Abstract: A casing for a turbomachine is disclosed. The casing includes a casing body including an interior surface and an exterior surface. At least one sensor is coupled relative to the interior surface of the body, the at least one sensor at most only partially extending through the body. A communications lead is operatively coupled to the at least one sensor, and extends circumferentially along the interior surface of the body.

Abstract: A wireless sensor antenna system for a turbomachine including a rotating blade including a passive sensor is disclosed. The wireless sensor antenna system includes an antenna extending continuously along a circumferential interior surface of a casing of the turbomachine that surrounds the rotating blade. The antenna is configured to receive a return wireless signal from the passive sensor. A power transmission element extends along the at least portion of the circumferential interior surface of the casing to power the passive sensor by emitting an electromagnetic signal to power the passive sensor.

Abstract: A mounting member for a sensor for a turbomachine having an axis is disclosed. The mounting member includes a body configured to mount to a portion of a circumferential interior surface of a casing of the turbomachine. An opening extends through a radially inner surface of the body, and is configured to position the sensor facing radially inward relative to the axis. A passage in the body extends longitudinally through the body to route a communications lead of the sensor circumferentially relative to the circumferential interior surface of the casing.

Abstract: A mounting system for a tool for machining a half-shell casing of a turbomachine is disclosed. The mounting system includes a base frame including a mounting element configured to fixedly mount the base frame to the half-shell casing, wherein the base frame spans at least a portion of the half-shell casing. A tool mount includes a first end pivotally coupled to the base frame to pivot about a pivot axis that is substantially parallel relative to an axis of the half-shell casing, and a second end configured to couple to and position the tool for machining the half-shell casing.

Abstract: An optical sensor for a rotating blade stage of a turbomachine is disclosed. The optical sensor includes a housing to be mounted relative to a circumferential interior surface of a casing of the turbomachine. Optical fiber(s) are operatively coupled to the housing for communicating: an optical signal for sending toward the rotating blade stage and a return optical signal reflected by the rotating blade stage, through the casing. An optical signal redirecting element is configured to redirect the optical signal from optical fiber(s) inwardly toward the rotating blade stage relative to the casing, and redirect the return optical signal reflected by the rotating blade stage into the at least one optical fiber. Optical fiber(s) have a longitudinal shape configured to follow the circumferential interior surface of the casing.

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. Strength-of-signal data points are collected via an RF monitoring process that includes: emitting an RF signal from the RF reader; 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; measuring a signal strength of the return RF signal as received by the RF reader; and determining the strength-of-signal data point as being equal to the measured signal strength. The RF monitoring process is repeated until multiple strength-of-signal data points are collected. A maximum strength-of-signal is determined from the multiple strength-of-signal data points, and the arrival-time for the rotor blade is determined as being a time that corresponds to the maximum strength-of-signal.

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.

Abstract: A method for determining an arrival-time of a rotor blade in a turbine engine that includes the steps of: having an RF reader attached to a stationary surface in the turbine engine; having an RF tag attached to a first region of the rotor blade; having a reference RF tag attached to a rotating structure near the RF tag; in relation to a first revolution of the rotor blade occurring during the operation of the turbine engine, collecting an arrival-time for each of the RF tag and the reference RF tag with the RF reader via an RF monitoring process; comparing the arrival-time of the RF tag to the arrival-time of the reference RF tag to determine an arrival-time test result for the first region of the rotor blade for the first revolution.

Abstract: The present application thus provides a thermal barrier coating spallation detection system for a gas turbine. The thermal barrier coating spallation detection system may include a hot gas path component with a phosphor layer and a thermal barrier coating, a stimulant radiation source, and an optical device such that the optical device directs stimulant radiation at the thermal barrier coating and receives emission radiation. A change in the received emission radiation indicates spallation of the thermal barrier coating.

Abstract: Systems and methods include a blade monitoring system. The blade monitoring system includes a processor. The processor is configured to receive a sensor signal from a sensor configured to observe a blade of the turbomachinery.

