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71. 发明授权

US5927655A Device for controlling the thrust of a multi-engine aircraft 失效
标题翻译：用于控制多发飞机的推力的装置
公开(公告)号：US5927655A
公开(公告)日：1999-07-27
申请号：US925605
申请日：1997-09-08
申请人： Panxika Larramendy , Patrick Zaccaria , Thierry Clavel , Fran.cedilla.ois Garavel
发明人： Panxika Larramendy , Patrick Zaccaria , Thierry Clavel , Fran.cedilla.ois Garavel
IPC分类号： B64D31/10 , F02C9/42 , G05D1/00
CPC分类号： B64D31/10 , F02C9/42 , G05D1/0072 , Y02T50/671
摘要： The present invention relates to a device for controlling the thrust of an aircraft, with several engines (M1, M4), comprising calculation units (UC1, UC4) that formulate first commands for controlling the engine speeds. According to the invention, said device (1) additionally comprises means (CONT1, CONT4) of controlling the two outer engines (M1, M4), calculation means that formulate second commands for controlling the speed of the outer engines (M1, M4) making it possible to obtain a reduction in thrust, and switching means which, during normal operation of the outer engines (M1, M4) send the first commands to these engines and, when one outer engine (M1) fails, send the second commands to the opposite outer engine (M4).
摘要翻译：本发明涉及一种用于控制飞机的推力的装置，其中包括计算单元（UC1，UC4）的几个发动机（M1，M4），其配置用于控制发动机速度的第一命令。根据本发明，所述装置（1）还包括控制两个外部发动机（M1，M4）的装置（CONT1，CONT4），制定用于控制外部发动机（M1，M4）的速度的第二命令的计算装置可以获得推力的减小，以及在外部发动机（M1，M4）的正常操作期间向这些发动机发送第一命令的切换装置，并且当一个外部发动机（M1）失效时，将第二个命令发送到对面的外引擎（M4）。

72. 发明授权

US5224340A Turbofan synchrophaser 失效
标题翻译： Turbofan同步激光器
公开(公告)号：US5224340A
公开(公告)日：1993-07-06
申请号：US691251
申请日：1991-04-25
申请人： Barton H. Snow
发明人： Barton H. Snow
IPC分类号： B64D31/12 , F02C9/42
CPC分类号： F02C9/42 , B64D31/12
摘要： An improved synchrophasing system for synchrophasing fan spools and engine core spools of one or more "slave" turbofan engines to a "master" engine is disclosed. A fuel control means is provided for modulating the flow of fuel to the slave engines to first synchrophase the operation of the engine fan spools. A variable stator vane control means is provided for then modulating the position of variable stator vanes within the slave engines to synchrophase the operation of the engine core spools.
摘要翻译：公开了一种用于将一个或多个“从”“涡扇发动机的”主“发动机的同步气扇卷轴和发动机芯轴的改进的同步相位系统。提供了一种燃料控制装置，用于调节到从动发动机的燃料流，以便首先使发动机风扇叶片的操作同步化。提供了一种可变的定子叶片控制装置，用于随后调节从动发动机内的可变定子叶片的位置以使发动机芯线轴的操作同步。

