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    Methods and apparatus for trimming engine control systems
    3.
    发明授权
    Methods and apparatus for trimming engine control systems 有权
    调整发动机控制系统的方法和装置

    公开(公告)号：US06459963B1

    公开(公告)日：2002-10-01

    申请号：US09629529

    申请日：2000-07-31

    申请人： George Washington Bennett ,  Sridhar Adibhatla ,  Matthew William Wiseman

    发明人： George Washington Bennett ,  Sridhar Adibhatla ,  Matthew William Wiseman

    IPC分类号： G06F700

    CPC分类号： F02C9/28

    摘要： A control system trims a gas turbine engine in real-time to provide a desired amount of thrust. The control system includes a controller coupled to the engine for receiving inputs from the engine regarding a status of the engine. The controller includes a processor and a non-volatile memory coupled to the processor. The processor is programmed to execute control logic. An engine power schedule representing values for a controlled variable is stored in the memory.

    摘要翻译： 控制系统实时修整燃气涡轮发动机以提供所需量的推力。 控制系统包括耦合到发动机的控制器，用于从发动机接收关于发动机状态的输入。 控制器包括耦合到处理器的处理器和非易失性存储器。 处理器被编程为执行控制逻辑。 表示受控变量值的发动机功率计划被存储在存储器中。

    Sensor fault detection, isolation and accommodation
    4.
    发明授权
    Sensor fault detection, isolation and accommodation 有权
    传感器故障检测，隔离和调节

    公开(公告)号：US06598195B1

    公开(公告)日：2003-07-22

    申请号：US09643007

    申请日：2000-08-21

    申请人： Sridhar Adibhatla ,  Matthew William Wiseman

    发明人： Sridhar Adibhatla ,  Matthew William Wiseman

    IPC分类号： G01R3130

    CPC分类号： G01D3/08 ,  G05B23/0275

    摘要： A sensor in an engineering system can be tested to detect, isolate and accommodate faults. Initially, a modeled sensor value of each actual sensor value is generated as a function of a plurality of other sensors. An absolute value of a difference between the actual sensor value and the modeled sensor value is then computed and compared to a predetermined threshold. A sensor fault is detected if the difference is greater than the predetermined threshold. Once a sensor fault is detected, it is isolated using hypothesis testing and maximum wins strategies. After the fault is isolated, the fault is accommodated by substituting the modeled sensor value for the actual sensor value.

    摘要翻译： 可以测试工程系统中的传感器来检测，隔离和适应故障。 最初，产生每个实际传感器值的建模传感器值作为多个其它传感器的函数。 然后计算实际传感器值和建模的传感器值之间的差的绝对值，并将其与预定阈值进行比较。 如果差值大于预定阈值，则检测到传感器故障。 一旦检测到传感器故障，就会使用假设检验和最大胜利策略进行隔离。 在故障隔离之后，通过将建模的传感器值替换为实际传感器值来容纳故障。

    Methods and apparatus for assessing gas turbine engine damage
    6.
    发明授权
    Methods and apparatus for assessing gas turbine engine damage 有权
    评估燃气轮机发动机损坏的方法和装置

    公开(公告)号：US06892127B2

    公开(公告)日：2005-05-10

    申请号：US10376510

    申请日：2003-02-28

    申请人： Matthew William Wiseman

    发明人： Matthew William Wiseman

    IPC分类号： F01D25/00 ,  F02C7/00 ,  G05B23/02 ,  G06F19/00

    CPC分类号： G05B23/0218

    摘要： A method and apparatus for assessing damage to machine components is provided. The method includes calculating an expected parameter value based on a first parameter value indicator, calculating an estimate of an actual parameter value based on a second parameter value indicator, the second parameter value indicator being different than the first parameter value indicator, determining if the calculated expected parameter value is different than the calculated estimate of the actual parameter value by a predefined limit, and generating a damage flag based on a result of the comparison. The apparatus includes a computing device including a processor and a memory communicatively coupled to the processor, the processor programmed to execute a software product code segment that includes a detection boundary module, an estimator, and a comparator wherein the computing device is programmed to assess damage within an engine.

