General Electric Company

Ge Aviation Systems Limited

Unison Industries, Inc.

Amphenol Thermometrics, Inc.

Aaron Jay Knobloch

David Mulford Shaddock

Stacey Joy Kennerly

Ertugrul Berkcan

Emad Andarawis Andarawis

David Richard Esler

Jeffrey Bernard Fortin

David William Vernooy

Harry Kirk Mathews, Jr

William Albert Challener

Richard J Saia

Canan Uslu Hardwicke

Kanakasabapathi Subramanian

Joseph Alfred Iannotti

Yizhen Lin

Glen Peter Koste

Alfred Albert Mancini

Marco Francesco Aimi

Douglas Scott Byrd

Vinayak Tilak

Jason Harris Karp

Anis Zribi

Wei-Cheng Tian

Minesh Ashok Shah

David Joseph Najewicz

Leonardo Cesar Kammer

Avinash Srikrishnan Kashyap

Ansas Matthias Kasten

Sachin Narahari Dekate

Joseph Bernard Steffler

Sameer Dinkar Vartak

Nicholas Okruch, Jr

Weizhuo Li

Andrew Scott Kessie

David Robert O'Connor

Boon Kwee Lee

Brian Allen Engle

Chukwueloka Obiora Umeh

Jie Jiang

Sergey Alexandrovich Zotov

Christian M Heller

Robert Edward Goeller

David John Geer

Douglas Scott Jacobs

Gerald Schultz

Brian Jacob Loyal

Naresh Kesa Van Rao

Seema Somani

Glen Peter Kose

Mudassar Ali Muhammad

William J Myers

Harry Kirk Mathews

Jr Harry Kirk Mathews

Systems and methods disclosed herein use a multi-color pyrometer configured to determine a first temperature in a high temperature range and a single-color pyrometer configured to determine second temperature in a low temperature range. The system uses information gained from determination of the first temperature in the high temperature range to facilitate later determining the second temperature in the low temperature range. The first temperature in the high temperature range and the second temperature in the low temperature range are used to monitor and control different engine operations that occur at different times.

Systems and methods for measuring temperature

An apparatus and method for determining a temperature in a system having an object, an optical sensor, and a gas flow passing between the object and the optical sensor, sensing, with the optical sensor, a wavelength emitted from the object and indicative of an attenuation, sensing, with the optical sensor, a wavelength emitted from the object and indicative of a temperature of at least one of the object or the gas; and calculating a temperature of the gas using the wavelengths.

Thermal measurement system

An accelerometer includes a controller, a light source operatively coupled to the controller, and a bifurcated waveguide coupled to the light source and configured to receive light output by the light source. The bifurcated waveguide includes a first waveguide portion and a second waveguide portion. The accelerometer also includes a first resonator operatively coupled to the controller and configured to receive light from the first waveguide portion, and a second resonator operatively coupled to the controller and configured to receive light from the second waveguide portion. The first resonator includes a first proof mass, and the second resonator includes a second proof mass.

Resonant opto-mechanical accelerometer for use in navigation grade environments

A gas turbine engine and system for measuring torque for a gas turbine engine shaft is provided. The system may include a first sensor module, a second sensor module, a first coupler, a second coupler, and a static antenna. The first and second sensor modules may include strain sensors positioned on the gas turbine engine shaft. The first coupler may be positioned on the gas turbine engine shaft and electrically connected with the first sensor module. The second coupler may be positioned on the gas turbine engine shaft and electrically connected with the second sensor module. The static antenna may include a first band and a second band. The first signal band may be in operable communication with the first sensor module and positioned radially outward from the first coupler. The second signal band may be in operable communication with the second sensor module and positioned radially outward from the second coupler.

Turbine engine shaft torque sensing

An aircraft including a jet engine including a core having a compressor and combustion chamber, and a particulate sensor located within the core and a particulate detection method for an aircraft having a jet engine where the method includes sensing particulates within the core and providing a corresponding value for the sensed particulates and providing an indication related thereto.

Aircraft and particulate detection method

A system for sensing the position of a movable object includes a polarization maintaining fiber configured to receive light from a light source; an optical system configured to rotate an angle of polarization of the light by a first predetermined angle; a low birefringence fiber connected to the optical system at a first end and having a mirror connected to a second end configured to reflect the light and rotate the angle of polarization at a second predetermined angle, the second end being configured to overlap a magnetic field of the a magnet attached to the object. The angle of polarization is rotated to a third predetermined angle proportional to at least one of the strength of the magnetic field and an amount of the overlap. The optical system is configured to decompose the third predetermined angle into a first component and a second component. A detector is configured to detect a differential between the first and second components indicative of the amount of the overlap.

Fiber optic sensor for position sensing

A battery cell that comprises a sensing platform with sensing elements configured to provide information about in-situ characteristics and parameters of the battery cell. Embodiments of the battery cell can have the sensing platform integrated into the structure of the battery cell, as a separate structure incorporated in the battery cell, and combinations thereof. In one embodiment, the battery cell comprises a sensing platform having sensing elements proximate a localized measurement region, where the sensing platform comprises a substrate with material layers disposed thereon. The material layers comprise at least one sensing layer that forms the sensing elements so that the sensing elements are responsive to properties of the battery cell.

