公开(公告)号：US09157372B2

公开(公告)日：2015-10-13

申请号：US13794200

申请日：2013-03-11

申请人： Bell Helicopter Textron Inc.

发明人： Chandler Sowden

IPC分类号： H02J7/00 ,  H02J7/14 ,  F02C7/266 ,  H02J1/00 ,  F02N11/08 ,  F02C7/26 ,  F02C7/262 ,  H02P9/08 ,  F02C7/275

CPC分类号： F02C7/266 ,  F02C7/26 ,  F02C7/262 ,  F02C7/275 ,  F02N11/0866 ,  F02N11/087 ,  F02N2011/0877 ,  F05D2220/329 ,  F05D2270/52 ,  H02J1/00 ,  H02P9/08 ,  Y10T307/653

摘要： A series battery start controller for starting an aircraft turbine engine and method thereof is provided, wherein the battery series start controller connects two batteries in series when an aircraft engine starter is engaged to provide a higher voltage to start the aircraft engine and to provide adequate operational voltage to aircraft engine instruments and other aircraft electrical systems, and wherein the battery series start controller reconnects the batteries in parallel when the electrical load drawn by the starting aircraft engine decreases and the supplied voltage to the aircraft rises to a predetermined threshold.

摘要翻译： 提供一种用于启动飞行器涡轮发动机的串联电池启动控制器及其方法，其中当飞行器发动机起动器被接合以提供更高的电压以启动飞机发动机并且提供足够的操作时，电池组起动控制器串联连接两个电池 飞机发动机仪表和其他飞行器电气系统的电压，并且其中当由起动飞机发动机牵引的电负载减小并且飞机提供的电压升高到预定阈值时，电池组起动控制器并联重新连接电池。

公开(公告)号：US09057342B2

公开(公告)日：2015-06-16

申请号：US13264893

申请日：2010-04-06

申请人： Hakim Maalioune ,  Vincent Le-Coq ,  Pierre Moradell-Casellas ,  Djemouai Hadjidj ,  Guillermo Garcia Soto

发明人： Hakim Maalioune ,  Vincent Le-Coq ,  Pierre Moradell-Casellas ,  Djemouai Hadjidj ,  Guillermo Garcia Soto

IPC分类号： F02K1/70 ,  B64D33/04 ,  F02K1/12 ,  F02K1/76

CPC分类号： F02K1/70 ,  B64D33/04 ,  F02K1/12 ,  F02K1/76 ,  F02K1/763 ,  F05D2270/52 ,  F05D2270/54 ,  F05D2270/62

摘要： The invention relates to a system for controlling a plurality of actuators (15) that can displace a mobile panel (13, 17) pertaining to a nacelle (1) of an aircraft, said system comprising at least two motors (16) that can drive the actuators (15). The system also comprises two separate control units (33, 35), each unit being configured in such a way as to control and feed at least one motor that is not fed or controlled by the other control unit. The invention also relates to a nacelle comprising such a system.

摘要翻译： 本发明涉及一种用于控制多个致动器（15）的系统，所述致动器能够移动与飞行器的机舱（1）相关的移动面板（13,17），所述系统包括至少两个可驱动的马达（16） 致动器（15）。 该系统还包括两个单独的控制单元（33,35），每个单元被配置为控制和馈送至少一个不由另一控制单元馈送或控制的电动机。 本发明还涉及包括这种系统的机舱。

公开(公告)号：US09051898B2

公开(公告)日：2015-06-09

申请号：US13264951

申请日：2010-03-18

申请人： Hakim Maalioune

发明人： Hakim Maalioune

IPC分类号： F02K1/70 ,  F02K1/76 ,  H02K11/00 ,  H02K16/04

CPC分类号： F02K1/70 ,  F02K1/76 ,  F02K1/763 ,  F05D2270/52 ,  F05D2270/54 ,  F05D2270/62 ,  H02K11/33 ,  H02K16/04

摘要： The invention relates to a thrust reversal device comprising at least one cowl arranged in such a way that it can be moved between a closed position and an open position, said cowl being actuated by at least one actuator that can be driven by at least one electric engine. The invention is characterized in that at least one electric engine is connected to at least two separate power supplies (7a, 7b).

