Abstract: A method of determining a turbine inlet temperature for a gas turbine engine includes measuring pressure changes within a combustion section of the gas turbine engine during operation of the gas turbine engine to produce pressure versus time data, extracting a resonant frequency from the pressure versus time data, and calculating the turbine inlet temperature based solely on the resonant frequency.

Abstract: A method of detecting combustor flashback in a gas turbine engine includes positioning a dynamic pressure sensor within a combustion section having a flame tube, providing a flow of fuel to the gas turbine engine, and operating the gas turbine engine to establish a flame having a flame front spaced a non-zero distance from an outlet of the flame tube. The method also includes detecting pressure changes adjacent the flame tube to produce pressure signals, monitoring the amplitude of the signals provided by the dynamic pressure sensor, detecting a flashback signal within the signals provided by the dynamic pressure sensor, and varying the fuel flow in response to the detection of the flashback signal.

Abstract: A sensing system is provided. The sensing system includes a processor, a sensor node, a plurality of sensors, a power source and a controller. The sensor node is operably connected to the processor on an industrial side and to the sensors on a sensor side. The sensors each measure a parameter of the sensing system and transmit the parameter to the processor via the sensor node. The power source delivers power to the processor. The controller is in operable communication with the processor. The sensor node, disposed in close proximity to the sensors, converts a data protocol for each of the sensors to a different industrial protocol and transmits the converted data through a communication port via the industrial data protocol to the processor. The processor then collects the measurements of each parameter of the plurality of sensors, analyses the measurements and transmits the analyzed data to the controller.

Abstract: A hyper-redundant monitoring system and a gas turbine including the hyper-redundant monitoring system are provided. The hyper-redundant monitoring system includes a processor, a sensor node operably connected to the processor. The sensor node includes a plurality of sensors disposed in close proximity to one another such that a single parameter is measured by each of the plurality of sensors and each sensor is configured to transmit the parameter. The system also includes a power source and a controller in operable communication with the processor. The single parameter is output by each of the sensors and transmitted to the processor which collects the output parameters, analyzes the output parameters, and transmits analyzed data to the controller.

Abstract: A method of monitoring a rotor blade 14 is provided. The method includes disposing a probe 22 including an optical sensor 25 within a mounting hole in a turbine casing 36 of a turbine engine. A laser beam is them emitted by a light source 54 radially inward from the probe position onto a rotor blade tip 100 of the rotor blade 14. The rotor blade 14 is positioned such that it periodically passes the laser beam. The rotor blade tip 100 includes a predetermined pattern 120. The reflected light images from the rotor blade tip 100 are received by the optical sensor 25. From the reflected light images, a blade profile is constructed. Based on this constructed blade profile from the reflected light images off the predetermined pattern 120, a position of the rotor blade 14 is determined. A system of monitoring a rotor blade 14 is also provided.

Abstract: A system and a method for removing debris from a flow path of a cooling flow is provided. The system includes a turbine including at least one airfoil. A cooling flow is communicated to cooling holes via piping that includes a dead leg debris extractor in order to cool the airfoil. The dead leg debris extractor includes a means to capture and retain debris from the cooling flow continuously during online operation of the turbine.

Abstract: A system and a method for removing debris from a flow path of a cooling flow is provided. The system includes a turbine including at least one airfoil. A cooling flow is communicated to cooling holes via piping that includes a dead leg debris extractor in order to cool the airfoil. The dead leg debris extractor includes a means to capture and retain debris from the cooling flow continuously during online operation of the turbine.

Abstract: Systems and methods for volumetrically fabricating 3D objects. The system includes at least a controller operably connected to a build volume and one or more energy sources. The build volume defines a volumetric buildable size of the object to be fabricated and includes media for fabricating the object therein. The energy source(s) is configured to emit at least a first and second energy beam therefrom. The controller is configured to direct the first and second emitted energy beams towards an intersecting point in the build volume to begin fabricating the media therein. The energy from each of the first and second beams is not sufficient to fabricate the object out of the media. The object is fabricated once multiple beams intersect, as collectively, the energy of the intersecting beams is sufficient to fabricate the object.

