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公开(公告)号：US10480423B2
公开(公告)日：2019-11-19
申请号：US15666441
申请日：2017-08-01
IPC分类号： F02C9/58
摘要： A control system (10) of a turbopropeller (1) including: a centralized control (24) configured to slave the screw propeller power PRW of the turbopropeller (1) to the screw propeller power set point PRWref and the screw propeller rotation speed XNP of the turbopropeller (1) to the screw propeller rotation speed set point XNPref, the centralized control (24) supplying fuel flow rate WF and screw propeller pitch β controls for the turbopropeller (1); a screw propeller rotation speed error limiter (12) saturating the screw propeller rotation speed error ΔXNP with a limiting value Δ XNP sat ( min / max ) ; and a screw propeller power error limiter (11) saturating the screw propeller power error ΔPRW with a limiting value Δ PRW sat ( min / max ) .
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公开(公告)号：US10443412B2
公开(公告)日：2019-10-15
申请号：US14838405
申请日：2015-08-28
摘要： A variable pitch fan for gas turbine engine is provided. The variable pitch fan includes a plurality of fan blades rotatably coupled to a disk and an actuation assembly for changing a pitch of each of the plurality of fan blades. The actuation assembly generally includes an actuation member operably connected to at least one of the plurality of fan blades and a pin. The pin is movable between a first position in which the pin is positioned at least partially in a channel defined in the actuation member, and a second position. The pin blocks movement of the actuation member relative to the pin past a range defined by the channel when in the first position. The actuation assembly further includes a retraction system for selectively engaging the pin in moving the pin from the first position to the second position.
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公开(公告)号：US5299417A
公开(公告)日：1994-04-05
申请号：US762678
申请日：1991-09-18
CPC分类号： G05D1/0676 , F02C9/58 , G05D1/063
摘要： An aircraft is maintained at a constant glide slope and air speed by trimming delta torque commands provided by an autopilot. Delta torque commands that change by more than twenty percent are trimmed automatically to maintain the constant glide angle and to assist the pilot in maintaining air speed within .+-.5 knots on the approach glide slope.
摘要翻译： 通过修整由自动驾驶仪提供的三角扭矩指令，飞机保持恒定的滑翔坡和空气速度。 变化超过百分之二十的三角扭矩指令自动修整，以保持恒定的滑行角度，并协助飞行员保持进近滑坡的+ 5节内的空气速度。
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44.发明授权Apparatus for decoupling a torque loop from a speed loop in a power management system for turboprop engines 失效用于在涡轮螺旋桨发动机的功率管理系统中将扭矩回路与速度环解耦的装置
公开(公告)号：US5274558A
公开(公告)日：1993-12-28
申请号：US762324
申请日：1991-09-18
申请人： Glen T. High , Larry C. Prevallet , Joseph W. Free
发明人： Glen T. High , Larry C. Prevallet , Joseph W. Free
CPC分类号： G05D1/063 , F02C9/58 , F05D2200/13
摘要： A torque loop decoupler decouples a torque loop from a speed loop to allow only the speed loop to react to small, rapid changes in engine speed. The torque loop decoupler calculates a compensation signal and adds the compensation signal to a control signal of the torque control loop. The compensation signal keeps the control signal constant during small, rapid changes in engine speed. The compensation signal is calculated as the partial derivative of turbine torque with respect to changes in engine speed multiplied by a signal indicative of small, rapid changes in engine speed.
摘要翻译： 扭矩回路分离器将转矩回路与速度回路分离，只允许速度回路对发动机转速的小的快速变化做出反应。 扭矩环路去耦器计算补偿信号，并将补偿信号加到转矩控制回路的控制信号上。 补偿信号在发动机转速小而快速变化时保持控制信号恒定。 补偿信号被计算为相对于发动机速度变化乘以表示发动机转速的小的快速变化的信号的涡轮转矩的偏导数。
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公开(公告)号：US5029091A
公开(公告)日：1991-07-02
申请号：US336269
申请日：1989-04-11
CPC分类号： B64C11/30
摘要： A ground mode pitch position logic and control is shown and described in this invention. A method for scheduling and limiting the pitch actuator reference signal in accordance with the actuator commanded schedule, propeller overspeed and propeller underspeed.
