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公开(公告)号：US20200017229A1
公开(公告)日：2020-01-16
申请号：US16035340
申请日：2018-07-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Alan Hisashi Steinert , Thomas Dewey Parsons , Troy Cyril Schank
Abstract: Systems and methods include providing an aircraft with a fuselage and a convertible engine disposed within the fuselage. The convertible engine is operable as a turbofan engine in a thrust mode and a turboshaft engine in a shaft power mode. The convertible engine includes a housing, an engine core having a low pressure turbine shaft, and a bypass fan system. The bypass fan system includes a bypass fan having a fan clutch. The fan clutch selectively couples at least a portion of the bypass fan to the low pressure turbine shaft when the convertible engine is operated in the thrust mode and decouples at least a portion of the bypass fan from the low pressure turbine shaft when the convertible engine is operated in the shaft power mode.
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公开(公告)号：US20190256205A1
公开(公告)日：2019-08-22
申请号：US15902402
申请日：2018-02-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Maresh , Troy Cyril Schank , Chyausong Tzeng , John Richard McCullough , Robert Wardlaw
Abstract: An inboard bearing attachment for carrying centrifugal force (“CF”) loads in a rotor blade assembly of a rotorcraft includes a CF fitting having a curved surface and a shear bearing retainer aligned with the curved surface. A mounting flange connected to either the CF fitting or the shear bearing retainer is used to mount the inboard bearing attachment to a yoke.
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公开(公告)号：US20190248481A1
公开(公告)日：2019-08-15
申请号：US15897310
申请日：2018-02-15
Applicant: Bell Helicopter Textron Inc.
Inventor： Charles Hubert Speller , Troy Cyril Schank
CPC classification number: B64C27/50 , B64C29/0033
Abstract: A mast lockout system for a tiltrotor aircraft having a proprotor assembly. The system includes a mast coupled to and rotatable with the proprotor assembly. A proprotor gearbox having a proprotor gearbox housing is operable to transmit torque and rotation energy to the mast. A lock assembly has first and second lock members. The first lock member is coupled to and rotatable with the mast. The second lock member is coupled to the proprotor gearbox housing. The lock assembly has a first position in which the first and second lock members are disengaged, thereby allowing rotation of the proprotor assembly. The lock assembly has a second position in which the first and second lock members are engaged, thereby preventing rotation of the proprotor assembly. The lock assembly is actuatable between the first and second positions.
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公开(公告)号：US20160152329A1
公开(公告)日：2016-06-02
申请号：US14957321
申请日：2015-12-02
Applicant: Bell Helicopter Textron Inc.
Inventor： Chyau-Song Tzeng , Troy Cyril Schank
CPC classification number: B64C29/0033 , B64C11/28 , B64C27/30
Abstract: A gimbal lock mechanism for a rotor hub can include a cam member having a cuff lock lobe and a gimbal lock lobe. The cam member is configured so that rotation can cause the first cuff lobe to become adjacent to the root end of the rotor blade and at the same time causes the gimbal lock lobe to become adjacent to a gimbal so as to inhibit gimbaling of the gimbal. A first moveable pin can be located on the root end portion of the rotor blade and inserted into the cuff lock lobe to prevent pitch change of the rotor blade.
Abstract translation: 用于转子轮毂的万向节锁定机构可以包括具有袖带锁定凸角和万向锁定凸角的凸轮构件。 凸轮构件被构造成使得旋转可以使第一袖带瓣变得与转子叶片的根部相邻，并且同时使得万向节锁定凸耳变得与万向架相邻以抑制万向节的万向节。 第一可移动销可以位于转子叶片的根部端部并插入到袖带锁定凸角中以防止转子叶片的变桨。
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公开(公告)号：US20190352002A1
公开(公告)日：2019-11-21
申请号：US15980452
申请日：2018-05-15
Applicant: Bell Helicopter Textron Inc.
Inventor： Kynn Jerald Schulte , Troy Cyril Schank
Abstract: In one embodiment, a local control system for a rotor assembly of an apparatus includes a first actuator disposed in the rotor assembly and configured to control motion of a first controllable element in the rotor assembly. The rotor assembly is mounted to the apparatus and is rotated responsive to torque and rotational energy provided thereto. The local control system also includes a first sensor disposed in the rotor assembly and configured to provide position feedback in relation to the first controllable element. The local control system also includes a first local control computer disposed in the rotor assembly and communicably coupled to a first central control computer disposed in the apparatus external to the rotor assembly, where the first local control computer is configured to transmit a control signal to the first actuator and receive a feedback signal from the first sensor.
