General Electric Company

Lockheed Martin Corporation

Other

Robert Carl Murray

Byron Andrew Pritchard, Jr

Corey Bourassa

Jonathan Russell Ratzlaff

Curtis Walton Stover

Gregory Michael Laskowski

Robert Proctor

Robert Francis Manning

Victor Hugo Silva Correia

Seyed Gholamali Saddoughi

Fengfeng Tao

Jared Peter Buhler

Timothy Deryck Stone

Abdelkrim Younsi

Frank Jakob John Mueller

John Stanley Glaser

Glen Peter Koste

Aspi Rustom Wadia

Karim Younsi

John Howard Starkweather

Anurag Gupta

Erich Alois Krammer

Matthew Patrick Boespflug

David Vickery Parker

Grover Andrew Bennett, Jr

Boon Kwee Lee

William Collins Vining

Steven Martens

Joseph Taher Mossoba

Yaru Mendez Hernandez

Paul William Judge

Seyed Gholani Saddoughi

Katherine Anne Essenhigh

Paul Judge

A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft. A bypass conduit couples the compressor section to the turbine section. At least one centrifugal separator is fluidly coupled to the bypass stream, where the at least one centrifugal separator includes a body, a center body, a separator inlet, and a separator outlet fluidly coupled with the turbine section to output a reduced-particle stream that is provided to the turbine section for cooling. The centrifugal separator includes an angular velocity increaser, a flow splitter, a first outlet passage defined by an inner annular wall that receives the reduced-particle stream, and an angular velocity decreaser located downstream of the flow splitter. A second outlet passage receives the concentrated-particle stream.

Inducer assembly for a turbine engine

A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft that couples a portion of the turbine section and a portion of the compressor section. A bypass conduit couples the compressor section to the turbine section while bypassing at least the combustion section. At least one particle separator is located in the turbine engine having a separator inlet that receives a bypass stream, a separator outlet that receives a reduced-particle stream flows, and a particle outlet that receives a concentrated-particle stream comprising separated particles. A conduit, fluidly coupled to the particle outlet, extends through an interior of at least one stationary vane.

A turbine engine having an inducer assembly. The inducer assembly includes a centrifugal separator fluidly coupled to an inducer with an inducer inlet and an inducer outlet. The centrifugal separator includes a body, an angular velocity increaser to form a concentrated-particle stream and a reduced-particle stream, a flow splitter, and an exit conduit fluidly coupled to the body to receive the reduced-particle stream and define a separator outlet.

A turbine engine having a bypass fluid conduit coupled to the turbine section includes at least one particle separator located within the bypass fluid conduit to separate particles from a bypass fluid stream prior to the bypass stream reaching the turbine section for cooling. A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser, a particle outlet, an angular velocity decreaser downstream of the angular velocity increaser, and a bend provided between the angular velocity increaser and the angular velocity decreaser.

Turbine engine and particle separators therefore

A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser configured to increase the angular velocity of a fluid stream, a flow splitter configured to split the fluid stream to form a concentrated-particle stream and a reduced-particle stream, and an exit conduit configured to receive the reduced-particle stream. An inducer assembly for a turbine engine includes an inducer with a flow passage having an inducer inlet and an inducer outlet in fluid communication with a turbine section of the engine, and a particle separator, which includes a particle concentrator that receives a compressed stream from a compressor section of the engine and a flow splitter. A turbine engine includes a cooling air flow circuit which supplies a fluid stream to a turbine section of the engine for cooling, a particle separator located within the cooling air flow circuit, and an inducer forming a portion of the cooling air flow circuit in fluid communication with the particle separator. A method of cooling a rotating blade of a turbine engine having an inducer includes directing a cooling fluid stream from a portion of turbine engine toward the rotating blade, separating particles from the cooling fluid stream by passing the cooling fluid stream through a inertial separator, accelerating a reduced-particle stream emitted from the inertial separator to the speed of the rotating blade, and orienting the reduced-particle stream by emitting the reduced-particle stream from the inertial separator into a cooling passage in the inducer.

Turbine engine, components, and methods of cooling same

A separator assembly for removing entrained particles from a fluid stream passing through a gas turbine engine includes a first particle separator for separating the fluid stream into a reduced-particle stream and a particle-laden stream, and emitting the particle-laden stream through a scavenge outlet. Another particle remover is fluidly coupled to the scavenge outlet to remove more particles from the air stream.