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46.发明授权Apparatus and method for dynamic compensation of a propeller pitch speed control governor 失效螺旋桨俯仰速度调速器的动态补偿装置和方法
公开(公告)号：US5023793A
公开(公告)日：1991-06-11
申请号：US335901
申请日：1989-04-10
CPC分类号： F02C9/58 , B64C11/303 , G05D1/063
摘要： Governor stability of a propeller pitch controlled speed governor is improved by dynamically compensating a turbine engine speed error signal employed in determining fuel flow. The fuel flow requirement is a function of the dynamically compensated turbine engine speed error signal, an indicated air speed signal, and a power lever angle signal.
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47.发明授权
公开(公告)号：US5017089A
公开(公告)日：1991-05-21
申请号：US336273
申请日：1989-04-11
CPC分类号： B64C11/303 , G05B11/42
摘要： A propeller speed governor having a derivative feedback of propeller speed and having a means such as a switch to open the derivative feed back loop when airspeed exceeds a predetermined amount is shown and described. This derivative inhibit is used to provide improved dynamic compensation at high and low speeds.
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公开(公告)号：US4958289A
公开(公告)日：1990-09-18
申请号：US284261
申请日：1988-12-14
CPC分类号： F02C9/58 , B64C11/305
摘要： The invention concerns a control for an aircraft propeller. During operation in reverse pitch, as occurs upon thrust reversal during a landing maneuver, the speed of the propeller is controlled by adjusting pitch of the propeller, in order to prevent overspeeding. Further, during the transition period while the propeller is converting from forward pitch to reverse pitch, the propeller presents a light load to the engine. At this time, fuel flow to the engine is limited in order to restrict delivery of energy to the propeller, again, for the purpose of preventing overspeeding.
摘要翻译： 本发明涉及飞机螺旋桨的控制。 在反向间距操作期间，如在着陆操作中的推力反转时发生的那样，螺旋桨的速度通过调节螺旋桨的桨距来控制，以防止超速。 此外，在螺旋桨从前进桨距转换成反向桨距的过渡期间，螺旋桨对发动机施加轻负荷。 此时，限制向发动机的燃料流动，以限制向螺旋桨的能量输送，以防止超速。
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公开(公告)号：US4772179A
公开(公告)日：1988-09-20
申请号：US902285
申请日：1986-08-29
申请人： George W. Bennett , Neil Walker
发明人： George W. Bennett , Neil Walker
CPC分类号： F02C9/58 , B64C11/308 , F02K3/072 , B64D2027/005 , Y02T50/66
摘要： An integrated control system for coaxial counterrotating aircraft propulsors driven by a common gas turbine engine. The system establishes an engine pressure ratio by control of fuel flow and uses the established pressure ratio to set propulsor speed. Propulsor speed is set by adjustment of blade pitch.
摘要翻译： 由普通燃气涡轮发动机驱动的同轴逆转飞行器推进器的综合控制系统。 该系统通过控制燃料流量建立发动机压力比，并使用建立的压力比设置推进器速度。 推进速度是通过调整叶片间距来设定的。
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公开(公告)号：US4370560A
公开(公告)日：1983-01-25
申请号：US242058
申请日：1981-03-09
CPC分类号： F02C9/58 , F04D27/02 , F05D2220/50
摘要： An auxiliary power unit for an aircraft drives an electrical generator and an air compressor. The auxiliary power unit is primarily intended for operation with the aircraft on the ground when other aircraft power systems are shut down. The auxiliary power unit may, however, be used in an emergency to supplement the main aircraft generating system, with the aircraft airborne. When the auxiliary power unit generator is used in conjunction with the aircraft generating system, inlet air to the compressor is controlled to vary the compressor load on the power unit to minimize power unit speed changes and electrical frequency transients.
摘要翻译： 用于飞行器的辅助动力单元驱动发电机和空气压缩机。 辅助动力装置主要用于当其他飞机动力系统关闭时飞机在地面上进行操作。 然而，辅助动力装置可以在紧急情况下用于补充主飞行器发电系统，飞机机载。 当辅助动力装置发电机与飞机发电系统一起使用时，控制到压缩机的入口空气以改变功率单元上的压缩机负载，以最小化功率单元速度变化和电频率瞬变。
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