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公开(公告)号：US11821360B2
公开(公告)日：2023-11-21
申请号：US17256984
申请日：2019-07-03
CPC分类号： F02C6/14 , B64D27/14 , B64D27/24 , F01D1/24 , F02C7/36 , B64D2027/026 , F05D2220/323 , F05D2220/76 , F05D2260/40311 , F05D2260/42
摘要： The invention relates to an aircraft propulsion system (100) intended for being built into the rear of an aircraft fuselage, the propulsion system comprising at least two gas generators (102a, 102b) supplying a power turbine (104) having two counter-rotating turbine rotors (104a, 104b) for driving two fans (112a, 12b), and separate air inlets (106a, 106b) for supplying each gas generator, characterised in that it comprises an electrical drive device (140) configured to rotate at least one of the turbine rotors, at least one electrical generator (142a, 142b) configured to transform part of the energy of the flow from the gas generators into electrical power and an electric motor (146) supplied by said electrical generator and capable of rotating at least one of the turbine rotors, said electrical generator being installed on one of said gas generators, and in that said turbine rotor is capable of being rotated simultaneously by a flow from said gas generators and by the electrical drive device.
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公开(公告)号：US11352980B2
公开(公告)日：2022-06-07
申请号：US16596609
申请日：2019-10-08
摘要： Turbine engine (10) with a contra-rotating turbine for an aircraft, the turbine engine comprising a contra-rotating turbine (22) whose first rotor (22a) is configured to rotate in a first direction of rotation and is connected to a first turbine shaft (36), and a second rotor (22b) is configured to rotate in an opposite direction of rotation and is connected to a second turbine shaft (38), the first rotor comprising turbine wheels (36a) inserted between turbine wheels (38a) of the second rotor, the turbine engine further comprising a mechanical reduction gear (42) with an epicyclic gear train which comprises a sun gear (44) driven in rotation by said second shaft, a ring gear (40) driven in rotation by said first shaft, and a planet carrier (46) fixed to a stator casing (28) of the turbine engine situated downstream from the contra-rotating turbine with respect to direction of flow of the gases in the turbine engine, the turbine engine further comprising a bearing (56) for guiding the second shaft with respect to the first shaft, and a bearing for guiding the second shaft with respect to said stator casing, characterised in that said bearings are all situated downstream from the trailing edge of the last turbine wheel of the contra-rotating turbine and upstream from the reduction gear.
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公开(公告)号：US11098592B2
公开(公告)日：2021-08-24
申请号：US15710164
申请日：2017-09-20
发明人： Peeyush Pankaj , Shashank Suresh Puranik , Darek Tomasz Zatorski , Christopher Charles Glynn , Richard Schmidt , Bhaskar Nanda Mondal
摘要： A turbomachine includes a spool; and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along an axial direction and rotatable with one another. The turbomachine also includes a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member; a second support member, the second plurality of turbine rotor blades supported by the second support member; and a bearing assembly including a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and each being supported by the turbine center frame.
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公开(公告)号：US10961850B2
公开(公告)日：2021-03-30
申请号：US15708762
申请日：2017-09-19
发明人： Gert Johannes van der Merwe , Darek Tomasz Zatorski , Richard Alan Wesling , Jeffrey Donald Clements
摘要： A gas turbine engine including a torque frame is provided. The torque frame includes an inner shroud defined circumferentially around the axial centerline, an outer shroud surrounding the inner shroud and defined circumferentially around the axial centerline, and a structural member extended along the radial direction and coupled to the inner shroud and the outer shroud. The torque frame is configured to rotate around the axial centerline.
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公开(公告)号：US10661910B2
公开(公告)日：2020-05-26
申请号：US15745661
申请日：2016-07-21
发明人： François Gallet
IPC分类号： F02K3/072 , B64D29/04 , F01D21/06 , F01D17/16 , B64C11/32 , B64C11/00 , F01D1/24 , F01D1/02 , B64C11/38 , F01D17/14 , B64C11/30 , B64D27/14 , B64D27/20 , F02K3/12
摘要： An aircraft comprising a fuselage and propelled by a turbine engine having two coaxial and contrarotating fans, the turbine engine comprising a power turbine having two contrarotating rotors, one of which drives a fan upstream from the turbine, the other a fan downstream from the turbine, each fan comprising a ring of blades, and the assembly of the fans and the power turbine being incorporated at the rear of the fuselage, in the extension of same. The aircraft comprises, for at least one of the fans, a device for blocking the rotation of the fan and a device configured to modify the pitch of the blades of the fan in such a way as to make it operate as a flow straightener with respect to the other fan.
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公开(公告)号：US10655537B2
公开(公告)日：2020-05-19
申请号：US15412197
申请日：2017-01-23
IPC分类号： F01D1/24 , F02C3/04 , F02C7/36 , F02K3/06 , F02C3/067 , F02K3/072 , F01D5/03 , F01D5/06 , F01D5/14
摘要： The present disclosure is directed to a method of operating a gas turbine engine with an interdigitated turbine section. The engine includes a fan rotor, an intermediate pressure compressor, a high pressure compressor, a combustion section, and a turbine section in serial flow arrangement. The turbine section includes, in serial flow arrangement, a first stage of a low speed turbine rotor, a high speed turbine rotor, a second stage of the low speed turbine rotor, an intermediate speed turbine rotor, and one or more additional stages of the low speed turbine rotor. The low speed turbine rotor is coupled to the fan rotor via a low pressure shaft. The intermediate speed turbine rotor is coupled to the intermediate pressure compressor via an intermediate pressure shaft. The high speed turbine rotor is coupled to the high pressure compressor via a high pressure shaft. The method includes rotating the low speed turbine rotor in a first direction along the circumferential direction; rotating the high speed turbine rotor in a second direction opposite of the first direction along the circumferential direction; and rotating the intermediate speed turbine rotor in the second direction.
