General Electric Company

Kenneth Gordon Herd

Evangelos Trifon Laskaris

Richard Andrew Ranze

Robert Adolph Ackermann

Bizhan Dorri

Thomas James Batzinger

Shridhar Champaknath Nath

Mark Ernest Vermilyea

Yuri Alexeyevich Plotnikov

Clifford Bueno

Curtis Wayne Rose

Raymond E Gabis

Nelson R Corby, Jr

Paul Shadforth Thompson

John Eric Tkaczyk

Xianrui Huang

William A Edelstein

Minfeng Xu

Sayed-Amr A El-Hamamsy

Charles S Korman

Constantinos Minas

Robert Arvin Hedeen

Richard Nils Dawson

James B Archibald

Gregory Alan Mohr

Clive W Reed

Kenneth W Lay

Michael Robert Hopple

Sandeep Kumar Dewangan

Carl Stephen Lester

Elizabeth Lockenberg Dixon

Gregory F Hayworth

Guanzhong Gao

Thompson Paul S

Evangelo T Laskaris

Bizham Dorri

Peter Angus Morgan

Robert Henry Becker, Jr

Dennis Michael Walsh

Ernest L Moore

Nelson Raymond Corby

A computed radiography (CR) system for imaging an object is provided. The system includes a radiation source, a storage phosphor screen, an illumination source and a two dimensional imager. The radiation source is configured to irradiate the storage phosphor screen, and the storage phosphor screen is configured to store the radiation energy. The illumination source is configured to illuminate at least a sub-area of the storage phosphor screen to stimulate emission of photons from the storage phosphor screen. The two dimensional (2D) imager is configured to capture a two dimensional image from the storage phosphor screen using the stimulated emission photons. A method of reading a storage phosphor screen is also provided. The method includes illuminating at least a sub-area of the storage phosphor screen using an illumination source to stimulate emission of photons from the storage phosphor screen. The method further includes capturing at least one 2D image using a 2D imager, from at least a sub-array of the storage phosphor screen using the stimulated photons.

Method for registering a storage phosphor screen

Computed radiography systems and methods of use

A monitoring system includes at least one partial discharge (PD) sensor. The PD sensor is configured to monitor a component of an aircraft wiring system and to acquire a monitoring signal. A method embodiment for monitoring an aircraft wiring system includes acquiring a number of monitoring signals for a number of components of the aircraft wiring system using a number of partial discharge PD sensors. The method further includes conveying the monitoring signals from at least one of the PD sensors to a data acquisition system.

Monitoring system and method for wiring systems

A pulsed eddy current sensor probe includes a sensor array board. A number of sensors are arranged on the sensor array board and are operable to sense and generate output signals from the transient electromagnetic flux in a part being inspected. Each of the sensors has a differential output with a positive and a negative output. At least one drive coil is disposed adjacent to the sensors and is operable to transmit transient electromagnetic flux into the part. A first and a second multiplexer are arranged on the sensor array board and are operable to switch between the sensors. The first and second multiplexers are connected to the positive and negative outputs of the sensors, respectively.

Pulsed eddy current sensor probes and inspection methods

A pulsed eddy current two-dimensional sensor array probe for electrically conducting component inspection includes a drive coil disposed adjacent to a structure under inspection, a pulse generator connected to the drive coil and operable to energize in a pulsed manner the drive coil to transmit transient electromagnetic flux into the structure under inspection, and an array of sensors arranged in a two-dimensional array and substantially surrounded by the drive coil and operable to sense and generate output signals from the transient electromagnetic flux in the structure under inspection.

Pulsed eddy current two-dimensional sensor array inspection probe and system

A method for in-situ eddy current inspection of at least one coated component includes applying a drive pulse at a measurement position on an outer surface of the coated component, while the coated component is installed in an operational environment of the coated component. The coated component includes a base metal and a coating disposed on the base metal. The method further includes receiving a response signal from the coated component, comparing the response signal with a reference signal to obtain a compared signal, analyzing the compared signal for crack detection, and determining whether a crack near the measurement position has penetrated into the base metal, if the presence of the crack in the coating is indicated.

Method for in-situ eddy current inspection of coated components in turbine engines

An embedded eddy current inspection apparatus includes a substrate having an opening, and a test eddy current coil (&ldquo;test coil&rdquo;) affixed to the substrate near the opening. An internally inspected multilayer component structure includes an upper layer, a lower layer, and an eddy current probe embedded between the upper and lower layers. The eddy current probe includes the test coil facing a subject layer selected from the upper and lower layers. A method of inspecting a multilayer component structure includes simultaneously energizing the test coil and a reference eddy current coil (&ldquo;reference coil&rdquo;) embedded between the upper and lower layers and facing the subject layer. The reference coil is located in a reference region of the multilayer structure. A test signal from the test coil is compared with a reference signal from the reference coil, to determine whether a flaw is present in the subject layer near the test coil.

