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公开(公告)号：US11767125B2
公开(公告)日：2023-09-26
申请号：US17017789
申请日：2020-09-11
发明人： Keith David Weaver , Michael Pujol , Andrew Jordan Birkenheuer , Nicholas Plagianos , Karl Burge , Thomas Mast
CPC分类号： B64D33/08 , B64C27/12 , F01P1/06 , F01P11/10 , F16H57/0416
摘要： A transition duct assembly includes a shared connector, and a plurality of primary cooling pathways for cooling one or more systems or components. Each primary cooling pathway includes a transition duct in fluid communication with the shared connector, and a transition connector in fluid communication with the transition duct.
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公开(公告)号：US11718392B2
公开(公告)日：2023-08-08
申请号：US17357361
申请日：2021-06-24
申请人： Bell Textron Inc.
发明人： Yann Lavallee , Scott D. Poster
CPC分类号： B64C27/56 , B64C13/044 , B64C27/12 , B64C27/82
摘要： Tail rotor control system is described for helicopters. A pedal position sensor operable by a pilot yields greater tail rotor RPM relative to the main rotor RPM, giving the pilot increased control over the vehicle. This proves especially useful in certain situations, such as high altitude, where increasing tail rotor speed from main rotor speed can give a pilot increased maneuverability and stability.
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公开(公告)号：US11680500B2
公开(公告)日：2023-06-20
申请号：US17164136
申请日：2021-02-01
申请人： Bell Textron Inc.
发明人： Scott David Poster
CPC分类号： F01M11/10 , B01D35/143 , B64C27/12 , F01M1/10 , F01M11/03 , F16H57/0404 , F16H57/0405 , F16N29/00
摘要： A removable oil filter system includes an oil filter mount, an oil filter element removably connected to the oil filter mount, an impending-bypass indicator connected to the oil filter mount and in fluid communication with an oil in the oil filter system, and a full-bypass indicator in fluid communication with the oil filter mount. The impending-bypass indicator is capable of reporting an impending-bypass condition of the oil filter system. The full-bypass indicator is capable of reporting a full-bypass condition of the oil filter system.
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公开(公告)号：US20230182896A1
公开(公告)日：2023-06-15
申请号：US17547578
申请日：2021-12-10
申请人： Bell Textron Inc.
发明人： Colton Gilliland , Russell Mueller
摘要： A bearing restraint, for use on a rotorcraft with a rotor mast and bearing assembly. The bearing restraint interfacing with a mast groove along the rotor mast to longitudinally restrain the bearing assembly. The bearing restraint includes a pilot ring, groove collar, and retaining ring.
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公开(公告)号：US20230175436A1
公开(公告)日：2023-06-08
申请号：US17540576
申请日：2021-12-02
摘要： There is described a method of operating a multi-engine system of an helicopter. The multi-engine system has a first turboshaft engine having a first shaft, a second turboshaft engine having a second shaft, a gearbox having a clutch system, and a range of rotation speeds defined as a placarded zone. The method generally has rotating the first shaft at a flight rotation speed when clutched and rotating the second shaft at a first idle rotation speed when unclutched, the first idle rotation speed above the placarded zone; decreasing a rotation speed of the first shaft from the flight rotation speed to a given rotation speed within the placarded zone; decreasing a rotation speed of the second shaft to the given rotation speed; clutching the second shaft; and decreasing the rotation speeds of the first and second shafts to a second idle rotation speed below the placarded zone.
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公开(公告)号：US20230002039A1
公开(公告)日：2023-01-05
申请号：US17367085
申请日：2021-07-02
申请人： Goodrich Corporation
发明人： Mark R. Gurvich , Michael King , Brayton Reed , Joyel M. Schaefer
摘要： An aircraft drive shaft including an outer shaft having a first diameter configured to couple a first gearbox and a second gearbox to provide power transfer between the two gearboxes, an inner shaft concentric with the outer shaft and having a second diameter configured to provide structural support to the outer shaft, a gap defined between an outer peripheral surface of the inner shaft and an inner peripheral surface of the outer shaft, wherein the gap is sized according to a ballistic projectile cross-section size that the aircraft is considered to encounter on an upcoming mission, and a sleeve located at least at first end of the outer shaft connecting the outer shaft to the inner shaft.
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公开(公告)号：US20220396353A1
公开(公告)日：2022-12-15
申请号：US17342963
申请日：2021-06-09
申请人： Bell Textron Inc.
摘要： A rotorcraft has a drive system including a main rotor coupled to a main rotor gearbox to rotate the main rotor at a rotor speed, a main engine coupled to the drive system to provide a first power, a supplemental engine coupled, when a first clutch is engaged, to the drive system to provide a second power additive to the first power, and a control system operable to control the main engine and the supplemental engine to provide a total power demand, where the main engine is controlled based on variations in rotor speed and a power compensation command to produce the first power, and the supplemental engine is controlled to produce the second power in response to a supplemental power demand.
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公开(公告)号：US20220388673A1
公开(公告)日：2022-12-08
申请号：US17769939
申请日：2020-10-15
摘要： A propulsion system (1) for a helicopter, comprising a turboshaft engine (2) with a linked turbine and an electric machine (3) capable of operating as an electric motor, the turboshaft engine (2) and the electric machine (3) being capable of driving in rotation at least one main rotor (5) intended to be coupled to a rotating wing (6) characterised in that it comprises means of coupling and decoupling (14) in rotation between a rotor (3a) of the electric machine (3) and a rotor (2a) of the turboshaft engine (2), the means of coupling and decoupling (14) being capable of allowing the rotor (2a) of the turboshaft engine (2) to be driven in rotation with the aid of the electric machine (3), in a first state of the propulsion system (1), and capable of allowing the rotor (2a) of the turboshaft engine (2) and the rotor (3a) of the electric machine (3) to be decoupled in rotation, in a second state of the propulsion system (1).
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公开(公告)号：US11498670B2
公开(公告)日：2022-11-15
申请号：US15580771
申请日：2016-08-02
摘要： A gearbox system includes a first drive gear rotatable about an axis of rotation and a second drive gear disposed coaxial with the first drive gear and rotatable about the axis of rotation. An input shaft provides a first torque and includes an input gear. Driving pinions are operably connected to the input gear and positioned between the first drive gear and the second drive gear compliantly along a direction parallel to the axis of rotation. Each driving pinion drives the first drive gear in a first direction about the axis of rotation and drives the second drive gear in a second direction opposite the first direction about the axis of rotation. Each driving pinion transfers an equal second torque to the first drive gear and the second drive gear.
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公开(公告)号：US20220315203A1
公开(公告)日：2022-10-06
申请号：US17597316
申请日：2020-07-02
发明人： Jacques ECHE , Yann TONDRIAUX
摘要： Aircraft comprising a primary propeller driven in rotation by a motor, the motor having a first assembly and a second assembly movable in rotation relative to each other along an axis of rotation, the primary propeller being secured in rotation to one of said first assembly and second assembly, the first assembly and the second assembly being movable in translation relative to each other along a direction of translation defined by the axis of rotation, between a rest position and a service position, characterized in that said aircraft comprises a locking system, comprising a housing and an indexing element, the housing being formed in one among the first assembly and the second assembly, the indexing element being secured to the other among the first assembly and the second assembly, the locking system having an engaged configuration in which the indexing element is at least partially inserted into the housing.
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