    摘要翻译： 提供了一种用于评估机器部件损坏的方法和装置。 该方法包括基于第一参数值指示符计算预期参数值，基于第二参数值指示器计算实际参数值的估计，第二参数值指示符与第一参数值指示符不同，确定所计算的 预期参数值与计算出的实际参数值的估计值不同，并根据比较结果生成损伤标志。 该设备包括计算设备，其包括处理器和通信地耦合到处理器的存储器，该处理器被编程为执行包括检测边界模块，估计器和比较器的软件产品代码段，其中计算设备被编程以评估损坏 在发动机内。

    Model-based iterative estimation of gas turbine engine component qualities
    7.
    发明授权
    Model-based iterative estimation of gas turbine engine component qualities 有权
    燃气轮机发动机部件质量的模型迭代估计

    公开(公告)号：US07505844B2

    公开(公告)日：2009-03-17

    申请号：US11283345

    申请日：2005-11-18

    申请人： Matthew William Wiseman ,  Malcolm John Ashby

    发明人： Matthew William Wiseman ,  Malcolm John Ashby

    IPC分类号： G06F19/00

    CPC分类号： G05B23/0283 ,  G05B23/0254 ,  Y10T477/40

    摘要： A method of estimating quality parameters for a plurality of engine components of a gas turbine engine is provided. The engine components have at least one sensor responsive to the engine component operation. The method includes providing an engine model having virtual sensor values and quality parameters corresponding to the plurality of sensors of the engine components; comparing the virtual sensor values to actual sensor values of the plurality of sensors of the engine components to determine the difference between the actual and virtual sensor values; amplifying the difference by a predetermined gain; generating a plurality of quality parameter deltas in response to the sensed difference; iteratively updating the embedded engine model by inputting a predetermined portion of the generated quality parameter deltas into the embedded engine model; adjusting the embedded engine model for engine operating conditions; and recalculating the virtual sensor values.

    摘要翻译： 提供了一种用于估计燃气涡轮发动机的多个发动机部件的质量参数的方法。 发动机部件具有响应于发动机部件操作的至少一个传感器。 该方法包括提供具有对应于发动机部件的多个传感器的虚拟传感器值和质量参数的发动机模型; 将虚拟传感器值与发动机部件的多个传感器的实际传感器值进行比较，以确定实际和虚拟传感器值之间的差异; 将差放大预定增益; 响应于所感测到的差异而产生多个质量参数增量; 通过将生成的质量参数三角洲的预定部分输入到嵌入式引擎模型中来迭代地更新嵌入式引擎模型; 调整发动机运行条件下的嵌入式发动机型号; 并重新计算虚拟传感器值。

    Methods and apparatus for assessing gas turbine engine damage
    8.
    发明授权
    Methods and apparatus for assessing gas turbine engine damage 有权

    公开(公告)号：US07065468B2

    公开(公告)日：2006-06-20

    申请号：US10955551

    申请日：2004-09-30

    申请人： Matthew William Wiseman

    发明人： Matthew William Wiseman

    IPC分类号： G06F3/01

    CPC分类号： G05B23/0218

    摘要： A method and apparatus for assessing damage to machine components is provided. The method includes calculating an expected parameter value based on a first parameter value indicator, calculating an estimate of an actual parameter value based on a second parameter value indicator, the second parameter value indicator being different than the first parameter value indicator, determining if the calculated expected parameter value is different than the calculated estimate of the actual parameter value by a predefined limit, and generating a damage flag based on a result of the comparison. The apparatus includes a computing device including a processor and a memory communicatively coupled to the processor, the processor programmed to execute a software product code segment that includes a detection boundary module, an estimator, and a comparator wherein the computing device is programmed to assess damage within an engine.