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公开(公告)号：US10519860B2
公开(公告)日：2019-12-31
申请号：US15451498
申请日：2017-03-07
发明人： Thomas Ory Moniz , Alan Roy Stuart , Jeffrey Donald Clements , Brandon Wayne Miller , Darek Tomasz Zatorski
IPC分类号： F01D25/16 , F02C7/06 , F02C3/067 , F01D5/06 , F01D1/24 , F01D11/00 , F02C7/28 , F02K3/072 , F01D25/18
摘要： The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction. The gas turbine engine defines an upstream end and a downstream end along the longitudinal direction and includes a turbine frame defined around the axial centerline. The turbine frame includes a first bearing surface, a second bearing surface, and a third bearing surface. The first bearing surface corresponds to a first turbine rotor, the second bearing surface corresponds to a second turbine rotor, and the third bearing surface corresponds to a third turbine rotor, and each turbine rotor is independently rotatable.
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公开(公告)号：US20190218913A1
公开(公告)日：2019-07-18
申请号：US15870313
申请日：2018-01-12
发明人： Arnab Sen , Jeffrey Douglas Rambo , Rajesh Kumar , Bhaskar Nanda Mondal , Alan Roy Stuart , Robert Proctor , Christopher Charles Glynn
摘要： An apparatus and method for cooling a portion of a turbine engine comprising an outer casing defining an axial centerline, a turbine section through which a flow of combustion gasses flows in a forward to aft direction, an outer drum located between the outer casing and the turbine section defining an annular cavity therebetween. A set of seals extends between the outer casing and outer drum to define at least one cooled cavity.
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公开(公告)号：US09273557B2
公开(公告)日：2016-03-01
申请号：US13983744
申请日：2012-02-02
申请人： Masahiro Mita
发明人： Masahiro Mita
摘要： Provided is a motor device capable of suppressing undesired vibrations occurring at the time of starting a motor, by canceling a torque in a motor device system so as to reduce a reaction torque acting on a motor base. The motor device is equipped with a dual axis motor having first and second rotating shafts and projecting at either end, a rotational direction converter having an input shaft to which the torque of the dual axis motor is inputted and an output shaft that outputs the torque by rotating in a direction opposite to that of the input shaft, and a flywheel provided at an end portion of the first rotating shaft, for balancing out the reaction torque acting on the input shaft and the output shaft of the rotational direction converter when the dual axis motor rotates.
摘要翻译： 提供一种电动机装置，其能够通过消除电动机装置系统中的转矩来抑制起动电动机时发生的不期望的振动，从而减小作用在电动机基座上的反作用转矩。 电动机装置配备有具有第一和第二旋转轴并在任一端突出的双轴电动机，具有输入轴的旋转方向转换器，输入轴输入双轴电动机的转矩，输出轴通过输出轴输出扭矩 在与所述输入轴的方向相反的方向上旋转;以及飞轮，设置在所述第一旋转轴的端部，用于平衡作用在所述输入轴和所述旋转方向转换器的输出轴上的反作用转矩， 电机旋转。
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10.发明授权Fan blade system with multiple spaced layers of blades and centrifugal fan using same 有权风扇叶片系统具有多个间隔层的叶片和离心式风机公开(公告)号：US09206808B2
公开(公告)日：2015-12-08
申请号：US13647634
申请日：2012-10-09
发明人： Meihua Yuan
CPC分类号： F04D25/064 , F04D25/166
摘要： A fan blade system with multiple spaced layers of blades and a centrifugal fan using same are disclosed. The centrifugal fan includes a housing, in which the fan blade system is mounted. The fan blade system includes a hub, and a first and a second blade group outward extended from a circumferential wall of the hub to axially space from each other. The housing includes a main housing portion and a secondary housing portion integrally formed on one side of the main housing portion. When the fan blade system is mounted in the housing, the two blade groups are separately located in the main housing portion and the secondary housing portion to produce higher airflow pressure and more air volume. With these arrangements, the centrifugal fan can have upgraded performance and be manufactured with reduced labor, time and material costs.
摘要翻译： 公开了一种具有多个间隔开的叶片的风扇叶片系统和使用它们的离心式风扇。 离心风扇包括壳体，风扇叶片系统安装在壳体中。 风扇叶片系统包括轮毂，以及第一和第二叶片组，其从轮毂的圆周壁向外延伸到彼此的轴向空间。 壳体包括主壳体部分和一体地形成在主壳体部分的一侧上的副壳体部分。 当风扇叶片系统安装在壳体中时，两个叶片组分别位于主壳体部分和副壳体部分中，以产生更高的气流压力和更多的空气体积。 通过这些布置，离心风机可以具有升级性能，并且可以减少人力，时间和材料成本。
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