摘要翻译： 本发明涉及一种推力反向装置，其包括至少一个整流罩，其布置成使得其能够在关闭位置和打开位置之间移动，所述整流罩由至少一个致动器致动，所述致动器可由至少一个电动 发动机。 本发明的特征在于，至少一个电动发动机连接到至少两个单独的电源（7a，7b）。

公开(公告)号：US20090140679A1

公开(公告)日：2009-06-04

申请号：US12115375

申请日：2008-05-05

申请人： Terry L. Ahrendt

发明人： Terry L. Ahrendt

IPC分类号： H02P7/292

CPC分类号： F02K1/72 ,  F02K1/763 ,  F02K1/766 ,  F05D2270/09 ,  F05D2270/52 ,  F05D2270/62

摘要： A system for moving an aircraft thrust reverser component includes a power drive unit, a thrust reverser actuator assembly, and a tertiary lock system. The power drive unit is operable to rotate and supply a rotational drive force. The thrust reverser actuator assembly receives the rotational drive force from the power drive unit and moves the thrust reverser component between a stowed position and a deployed position. The tertiary lock system selectively engages and disengages the thrust reverser component and includes a tertiary lock power unit, an electromechanical tertiary lock assembly, and a voltage limiting circuit. The voltage limiting circuit limits the voltage magnitude of a control signal supplied to the tertiary lock assembly to a predetermined value.

摘要翻译： 用于移动飞机推力反向器部件的系统包括动力驱动单元，推力反向器致动器组件和三级锁定系统。 动力驱动单元可操作以旋转和提供旋转驱动力。 推力反向器致动器组件接收来自动力驱动单元的旋转驱动力，并且使推力反向器部件在收起位置和展开位置之间移动。 三级锁定系统选择性地接合和分离推力反向器部件，并且包括三级锁定动力单元，机电三级锁定组件和电压限制电路。 电压限制电路将提供给第三锁组件的控制信号的电压幅值限制到预定值。

公开(公告)号：US20070200352A1

公开(公告)日：2007-08-30

申请号：US11706967

申请日：2007-02-16

申请人： Gustavo Arguello

发明人： Gustavo Arguello

IPC分类号： F01D15/10 ,  H02P9/04 ,  H02K7/18

CPC分类号： F02C7/266 ,  F05D2270/09 ,  F05D2270/094 ,  F05D2270/52 ,  F05D2270/66 ,  Y10T307/344 ,  Y10T307/615

摘要： In the case of an ignition system for a gas turbine engine, the power (P1, P2) intended for the two ignition units (1, 2) is supplied via a power supply bus (10, 14) each comprising a standard bus (11, 11′; 15, 15′) and an emergency bus (12, 12′; 16, 16′), and a relay (13, 17) connected to the respective power supply line to the corresponding ignition unit. In the event of failure of power supply in a supply line for power P1 or P2, the corresponding relay will automatically (mechanically) switch over to the respective other power supply line, thus ensuring that the function of the ignition unit is maintained, even if—for whatever reasons—power supply to one or the other ignition unit is interrupted.