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Patent Agency Ranking
公开(公告)号：US10336447B2
公开(公告)日：2019-07-02
申请号：US14957321
申请日：2015-12-02
Applicant: Bell Helicopter Textron Inc.
Inventor： Chyau-Song Tzeng , Troy Cyril Schank
Abstract: A gimbal lock mechanism for a rotor hub can include a cam member having a cuff lock lobe and a gimbal lock lobe. The cam member is configured so that rotation can cause the first cuff lobe to become adjacent to the root end of the rotor blade and at the same time causes the gimbal lock lobe to become adjacent to a gimbal so as to inhibit gimbaling of the gimbal. A first moveable pin can be located on the root end portion of the rotor blade and inserted into the cuff lock lobe to prevent pitch change of the rotor blade.
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公开(公告)号：US20170144746A1
公开(公告)日：2017-05-25
申请号：US15428687
申请日：2017-02-09
Applicant: Bell Helicopter Textron Inc.
Inventor： Troy Cyril Schank , Carlos Alexander Fenny , Andrew Maresh , Chyau-Song Tzeng
CPC classification number: B64C11/28 , B64C27/30 , B64C29/0033 , B64D27/20
Abstract: A mechanism for transitioning a tiltrotor aircraft between rotary and non rotary flight modes. The mechanism includes a gimbal lock positioned about a mast that is operable to selectively enable and disable a gimballing degree of freedom of a rotor assembly relative to the mast. A blade stop assembly, positioned about the mast, includes a plurality of arms having a radially contracted orientation and a radially extended orientation. A blade lock assembly is operably associated with each rotor blade assembly. Each blade lock assembly is operable to selectively enable and disable a folding degree of freedom and a pitching degree of freedom of the respective rotor blade assembly. A swash plate is operable to change the pitch of the rotor blade assemblies in the rotary flight mode and fold the rotor blade assemblies in the non rotary flight mode.
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公开(公告)号：US11235858B2
公开(公告)日：2022-02-01
申请号：US16035397
申请日：2018-07-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Troy Cyril Schank , Andrew Ryan Maresh , Chyau-Song Tzeng
Abstract: A mechanism for folding a rotor blade that is rotatably coupled to a blade cuff about a blade-fold axis between an extended position and a folded position. The mechanism includes a swash plate configured to translate relative to a mast, a pitch link rotatably coupled to the swash plate, a pitch horn rotatably coupled to the pitch link, a crank coupled to the pitch horn, and a link rotatably coupled to the crank and rotatably coupled to the rotor blade. The pitch horn and the crank being configured to commonly rotate relative to the blade cuff about a crank axis in response to translation of the swash plate, wherein the crank axis passes through the blade cuff.
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公开(公告)号：US20200172235A1
公开(公告)日：2020-06-04
申请号：US16208960
申请日：2018-12-04
Applicant: Bell Helicopter Textron Inc.
Inventor： Jeffrey Paul NISSEN , Troy Cyril Schank
Abstract: An exemplary high-speed hybrid propulsion system for a tiltrotor aircraft includes two pivotal nacelles, each nacelle comprising an electric motor coupled to a proprotor; an electric aircraft system; an electric generator; an electrical bus electrically connected to the electric generator, the electric motors, and the electric aircraft system; and a convertible turbofan engine coupled to an electric generator through a drive shaft.
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公开(公告)号：US20200003295A1
公开(公告)日：2020-01-02
申请号：US16025147
申请日：2018-07-02
Applicant: Bell Helicopter Textron Inc.
Inventor： Thomas Dewey Parsons , Troy Cyril Schank
IPC: F16H57/04
Abstract: A drive system for a tiltrotor aircraft operable to transition between rotary and non rotary flight modes. The drive system includes an engine to provide rotational energy and a proprotor assembly to receive rotational energy from the engine when the tiltrotor aircraft is in the rotary flight mode. The proprotor assembly is disengaged from the engine in the non rotary flight mode. The drive system includes a proprotor gearbox including one or more gears mechanically interposed between the engine and the proprotor assembly. The proprotor gearbox transfers rotational energy from the engine to the proprotor assembly when the tiltrotor aircraft is in the rotary flight mode. The drive system includes a lubricant operable to reduce friction between the gears and a lubrication management system to affect a temperature of the lubricant to enhance lubrication between the gears in the proprotor gearbox in the rotary flight mode.
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