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公开(公告)号：US20210010584A1
公开(公告)日：2021-01-14
申请号：US17038724
申请日：2020-09-30
摘要： A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a turbo fan supported on a turbo fan shaft, a turbine section including a turbine shaft, and an epicyclic gear train interconnecting the turbo fan shaft and the turbine shaft. The epicyclic gear train includes a sun gear coupled to the turbine shaft, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier supporting the intermediary gears, and a ring gear including first and second portions each having an inner periphery with teeth, the first and second portions arranged about and intermeshing with the intermediate gears, the first and second portions abutting one another at a radial interface, the first and second portions including respective flanges extending along the radial interface radially outward from the teeth, and the teeth of the first and second portions being oppositely angled teeth.
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公开(公告)号：US11680492B2
公开(公告)日：2023-06-20
申请号：US17711177
申请日：2022-04-01
IPC分类号： F16H57/04 , F01D15/12 , F01D25/18 , F01D25/16 , F01D1/02 , F01D5/02 , F02C7/32 , F16H57/08 , F02C7/36 , F02K3/06
CPC分类号： F01D15/12 , F01D1/02 , F01D5/02 , F01D5/027 , F01D25/16 , F01D25/18 , F02C7/32 , F16H57/04 , F02C7/36 , F02K3/06 , F05D2220/32 , F05D2220/36 , F05D2240/70 , F05D2260/34 , F05D2260/40311 , F16H57/0423 , F16H57/0479 , F16H57/0486 , F16H2057/085
摘要： A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, a compressor section, and an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft. The gear train includes a sun gear coupled to the turbine shaft, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier supporting the intermediary gears, and a ring gear including first and second portions each having an inner periphery with teeth intermeshing with the intermediate gears. The first and second portions have axially opposed faces abutting one another at a radial interface. The first and second portions have grooves at the radial interface that form a hole that expels oil through the ring gear.
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公开(公告)号：US20210231025A1
公开(公告)日：2021-07-29
申请号：US17145766
申请日：2021-01-11
摘要： A turbine engine according to an example of the present disclosure includes, among other things, a fan shaft, at least one tapered bearing mounted on the fan shaft, the fan shaft including at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing, a fan mounted for rotation on the at least one tapered bearing. An epicyclic gear train is coupled to drive the fan, the epicyclic gear train including a carrier supporting intermediate gears that mesh with a sun gear, and a ring gear surrounding and meshing with the intermediate gears, wherein the epicyclic gear train defines a gear reduction ratio of greater than or equal to 2.3. A turbine section is coupled to drive the fan through the epicyclic gear train, the turbine section having a fan drive turbine that includes a pressure ratio that is greater than 5. The fan includes a pressure ratio that is less than 1.45, and the fan has a bypass ratio of greater than ten (10).
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