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公开(公告)号：US20230279805A1
公开(公告)日：2023-09-07
申请号：US18314187
申请日：2023-05-09
发明人： Nicholas M. Daggett , Gert Johannes van der Merwe , Daniel Alan Niergarth , Brian Lewis Devendorf
CPC分类号： F02C3/06 , F02C9/58 , F02K3/06 , F05D2220/36 , F05D2220/32
摘要： A fan assembly for a gas turbine engine includes a fan disk, a trunnion, an actuation device, a fan blade, and a counterweight assembly. The trunnion is mounted to the fan disk. The actuation device is operably coupled to the trunnion. The fan blade is rotatably attached to the fan disk. The counterweight assembly includes a link arm, a lever arm, a hinge, and a counterweight. The link arm is connected to the trunnion, to the actuation device, or to both. The link arm is configured to drive rotation of the trunnion relative to the fan disk. The hinge is pivotably connected to the lever arm. The lever arm is connected to the link arm and is disposed to rotate about a connection point of the lever arm and the hinge. The counterweight is mounted to the lever arm at a location spaced from the hinge.
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公开(公告)号：US11655778B2
公开(公告)日：2023-05-23
申请号：US17396050
申请日：2021-08-06
发明人： Michael M. Joly , Zaffir A. Chaudhry , Andrzej Ernest Kuczek , Om P. Sharma , Georgi Kalitzin , Simon W. Evans
CPC分类号： F02K3/06 , F01D5/28 , F02C9/20 , F02C9/22 , F02C9/54 , F02C9/58 , F05D2220/36 , F05D2240/128
摘要： A gas turbine engine includes a fan section, a compressor section, and a turbine section. The fan section has a plurality of vane assemblies spaced circumferentially about an engine axis. The vane assemblies each include an airfoil extending between a leading edge and a trailing edge, a control rod extending through the airfoil, and a mechanism driven by the control rod to change the shape of the airfoil. A vane system for a gas turbine engine is also disclosed.
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公开(公告)号：US11549448B2
公开(公告)日：2023-01-10
申请号：US16484037
申请日：2018-02-07
发明人： Cedrik Djelassi
摘要： The invention relates to a method for controlling the speed and the power of a turbine engine propeller, wherein at least two operating modes are implemented: —one operating mode, called “speed mode”, in which the pitch (β) of the propeller is controlled as a function of the desired propeller speed, while the fuel flow is controlled as a function of the desired torque; the other operating mode, called “β mode”, in which the fuel flow is controlled as a function of the desired propeller speed, the pitch (β) of the propeller being set to a limit angle (βmin) that limits the pitch of the propeller in the two operating modes, the pitch angle (βmin(t)) being continuously computed and updated during a flight on the basis of parameters relating to the flight conditions estimated in real time.
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公开(公告)号：US10823113B2
公开(公告)日：2020-11-03
申请号：US15681531
申请日：2017-08-21
摘要： Systems and methods for limiting power of a gas turbine engine for an aircraft are described herein. A blade angle of a propeller blade of the engine and a commanded power for the engine are obtained. A thrust transition direction is determined. The commanded power is compared to a selected threshold based on the blade angle and the thrust transition direction. Power to the engine is limited when the commanded power exceeds the selected threshold.
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公开(公告)号：US20200232395A1
公开(公告)日：2020-07-23
申请号：US16250256
申请日：2019-01-17
摘要： Methods and systems for operating a gas turbine engine coupled to an aircraft propeller are described herein. A request for reverse of the propeller thrust is received from a power lever of the aircraft. A blade angle of the propeller is determined. Reverse thrust of the propeller is inhibited when the blade angle exceeds a threshold. Reverse thrust of the propeller based on the request is enabled when the blade angle is below the threshold.
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公开(公告)号：US20200164996A1
公开(公告)日：2020-05-28
申请号：US16775489
申请日：2020-01-29
发明人： Carmine LISIO , Kenneth Matheson
摘要： There are described methods and systems for controlling an aircraft. The system comprises a power plant controller configured for controlling operation of an engine and a propeller coupled to the engine, a power throttle having at least one throttle lever to regulate output power of the engine and thrust produced by the propeller, and an autothrottle controller operatively connected to the power plant controller and to the power throttle and configured to modulate engine power without pilot input by causing a change to at least one setting of the power throttle.
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7.发明申请公开(公告)号：US20170107914A1
公开(公告)日：2017-04-20
申请号：US14886169
申请日：2015-10-19
发明人： Manxue Lu , Jeffrey Anthony Hamel
CPC分类号： F02C9/58 , B64D27/10 , F02C9/44 , F02C9/54 , F02K1/66 , F02K3/04 , F02K3/06 , F05D2220/323 , F05D2220/325 , F05D2270/051 , F05D2270/3011 , F05D2270/303 , F05D2270/304
摘要： A thrust scheduling method for a gas turbine engine that includes a plurality of blades having a variable pitch beta angle is provided. The method can include receiving into a control system at least one condition input from a respective sensor; receiving into a control system a low pressure shaft speed from a low pressure shaft speed sensor; receiving a control command from a full authority digital engine control (FADEC) in the control system; generating a low pressure shaft speed base reference from a first schedule logic in the control system based upon the at least one condition input received and the control command received; generating a beta angle base reference from a second schedule logic from the at least one condition input received, the low pressure shaft speed, and the control command received; and supplying the low pressure shaft speed base reference and the beta angle base reference to an engine control system, wherein the engine control system adjusts at least the pitch angle of the plurality of fan blades or a fuel flow to the engine.
