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    SYSTEMS AND METHODS FOR ATTACHING A PROBE TO A CASING OF A GAS TURBINE ENGINE
    11.
    发明申请
    SYSTEMS AND METHODS FOR ATTACHING A PROBE TO A CASING OF A GAS TURBINE ENGINE 有权
    将探测器连接到气体涡轮发动机的系统和方法

    公开(公告)号：US20160084736A1

    公开(公告)日：2016-03-24

    申请号：US14489759

    申请日：2014-09-18

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Kurt Kramer Schleif ,  Zachary John Snider ,  Nathan Lee Brown ,  Andrea Booher Kretschmar ,  Michael Allen Ball

    IPC: G01M15/14 ,  G01D11/18 ,  G01D11/30

    CPC classification number: G01M15/14 ,  F01D17/02 ,  G01D11/30

    Abstract: A system for attaching a probe to a casing of a gas turbine engine is disclosed. The system may include a probe receptacle attachable to the casing. The probe receptacle may include an internal bore, a bayonet slot, a spring disposed within the internal bore adjacent to the bayonet slot, and a sealing surface within the internal bore. The system also may include a probe attachment assembly disposed about the probe and configured to engage the probe receptacle. The probe attachment assembly may include at least one bayonet positionable within the bayonet slot and a seal positionable adjacent to the sealing surface within the internal bore.

    Abstract translation: 公开了一种用于将探头附接到燃气涡轮发动机的壳体的系统。 该系统可以包括可附接到壳体的探针插座。 探针插座可以包括内孔，卡口槽，布置在邻近卡口槽的内孔内的弹簧以及内孔内的密封表面。 该系统还可以包括围绕探针设置的探测器附接组件，并且被配置成接合探针插座。 探针附接组件可以包括可定位在卡口槽内的至少一个卡口和可在内孔内靠近密封表面定位的密封件。

    SYSTEMS AND METHODS TO MONITOR A ROTATING COMPONENT
    12.
    发明申请
    SYSTEMS AND METHODS TO MONITOR A ROTATING COMPONENT 有权
    监控旋转部件的系统和方法

    公开(公告)号：US20150066389A1

    公开(公告)日：2015-03-05

    申请号：US14016930

    申请日：2013-09-03

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Senthilkumar Datchanamoorthy ,  Michael Allen Ball ,  Aninda Bhattacharya ,  Venkata Ramana Murthy Hemadribhotla

    IPC: F01D21/00 ,  G01B7/14 ,  G01M15/14

    CPC classification number: F01D21/003 ,  F01D11/14 ,  G01B7/14 ,  G01B21/16 ,  G01M15/14

    Abstract: A method is presented. The method includes selecting a first window of signals and a second window of signals from clearance signals representative of clearances between a rotating component and a stationary casing surrounding the rotating component, determining a first signed average power value corresponding to the first window of signals, and a second signed average power value corresponding to the second window of signals, determining a resultant value based upon the first signed average power value and the second signed average power value, and determining one or more defects or potential defects in the rotating component based upon the resultant value.

    Abstract translation: 提出了一种方法。 该方法包括从表示旋转部件和围绕旋转部件的固定壳体之间的间隙的间隙信号中选择信号的第一窗口和第二窗口信号，确定对应于第一信号窗口的第一带符号平均功率值，以及 对应于所述第二窗信号的第二有符号平均功率值，基于所述第一有符号平均功率值和所述第二带符号平均功率值确定合成值，以及基于所述第二有效平均功率值确定所述旋转分量中的一个或多个缺陷或潜在缺陷， 结果值。

    METHODS AND SYSTEMS FOR MONITORING ROTOR BLADES IN TURBINE ENGINES
    16.
    发明申请
    METHODS AND SYSTEMS FOR MONITORING ROTOR BLADES IN TURBINE ENGINES 审中-公开

    公开(公告)号：US20200165934A1

    公开(公告)日：2020-05-28

    申请号：US16200828

    申请日：2018-11-27

    Applicant: General Electric Company

    Inventor： Kurt Kramer Schleif ,  Michael Allen Ball ,  Mario Joseph Arceneaux ,  Andrew David Ellis ,  Vincent Carmona

    IPC: F01D21/00 ,  G01S7/42 ,  G01S11/02 ,  F01D21/14 ,  G01M15/14 ,  G01M7/02

    Abstract: A method for determining an arrival-time of a rotor blade that includes attaching an RF reader to a stationary surface and an RF tag to the rotor blade. Time-of-flight data points are collected via an RF monitoring process that includes: emitting an RF signal from the RF reader and recording a first time; receiving the RF signal at the RF tag and emitting a return RF signal by the RF tag in response thereto; receiving the return RF signal at the RF reader and recording a second time; and determining the time-of-flight data point as being the duration occurring between the first time and the second time. The RF monitoring process is repeated until multiple time-of-flight data points are collected. A minimum time-of-flight is determined from the multiple time-of-flight data points, and the arrival-time for the rotor blade is determined as being a time that corresponds to the minimum time-of-flight.