73. 发明授权

US4817046A Detection of engine failure in a multi-engine aircraft 失效
标题翻译：在多引擎飞机中检测发动机故障
公开(公告)号：US4817046A
公开(公告)日：1989-03-28
申请号：US849983
申请日：1986-04-10
申请人： Robert W. Rice , David H. Sweet , Charles W. Evans , Gregory P. Wright , James J. Howlett , Nicholas D. Lappos , Mark A. Johnston
发明人： Robert W. Rice , David H. Sweet , Charles W. Evans , Gregory P. Wright , James J. Howlett , Nicholas D. Lappos , Mark A. Johnston
IPC分类号： B64D45/00 , F02C9/28 , F02C9/42 , G05D1/00 , G08B21/00
CPC分类号： G05D1/0072 , F02C9/28 , F02C9/42 , F05D2270/09
摘要： Primary logic (116-128) for engine failure detection in a multi-engine aircraft is based on thresholds for engine torque (Q), gas generator speed (NG), power turbine inner stage temperature (T5), power turbine speed (NF), throttle setting (PLA), and throttle manipulation (PLADOT).Subroutines for return to dual engine operation (110), backup of the primary logic (200,300) and remaining engine failure (200) are disclosed.
摘要翻译：在多引擎飞机中用于发动机故障检测的主要逻辑（116-128）基于发动机扭矩（Q），气体发生器速度（NG），动力涡轮机内部温度（T5），动力涡轮机速度（NF），油门设定（PLA）和油门操纵（PLADOT）。公开了用于返回双发动机操作（110），主逻辑（200,300）的备份和剩余发动机故障（200）的子程序。

74. 发明授权

US4305129A System for providing load-frequency control through predictively and _dynamically dispatched gas turbine-generator units 失效
标题翻译：通过预测和动态调度的燃气轮机 - 发电机单元提供负载频率控制的系统
公开(公告)号：US4305129A
公开(公告)日：1981-12-08
申请号：US111417
申请日：1980-01-11
申请人： Robert A. Yannone , John F. Reuther
发明人： Robert A. Yannone , John F. Reuther
IPC分类号： F02C9/42 , H02J3/48 , F01D17/04
CPC分类号： H02J3/48 , F02C9/42
摘要： An optimized high load blocking limit is independently computer calculated for each gas turbine-generator unit as a dynamic function of combustor shell pressure and exhaust temperature every second. A low load blocking limit can be calculated as a function of the high blocking limit. The high and low dynamic limits then define a band of megawatts instantaneously available to the system. At the dispatch computer, load-frequency control is executed and the calculated load demands are dispatched to the various gas turbine-generator units which respond without exceeding the respective high and low load blocking limits. A turbine control unit load reference is modified by the dispatched load change and each unit load control operates its turbine fuel control valves to satisfy the load demand.
摘要翻译：每个燃气轮机 - 发电机单元独立地计算优化的高负荷阻力极限，作为燃烧器壳体压力和排气温度每秒的动态函数。可以计算低负载阻塞极限，作为高阻塞极限的函数。然后，高和低动态极限定义了瞬时可用于系统的兆瓦带。在调度计算机中，执行负载频率控制，并将计算出的负载需求调度到各种燃气轮机 - 发电机单元，在不超过相应的高和低负载阻断极限的情况下进行响应。涡轮机控制单元负载基准通过调度负载变化而改变，并且每个单元负载控制操作其涡轮燃料控制阀以满足负载需求。

75. 发明授权

US4259838A Throttle tracking in multiengine aircraft 失效
标题翻译：多引擎飞机中的油门跟踪
公开(公告)号：US4259838A
公开(公告)日：1981-04-07
申请号：US52167
申请日：1979-06-26
申请人： James H. McCollum, Jr. , Leo P. Kammerer
发明人： James H. McCollum, Jr. , Leo P. Kammerer
IPC分类号： F02C9/42 , F02K3/12
CPC分类号： F02C9/42
摘要： A throttle servo for each engine of a multiengine aircraft and servo tracking means for detecting and compensating for servo drift during autothrottle mode of operation.
摘要翻译：用于多引擎飞机的每个发动机的油门伺服器和用于在自动油门操作模式期间检测和补偿伺服漂移的伺服跟踪装置。