Abstract: In one embodiment, a blade monitoring system is provided. The blade monitoring system includes a processor. The processor is configured to receive a sensor signal from a sensor configured to observe a blade of the turbomachinery, and to derive a measurement based on a marking disposed on the blade of the turbomachinery, wherein the marking comprises a continuous feature. The processor is also configured to display the measurement to an operator of the turbomachinery.

Abstract: The present application thus provides a thermal barrier coating spallation detection system for a gas turbine. The thermal barrier coating spallation detection system may include a hot gas path component with a phosphor layer and a thermal barrier coating, a stimulant radiation source, and an optical device such that the optical device directs stimulant radiation at the thermal barrier coating and receives emission radiation. A change in the received emission radiation indicates spallation of the thermal barrier coating.

Abstract: An extension arm for attachment to a resistance welding hand piece is disclosed. The extension arm may include an elongated main body extending between a first end and a second end. The first end of the elongated main body may be attachable to the hand piece such that the second end of the elongated main body is spaced apart from the hand piece. The extension arm also may include an electrode extending from the second end of the elongated main body. The electrode may be in electrical communication with the hand piece by way of at least one electrical pathway.

Abstract: Methods and systems for communicating a signal between a rotating antenna and a plurality of stationary antennae based on an axial displacement of the rotating antenna are provided. In one example, the method can include obtaining one or more measurements of an axial displacement of the rotating antenna from one or more axial displacement sensors. The method can further include determining a selected stationary antenna from the plurality of stationary antennae based at least in part on the measurements of an axial displacement of the rotating antenna. The method can further include activating the selected stationary antenna to communicate a signal with the rotating antenna. The method can further include communicating a signal between the rotating antenna and the selected stationary antenna.

Abstract: A system for attaching a device to a rotating shaft is provided herein. The system may include a rotating shaft, a telemetry transmitter positioned about the rotating shaft, and a housing positioned about the telemetry transmitter. The telemetry transmitter may be trapped by the housing. The system also may include a connector configured to connect the housing to the rotating shaft.

Abstract: Methods and systems for communicating a signal between a rotating antenna and a plurality of stationary antennae based on an axial displacement of the rotating antenna are provided. In one example, the method can include obtaining one or more measurements of an axial displacement of the rotating antenna from one or more axial displacement sensors. The method can further include determining a selected stationary antenna from the plurality of stationary antennae based at least in part on the measurements of an axial displacement of the rotating antenna. The method can further include activating the selected stationary antenna to communicate a signal with the rotating antenna. The method can further include communicating a signal between the rotating antenna and the selected stationary antenna.

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: A system for packaging electronic components in a rotatable shaft includes an annular carrier shaft having a first end that is axially spaced from a second end and an inner surface that is radially spaced from an outer surface, and a plurality of transmitter assemblies annularly arranged within the carrier shaft. Each transmitter assembly includes a transmitter housing radially supported within the carrier shaft via a pair of circumferentially spaced rail members. Each transmitter assembly comprises a daughter board that extends laterally and longitudinally across a bottom portion of the transmitter housing and at least one electronic component electrically coupled to the daughter board. The electronic component extends substantially perpendicular to the daughter board within the transmitter housing.

Abstract: The present disclosure is directed to a system for attaching an instrument lead to a gas turbine engine component. The system includes a gas turbine engine component that includes a surface. A first sleeve couples to the surface of the gas turbine engine component. The first sleeve defines a first sleeve passageway extending therethrough. An instrument lead extends through the first sleeve passageway. A first potting material couples the instrument lead to the first sleeve to prevent the instrument lead from moving longitudinally relative to the first sleeve.

Abstract: A system for routing rotatable wire bundles which extend from a rotor shaft of a turbomachine includes a plurality of wire bundles which extend outwardly from an inner passage of the rotor shaft of the turbomachine. An annular wire barrel is coupled to an end of the rotor shaft. A plurality of thru-holes is defined within and/or by the wire barrel. The plurality of thru-holes is annularly arranged therein. Each thru-hole extends through an aft wall of the wire barrel and is circumferentially spaced from adjacent thru-holes. Each wire bundle extends individually through a corresponding thru-hole of the plurality of thru-holes.