利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

12 条记录 (耗时 0.022 秒)

    Engine failure monitor for a multi-engine aircraft having partial engine failure and driveshaft failure detection
    1.
    发明授权
    Engine failure monitor for a multi-engine aircraft having partial engine failure and driveshaft failure detection 失效
    发动机故障监视器，用于具有局部发动机故障和驱动轴故障检测的多发飞机

    公开(公告)号：US5363317A

    公开(公告)日：1994-11-08

    申请号：US968107

    申请日：1992-10-29

    申请人： Robert W. Rice ,  David H. Sweet

    发明人： Robert W. Rice ,  David H. Sweet

    IPC分类号： B64D31/00 ,  B64D31/12 ,  F02C3/10 ,  F02C6/02 ,  F02C7/00 ,  G07C3/00 ,  G01B7/00

    CPC分类号： B64D31/12 ,  G07C3/00

    摘要： An engine failure monitor 50 for use with a multi-engine aircraft having at least two engines detects conditions indicative of a partial (700) or total (400) engine failure, including turbine shaft failures (600). In response to an engine failure, suitable inputs (134, 138, 712) are provided to an electronic engine control for operating the remaining engine. Additionally, indications indicative of the engine failure (132, 710) are provided to the cockpit.

    摘要翻译： 与具有至少两个发动机的多发飞机一起使用的发动机故障监视器50检测指示部分（700）或总（400）发动机故障的条件，包括涡轮轴故障（600）。 响应于发动机故障，适当的输入（134,138,712）被提供给用于操作剩余发动机的电子发动机控制。 此外，指示发动机故障的指示（132,710）被提供给驾驶舱。

    Helicopter engine control having lateral cyclic pitch anticipation
    6.
    发明授权
    Helicopter engine control having lateral cyclic pitch anticipation 失效
    直升机发动机控制具有侧向循环俯仰预期

    公开(公告)号：US5265826A

    公开(公告)日：1993-11-30

    申请号：US935764

    申请日：1992-08-26

    申请人： Frederick J. Ebert ,  Joseph T. Driscoll ,  Byron Graham, Jr. ,  David H. Sweet

    发明人： Frederick J. Ebert ,  Joseph T. Driscoll ,  Byron Graham, Jr. ,  David H. Sweet

    IPC分类号： F02C9/28 ,  B64D31/00 ,  B64D31/06 ,  G05D1/00 ,  G05D1/08 ,  B64C11/34 ,  B64C27/57

    CPC分类号： G05D1/0055 ,  G05D1/0858

    摘要： A helicopter engine fuel control anticipates changes in main rotor torque in response to lateral cyclic pitch commands, to thereby minimize engine and main rotor speed droop and overspeed during left and right roll maneuvers. A fuel compensation signal (100,101) is summed with a helicopter fuel control (52) fuel command signal (67) in response both to a lateral cyclic pitch command signal (LCP) (107) from a pilot operated cyclic pitch control exceeding a left or right threshold magnitude (201,210) and a total lateral cyclic pitch command signal (TCP) (108) from a lateral cyclic pitch control system exceeding a left or right threshold magnitude (202,207,215,220). The magnitude of the fuel compensation signal is dependant upon the direction of TCP and LCP, e.g., left or right, and helicopter roll acceleration (115). Alternatively, the magnitude and duration of the fuel compensation signal is dependant upon the rate of change in commanded lateral cyclic pitch (107,400,407). A limiter (120) limits the magnitude of the fuel compensation signal. The fuel compensation signal is overridden (127,125,103) when it is increasing fuel flow ( 303) during rotor overspeed (128,301), and when it is decreasing fuel flow (311) if rotor acceleration (130,133) is negative (310) during rotor droop (128,301).

    摘要翻译： 直升机发动机燃料控制预测主旋翼扭矩响应于横向循环俯仰命令的变化，从而使左右滚动机动中的发动机和主转子速度下降和超速最小化。 燃料补偿信号（100,101）与直升机燃料控制（52）燃料指令信号（67）相加，响应于来自超过左边的先导操作的循环音调控制的横向循环音调指令信号（LCP）（107） 右侧阈值幅度（201,210）和来自横向循环音调控制系统的总横向循环音调指令信号（TCP）（108）超过左阈值或右阈值幅度（202,207,215,220）。 燃料补偿信号的大小取决于TCP和LCP的方向，例如左或右，以及直升机滚动加速度（115）。 或者，燃料补偿信号的幅度和持续时间取决于指令的横向循环间距的变化率（107,400,407）。 限制器（120）限制燃料补偿信号的大小。 当转子超速（128,301）期间增加燃料流量（303）时，以及如果在转子下降期间转子加速度（130,133）为负（310）时，燃料补偿信号被减少（127,125,103） 128,301）。

    Range maximizing, stable, helicopter cruise fuel conservation
    7.
    发明授权
    Range maximizing, stable, helicopter cruise fuel conservation 失效
    范围最大化，稳定，直升机巡航燃油节约

    公开(公告)号：US5023797A

    公开(公告)日：1991-06-11

    申请号：US587495

    申请日：1990-09-20

    申请人： Nicholas D. Lappos ,  David M. Walsh ,  David H. Sweet ,  Charles E. Greenberg

    发明人： Nicholas D. Lappos ,  David M. Walsh ,  David H. Sweet ,  Charles E. Greenberg

    IPC分类号： G05D1/00

    CPC分类号： G05D1/0005

    摘要： The reference speed for a helicopter engine is incremented or decremented (237, 239) in dependence upon whether a specific range (miles per unit of fuel) has increased or decreased (236a) in a current period of time compared to the next preceding period of time, separated therefrom by at least 20 seconds (243, 244) to thereby set engine speed for minimizing use of fuel over distance traveled. Fuel is sampled only during steady flight (250-255).