76. 发明授权

US3969890A Helicopter power plant control 失效
标题翻译：直升机电厂控制
公开(公告)号：US3969890A
公开(公告)日：1976-07-20
申请号：US489262
申请日：1974-07-17
申请人： Robert E. Nelson
发明人： Robert E. Nelson
IPC分类号： F02C9/42 , F02C7/02
CPC分类号： F02C9/42
摘要： A control system for a helicopter power plant with three power units driving the lifting rotor system through a main gearbox. Each power unit comprises a gas turbine engine of the gas-coupled type, a hydromechanical fuel control receiving electrical inputs to set a gas generator governor in the fuel control, an engine electronic control, and various engine accessories.
摘要翻译：具有三个动力单元的直升机动力装置的控制系统通过主变速箱驱动提升转子系统。每个动力单元包括气体耦合型的燃气轮机，接收电输入以在燃料控制中设置气体发生器调速器的液压机械燃料控制装置，发动机电子控制装置和各种发动机附件。

77. 发明授权

US3930366A Helicopter power plant control 失效
公开(公告)号：US3930366A
公开(公告)日：1976-01-06
申请号：US489263
申请日：1974-07-17
申请人： Robert E. Nelson
发明人： Robert E. Nelson
IPC分类号： F02C6/00 , B64D31/06 , F02C6/20 , F02C9/28 , F02C9/42 , F02C9/56 , F02C9/58 , F02C9/08
CPC分类号： F02C9/42
摘要： A control system for a helicopter power plant with three power units driving the lifting rotor system through a main gearbox. Each power unit comprises a gas turbine engine of the gas-coupled type, a hydromechanical fuel control receiving electrical inputs to set a gas generator governor in the fuel control, an engine electronic control, and various engine accessories.The operation of the power plant is normally controlled by the pilot through condition levers and switches on a control quadrant, through a pitch control by which the collective pitch of the rotor blades is controlled, and through a master beeper switch which is operable to trim the setting of an isochronous governor for the rotor system and the gas generator governors. The condition lever of each engine transmits a speed command signal through the electronic control of each power unit to its gas generator governor. A signal of collective pitch transmitted from the rotor control system to each engine electronic control is another factor in setting the governor.The power plant includes a power management control, the principal function of which is to equalize the power outputs of the engines. It also includes the rotor isochronous governor. The power management control receives inputs of rotor system speed command and actual rotor speed and of the torques of the individual engines and transmits a governor trim signal to increase or decrease engine power to the several electronic controls.All signals are transmitted electrically between the rotor system, control panel, power management control, and engine electronic controls. Excessive engine torque during rotor startup is avoided.

78. 发明授权

US3308618A Range blower pressure control 失效
标题翻译：范围鼓风机压力控制
公开(公告)号：US3308618A
公开(公告)日：1967-03-14
申请号：US41605864
申请日：1964-12-04
申请人： ROLLS ROYCE
发明人： ALBERT JUBB , ANTHONY HATCHETT KEITH
IPC分类号： F01K23/16 , F02C3/10 , F02C9/42 , F02C9/54
CPC分类号： F02C3/10 , F01K23/16 , F02C9/42 , F02C9/54

79. 发明授权

US3306048A Group thrust compensator 失效
公开(公告)号：US3306048A
公开(公告)日：1967-02-28
申请号：US36408764
申请日：1964-05-01
申请人： ELLIOTT BROTHERS LONDON LTD
发明人： MALCOLM ELLIS STAFFORD
IPC分类号： B64C29/00 , F02C9/42
CPC分类号： B64C29/0091 , F02C9/42

80. 发明授权

US2769306A Means for synchronizing the speeds of a pair of aircraft engines to which fuel is supplied by pumps and air by blowers 失效
标题翻译：用于使通过鼓风机由泵和空气供应燃料的一对飞机发动机的速度同步的装置
公开(公告)号：US2769306A
公开(公告)日：1956-11-06
申请号：US19596050
申请日：1950-11-16
申请人： LUCAS LTD JOSEPH
发明人： ALFRED HARRIS THOMAS
IPC分类号： B64D31/12 , F02C9/42 , H02P5/50
CPC分类号： F02C9/42 , B64D31/12 , H02P5/50

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