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公开(公告)号：US09376202B2
公开(公告)日：2016-06-28
申请号：US13588180
申请日：2012-08-17
CPC分类号： B64C11/306 , B64C11/308 , B64D27/16 , B64D2027/005 , F01D1/26 , F02C9/58 , F02K3/025 , F02K3/072 , F05D2220/323 , F05D2240/30 , F05D2260/40311 , Y02T50/66
摘要： A pitch control mechanism for an open rotor gas turbine engine is provided, the engine having a first rotor assembly and a second rotor assembly, with a plurality of airfoil blades circumferentially mounted on each rotor assembly, and arranged in contra-rotational relationship to each other. The pitch control mechanism includes an actuator assembly configured to be secured to a non-rotating frame of the engine, the actuator assembly having a first actuator and a second actuator, with the actuator assembly being rotationally isolatable from and couplable to the first and second rotor assemblies such that, in use, an actuation signal from the first or second actuator induces a corresponding desired change in pitch of the airfoil blades of the respective first or second rotor assembly independently of the pitch of the airfoil blades of the second or first rotor assembly.
摘要翻译： 提供了一种用于开式转子燃气涡轮发动机的变桨控制机构，该发动机具有第一转子组件和第二转子组件，多个翼型叶片周向地安装在每个转子组件上，并且以彼此相互旋转的关系布置 。 桨距控制机构包括构造成固定到发动机的非旋转框架的致动器组件，致动器组件具有第一致动器和第二致动器，致动器组件可旋转地隔离并可联接到第一和第二转子 组件，使得在使用中来自第一或第二致动器的致动信号独立于第二或第一转子组件的翼型叶片的桨距而引起相应的第一或第二转子组件的翼型叶片的螺距的相应的期望变化 。
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公开(公告)号：US09169783B2
公开(公告)日：2015-10-27
申请号：US13483714
申请日：2012-05-30
申请人： Joel W. Kleckler
发明人： Joel W. Kleckler
CPC分类号： F02C9/58 , B64C11/303 , B64C11/385 , B64C11/40 , F05D2260/77 , Y02T50/671
摘要： A propeller governor for controlling blade pitch of a variable pitch propeller has a hydraulic control circuit coupled to the propeller to change blade pitch in response to hydraulic pressure. The hydraulic control circuit has a first pressure path configured to adjust blade pitch within a first range of blade pitch, and a second, different pressure path configured to adjust blade pitch within a second range of blade pitch. An electrohydraulic servo valve of the governor is configured to adjust hydraulic pressure in the first pressure path to adjust blade pitch within the first range and to adjust hydraulic pressure in the second pressure path to adjust blade pitch within the second range.
摘要翻译： 用于控制可变螺距螺旋桨的叶片桨距的螺旋桨调速器具有联接到螺旋桨的液压控制回路，以响应于液压来改变叶片间距。 液压控制回路具有第一压力路径，其构造成在叶片间距的第一范围内调节叶片间距，以及第二不同压力路径，其构造成在叶片间距的第二范围内调节叶片间距。 调速器的电动液压伺服阀构造成调节第一压力路径中的液压压力，以将叶片间距调整到第一范围内，并且调节第二压力路径中的液压压力，以将叶片间距调整到第二范围内。
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公开(公告)号：US5078345A
公开(公告)日：1992-01-07
申请号：US610518
申请日：1990-11-08
申请人： Luitzen De Vries , Jan Meuzelaar
发明人： Luitzen De Vries , Jan Meuzelaar
CPC分类号： F02C9/58 , F02C9/28 , G05D1/063 , G05D1/0661 , G05D1/0676 , F05D2270/02 , F05D2270/052 , F05D2270/122
摘要： A flight control system of a turboprop airplane includes electronic controlled engines, which are governed by a manual operating device for setting the engine power in order to obtain a certain airspeed, a device for selecting a desired airspeed, and an engine control system for computing and controlling the required engine torque and speed as a function of ambient and engine conditions, the selected engine speed and the setting of said operating device. For automatically controlling the engine speed during the final approach to an airfield, the system includes an electronic approach speed control unit of which the adjustment signal influences the engine control device keeping the speed of the airplane during approach at a selected value whereby said manual operating device has a fixed setpoint. This electronic speed control unit may be carried out as an add-on device for retrofitting on a flight control system.
摘要翻译： 涡轮螺旋桨飞机的飞行控制系统包括电子控制发动机，其由手动操作装置控制，用于设定发动机功率以获得一定的空速，用于选择所需空速的装置，以及用于计算和 根据环境和发动机条件，所选择的发动机速度和所述操作装置的设置来控制所需的发动机扭矩和速度。 为了在最后接近机场期间自动控制发动机转速，该系统包括电子接近速度控制单元，其中调节信号影响发动机控制装置，以在接近期间将飞机的速度保持在选定值，由此所述手动操作装置 具有固定设定值。 该电子速度控制单元可以作为用于在飞行控制系统上进行改装的附加装置来执行。
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