公开(公告)号：US09448557B2

公开(公告)日：2016-09-20

申请号：US12673778

申请日：2008-07-07

申请人： Hakim Maalioune

发明人： Hakim Maalioune

IPC分类号： F02K1/76 ,  G05B23/02 ,  G05B9/02

CPC分类号： G05B23/0291 ,  F02K1/763 ,  F05D2270/094 ,  G05B9/02 ,  G05B2219/42329 ,  Y02T50/671

摘要： The invention relates to a control system for at least one actuator (6) for the cowlings of a thrust inverter in a turbojet engine, that comprises an assembly of actuation and/or control components. A control means (9) is provided for detecting the failure of an actuation and/or control component (7, 16, 13), for determining the blocking or non-blocking character of the failure for the system operation and, in case of a non-blocking failure, for switching from a nominal operation mode to a failure-adaptation operation mode in which the failure of the actuation and/or control component (7, 16, 13) is compensated at least partially by a modified instruction of the other actuation and/or control components (7, 16, 13).

摘要翻译： 本发明涉及一种用于至少一个用于涡轮喷气发动机中的推力逆变器的整流罩的致动器（6）的控制系统，其包括致动和/或控制部件的组件。 提供控制装置（9），用于检测致动和/或控制部件（7,16,13）的故障，用于确定用于系统操作的故障的阻塞或非阻塞特性，并且在 用于从标称操作模式切换到故障适应操作模式的非阻塞故障，其中致动和/或控制部件（7,16,13）的故障至少部分地由另一个的修改指令补偿 致动和/或控制部件（7,16,13）。

公开(公告)号：US09217376B2

公开(公告)日：2015-12-22

申请号：US13121209

申请日：2008-11-13

申请人： David H. Sweet ,  Stephen H. Silder

发明人： David H. Sweet ,  Stephen H. Silder

IPC分类号： F02C9/26 ,  B64D31/06 ,  F02C9/46 ,  F02C9/44 ,  F02C9/22 ,  F23N5/18 ,  F02C9/28

CPC分类号： F02C9/263 ,  B64D31/06 ,  F02C9/22 ,  F02C9/26 ,  F02C9/28 ,  F02C9/44 ,  F02C9/46 ,  F05D2270/09 ,  F05D2270/094 ,  F23N2005/185

摘要： A gas turbine engine control system according to an exemplary aspect of the present disclosure includes, among other things, an automatic control operable to control a gas turbine engine. The gas turbine engine control system further comprises a module operable to fail-fix the gas turbine engine to one of a multiple of pre-determined modes in response to failure of the automatic control. The exemplary gas turbine engine control system may further comprise a fuel flow meter to sense a fuel flow to the engine, a fuel control to control the fuel flow to the engine, and the module in electrical communication with the fuel flow meter to fix the fuel control in response to one of the multiple of pre-determined modes.

摘要翻译： 根据本公开的示例性方面的燃气涡轮发动机控制系统尤其包括可操作以控制燃气涡轮发动机的自动控制装置。 燃气涡轮发动机控制系统还包括可操作以响应于自动控制的故障将燃气涡轮发动机故障固定为多个预定模式中的一个的模块。 示例性燃气涡轮发动机控制系统还可以包括用于感测到发动机的燃料流的燃料流量计，用于控制到发动机的燃料流的燃料控制器，以及与燃料流量计电连通的模块以固定燃料 响应于多个预定模式之一进行控制。

公开(公告)号：US20110142640A1

公开(公告)日：2011-06-16

申请号：US13059072

申请日：2009-11-10

申请人： Keitaro Kamata ,  Atsushi Yuge

发明人： Keitaro Kamata ,  Atsushi Yuge

IPC分类号： F03D7/04

CPC分类号： F03D7/0224 ,  F01D17/26 ,  F05B2260/502 ,  F05B2270/1074 ,  F05B2270/604 ,  F05D2260/52 ,  F05D2270/094 ,  F05D2270/64 ,  Y02E10/723

摘要： An object is to provide a cylinder driving device of a wind-power generation system capable of appropriately controlling a pitch angle of each rotor blade at a time of power failure with a simple configuration. The present invention achieves the object by including a piston connected to the rotor blade; a cylinder that moves the piston by a hydraulic pressure; an urging member that urges the piston in one direction; an accumulator that is connected to the cylinder, and supplies hydraulic oil urging the piston in an opposite direction to a direction where the piston is urged by the urging member to the cylinder; and an on/off valve that controls opening or closing of a channel between the accumulator and the cylinder.

