General Electric Company

John Thomas Herbon

Seyed Gholamali Saddoughi

Sridhar Adibhatla

Fengfeng Tao

Steven Clayton Vise

Clayton Stuart Cooper

Geoffrey David Myers

Michael Terry Bucaro

Kwanwoo Kim

Joseph Zelina

Joel Meier Haynes

Hasan Ul Karim

Matthew Patrick Boespflug

Abdelkrim Younsi

Keith Robert McManus

Grover Andrew Bennett, Jr

Florian Peter Pintgen

Ahmed Mostafa ELKady

Changjin Yoon

Uyigue Omoma Idahosa

Zekai Hong

A system and method for determining performance of an engine is provided. The system includes two or more sensors configured in operable arrangement at two or more respective positions at a flowpath. The system includes one or more computing devices configured to perform operations, the operations include acquiring, via the two or more sensors, parameter sets each corresponding to two or more engine conditions different from one another, wherein each parameter set indicates a health condition at a respective location at the engine; comparing, via the computing device, the parameter sets to determine the respective health condition corresponding to the respective location at the engine; and generating, via the computing device, a health condition prediction based on the compared parameter sets.

Method for operating a turbo machine

A combustor for a turbine engine is provided, the combustor includes an outer liner, an inner liner and a dome that together define a combustion chamber; a diffuser positioned upstream of the combustion chamber, the diffuser being configured to receive air flow from a compressor section and to provide a flow of compressed air to the combustion chamber; and an outer cowl and an inner cowl located upstream of the combustion chamber, the outer cowl and the inner cowl being configured to direct a portion of air flow from the diffuser to the combustion chamber. The diffuser is configured to output air flow having an amount of air pressure maximized at a center of the air flow so as to optimize total air pressure fed to the combustion chamber through the dome.

Active boundary layer control in diffuser

A system and method for determining performance of a turbine engine, and operation thereof. The system and method includes a plurality of sensors and one or more computing devices executing operations including acquiring a plurality of parameter sets each corresponding to a plurality of engine conditions in which each parameter set corresponding to each engine condition indicates a health condition at a plurality of locations at the engine; comparing the plurality of parameter sets to determine a health condition corresponding to a location at the engine; and generating a health condition prediction at the engine based on the compared parameters.

An acoustic damping device is provided that includes a resonating tube defining a resonating cavity with a predetermined characteristic length and a tube end defining a cavity opening, as well as a case configured to reversibly secure the tube end in fluidic communication with a fluid volume enclosed by a liner. The cavity opening is connected with the resonating cavity. The case includes a vented ferrule adpressed over a perforated region of the liner. The vented ferrule defines a ferrule opening that is aligned with the perforated region of the liner and the cavity opening to form the fluidic communication between the fluid volume and the resonating cavity.

High frequency acoustic damper for combustor liners

In one embodiment, a system for reducing pressure oscillations within a gas turbine engine includes at least one fuel injector configured to inject fuel into a combustor. The system also includes a valve fluidly coupled to the at least one fuel injector. The system further includes a controller communicatively coupled to the valve. The controller is configured to cycle the valve between an open position and a closed position at a first frequency and a first duty cycle while a magnitude of pressure oscillations within the combustor is less than a threshold value, to cycle the valve between the open position and the closed position at a second frequency and a second duty cycle while the magnitude of the pressure oscillations within the combustor is greater than or equal to the threshold value, and to adjust the second frequency based on a measured frequency of the pressure oscillations.

System and method for reducing pressure oscillations within a gas turbine engine

A gate drive circuit includes an insulated gate semiconductor switch. A controlled current source is connected to the semiconductor switch gate terminal to provide a gate drive circuit that is responsive to recycled gate charge corresponding to an internal gate capacitance of the insulated gate semiconductor switch.

High speed low loss gate drive circuit

A system and a method of generating energy in a power plant using a turbine are provided. The system includes an air separation unit providing an oxygen output; a plasma generator that is capable of generating plasma; and a combustor configured to receive oxygen and to combust a fuel stream in the presence of the plasma, so as to maintain a stable flame, generating an exhaust gas. The system can further include a water condensation system, fluidly-coupled to the combustor, that is capable of producing a high-content carbon dioxide stream that is substantially free of oxygen. The method of generating energy in a power plant includes the steps of operating an air separation unit to separate oxygen from air, combusting a fuel stream in a combustor in the presence of oxygen, and generating an exhaust gas from the combustion. The exhaust gas can be used in a turbine to generate electricity. A plasma is generated inside the combustor, and a stable flame is maintained in the combustor.

Systems and methods for power generation using oxy-fuel combustion

A power generator includes one or more full bridge inverter modules coupled to a semiconductor opening switch (SOS) through an inductive resonant branch. Each module includes a plurality of switches that are switched in a fashion causing the one or more full bridge inverter modules to drive the semiconductor opening switch SOS through the resonant circuit to generate pulses to a load connected in parallel with the SOS.

Solid state pulsed power generator

In one embodiment, a combustion apparatus comprises: an oxidant inlet, a fuel inlet, a mixing zone configured to mix fuel and oxidant to form a mixture, a combustion zone in fluid communication with the mixing zone and configured to combust the mixture, and an outlet in fluid communication with the combustion zone. The mixing zone, the combustion zone, and/or the outlet comprises an electro-dynamic swirler configured to swirl ionized gas. The electro-dynamic swirler comprises a plurality of electrodes in electrical communication with a power source. In one embodiment, a method of creating thrust comprises: mixing a fuel and an oxidant to form a mixture, igniting the mixture to form an ignited mixture, combusting the ignited mixture to form a flame, and using the flame to create thrust, wherein the flame and/or the fuel and oxidant are electro-dynamically swirled.

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Loveland, OH, United States of America

John Thomas Herbon