摘要翻译： 在用于燃气涡轮发动机的点火系统的情况下，用于两个点火单元（1,2）的电力（P1，P2）经由电源总线（10,14）供应，每个电源总线包括标准总线（11 ，11'; 15,15'）和紧急总线（12,12'; 16,16'）和连接到相应的电源线到对应的点火单元的继电器（13,17）。 在电源P1或P2的电源线供电故障的情况下，对应的继电器将自动（机械地）切换到相应的其他电源线，从而确保点火单元的功能得以保持，即使 - 无论什么原因 - 一个或另一个点火单元的电源中断。

公开(公告)号：US06659712B2

公开(公告)日：2003-12-09

申请号：US10173116

申请日：2002-06-18

申请人： Richard V Brooks ,  Arthur L Rowe ,  Michael A Horswill

发明人： Richard V Brooks ,  Arthur L Rowe ,  Michael A Horswill

IPC分类号： F01D2114

CPC分类号： G01M15/12 ,  F01D17/04 ,  F01D17/06 ,  F01D21/003 ,  F01D21/04 ,  F01D21/14 ,  F05D2270/301 ,  F05D2270/304 ,  F05D2270/52 ,  G01M15/14 ,  Y02T50/671

摘要： A gas turbine engine (10) comprises a fan rotor (26) having a plurality of fan blades (24) and an apparatus (34) for detecting damage to the fan blades (24). The apparatus (34) comprises a transducer (36) arranged to detect the pressure in the gas flow around the fan blades (34) and to produce a pressure signal. A speed sensor (48) is arranged to measure the speed of rotation of the fan rotor (26) and to produce a speed signal. A processor unit (40) analyses the pressure signal and the speed signal to detect changes in the amplitude of the pressure signal, which occur at multiples of the rotational frequency of the fan rotor (24). The changes indicate differences in pressure between the gas flow around a damaged fan blade (24) and the gas flow around the remainder of the fan blades (24). The processor unit (40) sends a signal indicative of damage to a fan blade (24), if the difference in pressure is above the predetermined level, to an indicator device (44, 46).

摘要翻译： 燃气涡轮发动机（10）包括具有多个风扇叶片（24）的风扇转子（26）和用于检测对风扇叶片（24）的损坏的装置（34）。 设备（34）包括被设置成检测围绕风扇叶片（34）的气流中的压力并产生压力信号的换能器（36）。 速度传感器（48）布置成测量风扇转子（26）的旋转速度并产生速度信号。 处理器单元（40）分析压力信号和速度信号，以检测以风扇转子（24）的转数的倍数发生的压力信号的幅度变化。 这些变化表示损坏的风扇叶片（24）周围的气体流与围绕其余风扇叶片（24）的气流之间的压力差异。 处理器单元（40）向指示器装置（44,46）发送指示对风扇叶片（24）的损坏的信号（如果压力差超过预定水平）。

公开(公告)号：US11668250B2

公开(公告)日：2023-06-06

申请号：US16679901

申请日：2019-11-11

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Patrick Manoukian

IPC分类号： F02C9/18 ,  B64D31/00 ,  G05B11/28

CPC分类号： F02C9/18 ,  B64D31/00 ,  G05B11/28 ,  F05D2260/606 ,  F05D2270/52

摘要： Methods and systems for operating a gas turbine engine in a multi-engine aircraft are described. The method comprises operating the gas turbine engine in a standby mode to provide substantially no motive power to the aircraft when another engine of the multi-engine aircraft is operated in an active mode to provide motive power to the aircraft, transitioning the gas turbine engine from the standby mode to the non-standby mode, and applying pulse width modulation to an air switching system of the gas turbine engine while transitioning the gas turbine engine from the standby mode to the non-standby mode.

公开(公告)号：US10018070B2

公开(公告)日：2018-07-10

申请号：US14904841

申请日：2014-09-05

申请人： SIEMENS AKTIENGESELLSCHAFT

发明人： Hans-Gerd Brummel ,  Dirk Grieshaber ,  Uwe Pfeifer ,  Huub De Bruyn

IPC分类号： F01D17/00 ,  F01D21/00 ,  F01D17/02 ,  F01D15/08 ,  F04D25/04 ,  F04D27/00 ,  G01L3/10 ,  F01D5/02 ,  F03B3/12 ,  F03B15/00 ,  F04D15/00 ,  F04D29/18 ,  F04D29/32