Embedded eddy current inspection apparatus, system, and method

A system and method for radiographic inspection of aircraft fuselages includes a radiation source preferably located inside of the fuselage and a radiation detector preferably located outside of the fuselage. A source positioning system is provided for moving the radiation source longitudinally with respect to the fuselage, and a detector positioning system is provided for positioning the radiation detector in longitudinal alignment with the radiation source. The detector positioning system also moves the radiation detector circumferentially with respect to the fuselage. In operation, the radiation detector is moved over the fuselage in a circumferential direction while the radiation source illuminates an adjacent region of the fuselage with radiation.

High speed digital radiographic inspection of aircraft fuselages

A cryostatic vessel is radially interconnected inside a tubular thermal shield A shield first endplate includes a plurality of spacers which are disposed in axial abutment with a corresponding first endplate of the vessel during assembly. A shield second endplate is disposed in axial abutment against an opposite end of the shield, and includes alignment holes receiving corresponding alignment pins extending from an opposite endplate of the vessel. The spacers maintain a predetermined clearance between the endplates of the vessel and shield which clearance is precisely maintained upon fixedly joining both shield endplates to the shield.

Cryostat, cryostat positioning method and cryostat alignment set

A cryostatic vessel is radially interconnected inside a tubular thermal shield. A shield first endplate includes a plurality of spacers which are disposed in axial abutment with a corresponding first endplate of the vessel during assembly. A shield second endplate is disposed in axial abutment against an opposite end of the shield, and includes alignment holes receiving corresponding alignment pins extending from an opposite endplate of the vessel. The spacers maintain a predetermined clearance between the endplates of the vessel and shield which clearance is precisely maintained upon fixedly joining both shield endplates to the shield.

Cryostat, cryostat positioning method, and cryostat alignment set

An MR magnet assembly includes a cylindrical vessel for housing a superconducting magnet and having a vacuum between its inner and outer walls. The vessel defines a magnet bore for receiving a patient to be imaged. A gradient coil assembly is mounted in the bore adjacent the inner wall of the magnet assembly. To reduce gradient coil noise, the inner wall is constructed of a non-conductive material which does not support eddy currents.

MRI magnet assembly with non-conductive inner wall

A passive shimming system for a superconducting magnet to improve bore magnetic homogeneity includes a plurality of axially extending non-magnetic drawers each including a plurality of pockets along the drawer with a securable cover for each pocket to enclose the selected ferromagnetic shim disks and compressible spring material to enable individual access and shimming of selected pockets.

Magnetic resonance imaging passively shimmed superconducting magnet

A superconducting device, such as a superconducting rotor for a generator or motor. A vacuum enclosure has an interior wall surrounding a cavity containing a vacuum. A superconductive coil is placed in the cavity. A generally-annularly-arranged, thermally-conductive sheet has an inward-facing surface contacting generally the entire outward-facing surface of the superconductive coil. A generally-annularly-arranged coolant tube contains a cryogenic fluid and contacts a generally-circumferential portion of the outward-facing surface of the sheet. A generally-annularly-arranged, thermally-insulative coil overwrap generally circumferentially surrounds the sheet. The coolant tube and the inward-facing surface of the coil overwrap together contact generally the entire outward-facing surface of the sheet.

Cooling arrangement for a superconducting coil

A superconductive device (e.g., magnet) having a superconductive lead assembly and cooled by a cryocooler coldhead having first and second stages. A first ceramic superconductive lead has a first end thermally connected to the first stage and a second end thermally connected to the second stage. A jacket of open cell material (e.g., polystyrene foam) is in surrounding compressive contact with the first ceramic superconductive lead, and a rigid, nonporous support tube surrounds the jacket. This protects the first ceramic superconductive lead against shock and vibration while in the device. The rigid support tube has a first end and a second end, with the second end thermally connected to the second stage.

Superconductive device having a ceramic superconducting lead resistant

A superconductive lead assembly for a superconductive device (e.g., magnet) cooled by a cryocooler coldhead having first and second stages. A first ceramic superconductive lead has a first end flexibly, dielectrically, and thermally connected to the first stage and a second end flexibly, dielectrically, and thermally connected to the second stage. A first glass-reinforced-epoxy lead overwrap is in general surrounding contact with and attached to the first superconductive lead. The first lead overwrap has a coefficient of thermal expansion generally equal to that of the first superconductive lead. The lead overwrap protects the lead from moisture damage and from breakage during handling. For added protection against shock and vibration while in the device, the lead assembly is surrounded by a (e.g., polystyrene foam) jacket surrounded by a helically-wound metallic wire surrounded by a glass-reinforced-epoxy jacket overwrap surrounded by a rigid support tube.

Ceramic superconducting lead resistant to moisture and breakage

Growing community of inventors

Niskayuna, NY, United States of America

Kenneth Gordon Herd