Ingersoll-rand Energy Systems Corporation

Dresser-rand Company

General Electric Company

Flexenergy Energy Systems, Inc.

Andrew J Olsen

Zheji Liu

Shaun Sullivan

Malcolm S Child

Ivar Austrem

James B Kesseli

James S Nash

Silvano R Saretto

Scott David Wisler

George C Talabisco

William L Blair

Ernest J Sandoe

David G Glista

John H Thomson

Serkan Yildirim

M Serkan Yildirim

Jason K Hargrove

Shaun D Sullivan

A gas turbine may include a rotatable shaft, a compressor disposed about the rotatable shaft and configured to output compressed air, and a combustor disposed about the rotatable shaft. The combustor may be configured to receive the compressed air and output high temperature compressed gas. The gas turbine may further include a power turbine disposed about the rotatable shaft and configured to receive the high temperature compressed gas, and a first liner defining a plurality of holes and disposed around the combustor. The power turbine may be configured to expand the high temperature compressed gas and rotate the rotatable shaft. The first liner may have a first end and a longitudinally opposite second end. The first end may be coupled to an inner surface of the casing at or adjacent an upstream end of the combustor and the second end may be substantially free from any connection with the casing.

Gas turbine combustion acoustic damping system

A gas turbine assembly and method for operating the gas turbine assembly are provided. The method for operating the gas turbine assembly may include compressing a process fluid containing inlet air through a compressor to produce compressed inlet air, combining fuel from a main fuel source with the process fluid, and preheating the process fluid containing the inlet air and the fuel in a warmer disposed downstream from the compressor. The method may also include heating an oxidizer by flowing the preheated process fluid from the warmer to the oxidizer, and oxidizing the process fluid containing the compressed inlet air and the fuel in the oxidizer to produce an oxidation product. The method may further include expanding the oxidation product in a turbine to generate rotational energy, and preventing the process fluid from flowing upstream to the compressor with a check valve.

System and method for operating a gas turbine assembly including heating a reaction/oxidation chamber

A method of removing siloxanes from a gas that contains siloxanes and water, the method comprising: (a) expanding the gas to cool the gas and freeze at least some of the water in the gas; and (b) removing the siloxanes and frozen water from the expanded and cooled gas. The method may also include compressing the gas prior to expanding it. The step of expanding the gas may include expanding it through a turbine. The method may also include using an energy input mechanism to drive one or both of the compressor or turbine. The ice and siloxanes may be removed from the gas with a cyclonic separator.

System and method for removing water and siloxanes from gas

A radial flow turbine including a rotor having a plurality of vanes defining an inlet, an outlet, and a flow path therebetween. A shroud is positioned to cover at least a portion of the flow path and a housing is positioned to at least partially support the rotor for rotation about a rotational axis. The housing at least partially defines a chamber for the receipt of a flow of products of combustion. A plurality of nozzle guide vane assemblies are positioned to provide fluid communication between the chamber and the inlet. Each of the plurality of nozzle guide vane assemblies is positioned adjacent another nozzle guide vane assembly to at least partially define one of a plurality of converging flow paths. Each nozzle guide vane assembly includes a guide vane positioned between the shroud and the housing and including an aperture therethrough. A bolt engages with the shroud and extends through the aperture to sandwich the guide vane between the shroud and the housing. A resilient member having a stiffness less than the bolt cooperates with the bolt to apply a compressive force to the guide vane.

Nozzle bolting arrangement for a turbine

A microturbine engine comprising a turbine including a first housing and a turbine rotor. The engine also includes a generator having a second housing and a generator rotor. The generator rotor is supported for low-speed rotation by a low-speed bearing. The engine also includes a gearbox having a third housing connected to the first housing and the second housing, a pinion gear, and a low-speed gear connected to the generator rotor and at least partially supported by the low-speed bearing. A shaft is connected to the turbine rotor and the pinion gear and a first high-speed bearing and a second high-speed bearing are positioned to support the turbine rotor and the shaft for high-speed rotation.

Integrated microturbine gearbox generator assembly

The invention recites a power turbine assembly including a turbine rotor and a plurality of turbine blades mounted to said rotor and adapted to rotate said rotor in response to a flow of hot gas over said blades. A support structure having a journal bearing and at least one other bearing supports said rotor for rotation, said journal bearing having a proximal end and a distal end with respect to said turbine blades. A supply of lubricant communicates with said journal bearing to provide lubricant between said rotor and an inner surface of said journal bearing, said lubricant damping rotational frequencies of said rotor and creating a temperature gradient from greater than about 1000&deg; F. at said blades to less than about 350&deg; F. at said distal end.

Interchangeable power turbine cartridge assembly

The invention recites a microturbine system comprising a housing and a turbine including a rotary element having a shaft supported by the housing and rotatable about a rotary axis. A starter wheel is coupled to the shaft and rotatable in response to a stream of high-pressure fluid flowing from a high-pressure flow path. A pump is operable to provide a supply of lubricating fluid. The engine further includes a starter valve receiving the supply of lubricating fluid and being selectively operable to provide one of the stream of high-pressure fluid to the high-pressure flow path and a stream of low-pressure fluid to a low-pressure flow path.

Single pump lubrication and starter system

A cogenerating recuperated microturbine includes a recuperator, an air compressor and a combustor. The combustor burns a fuel along with the compressed air received from the recuperator to create products of combustion. A turbine generator operates in response to expansion of the products of combustion to generate electricity. The products of combustion then flow through the recuperator to preheat the compressed air. The products of combustion then flow out of the recuperator as an exhaust flow. A heat exchanger is movable into and out of the exhaust flow to selectively heat a fluid in the heat exchanger. The heat exchanger is actuated by a piston-cylinder type actuator that operates under the influence of compressed air selectively bled from the air compressor. The actuator may be a single-acting cylinder used in conjunction with a biasing spring, or may be a double-acting cylinder.

Gas turbine with articulated heat recovery heat exchanger

A flexible duct for fluidly communicating between first and second components includes a first duct section with an intake end and an exhaust end. A first joint pivotally couples the intake end to the first component for pivotal movement about a first axis. The flexible duct also includes a second duct section with a first end and a second end. The first end is pivotally coupled to the exhaust end by a second joint, and a third joint pivotally couples the second end to the second component. The second joint is pivotable about a second axis that is generally parallel to the first axis, and the third joint is pivotable about a third axis that is generally perpendicular to the first and second axes.

Flexible duct for a microturbine

A gas booster system in which a variable frequency drive is used to control, by means of a variable speed motor, the compression rate of a pump in a gas turbine combustion engine. The rate of the variable speed motor, and thus the rate of compression, is controlled by monitoring turbine temperature. The gas turbine system responds to the turbine temperature to regulate the rate of compression of the fuel.

Gas turbine system and method

A turbine nozzle includes outer and inner bands having respective mounting holes therein. A plurality of vanes extends through respective pairs of outer and inner holes in the bands. The vane outer and inner ends are resiliently supported to the bands to allow differential thermal movement therebetween so that the individual vanes float relative to the outer and inner bands to prevent thermal stress failure thereof.

Growing community of inventors

Amesbury, MA, United States of America

Andrew J Olsen