the rotational shaft to the oil-drain port portion. The oil-guide channel portion has an asymmetric shape with respect to a rotational direction of the rotational shaft, the oil-guide channel portion having a minimum flow-path cross sectional area at a first position on an upstream side in the rotational direction, and a maximum flow-path cross sectional area at a second position on a downstream side of the first position.
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公开(公告)号：US09677568B2
公开(公告)日：2017-06-13
申请号：US13638804
申请日：2011-03-18
申请人： Robert Vetter , Alexandre Pfister
发明人： Robert Vetter , Alexandre Pfister
CPC分类号： F04D27/009 , B22D17/00 , B22D17/24 , F01D9/026 , F01D17/105 , F04D27/0215 , F04D29/4206 , F05D2220/40 , F05D2230/21 , F05D2250/312
摘要： A turbocharger housing has a valve device. The valve device is formed with at least one first duct section and a second duct section. The two duct sections are arranged with their longitudinal axes parallel to one another and they are formed without any undercuts.
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公开(公告)号：US20170137135A1
公开(公告)日：2017-05-18
申请号：US15346612
申请日：2016-11-08
CPC分类号： B64D27/18 , B64D27/12 , B64D33/02 , B64D2033/0286 , F02C7/05 , F02K1/52 , F02K3/06 , F02K3/077 , F05D2240/40 , F05D2250/312
摘要： The invention relates to an aircraft propulsion assembly (10), comprising a single gas generator (11) and two fans (12) drive in rotation by the gas generator (11) and offset on either side of a vertical plane passing through a longitudinal axis (X) of the gas generator, the rotational axes of the fans lying substantially in the same fan plane.According to the invention, the propulsion assembly (10) comprises an air inlet fairing formed upstream of a nacelle (25) connecting the fans, said fairing (15) having, between the fans (12), an air inlet opening (17, 17′) lying substantially perpendicular to the fan plane and on either side of this plane, the propulsion assembly further comprising an air supply device configured so as to supply the gas generator (11) with a part of the incoming air and to take off, from the remaining part of the incoming air, a cooling airflow intended to cool elements of the propulsion assembly and/or a wing supporting the propulsion assembly.
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公开(公告)号：US09650915B2
公开(公告)日：2017-05-16
申请号：US14407051
申请日：2013-06-14
申请人： GE AVIO S.R.L.
发明人： Paolo Calza , Matteo Usseglio
CPC分类号： F01D25/06 , F01D5/16 , F01D5/22 , F01D5/225 , F01D9/041 , F05D2220/32 , F05D2250/312 , F05D2260/961 , Y02T50/671 , Y02T50/673
摘要： An aerofoil array for a gas turbine system has an inner annular platform and an outer annular platform, which extend about a longitudinal axis and radially delimit an annular channel for a gas flow; the annular channel houses a plurality of aerofoils, arranged at a substantially constant angular pitch and comprising respective central portions and respective ends connected to the platforms; the aerofoils are formed by two series of aerofoils having a different geometrical feature in order to intentionally vary the eigenfrequencies and arranged about the longitudinal axis with a sequence that is regularly repeated all along the annular channel; even though the external geometry of the aerofoils is varied, the cross-sections remain unchanged in the central portions, at any given radius with respect to the longitudinal axis.
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公开(公告)号：US20160047313A1
公开(公告)日：2016-02-18
申请号：US14460470
申请日：2014-08-15
CPC分类号： F16B43/00 , F01D9/023 , F01D25/28 , F05D2230/64 , F05D2240/91 , F05D2250/312 , F05D2260/36 , F16B37/122 , Y02T50/675
摘要： A bushing includes a body extending from a first end to a second end through an intermediate portion. The body includes a passage having a first centerline extending from the first end to the second end. A first alignment member is formed on a first section of the intermediate portion at the first end. The first alignment member includes an outer surface having a plurality of splines configured to be received by a first component to be joined. A second alignment member is formed on a second section of the intermediate portion. The second alignment member includes a second centerline that is off-set relative to the first centerline and is configured to be received by a second component to be joined with the first component.
摘要翻译： 衬套包括从第一端延伸到第二端穿过中间部分的主体。 主体包括具有从第一端延伸到第二端的第一中心线的通道。 第一对准部件在第一端部的中间部分的第一部分上形成。 第一对准构件包括具有多个花键的外表面，该多个花键构造成被待接合的第一构件接收。 第二对准构件形成在中间部分的第二部分上。 第二对准构件包括相对于第一中心线偏移的第二中心线，并且构造成由第二部件接收以与第一部件接合。
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公开(公告)号：US20160025142A1
公开(公告)日：2016-01-28
申请号：US14775454
申请日：2014-03-14
发明人： David J. Wasserman
IPC分类号： F16C35/063 , F01D25/16 , F16C19/06
CPC分类号： F16C35/063 , F01D25/16 , F01D25/162 , F05D2240/50 , F05D2250/312 , F05D2250/36 , F16C19/04 , F16C19/06 , F16C35/067 , F16C2360/23
摘要： A bearing assembly includes a sleeve and a bearing located within a bore of the sleeve. The sleeve extends between an inner surface and an outer surface. The inner surface at least partially defines the bore, which extends through the sleeve. The inner surface is configured eccentric to the outer surface. The bearing includes a plurality of rolling elements arranged between an inner ring and an outer ring. The outer ring is mounted to the sleeve.
摘要翻译： 轴承组件包括套筒和位于套筒的孔内的轴承。 套筒在内表面和外表面之间延伸。 内表面至少部分地限定穿过套筒延伸的孔。 内表面配置成偏心于外表面。 轴承包括布置在内圈和外圈之间的多个滚动元件。 外圈安装到套筒上。
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