Battery cell with integrated sensing platform

A method of method of forming a wide band-gap semiconductor transient voltage suppressor (TVS) assembly and a system for a transient voltage suppressor (TVS) assembly are provided. The TVS assembly includes a connecting component configured to electrically couple a first electrical component to a second electrical component located remotely from the first electrical component through one or more electrical conduits and a transient voltage suppressor device positioned within the connecting component and electrically coupled to the one or more electrical conduits wherein the TVS device includes a wide band-gap semiconductor material.

Method and system for lightning protection with distributed transient voltage suppression

A sensor assembly for electric field sensing is provided. The sensor assembly may include an array of Micro-Electro-Mechanical System (MEMS)-based resonant tunneling devices. A resonant tunneling device may be configured to generate a resonant tunneling signal in response to the electric field. The resonant tunneling device may include at least one electron state definer responsive to changes in at least one respective controllable characteristic of the electron state definer. The changes in the controllable characteristic are configured to affect the tunneling signal. An excitation device may be coupled to the resonant tunneling device to effect at least one of the changes in the controllable characteristic affecting the tunneling signal. A controller may be coupled to the resonant tunneling device and the excitation device to control the changes of the controllable characteristic in accordance with an automated control strategy configured to reduce an effect of noise on a measurement of the electric field.

MEMS-based resonant tunneling devices and arrays of such devices for electric field sensing

An optical pressure sensor interrogation system is provided. The system includes a light source for providing an optical signal to an optical pressure sensor and an optical coupler for receiving a reflected signal from the optical pressure sensor. The optical coupler splits the reflected signal and provides a first portion of the reflected signal to a first optical detector. The system further includes a filter for receiving a second portion of the reflected signal and providing a filtered signal to a second optical detector and a processing circuitry configured to obtain pressure based on a division or a subtraction of light intensities of the first and the second optical detector output signals. The processing circuitry is further configured to provide a feedback signal to the light source to control a wavelength of the optical signal.

Self-calibrated interrogation system for optical sensors

An Active Combustion Control System and method provides for monitoring combustor pressure and modulating fuel to a gas turbine combustor to prevent combustion dynamics and/or flame extinguishments. The system includes an actuator, wherein the actuator periodically injects pulsed fuel into the combustor. The apparatus also includes a sensor connected to the combustion chamber down stream from an inlet, where the sensor generates a signal detecting the pressure oscillations in the combustor. The apparatus controls the actuator in response to the sensor. The apparatus prompts the actuator to periodically inject pulsed fuel into the combustor at a predetermined sympathetic frequency and magnitude, thereby controlling the amplitude of the pressure oscillations in the combustor by modulating the natural oscillations.

Apparatus and method for gas turbine active combustion control system

A high-temperature pressure sensor is provided. The sensor includes a quartz substrate with a cavity etched on one side. A reflective coating is deposited on at least a portion of the cavity. The sensor further includes a ferrule section coupled to the quartz substrate with the cavity therebetween. The cavity exists in a vacuum, and cavity gap is formed between the reflective metal coating and a surface of the ferrule. The sensor also includes an optical fiber enclosed by the ferrule section and extending from the cavity gap to an opposing end of the ferrule section and a metal casing surrounding the ferrule section and the quartz substrate with an opening for said optical fiber extending therefrom. The pressure applied to the quartz substrate changes the dimensions of the cavity gap and a reflected signal from the reflective coating is processed as a pressure.

High temperature optical pressure sensor and method of fabrication of the same

According to some embodiments, a first layer of doped material may be provided to form a resistor. A second layer of undoped material may then be formed on the first layer. The first layer might comprise, for example, a layer of doped silicon carbide while the second layer comprises a layer of undoped silicon carbide. The resistance of the resistor may then be measured to determine a temperature.

Thermistor having doped and undoped layers of material

A method of manufacturing an ignition device is provided. The method includes patterning a plurality of resistors on a membrane to form heating elements and thermally isolating the heating elements from an external environment via a cavity disposed adjacent to the heating elements.

Method of making an ignition device

A method for assembling a Fabry-Perot interferometer includes depositing a first metal layer on an end portion of a ferrule, depositing a second metal layer on a back portion of a die, placing the first metal layer and the second metal layer in contact with each other with respective first and second orifices aligned with respect to each other, and bonding the ferrule to the die by thermo compression. The resulting interferometer includes a glass die with a cavity, a silicon diaphragm disposed over the opening of the cavity and bonded to the glass die, a ferrule bonded to the glass die by thermo compression with the first and second orifices being aligned to each other, and an optical fiber inserted through the other end of the ferrule in direct contact to a back portion of the die and aligned with the first orifice.

High-temperature pressure sensor and method of assembly

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Mechanicville, NY, United States of America

Aaron Jay Knobloch