CPC分类号： F01D21/003 ,  F01D5/02 ,  F01D15/08 ,  F01D17/02 ,  F03B3/12 ,  F03B15/00 ,  F04D15/0066 ,  F04D25/045 ,  F04D27/001 ,  F04D27/004 ,  F04D29/181 ,  F04D29/321 ,  F05D2220/31 ,  F05D2220/32 ,  F05D2220/40 ,  F05D2270/335 ,  F05D2270/52 ,  F05D2270/804 ,  G01L3/102

摘要： A turbo-machine, which can be operated in an optimized driving range is provided. To this end, a method for operating a turbo-machine having at least one turbo-machine stage, which has at least one rotary shaft is disclosed. According to the method, the following method steps are carried out: a) determining a desired efficiency characteristic value ηsoll of the turbomachine stage; b) determining an actual efficiency characteristic value ηist of the turbo-machine-stage; c) determining a comparison efficiency characteristic value of the turbo-machine stage by comparing the actual efficiency characteristic value ηist and the desired efficiency characteristic value ηsoll to one another; and d) changing at least one operating parameter of the turbo-machine stage subject to the comparison efficiency characteristic value ηvgl, wherein in order to determine the actual efficiency characteristic value ηist, a measuring of a torque of the rotary shaft of the turbo-machine-stage is carried out.

公开(公告)号：US09909498B2

公开(公告)日：2018-03-06

申请号：US15306936

申请日：2015-04-27

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Sebastien Chalaud

IPC分类号： F02C7/06 ,  F01D25/22 ,  F02C9/36 ,  F02C7/36 ,  F01D25/20 ,  F02C9/26 ,  F02C7/22 ,  F02C7/236

CPC分类号： F02C7/06 ,  F01D25/20 ,  F01D25/22 ,  F02C7/22 ,  F02C7/222 ,  F02C7/236 ,  F02C7/36 ,  F02C9/263 ,  F02C9/36 ,  F05D2260/40311 ,  F05D2260/406 ,  F05D2270/52 ,  Y02T50/671

摘要： A system for supplying a turbomachine with fluid, the supply system including a low-pressure pumping unit intended to increase the pressure of the fluid flowing toward a downstream circuit. The downstream circuit divides at an inlet node, situated between the low-pressure pumping unit and the high-pressure volumetric pump, into a circuit supplying an injection system and a variable geometries supply circuit. The circuit supplying the injection system includes a high-pressure volumetric pump. The variable geometries supply circuit is configured to convey the fluid toward variable geometry from the inlet node to an outlet node connecting the variable geometries supply circuit to the upstream circuit between two pumps of the low-pressure pumping unit.

公开(公告)号：US09488109B2

公开(公告)日：2016-11-08

申请号：US14877409

申请日：2015-10-07

申请人： Bell Helicopter Textron Inc.

发明人： Chandler Sowden

IPC分类号： H02J7/14 ,  H02J7/00 ,  F02C7/266 ,  H02J1/00 ,  F02N11/08 ,  F02C7/26 ,  F02C7/262 ,  H02P9/08 ,  F02C7/275

CPC分类号： F02C7/266 ,  F02C7/26 ,  F02C7/262 ,  F02C7/275 ,  F02N11/0866 ,  F02N11/087 ,  F02N2011/0877 ,  F05D2220/329 ,  F05D2270/52 ,  H02J1/00 ,  H02P9/08 ,  Y10T307/653

摘要： A series battery start controller for starting an aircraft turbine engine and method thereof is provided, wherein the battery series start controller connects two batteries in series when an aircraft engine starter is engaged to provide a higher voltage to start the aircraft engine and to provide adequate operational voltage to aircraft engine instruments and other aircraft electrical systems, and wherein the battery series start controller reconnects the batteries in parallel when the electrical load drawn by the starting aircraft engine decreases and the supplied voltage to the aircraft rises to a predetermined threshold.