摘要翻译： 本发明的目的是提供一种能够以简单的结构在停电时适当地控制每个转子叶片的俯仰角的风力发电系统的气缸驱动装置。 本发明通过包括连接到转子叶片的活塞来实现该目的; 缸体，其通过液压移动活塞; 推动构件，其在一个方向上推动活塞; 蓄压器，其连接到所述气缸，并且供应液压油，其沿与所述推动构件将所述活塞推压到所述气缸的方向相反的方向推动所述活塞; 以及控制蓄能器和气缸之间的通道的打开或关闭的开闭阀。

公开(公告)号：US20110060482A1

公开(公告)日：2011-03-10

申请号：US12851120

申请日：2010-08-05

申请人： Mark Harrison

发明人： Mark Harrison

IPC分类号： G06F19/00

CPC分类号： F01D21/12 ,  B64D31/06 ,  B64D45/00 ,  B64D2045/009 ,  F02D41/22 ,  F02D41/26 ,  F05D2270/094 ,  G05B23/0235 ,  G05B23/0289 ,  Y02T50/671

摘要： A control assembly operable in the event of overheating of an engine electronic controller on an aircraft. The assembly including one or more temperature sensors located in the vicinity of the aircraft engine and connected to a control unit. The control unit is arranged to measure the temperature or temperatures detected by the sensors, and to determine whether in view of detected increased temperatures, a situation constitutes an emergency situation or a controlled situation. The control unit communicates a controlled situation to a pilot of the aircraft, and automatically causes an override action to occur to the aircraft engine when an emergency situation is determined.

摘要翻译： 在飞机上的发动机电子控制器过热的情况下可操作的控制组件。 该组件包括位于飞行器发动机附近并连接到控制单元的一个或多个温度传感器。 控制单元设置为测量由传感器检测到的温度或温度，并且确定是否考虑检测到的升高的温度，情况构成紧急情况或受控情况。 控制单元将受控情况与飞行员的驾驶员进行通信，并且当确定紧急情况时，自动地使飞机发动机发生超控动作。

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：US20070005219A1

公开(公告)日：2007-01-04

申请号：US11165497

申请日：2005-06-24

申请人： Hironori Muramatsu ,  Yukinobu Sugitani

发明人： Hironori Muramatsu ,  Yukinobu Sugitani

IPC分类号： G06F19/00

CPC分类号： F02C9/28 ,  F01D21/003 ,  F05D2260/80 ,  F05D2270/094 ,  F05D2270/301 ,  F05D2270/303 ,  F05D2270/304 ,  F05D2270/708 ,  G01D3/022 ,  G01D3/08 ,  Y10T477/40

摘要： In a system for monitoring an output of a sensor for detecting an operating state of a gas turbine engine by comparing a value of an output of the sensor with a prescribed reference value, a calibration map for converting the output of the sensor into a variable that is normally used for controlling the engine is used for defining the reference value for determining the state of the sensor. Thereby, a fault of a sensor can be detected both accurately and promptly by using the existing resource without unduly complicating the control program. It is particularly desirable to monitor the output of the sensor by taking into account the current operating condition of the engine to improve the reliability in detecting a fault in the sensor.

摘要翻译： 在用于通过将传感器的输出值与规定的基准值进行比较来监视燃气轮机的运转状态的传感器的输出的系统中，将用于将传感器的输出转换为变量的校准图， 通常用于控制发动机用于定义用于确定传感器状态的参考值。 因此，可以通过使用现有资源来准确和及时地检测传感器的故障，而不会使控制程序过度复杂化。 特别希望通过考虑发动机的当前运行状况来监测传感器的输出，以提高检测传感器故障的可靠性。

公开(公告)号：US20060283191A1

公开(公告)日：2006-12-21

申请号：US11342838

申请日：2006-01-31

申请人： Michael Horswill ,  Stephen Garner

发明人： Michael Horswill ,  Stephen Garner

IPC分类号： F02C9/28

CPC分类号： F02C9/28 ,  F02C9/46 ,  F02C9/48 ,  F05D2270/094

摘要： A control apparatus 50 for a gas turbine engine for an aircraft includes engine control means 52 forming part of an outer fuel control loop and fuel control means/overthrust protector 76 forming part of an inner fuel control loop. Overthrust protection is provided within each of the engine control means 52 and the fuel control means/overthrust protector 76, which are powered and housed separately. Thus, a failure within one of these systems could not result in overthrust and demonstrably reliable overthrust protection is provided within a single channel.

摘要翻译： 用于飞机的燃气涡轮发动机的控制装置50包括形成外部燃料控制回路的一部分的发动机控制装置52和形成内部燃料控制回路的一部分的燃料控制装置/反向保护器76。 在每个发动机控制装置52和燃料控制装置/推压保护器76内设置有反向保护装置，其分开供电和容纳。 因此，在这些系统之一内的故障不能导致过度推断，并且在单个通道内提供可靠的过度保护。

公开(公告)号：US07043896B2

公开(公告)日：2006-05-16

申请号：US10717627

申请日：2003-11-21

申请人： Peter John David Matthews

发明人： Peter John David Matthews

IPC分类号： F02C9/26

CPC分类号： F02C9/28 ,  F01D21/16 ,  F02C9/46 ,  F05D2270/09 ,  F05D2270/094 ,  F05D2270/54 ,  G05B9/03

摘要： An engine shutdown device for controlling a fuel shut-off valve to thereby selectively interrupt fuel flow to an engine. The device comprises a normal switch connected to the fuel shut-off valve and configured to respond to at least one of a normal shutdown signal and an emergency shutdown signal. The device further comprises an emergency switch connected to the fuel shut-off valve and configured to respond to the emergency shutdown signal.

