-
公开(公告)号：US12072016B2
公开(公告)日：2024-08-27
申请号：US18532743
申请日：2023-12-07
发明人： Juan-Luis Marcos Izquierdo , Mohamed Bouyakoub , Jordane Emile André Peltier , Anthony Cuffaro , Antoine Jacques Marie Pennacino , Jérémy David Seban
CPC分类号： F16H57/0427 , F02C7/06 , F02C7/36 , F16H57/0423 , F05D2260/602 , F05D2260/609 , F05D2260/98
摘要： A gutter for recovering lubrication oil, particularly for a mechanical reducer of an aircraft turbomachine, annular around a central axis, and comprising a first radial wall extending radially with respect to the central axis, an inclined wall extending from a radially outer end of the first radial wall, a guide portion having an overall U shape extending from one end of the inclined wall, and a second radial wall extending radially outward with respect to the central axis from one end of the guide portion, a space delimited by the first radial wall, the second radial wall and the inclined wall forming an oil intake chamber, and a space delimited by the guide portion and the second radial wall forming an oil evacuation cavity.
-
公开(公告)号：US20240191793A1
公开(公告)日：2024-06-13
申请号：US18532743
申请日：2023-12-07
发明人： Juan-Luis MARCOS IZQUIERDO , Mohamed BOUYAKOUB , Jordane Emile André PELTIER , Anthony CUFFARO , Antoine Jacques Marie PENNACINO , Jérémy David SEBAN
CPC分类号： F16H57/0427 , F02C7/06 , F02C7/36 , F16H57/0423 , F05D2260/602 , F05D2260/609 , F05D2260/98
摘要： A gutter for recovering lubrication oil, particularly for a mechanical reducer of an aircraft turbomachine, annular around a central axis, and comprising a first radial wall extending radially with respect to the central axis, an inclined wall extending from a radially outer end of the first radial wall, a guide portion having an overall U shape extending from one end of the inclined wall, and a second radial wall extending radially outward with respect to the central axis from one end of the guide portion, a space delimited by the first radial wall, the second radial wall and the inclined wall forming an oil intake chamber, and a space delimited by the guide portion and the second radial wall forming an oil evacuation cavity.
-
公开(公告)号：US11994257B2
公开(公告)日：2024-05-28
申请号：US15931032
申请日：2020-05-13
发明人： Marion Daniel , Pierre Gauvin , Adam Logan
CPC分类号： F16N39/002 , B01D19/0052 , F01D25/18 , F05D2220/323 , F05D2260/609 , F05D2260/98 , F16N2210/02
摘要： A de-aerator for a lubrication system, has: a housing defining an air-oil inlet, an oil outlet, and an air outlet of the de-aerator; a rotor received within the housing and rotatable relative to the housing about a central axis, the rotor having blades distributed about the central axis and extending at least partially radially relative to the central axis, flow passages extending between the blades, the rotor having a hub circumferentially extending around the central axis and around the blades, the hub having a peripheral wall oriented radially inwardly and defining a fore opening leading to the flow passages; and a gap between the housing and the hub of the rotor, a portion of the housing received within the fore opening and axially overlapping the peripheral wall of the hub, the gap having a fore gap inlet between the portion of the housing and the peripheral wall of the hub.
-
公开(公告)号：US20240082755A1
公开(公告)日：2024-03-14
申请号：US17930772
申请日：2022-09-09
CPC分类号： B01D19/0052 , F02C7/06 , F05D2220/323 , F05D2260/609 , F05D2260/98
摘要： A deaeration rotor for an aircraft engine lubrication system comprising: an internal ring about an axis having a radially outer internal ring surface defining an inner boundary of an inner passage of the deaeration rotor; an external ring about the axis having a radially inner external ring surface defining an outer boundary of an outer passage of the deaeration rotor; a disc about the axis radially between the internal ring and the external ring, the disc having a radially inner disc surface defining an outer boundary of the inner passage and a radially outer disc surface defining an inner boundary of the outer passage; and blades circumferentially spaced from one another relative to the axis extending in the outer passage from at least one of the external ring and the disc, the blades located radially inward of an annular portion of the outer passage immediately downstream of the blades.
-
公开(公告)号：US11719243B2
公开(公告)日：2023-08-08
申请号：US17395850
申请日：2021-08-06
发明人： Simon Baker-Ostiguy
CPC分类号： F04D9/003 , F04D29/086 , F04D29/12 , F04D29/20 , F04D29/2288 , F04D31/00 , F05D2240/55 , F05D2240/61 , F05D2260/609 , F05D2300/171 , F05D2300/173 , F16J15/3212
摘要： An assembly is provided for a turbine engine. This turbine engine assembly includes an impeller rotor, a seal land and a lip seal. The impeller rotor is configured to rotate about a rotational axis. The impeller rotor is configured from or otherwise includes impeller rotor material. The seal land extends axially along and circumferentially about the rotational axis. The seal land is mechanically attached to and rotatable with the impeller rotor. The seal land is configured from or otherwise includes seal land material that is different than the impeller rotor material. The lip seal radially engages the seal land.
