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公开(公告)号:US09790804B2
公开(公告)日:2017-10-17
申请号:US15313036
申请日:2015-05-22
CPC分类号: F01D15/12 , F01D15/08 , F01D15/10 , F01D25/16 , F01D25/18 , F02C7/06 , F02C7/32 , F05D2220/323 , F05D2240/63 , F05D2260/4031 , F05D2260/98 , F16H57/0431 , F16H57/0495
摘要: A gearbox for an aircraft turbine engine has a casing defining an enclosure for housing rotating elements lubricated by oil. At least one tubular sleeve is coupled to the rotating elements and configured to rotate a shaft. The sleeve includes splines configured to cooperate with complementary splines of said shaft. The gearbox further includes means for recovering lubricating oil from the rotating elements and conveying the recovered oil by streaming to the splines to lubricate the splines.
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公开(公告)号:US09982556B2
公开(公告)日:2018-05-29
申请号:US15317335
申请日:2015-06-11
IPC分类号: F01D15/10 , F01D15/12 , F01D15/08 , F01D25/24 , F01D25/04 , F01D25/16 , F01D25/20 , F02C7/32
CPC分类号: F01D15/12 , F01D15/08 , F01D15/10 , F01D25/04 , F01D25/16 , F01D25/20 , F01D25/24 , F02C7/32 , F02C7/36 , F05D2220/30 , F05D2220/50 , F05D2240/60 , F05D2260/96
摘要: The present invention relates to a turbine engine (10) comprising: at least one hollow guidance arm (44) radially extending from a hub (38) to an annular housing (42), and having one radially external end which opens out in an opening (60) of said annular housing, a radial countershaft (48) located in said guidance arm (44) for rotatably driving at least one device arranged at the periphery of said annular housing (42). According to the invention, a transfer case (50) is disposed facing the opening (60) of the annular housing, and the turbine engine comprises rotational power transfer means (78, 52) between the radial countershaft (48) and the device, with the guidance arm (44) being equipped, at the external end thereof, with a widened section (56) by which it opens out in the opening (60) of the annular housing and in which part of the transfer case (50) is accommodated.
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公开(公告)号:US20170122122A1
公开(公告)日:2017-05-04
申请号:US15317335
申请日:2015-06-11
CPC分类号: F01D15/12 , F01D15/08 , F01D15/10 , F01D25/04 , F01D25/16 , F01D25/20 , F01D25/24 , F02C7/32 , F02C7/36 , F05D2220/30 , F05D2220/50 , F05D2240/60 , F05D2260/96
摘要: The present invention relates to a turbine engine (10) comprising: at least one hollow guidance arm (44) radially extending from a hub (38) to an annular housing (42), and having one radially external end which opens out in an opening (60) of said annular housing, a radial countershaft (48) located in said guidance arm (44) for rotatably driving at least one device arranged at the periphery of said annular housing (42). According to the invention, a transfer case (50) is disposed facing the opening (60) of the annular housing, and the turbine engine comprises rotational power transfer means (78, 52) between the radial countershaft (48) and the device, with the guidance arm (44) being equipped, at the external end thereof, with a widened section (56) by which it opens out in the opening (60) of the annular housing and in which part of the transfer case (50) is accommodated.
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公开(公告)号:US11384695B2
公开(公告)日:2022-07-12
申请号:US16972797
申请日:2019-06-12
摘要: An assembly includes: a fan drive reducing gear of an aircraft turbine engine, and a lubrication system including: a housing enclosing the reducing gear; a device for spraying lubricant onto the reducing gear; a lubricant supply pipe intended to convey the lubricant towards the spraying device; a lubricant recovery pipe communicating with a bottom of the housing; a controlled valve equipping the recovery pipe; and a lubricant overflow discharge pipe connected to an overflow outlet of the bottom of the housing situated above a horizontal level of a bottom point of a gearing of the reducing gear, and to the recovery pipe, downstream from the valve.
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公开(公告)号:US20170138214A1
公开(公告)日:2017-05-18
申请号:US15313036
申请日:2015-05-22
CPC分类号: F01D15/12 , F01D15/08 , F01D15/10 , F01D25/16 , F01D25/18 , F02C7/06 , F02C7/32 , F05D2220/323 , F05D2240/63 , F05D2260/4031 , F05D2260/98 , F16H57/0431 , F16H57/0495
摘要: A gearbox for an aircraft turbine engine has a casing defining an enclosure for housing rotating elements lubricated by oil. At least one tubular sleeve is coupled to the rotating elements and configured to rotate a shaft. The sleeve includes splines configured to cooperate with complementary splines of said shaft. The gearbox further includes means for recovering lubricating oil from the rotating elements and conveying the recovered oil by streaming to the splines to lubricate the splines.
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