General Electric Company

Ford Global Technolgoies, LLC

Ge Infrastructure Technology, LLC

General Electric Technology Gmbh

Kurt Kramer Schleif

Andrew David Ellis

Mario Joseph Arceneaux

Donald Shaw

Michael Allen Ball

Zachary John Snider

Robert D Jones

Robert Michel

Seung-Woo Choi

Philip Michael Caruso

Gregory Quentin Brown

Vincent Carmona

Nathan Lee Brown

Jong Youn Pak

Matthew Ryan Ferslew

Andrew Clifford Hart

Fernando Jorge Casanova

Peter Ping-Liang Sue

Josef Scott Cummins

Fabian Gubelmann

Francesco Soranna

Bruce Howard Whittle

Andrea Booher Kretschmar

David Howard Syck

Roman Stefan Peter

Paul Walter Dausacker

Timothy J Kapelanski

Michael Davis Jacobs

Thomas Gloor

Srikanth Chandrudu Kottilingam

Canan Uslu Hardwicke

Stephen Paul Wassynger

David Michael Russell

Sylvain Pierre

Glen Alan Aussiker

Jochen E Scheuing

William J Fox

Elton R Eaton, Iii

Brian B Wampler

Donald W Shaw

Cale Brittain

Brian J Wampler

Robert David Jones

An apparatus and method for radiation measurement are used to determine clearance of a rotating gas turbine component. The apparatus includes a probe body on a stationary component outward of the rotating component and a pair of sensor assemblies coupled to the probe body. Each sensor assembly includes a plurality of prisms coupled to the probe body Each prism of the plurality of prisms has a distinct angular orientation to direct radiation from the focusing lens to the rotating component surface off-axis with respect to an axis of the respective radiation source of the pair of radiation sources and with less directional variation than radiation from the respective radiation source.

Apparatus and method for transmitting radiation to a rotating component

A sensor system for a turbomachine having an axis is disclosed. The sensor system includes a mounting member including a body configured to be mounted to a circumferential slot defined in at least a circumferential portion of a circumferential interior surface of a casing of the turbomachine. A plurality of sensors is coupled to the mounting member and configured to measure an operational parameter of the turbomachine.

Systems and methods for sensors on circumferential interior surface of turbomachine casing

A sensor system for a turbomachine having an axis is disclosed. The sensor system includes a mounting member including a body configured to be mounted to only a circumferential portion of a circumferential interior surface of a casing of the turbomachine. A plurality of sensors are coupled to the mounting member and configured to measure an operational parameter of the turbomachine.

Systems and methods for sensors on only part of circumferential interior surface of turbomachine casing

A milling device for machining a slot into an inner surface of a casing for a gas turbine engine. The milling device includes a frame assembly including multiple structural guides configured to engage structural features on the inner surface of the casing to maintain an axial position of the milling device relative to a longitudinal axis of the casing. The milling device also includes a milling cutter coupled to the frame assembly. The milling device is configured to be displaced in a circumferential direction relative to the longitudinal axis to machine the slot, via the milling cutter, along the inner surface of the casing in the circumferential direction.

System and method for machining a slot in an inner surface of a casing for a gas turbine engine

Thermocouples for high temperature applications are provided. A thermocouple includes a vessel formed from a dielectric material, the vessel defining a first chamber and a second chamber, the first chamber and second chamber in fluid communication. The thermocouple further includes a first thermoelement disposed in the first chamber, the first thermoelement formed from a first thermoelectric material. The thermocouple further includes a second thermoelement disposed in the second chamber, the second thermoelement formed from a second thermoelectric material different from the first thermoelectric material, and wherein the second thermoelement is a liquid at operating conditions of the thermocouple.

Thermocouples for high temperature applications

A turbine engine including a stationary component having a probe opening, a plurality of rotor blades rotatable relative to the stationary component, and a sensor assembly disposed within the probe opening. The sensor assembly includes a sensor and a shutter mechanism having a shutter frame with a sensing window and at least one leaf member coupled to the shutter frame. The sensor assembly includes an actuator including a rotatable member having a receiving slot and a stator having a stopper member within the receiving slot. The rotatable member rotates relative to the stator over a range of motion defined relative to the stopper member, and the rotatable member is coupled to the at least one leaf member such that rotating the rotatable member in a first direction uncovers the sensing window, and such that counter-rotating the rotatable member in a second direction covers the sensing window with the at least one leaf member. Selectively covering the sensor when not in use protects the sensor from exposure to harsh conditions, extending its operative life.

Gas turbine sensor assembly and associated shutter mechanism

A measurement system for a gas turbine engine is provided. The measurement system comprises a sensor assembly. The measurement system also includes multiple sensors coupled to the sensor assembly. The sensor assembly is configured to be removably inserted within a space defined by a circumferential track embedded within an inner diameter of a casing of the gas turbine engine without having to disassemble the casing.

System and method for removably inserting a sensor assembly into a compressor casing

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.

Sensor mounting for circumferential interior surface of turbomachine casing

A system is provided with a measurement system having a light source, a light sensor, and a controller coupled to the light source and the light sensor. The controller is configured to determine a clearance between a rotor and a casing at least partially based on an interruption of light transmitted from the light source to the light sensor.

System and method for optical measurements in a rotary machine

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. The processor is also configured to derive a measurement based on a marking disposed on the blade of the turbomachinery, wherein the marking comprises a discrete feature; and to display the measurement to an operator of the turbomachinery

System and method for turbomachinery blade diagnostics via discrete markings

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.

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.

Methods and systems for monitoring rotor blades in turbine engines

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.

Mounting system for tool for machining circumferential interior surface of turbomachine casing

A system is provided with a measurement system having a plurality of light sources, a plurality of light sensors, and a controller coupled to the plurality of light sources and the plurality of light sensors. The controller is configured to monitor one or more parameters between a rotor and a casing at least partially based on an interruption or a transmission of one or more paths of light from the plurality of light sources to the plurality of light sensors.

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Greenville, SC, United States of America

Kurt Kramer Schleif