    摘要翻译： 直升机发动机的参考速度根据在当前时间段内的特定范围（单位燃料里程）是否增加或减少（236a）而增加或减少（236,39） 时间，与其隔开至少20秒（243,244），从而设定发动机转速，以使燃料在行驶距离上的使用最小化。 燃油仅在稳定飞行期间进行采样（250-255）。

    Automatic turbine engine bleed valve control for enhanced fuel management
    8.
    发明授权
    Automatic turbine engine bleed valve control for enhanced fuel management 失效
    自动涡轮发动机泄放阀控制，用于加强燃油管理

    公开(公告)号：US5313778A

    公开(公告)日：1994-05-24

    申请号：US988520

    申请日：1992-12-10

    申请人： David H. Sweet ,  Charles W. Evans

    发明人： David H. Sweet ,  Charles W. Evans

    IPC分类号： F02C9/18

    CPC分类号： F02C9/18 ,  F05D2270/07

    摘要： A bleed air control system for an aircraft gas turbine engine operates in a fuel saving mode in response to operation of the aircraft in a steady-state cruise condition (215,350) within a threshold flight envelope (202,310) during steady-state engine operation above a threshold range. During operation in the fuel saving mode, a gas turbine engine compressor bleed valve (10) is closed. The rate of bleed valve closure is determined as a function of bleed valve position (12,20) and gas generator speed (26,30) at the instant the fuel savings mode is initiated. The bleed air control system is returned to normal operation in response to actual or commanded engine acceleration above respective threshold magnitudes, in response to aircraft load factor differing from a reference load factor by a threshold magnitude, and in response to the discontinued operation of the aircraft at steady-state cruise conditions, discontinued steady-state operation of the engine above the transient range, or operation of the aircraft outside of the threshold flight envelope.

    摘要翻译： 用于飞机燃气涡轮发动机的排气控制系统响应于在稳态发动机操作中的稳定状态巡航状态（202,310）内的飞行器的操作，在燃料节省模式下操作， 阈值范围 在节油模式的运转中，关闭燃气涡轮发动机压缩机排气阀（10）。 泄放阀关闭的速率在燃料节省模式启动时被确定为泄放阀位置（12,20）和气体发生器速度（26,30）的函数。 响应于不同于参考负载因子的飞行器负载因子阈值大小，以及响应于飞行器的停止的操作，排气控制系统响应于实际或命令的发动机加速度高于相应阈值幅值而返回正常操作 在稳态巡航条件下，停止在瞬态范围之上的发动机的稳态运行，或飞机超出阈值飞行包线的操作。

    Helicopter engine control having yaw input anticipation
    9.
    发明授权
    Helicopter engine control having yaw input anticipation 失效
    具有偏航输入预期的直升机发动机控制

    公开(公告)号：US5265825A

    公开(公告)日：1993-11-30

    申请号：US936187

    申请日：1992-08-26

    申请人： Frederick J. Ebert ,  Joseph T. Driscoll ,  David H. Sweet

    发明人： Frederick J. Ebert ,  Joseph T. Driscoll ,  David H. Sweet

    IPC分类号： B64D31/00 ,  F02C9/28 ,  G05B1/08 ,  G05D1/00 ,  G05D1/08 ,  B64C11/44 ,  B64C27/54

    CPC分类号： G05D1/0055 ,  G05D1/0858

    摘要： A helicopter engine fuel control anticipates sudden changes in engine power demand during yaw inputs to thereby minimize engine and main rotor speed droop and overspeed during yaw maneuvers. The rate (121,123) of yaw control (107) position change generates (110) a yaw component (104) of a helicopter fuel control (52) fuel command signal (70). The magnitude of the yaw component is also dependant upon the rate of yaw control position change (703). The fuel command signal yaw component (104) is overridden (113,115) when rotor decay rate (209,217) has been arrested during a sharp left hover turn (216); when the yaw component is removing fuel (239) during rotor droop (238); and when the yaw component is adding fuel (228) during rotor overspeed (227).

    摘要翻译： 直升机发动机燃料控制预计在偏航输入期间发动机功率需求的突然变化，从而使偏航操纵期间的发动机和主转子速度下降和超速最小化。 偏航控制（107）位置变化的速率（121,123）产生（110）直升机燃料控制（52）燃料指令信号（70）的偏航分量（104）。 偏航分量的大小也取决于偏航控制位置变化的速度（703）。 当旋转衰减速率（209,217）在急停的左悬停转弯（216）期间被停止时，燃料指令信号偏航分量（104）被覆盖（113,115）。 当偏转分量在转子下垂期间移除燃料（239）时; 并且当偏转分量在转子超速期间添加燃料（228）（227）时。

    Multi-mode adaptive fail-fixed system for FADEC controlled gas turbine engines
    10.
    发明授权
    Multi-mode adaptive fail-fixed system for FADEC controlled gas turbine engines 有权
    用于FADEC控制燃气轮机的多模式自适应故障固定系统

    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。