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公开(公告)号：US12092020B2
公开(公告)日：2024-09-17
申请号：US17594626
申请日：2020-04-02
发明人： Francois Gallet
CPC分类号： F02C3/067 , F02C7/06 , F04D19/024 , F05D2240/54 , F05D2240/60 , F05D2260/98
摘要： Counter-rotating turbine of a turbomachine extending about an axis of rotation and comprising an inner rotor rotating about the axis of rotation, and comprising at least one inner movable blade rotatably supported by a first shaft, an outer rotor rotating about the axis of rotation in a direction opposite to the inner rotor, and comprising at least one outer movable blade rotatably supported by a second shaft coaxial with the first shaft, the first and second shafts extending axially from upstream to downstream of the turbine, wherein the first shaft is guided in rotation by a first bearing disposed between the first shaft and an upstream casing of the turbine, and the second shaft is guided in rotation by a second bearing disposed between the second shaft and said upstream casing of the turbine.
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公开(公告)号：US20240254925A1
公开(公告)日：2024-08-01
申请号：US18604985
申请日：2024-03-14
发明人： Andrea Piazza , Jeffrey D. Clements
CPC分类号： F02C7/36 , F02C3/067 , F02K3/06 , F05D2200/13 , F05D2200/14 , F05D2200/221 , F05D2260/40311 , F05D2260/98
摘要： A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 2.0-4.0.
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公开(公告)号：US20240093638A1
公开(公告)日：2024-03-21
申请号：US17754858
申请日：2020-10-08
发明人： Simon Jean-Marie Bernard COUSSEAU , Mathieu Patrick Henri DELALANDRE , Patrick Jean Laurent SULTANA , Laurent Cédric ZAMAI
IPC分类号： F02C3/067
CPC分类号： F02C3/067 , F05D2240/24 , F05D2250/44
摘要： A counter-rotating turbine for a turbine engine comprising an inner rotor having an inner drum to which is attached a plurality of inner impellers rotatably supported by a first shaft, an outer rotor comprising an outer drum to which is fastened a plurality of outer impellers rotatably supported by a second shaft coaxial with the first shaft, the outer rotor comprising a downstream impeller having a plurality of downstream moving blades extending between an outer shroud and an inner shroud, one upstream end of the outer shroud being attached downstream of said outer drum, the inner shroud being attached to the second shaft, at least one of the inner shroud and of the outer shroud comprising at least one flexible transition part configured to allow elastic deformation of said shroud in the radial direction.
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公开(公告)号：US11814967B2
公开(公告)日：2023-11-14
申请号：US17617692
申请日：2020-06-11
CPC分类号： F01D11/24 , F01D25/12 , F01D25/14 , F02C3/067 , F02C7/18 , F05D2250/182 , F05D2250/44 , F05D2260/201
摘要： A turbine for a turbomachine has a first rotor and a second rotor configured to pivot about an axis in two opposite directions of rotation. The first rotor includes a radially outer drum from which blades extend radially inwards. The turbine has cooling means attached relative to the outer drum. The cooling means include a support plate with at least one first orifice and a calibration plate that is attached to the support plate and located radially inside the support plate. The calibration plate has at least one second calibration orifice facing the outer drum to allow the passage of cooling air radially from the outside to the inside through the first and second orifices.
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公开(公告)号：US20230340906A1
公开(公告)日：2023-10-26
申请号：US17713649
申请日：2022-04-05
发明人： Paul Hadley Vitt , Lyle Douglas Dailey , Matteo Renato Usseglio , Andreas Peters , Jonathan Ong
CPC分类号： F02C3/067 , F02C7/141 , F02C7/36 , F05D2220/60 , F05D2260/213 , F05D2260/40311
摘要： A turbine section and an exhaust section for a gas turbine engine includes a low pressure (LP) turbine having first stage LP turbine blades that rotate in a first direction at a first speed, and final stage LP turbine blades downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed. The second speed is lower than the first speed.
