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    MULTI SENSOR CLEARANCE PROBE
    11.
    发明申请
    MULTI SENSOR CLEARANCE PROBE 有权
    多传感器清除探头

    公开(公告)号：US20090064522A1

    公开(公告)日：2009-03-12

    申请号：US11688354

    申请日：2007-03-20

    申请人： William Lee Herron ,  Robert Joseph Albers ,  Rafael Jose Ruiz ,  Samhita Dasgupta

    发明人： William Lee Herron ,  Robert Joseph Albers ,  Rafael Jose Ruiz ,  Samhita Dasgupta

    IPC分类号： G01D21/00

    CPC分类号： G01B7/14 ,  F01D5/20 ,  F01D21/003 ,  G01B21/16

    摘要： A multi sensor clearance probe with at least longitudinally and transversely spaced apart first and second sensors operable to measure first and second distances respectively between the sensors and a longitudinally spaced apart rotating rotor. The sensors being operable to measure blade tip clearances between radially outer turbine blade tips and an annular stator shroud circumscribing the blade tips. The blade tips may be squealer tips and the sensors operable to measure the distances between the sensors and tops of squealer tip walls and outwardly facing walls within cavities of the squealer tips. The probe may be operably connected to a controller for sending signals to the controller indicating the first and second distances for controlling an air valve used for active clearance control. Two or more of the probe may be used to determine rotor centerline offset.

    摘要翻译： 多传感器间隙探头，其至少纵向和横向间隔开的第一和第二传感器可操作以分别测量传感器和纵向间隔开的旋转转子之间的第一和第二距离。 传感器可操作以测量径向外部涡轮叶片尖端与环绕叶片尖端的环形定子罩之间的叶片间隙。 叶片尖端可以是尖叫尖端，并且传感器可操作以测量传感器之间的距离，以及鸣叫器顶端壁之间的距离以及在尖叫尖端的空腔内的面向外壁的距离。 探头可以可操作地连接到控制器，用于向控制器发送信号，指示用于控制用于主动间隙控制的空气阀的第一和第二距离。 可以使用两个或更多个探头来确定转子中心线偏移。

    AIRCRAFT GAS TURBINE ENGINE BLADE TIP CLEARANCE CONTROL
    12.
    发明申请
    AIRCRAFT GAS TURBINE ENGINE BLADE TIP CLEARANCE CONTROL 有权
    飞机气涡轮发动机叶片间隙控制

    公开(公告)号：US20090037035A1

    公开(公告)日：2009-02-05

    申请号：US11833596

    申请日：2007-08-03

    申请人： John Erik Hershey ,  Brock Estel Osborn ,  Donald Lee Gardner ,  Rafael Jose Ruiz ,  William Lee Herron

    发明人： John Erik Hershey ,  Brock Estel Osborn ,  Donald Lee Gardner ,  Rafael Jose Ruiz ,  William Lee Herron

    IPC分类号： G06F17/18 ,  G06F15/18 ,  G06G7/48 ,  G06F17/00

    CPC分类号： F01D11/24 ,  F02C9/00 ,  F02C9/26 ,  F02C9/48 ,  F05D2270/305 ,  F05D2270/44 ,  F05D2270/70

    摘要： A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin adjusting the tip clearance by expanding or contracting the shroud before the engine command and may be based on monitored aircraft and/or aircraft crew data indicative of the engine. The aircraft and/or aircraft crew data may include communications between aircraft crew and air traffic control authorities or air traffic control surrogates. Determining when to begin adjusting the tip clearance may include using learning algorithms which may use the aircraft gas turbine engine's operating experience and/or operating experience of other jet engines on an aircraft containing the aircraft gas turbine engine and/or on other aircraft.

    摘要翻译： 一种方法和系统预期在改变发动机转速的发动机命令之前和之前调整旋转飞机燃气涡轮发动机叶片尖端和周围罩之间的叶片顶端间隙。 该方法可以包括通过在发动机命令之前扩展或收缩护罩来确定何时开始调整顶端间隙，并且可以基于指示发动机的受监视的飞行器和/或飞机机组数据。 飞机和/或飞机机组数据可以包括飞机机组人员和空中交通管制机构或空中交通管制代理人之间的通信。 确定何时开始调整尖端间隙可以包括使用学习算法，其可以使用飞机燃气涡轮发动机在包含飞机燃气涡轮发动机的飞机和/或其它飞行器上的其它喷气发动机的操作经验和/或操作经验。

    Eddy current wide probe
    16.
    发明授权
    Eddy current wide probe 有权
    涡流宽探头

    公开(公告)号：US06215300B1

    公开(公告)日：2001-04-10

    申请号：US09231881

    申请日：1999-01-14

    申请人： William Lee Herron

    发明人： William Lee Herron

    IPC分类号： G01N2782

    CPC分类号： G01N27/904

    摘要： An eddy current probe is configured with one axis of the electrical coil elongated to span a much larger distance than that of conventional coils. Thus, a single pass of the elongated coil can inspect a path of up to 100 times wider than the conventional coil. The parts of the eddy current probe include a pair of elongated ferrite cores disposed end-to-end in a housing block. A pair of receive coils are disposed in the housing block respectively surrounding the elongated ferrite cores. A transmit coil is wound around the receive coils in the housing block, and a pair of ferrite shields are disposed in the housing block sandwiching the transmit coil, the pair of receive coils, and the pair of elongated ferrite cores.