-
6.发明申请公开(公告)号：US20180313268A1
公开(公告)日：2018-11-01
申请号：US15769060
申请日：2016-10-25
CPC分类号： F02C7/06 , F02K1/04 , F05D2260/30 , F05D2260/605 , F05D2260/608 , F05D2260/609
摘要： The invention relates to an aircraft turbine engine module (10), comprising a degassing tube (14) and an ejection cone (12). The tube end the cone comprise centring means engaging together. The invention also relates to a locating and adjusting tool for assembling said module.
-
公开(公告)号：US20180087404A1
公开(公告)日：2018-03-29
申请号：US15274405
申请日：2016-09-23
发明人： Kerry J. Lighty
CPC分类号： F01D25/183 , F01D11/003 , F01D25/18 , F05D2220/30 , F05D2240/60 , F05D2260/232 , F05D2260/601 , F05D2260/602 , F05D2260/609
摘要： Systems and methods of providing oil for lubrication and/or cooling to an engine component in a turbine engine. A system for directing oil flow across a radially inward facing surface of the engine component comprises a nozzle axially forward of the component which is configured to eject a stream of oil, a deflecting body having a deflecting surface positioned to receive the stream of oil incident thereon and configured to deflect the stream of oil axially rearward, and an oil catcher comprising an annular catching flange positioned to receive the deflected stream of oil incident thereon and defining a plurality of grooves configured to channel the incident oil axially rearward to the component.
-
公开(公告)号：US20170363011A1
公开(公告)日：2017-12-21
申请号：US15183046
申请日：2016-06-15
CPC分类号： F02C7/28 , F01D5/025 , F01D25/12 , F01D25/183 , F01D25/32 , F02C3/06 , F02C7/24 , F05D2220/32 , F05D2230/22 , F05D2230/50 , F05D2240/35 , F05D2240/63 , F05D2250/25 , F05D2260/231 , F05D2260/602 , F05D2260/6022 , F05D2260/608 , F05D2260/609 , F05D2260/97 , F05D2300/175 , Y02T50/675
摘要： An apparatus and method of reducing a flow of fluid and heat between a first space and a second space in a rotatable machine and an integral seal and heat shield device are provided. The device includes an annular flange configured to couple to the rotating member of the rotatable machine and a multi-walled seal shield member extending axially from the flange. The multi-walled seal shield member is formed integrally with the flange. The seal shield member includes a first wall including a plurality of surface features, a second wall spaced radially inwardly with respect to the first wall, and a cavity formed between the first and second walls. The integral seal and heat shield device also includes a cap end integrally formed and configured to seal the first and second walls. Each of the flange, the seal shield member, and the cap end are formed of a sintered metal.
-
公开(公告)号：US09777576B2
公开(公告)日：2017-10-03
申请号：US14095462
申请日：2013-12-03
申请人： ROLLS-ROYCE PLC
发明人： Alan Robert Maguire
CPC分类号： F01D5/06 , F01D5/066 , F05D2260/60 , F05D2260/609 , Y02T50/671
摘要： A gas turbine engine comprising at least one drum pack having two or more annular discs 62a-c. Adjacent discs 62a-c are connected by drive arms 68 the drum pack is provided with a tubular sealing body 84 positioned radially inwards of the drive arms 68 and extending from a first disc 62a to a last disc 62c in the drum pack. The first 62a and last 62c discs have the greatest axial separation of all discs 62a-c in the drum pack. The sealing body 84 engaging the first 62a and last 62c discs and the engagement being arranged to limit or prevent the ingress of liquid into a drum cavity 76 defined between the first 62a and last 62c discs, the drive arms 68 and the sealing body 84.
-
公开(公告)号：US09745866B2
公开(公告)日：2017-08-29
申请号：US14448462
申请日：2014-07-31
发明人： Susumu Nakano , Koji Ishibashi , Kenjiro Narita , Takeshi Kudo
CPC分类号： F01D25/32 , F01D5/14 , F01D9/02 , F01D9/041 , F05D2220/31 , F05D2260/609
摘要： A steam turbine stationary blade is configured to be a stationary blade structure having a hollow structure. The steam turbine stationary blade is provided with a slit disposed on a stationary blade surface. The pressure of a stationary blade hollow is reduced to suction a liquid film through the slit for removing the liquid film formed on the stationary blade surface. An opening portion of the slit is covered with a sheet in a meshed pattern formed of a fine mesh thereby reducing an accompanied steam amount so as to effectively remove the liquid film.
-
-
-
-
-
-
-
-
-
搜索结果
108 条记录 (耗时 0.018 秒)