    Compensating for blade tip clearance deterioration in active clearance control
    9.
    发明授权
    Compensating for blade tip clearance deterioration in active clearance control 有权
    补偿主动间隙控制中的叶片顶端间隙变差

    公开(公告)号：US07431557B2

    公开(公告)日：2008-10-07

    申请号：US11441258

    申请日：2006-05-25

    申请人： William Lee Herron ,  Matthew William Wiseman ,  Jon Michael Vishnauski ,  Brian Edward Krupp ,  Ronald George Maruscik

    发明人： William Lee Herron ,  Matthew William Wiseman ,  Jon Michael Vishnauski ,  Brian Edward Krupp ,  Ronald George Maruscik

    IPC分类号： G06F19/00

    CPC分类号： F01D11/24 ,  F05D2260/80 ,  F05D2270/44 ,  Y02T50/672

    摘要： A method to compensate for blade tip clearance deterioration between rotating blade tips and a surrounding shroud in an aircraft gas turbine engine includes determining one or more variables based on at least one or more moving averages of one or more engine operating parameters respectively averaged over a fixed number of operational engine flight cycles and adjusting a flow rate of thermal control air to counter the blade tip clearance deterioration based on the one or more variables. The engine operating parameters may include running number of engine cycles, takeoff and cruise exhaust gas temperature margins, a cruise turbine efficiency, takeoff and cruise maximum turbine speeds, a cruise fuel flow. Some or all of the variables may be differences between the moving averages and corresponding baselines of the engine operating parameters respectively or the variables may all be moving averages. The flow rate may be adjusted incrementally.

    摘要翻译： 用于补偿在飞行器燃气涡轮发动机中的旋转叶片尖端和周围护罩之间的叶片顶端间隙变差的方法包括基于一个或多个发动机工作参数的至少一个或多个移动平均值确定一个或多个变量， 操作发动机飞行循环的数量，并且基于一个或多个变量来调节热控制空气的流量以对抗叶片顶端间隙恶化。 发动机运行参数可以包括发动机循环的运行次数，起飞和巡航废气温度裕度，巡航涡轮机效率，起飞和巡航最大涡轮机速度，巡航燃料流量。 变量的一些或全部可能分别是发动机运行参数的移动平均值和相应基线之间的差异，或者变量都可以是移动平均线。 流量可以逐渐调整。

    Compensating for blade tip clearance deterioration in active clearance control
    10.
    发明申请
    Compensating for blade tip clearance deterioration in active clearance control 有权
    补偿主动间隙控制中的叶片顶端间隙变差

    公开(公告)号：US20070276578A1

    公开(公告)日：2007-11-29

    申请号：US11441258

    申请日：2006-05-25

    申请人： William Lee Herron ,  Matthew William Wiseman ,  Jon Micheal Vishnauski ,  Brian Edward Krupp ,  Ronald George Maruscik

    发明人： William Lee Herron ,  Matthew William Wiseman ,  Jon Micheal Vishnauski ,  Brian Edward Krupp ,  Ronald George Maruscik

    IPC分类号： G06F19/00

    CPC分类号： F01D11/24 ,  F05D2260/80 ,  F05D2270/44 ,  Y02T50/672

    摘要： A method to compensate for blade tip clearance deterioration between rotating blade tips and a surrounding shroud in an aircraft gas turbine engine includes determining one or more variables based on at least one or more moving averages of one or more engine operating parameters respectively averaged over a fixed number of operational engine flight cycles and adjusting a flow rate of thermal control air to counter the blade tip clearance deterioration based on the one or more variables. The engine operating parameters may include running number of engine cycles, takeoff and cruise exhaust gas temperature margins, a cruise turbine efficiency, takeoff and cruise maximum turbine speeds, a cruise fuel flow. Some or all of the variables may be differences between the moving averages and corresponding baselines of the engine operating parameters respectively or the variables may all be moving averages. The flow rate may be adjusted incrementally.

    摘要翻译： 用于补偿在飞行器燃气涡轮发动机中的旋转叶片尖端和周围护罩之间的叶片顶端间隙变差的方法包括基于一个或多个发动机工作参数的至少一个或多个移动平均值确定一个或多个变量， 操作发动机飞行循环的数量，并且基于一个或多个变量来调节热控制空气的流量以对抗叶片顶端间隙恶化。 发动机运行参数可以包括发动机循环的运行次数，起飞和巡航废气温度裕度，巡航涡轮机效率，起飞和巡航最大涡轮机速度，巡航燃料流量。 变量的一些或全部可能分别是发动机运行参数的移动平均值和相应基线之间的差异，或者变量都可以是移动平均线。 流量可以逐渐调整。