    摘要翻译： 涡电流探针被配置为使电线圈的一个轴线伸长以跨越比常规线圈大得多的距离。 因此，细长线圈的单次通过可以检测比常规线圈宽达100倍的路径。 涡流探针的部分包括在壳体块中端对端设置的一对细长铁氧体磁芯。 一对接收线圈分别围绕细长的铁氧体磁芯设置在壳体块中。 发射线圈缠绕在壳体块中的接收线圈周围，并且一对铁氧体屏蔽件设置在夹持发射线圈，一对接收线圈和一对细长铁氧体磁芯的壳体块中。

    Method for determining cyclic service life for rotational parts of a rotary machine
    17.
    发明授权
    Method for determining cyclic service life for rotational parts of a rotary machine 失效
    用于确定旋转机器的旋转部件的循环使用寿命的方法

    公开(公告)号：US5654500A

    公开(公告)日：1997-08-05

    申请号：US633330

    申请日：1996-04-17

    申请人： William Lee Herron ,  Thomas Joseph Martini

    发明人： William Lee Herron ,  Thomas Joseph Martini

    IPC分类号： G01N3/00 ,  G01N3/02 ,  G07C3/00

    CPC分类号： G01N3/00 ,  G07C3/00 ,  G01N2203/0066 ,  G01N2203/0218

    摘要： Total transient stress, which is the sum of residual, mechanical and thermal stresses, is calculated. Transient stresses are estimated using compressor discharge temperature and pressure, the rotational speed of the component and the elapsed time from the beginning of a transient. By using a general stress calculation, the total stress at the end of transients at each location in the rotary part being measured can be calculated. Maximum and minimum stress peaks are recorded for the transients and stress intensity factors for each location are calculated. Crack propogation is then calculated based on the stress intensity factors and the remaining life of the machine can then be calculated using new assumed crack length and design cycle of the machine.

    摘要翻译： 计算总瞬态应力，即残余，机械和热应力之和。 使用压缩机排放温度和压力，组件的旋转速度和从瞬态开始起的经过时间来估计瞬态应力。 通过使用一般的应力计算，可以计算在被测量的旋转部件中的每个位置处的瞬变结束时的总应力。 记录瞬态的最大和最小应力峰值，并计算每个位置的应力强度因子。 然后根据应力强度因子计算裂纹传播，然后可以使用新的假定裂纹长度和机器的设计周期来计算机器的剩余寿命。

    Aircraft gas turbine engine blade tip clearance control
    18.
    发明授权
    Aircraft gas turbine engine blade tip clearance control 有权
    飞机燃气涡轮发动机叶片顶端间隙控制

    公开(公告)号：US08126628B2

    公开(公告)日：2012-02-28

    申请号：US11833596

    申请日：2007-08-03

    申请人： John Erik Hershey ,  Brock Estel Osborn ,  Donald Lee Gardner ,  Rafael Jose Ruiz ,  William Lee Herron

    发明人： John Erik Hershey ,  Brock Estel Osborn ,  Donald Lee Gardner ,  Rafael Jose Ruiz ,  William Lee Herron

    IPC分类号： G06F19/00 ,  G06G7/70

    CPC分类号： F01D11/24 ,  F02C9/00 ,  F02C9/26 ,  F02C9/48 ,  F05D2270/305 ,  F05D2270/44 ,  F05D2270/70

    摘要： A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin adjusting the tip clearance by expanding or contracting the shroud before the engine command and may be based on monitored aircraft and/or aircraft crew data indicative of the engine. The aircraft and/or aircraft crew data may include communications between aircraft crew and air traffic control authorities or air traffic control surrogates. Determining when to begin adjusting the tip clearance may include using learning algorithms which may use the aircraft gas turbine engine's operating experience and/or operating experience of other jet engines on an aircraft containing the aircraft gas turbine engine and/or on other aircraft.

    摘要翻译： 一种方法和系统预期在改变发动机转速的发动机命令之前和之前调整旋转飞机燃气涡轮发动机叶片尖端和周围罩之间的叶片顶端间隙。 该方法可以包括通过在发动机命令之前扩展或收缩护罩来确定何时开始调整顶端间隙，并且可以基于指示发动机的受监视的飞行器和/或飞机机组数据。 飞机和/或飞机机组数据可以包括飞机机组人员和空中交通管制机构或空中交通管制代理人之间的通信。 确定何时开始调整尖端间隙可以包括使用学习算法，其可以使用飞机燃气涡轮发动机在包含飞机燃气涡轮发动机的飞机和/或其它飞行器上的其它喷气发动机的操作经验和/或操作经验。