Separator assembly for a gas turbine engine

A shroud assembly for a turbine engine includes a shroud having a front side confronting the blades of a turbine and a back side opposite the front side, a hanger configured to couple the shroud to with casing of the turbine, a cooling conduit extending through the hanger to supply a cooling fluid stream to the back side of the shroud, and a particle separator having a through passage forming part of the cooling conduit and a scavenge conduit branching from the through passage.

Shroud assembly for turbine engine

Systems, apparatus, and program product and methods for controlling boundary layer flow across an aerodynamic structure which can produce separate regions of flow structures at different strengths by means of dielectric-barrier-discharge (DBD) type plasmas, are provided. An example of such apparatus provides plasma regions that are capable of being individually controlled by voltage and/or frequency, and modulated for the purposes of flow control. The apparatus includes an electrode assembly fitted with electrodes on either side of a dielectric such that different electrode geometries and arrangements create isolated regions of plasmas which results in separate regions of flow structures. These regions may be further controlled and modulated by the use of electronic-switching to produce irregularly shaped flow structures and strengths including those having a primarily vertical component.

System, apparatus, program product, and related methods for providing boundary layer flow control

A system is provided for estimating a condition of a non-conductive hollow structure exposed to a lightning strike. The structure has an internal cavity. The system includes a pressure transducer to measure a pressure of an acoustic wave generated within the internal cavity due to the lightning strike. The system further includes a controller coupled to the pressure transducer, to receive the measured pressure from the pressure transducer, and to process the condition of the structure, based on the measured pressure.

System for estimating a condition of non-conductive hollow structure exposed to a lightning strike

Embodiments of systems, program products, and computer implemented methods to measure the displacement of an object located in a hazardous or otherwise inaccessible location at a long range from an optical device with micron-level accuracy are provided the object being. The objects can be machinery, valves, containers, or any other object whose displacement is to be measured. The object can be located in radioactive, chemically reactive, high voltage, or otherwise hazardous or inaccessible locations that are not accessible for conventional displacement measurement by personnel. A system can comprise an identifier on the object to be tracked, an optical device, an computer with at least processing, storage, and memory facilities, and a communications network.

Method, system, and computer program product to detect micron scale displacement of objects from a long range with and optical device and related computer implemented methods

A micro-electromechanical system (MEMS) dielectric barrier discharge (DBD) based aerodynamic actuator is configured to modify a shockwave boundary layer interaction and limit incident boundary layer growth caused by a reflected shockwave.

Control of shockwave-boundarylayer-interaction using MEMS plasma devices

A high voltage, high speed, and high repetition rate pulse generator solves the high pulse repetition rate limitations associated with RF power amplifiers. The pulse generator employs resonant techniques to provide current limiting features that allow for continued high voltage, high speed, and high repetition pulse rate operation of the pulse generator without impairment of the pulse generator during both short circuit and open circuit load conditions.

High voltage, high speed, high pulse repetition rate pulse generator

A high voltage, fast pulse rise/fall time, and high repetition rate pulse generator solves the high pulse repetition rate limitations associated with RF power amplifiers and gap switch type pulse generators. The pulse generator employs a transmission line architecture and structural techniques that allow for continued high voltage, fast rise/fall time, and high repetition pulse rate operation of the pulse generator without impairment of the pulse generator while exceeding performance characteristics achievable with conventional RF power amplifiers and gap switch type pulse generators.

Transmission line based high voltage pulse generator

A plasma generation system includes a pulse generator having at least one switch and that is configured to convert a DC voltage to a desired high frequency, high breakdown voltage pulse sufficient to break down a high-breakdown voltage gap, wherein all pulse generator switches are solely low to medium voltage, high frequency switches, and further configured to apply the breakdown voltage to a plasma load for the generation of plasma. In one application, the plasma generation system is useful to manipulate the flow of jets and provide highly efficient acoustic noise reduction.

High efficiency and high bandwidth plasma generator system for flow control and noise reduction

A high-frequency, high-voltage electron switch includes an electron source, a steering mechanism, a mask or anode plate, and a target. The electron source produces a beam of electrons with a voltage of at least about 1 kV that impinges upon the anode plate. The steering mechanism scans the electron beam across the anode plate at a scanning frequency of at least about 10 MHz. A hole or aperture is provided in the anode plate that allows the electron beam to pass through and produce a pulsed, high-voltage current in the target with a very high-frequency repetition rate and a very fast rise time. The pulsed, high-voltage current produced in the target can be used to cause a high-voltage source to turn on and off.

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Rotterdam, NY, United States of America

Robert Carl Murray