Abstract: A system for powering instrumentation of a generator wirelessly via magnetic induction is provided. The system includes a generator having a power generating source disposed within its casing to convert the electromagnetic energy produced by the generator into electrical energy that may be stored in an energy storage device. This stored energy may then be utilized by at least one sensing component within the generator casing and configured to measure and collect operational data related to the generator. A method for powering a wireless sensor within a generator via magnetic induction is also provided.

Abstract: A gas turbine engine component formed of material having phononic regions. The phononic regions are formed of metallic glass nanostructures. The phononic regions modify the behavior of the phonons and control heat conduction.

Abstract: A gas turbine engine component formed of material having phononic regions. The phononic regions are formed of non-metallic nanostructures. The phononic regions modify the behavior of the phonons and control heat conduction.

Abstract: A gas turbine engine component formed of material having phononic regions. The phononic regions are formed of anisotropic nanostructures that are oriented in different directions than the bulk of the material forming the gas turbine engine component. The phononic regions modify the behavior of the phonons and manage heat conduction.

Abstract: A gas turbine engine component formed of material having phononic regions. The phononic regions are formed of doped nanostructures. The phononic regions modify the behavior of the phonons and control heat conduction.

Abstract: A method and a system to characterize the velocity of a fluid flow through a flow channel using particle image velocimetry with one camera is provided. The method includes introducing a fluid flow into the fluid channel. The fluid includes fluid particles and tracer particles. At least two planar cross sections of the fluid flow are illuminated by a light source of a different color and spaced apart by a fixed distance. Successive images are captured with a single image receiver such as a camera such that each illuminated planar cross section is captured separately with the image receiver. From the captured images, a velocity of the fluid flow through the channel is determined by a processor.

Abstract: A method and system to accurately characterize the velocity of a fluid flow through a flow channel using particle image velocimetry is provided. The method includes introducing a plurality of seeding particles to the fluid flow. The seeding particles are essentially two dimensional such that each particles length and width are much greater than its thickness. At least two closely spaced pluses of light are repetitively delivered to the fluid flow, each pulse of light illuminating a successive planar cross section of the fluid flow in a flow direction. Images of each illuminated cross section are captured using an image receiver. A processor receives the images from the image receiver and analyzes the captured images in order to characterize the velocity of the fluid flow.

Abstract: A gas turbine engine component formed of material having phononic regions. The phononic regions are formed of alloys or allotropes of the material. The phononic regions modify the behavior of the phonons and control heat conduction.

Abstract: A gas turbine engine component formed of material having phononic regions. The phononic regions are formed of void nanostructures. The phononic regions modify the behavior of the phonons and manage heat conduction.

Abstract: A sensing system is provided. The sensing system includes a processor, a sensor node, a plurality of sensors, a power source and a controller. The sensor node is operably connected to the processor on an industrial side and to the sensors on a sensor side. The sensors each measure a parameter of the sensing system and transmit the parameter to the processor via the sensor node. The power source delivers power to the processor. The controller is in operable communication with the processor. The sensor node, disposed in close proximity to the sensors, converts a data protocol for each of the sensors to a different industrial protocol and transmits the converted data through a communication port via the industrial data protocol to the processor. The processor then collects the measurements of each parameter of the plurality of sensors, analyses the measurements and transmits the analyzed data to the controller.

Abstract: A hyper-redundant monitoring system and a gas turbine including the hyper-redundant monitoring system are provided. The hyper-redundant monitoring system includes a processor, a sensor node operably connected to the processor. The sensor node includes a plurality of sensors disposed in close proximity to one another such that a single parameter is measured by each of the plurality of sensors and each sensor is configured to transmit the parameter. The system also includes a power source and a controller in operable communication with the processor. The single parameter is output by each of the sensors and transmitted to the processor which collects the output parameters, analyzes the output parameters, and transmits analyzed data to the controller.

Abstract: Systems and methods for volumetrically fabricating 3D objects. The system includes at least a controller operably connected to a build volume and one or more energy sources. The build volume defines a volumetric buildable size of the object to be fabricated and includes media for fabricating the object therein. The energy source(s) is configured to emit at least a first and second energy beam therefrom. The controller is configured to direct the first and second emitted energy beams towards an intersecting point in the build volume to begin fabricating the media therein. The energy from each of the first and second beams is not sufficient to fabricate the object out of the media. The object is fabricated once multiple beams intersect, as collectively, the energy of the intersecting beams is sufficient to fabricate the object.