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公开(公告)号：US11788423B2
公开(公告)日：2023-10-17
申请号：US17781286
申请日：2020-12-03
CPC分类号： F01D5/3023 , F01D1/26 , F01D5/08 , F01D5/3053 , F02C3/067 , F05D2240/15
摘要： A turbine rotor wheel for an aircraft turbomachine includes a rotor disk, an annular shroud extending around the disk, and blades arranged between the disk and the shroud. The root of each of the blades has two tabs configured for attachment to the disk. The tabs are arranged upstream and downstream, respectively, of a wall of the disk, relative to the axis. The tab arranged upstream is engaged in a first recess of the disk and configured to cooperate by abutment with a peripheral edge of the first recess. The tab arranged downstream is engaged in a second recess of the disk and is configured to cooperate by abutment with a peripheral edge of the second recess.
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公开(公告)号：US11773785B2
公开(公告)日：2023-10-03
申请号：US18096071
申请日：2023-01-12
发明人： Keith Morgan , Robert Peluso , Ghislain Plante , Eugene Gekht , Eric Durocher , Jean Dubreuil
IPC分类号： F02C7/32 , F02C3/14 , F02C6/20 , F02C3/04 , F02C3/067 , F02C3/113 , F02C7/36 , F01D1/26 , F04D25/02
CPC分类号： F02C7/32 , F01D1/26 , F02C3/04 , F02C3/067 , F02C3/113 , F02C3/145 , F02C6/206 , F02C7/36 , F04D25/024 , F05D2220/32 , F05D2250/38 , F05D2260/40 , Y02T50/60
摘要： A gas turbine engine has a first spool having a low pressure compressor section disposed forward of an air inlet along a direction of travel of the engine, and a low pressure turbine section disposed forward of the low pressure compressor section and drivingly engaged thereto. A second spool has a high pressure compressor section disposed forward of the low pressure compressor section, and a high pressure turbine section disposed forward of the high pressure compressor section and drivingly engaged thereto. The high pressure turbine section is disposed aft of the low pressure turbine section. An output drive shaft drivingly engages the low pressure turbine section and extends forwardly therefrom to drive a rotatable load. A method of operating a gas turbine engine is also discussed.
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公开(公告)号：US20230243309A1
公开(公告)日：2023-08-03
申请号：US17929542
申请日：2022-09-02
发明人： Andrea Piazza , Jeffrey D. Clements
CPC分类号： F02C7/36 , F02K3/06 , F02C3/067 , F05D2200/14 , F05D2260/98 , F05D2200/221 , F05D2260/40311 , F05D2200/13
摘要： A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 3.2-4.0. The overall engine efficiency rating is within a range of 0.57-8.0.
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公开(公告)号：US11572827B1
公开(公告)日：2023-02-07
申请号：US17503184
申请日：2021-10-15
摘要： Apparatuses and systems are provided herein for unducted propulsion systems. The system includes an aft housing for low drag for high subsonic sustained flight. A plurality of blades are affixed to the aft housing, wherein the housing defines a flowpath curve extending from the axial extent of the aft blade root to the aft end of the aft housing. The flowpath curve is described by an axial direction parallel to an axis of rotation and a radius from the axis of rotation. The flowpath curve includes first point having a first radius where the radius reaches a maximum aft of the aft blade root and a second point forward of the first point having a second radius where the radius stops decreasing. The ratio of the first radius to the second radius is greater than or equal to 1.081.
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公开(公告)号：US20220243605A1
公开(公告)日：2022-08-04
申请号：US17617692
申请日：2020-06-11
摘要： A turbine for a turbomachine has a first rotor and a second rotor configured to pivot about an axis in two opposite directions of rotation. The first rotor includes a radially outer drum from which blades extend radially inwards. The turbine has cooling means attached relative to the outer drum. The cooling means include a support plate with at least one first orifice and a calibration plate that is attached to the support plate and located radially inside the support plate. The calibration plate has at least one second calibration orifice facing the outer drum to allow the passage of cooling air radially from the outside to the inside through the first and second orifices.
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