    System and method for transmitting sensor data from a rotating component of a turbomachine
    18.
    发明授权
    System and method for transmitting sensor data from a rotating component of a turbomachine 有权
    用于从涡轮机的旋转部件传送传感器数据的系统和方法

    公开(公告)号：US09530307B2

    公开(公告)日：2016-12-27

    申请号：US14599587

    申请日：2015-01-19

    Applicant: General Electric Company

    Inventor： Donald W. Shaw ,  Kurt Kramer Schleif ,  Mario Joseph Arceneaux ,  Michael Allen Ball

    IPC: G08C19/22 ,  G08C17/02 ,  F02C3/00 ,  G08C19/02 ,  H04Q9/00 ,  F01D25/00 ,  F01D17/08 ,  H01R39/08

    CPC classification number: G08C17/02 ,  F01D17/085 ,  F01D25/00 ,  F02C3/00 ,  F05D2270/303 ,  G08C19/02 ,  H01R39/08 ,  H04Q9/00 ,  H04Q2209/30 ,  Y02E10/72

    Abstract: A system for transmitting data from a rotating component of a turbomachine includes a plurality of thermal sensors coupled to corresponding rotatable components within the turbomachine where each thermal sensor generates a discrete analog signal indicative of temperature. A plurality of transmitter assemblies is coupled to an end of a rotor shaft of the turbomachine. The plurality of transmitter assemblies comprises a first transmitter assembly and a second transmitter assembly. The first transmitter assembly is configured to receive the discrete analog signals from the plurality of thermal sensors, multiplex the plurality of discrete analog signals into a single amplifier and an analog-to-digital converter to generate a single stream of digital data therefrom. The system also includes a slip ring assembly having a plurality of conductive rings where at least one of the conductive rings defines a digital signal path between the first transmitter assembly and a data acquisition system.

    Abstract translation: 用于从涡轮机的旋转部件发送数据的系统包括耦合到涡轮机内的相应可旋转部件的多个热传感器，其中每个热传感器产生指示温度的离散模拟信号。 多个发射器组件联接到涡轮机的转子轴的端部。 多个发射器组件包括第一发射器组件和第二发射器组件。 第一发射机组件被配置为从多个热传感器接收离散的模拟信号，将多个离散模拟信号复用到单个放大器和模数转换器中以从其产生单个数字数据流。 该系统还包括具有多个导电环的滑环组件，其中至少一个导电环在第一发射器组件和数据采集系统之间限定数字信号路径。

    Methods and systems for monitoring rotor blades in turbine engines
    20.
    发明授权
    Methods and systems for monitoring rotor blades in turbine engines 有权

    公开(公告)号：US11193388B2

    公开(公告)日：2021-12-07

    申请号：US16200828

    申请日：2018-11-27

    Applicant: General Electric Company

    Inventor： Kurt Kramer Schleif ,  Michael Allen Ball ,  Mario Joseph Arceneaux ,  Andrew David Ellis ,  Vincent Carmona

    IPC: F01D21/00 ,  G01S7/42 ,  G01M7/02 ,  F01D21/14 ,  G01M15/14 ,  G01S11/02

    Abstract: A method for determining an arrival-time of a rotor blade that includes attaching an RF reader to a stationary surface and an RF tag to the rotor blade. Time-of-flight data points are collected via an RF monitoring process that includes: emitting an RF signal from the RF reader and recording a first time; receiving the RF signal at the RF tag and emitting a return RF signal by the RF tag in response thereto; receiving the return RF signal at the RF reader and recording a second time; and determining the time-of-flight data point as being the duration occurring between the first time and the second time. The RF monitoring process is repeated until multiple time-of-flight data points are collected. A minimum time-of-flight is determined from the multiple time-of-flight data points, and the arrival-time for the rotor blade is determined as being a time that corresponds to the minimum time-of-flight.

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