摘要翻译： 一种用于控制燃料切断阀从而选择性地中断向发动机的燃料流量的发动机关闭装置。 该装置包括连接到燃料切断阀的正常开关，并被配置为响应正常关闭信号和紧急关闭信号中的至少一个。 该装置还包括连接到燃料切断阀并被配置为响应紧急关闭信号的紧急开关。

公开(公告)号：US4391290A

公开(公告)日：1983-07-05

申请号：US200221

申请日：1980-10-23

申请人： Raymond L. Williams

发明人： Raymond L. Williams

IPC分类号： F02C7/00 ,  F01D11/10 ,  F01D11/24 ,  F02C7/28 ,  F02C9/00 ,  F02C9/28 ,  G01C5/06 ,  F16K31/12 ,  F16K37/00 ,  F16K49/00

CPC分类号： F01D11/24 ,  F02C9/28 ,  G01C5/06 ,  F05D2270/094 ,  Y10T137/2012 ,  Y10T137/6579 ,  Y10T137/8275

摘要： In one form of the invention, the control apparatus includes two stages: a poppet first stage and a piston second stage. The poppet first stage includes an altitude sensitive evacuated bellows coupled to a poppet valve. The second stage piston includes a pair of opposing head portions separated by a rod portion. The apparatus includes an output port which is coupled to a low pressure pneumatic signal or to a high pressure pneumatic signal, depending upon the position of the piston. For altitudes less than a predetermined altitude, e.g., 20,000 feet, the first stage develops a pneumatic servo signal which causes the piston to be in a first position which couples the output port of the apparatus to ambient air pressure. For altitudes greater than the predetermined altitude, the first stage develops a pneumatic servo signal which causes the piston to be in a second position which couples the output port of the apparatus to a high pressure pneumatic signal. The high pressure pneumatic signal may comprise the compressor discharge pressure of a gas turbine engine. Backup means is provided for accommodating failure of the bellows. Indicator and adjustment means are also provided for ensuring an accurate, reliable, and repeatable, control apparatus output signal.

摘要翻译： 在本发明的一种形式中，控制装置包括两个阶段：提升阀第一级和活塞第二级。 提升阀第一级包括耦合到提升阀的高度敏感的抽真空波纹管。 第二级活塞包括由杆部分开的一对相对的头部。 该装置包括根据活塞的位置而耦合到低压气动信号或高压气动信号的输出端口。 对于低于预定高度（例如20,000英尺）的高度，第一级产生气动伺服信号，其使活塞处于将装置的输出端口连接到环境空气压力的第一位置。 对于高于预定高度的高度，第一级产生气动伺服信号，该气动伺服信号使活塞处于将装置的输出端口耦合到高压气动信号的第二位置。 高压气动信号可以包括燃气涡轮发动机的压缩机排气压力。 提供了用于容纳波纹管故障的备用装置。 还提供指示器和调节装置，以确保准确，可靠和可重复的控制装置输出信号。

公开(公告)号：US4368618A

公开(公告)日：1983-01-18

申请号：US193229

申请日：1980-10-02

申请人： William E. Nave

发明人： William E. Nave

IPC分类号： F02C9/38 ,  F02C9/28 ,  F02C9/46 ,  F02D33/00

CPC分类号： F02C9/28 ,  F02C9/46 ,  F05D2270/09 ,  F05D2270/094

摘要： A fuel control having an electrically operated metering valve and a manually operated metering valve through which fuel is independently scheduled to an engine. During normal operation, the electrically operated metering valve controls the flow of fuel to the engine in response to an operator input signal. Linkage connected to a power lever supplies the manually operated metering valve with an input corresponding to the fuel flow requirement requested by the operator of the electrically operated metering valve. The manually operated metering valve is connected to the source of fuel through an electrically operated transfer valve. Should an electrical failure occur, the electrically operated transfer valve is deactivated and if the fuel flow requirement is below a fixed level, fuel flows from the source through the manually operated metering valve without moving the power lever to maintain a substantially constant engine speed.

摘要翻译： 燃料控制器具有电动计量阀和手动计量阀，通过该计量阀将燃料独立地调度到发动机。 在正常操作期间，电动计量阀响应于操作者输入信号控制到发动机的燃料流。 连接到动力杆的连接为手动计量阀提供与电动计量阀的操作者要求的燃料流量要求相对应的输入。 手动计量阀通过电动转换阀连接到燃料源。 如果发生电气故障，电动转换阀被停用，并且如果燃料流量要求低于固定水平，则燃料通过手动计量阀从源流出而不移动动力杆以保持基本恒定的发动机转速。