General Electric Company

Caterpillar Inc.

Southwest Research Institute

Stanley Kevin Widener

Lewis Berkley Davis, Jr

Thomas Edward Johnson

Jonathan Dwight Berry

Michael John Hughes

Kevin Weston McMahan

Gregory Thomas Foster

Kaitlin Marie Graham

Krishnakumar Venkataraman

Carlos Miguel Miranda

Ronald Scott Bunker

Matthew Troy Hafner

James Scott Flanagan

Joseph Vincent Citeno

Jeremy Clyde Bailey

Willard J Dodds

John Wilbur

Patrick Benedict Melton

Lucas John Stoia

John McConnell Delvaux

Geoffrey David Myers

Scott Robert Simmons

Jack Rogers Taylor

Alan Majors Walker

David Pratt Branyon

Carl Gerard Schott

Peter De Diego

John Charles Intile

James Zhang

David Walter Parry

Fabien Thibault Codron

Howard L Foltz

Attila Szabo

Steven C Steffens

William Michael Poschel

Keith K Taylor

Anil Salunkhe

Stefan Maier

Barry Edward Westmoreland

John Edward Pritchard

John Wilber

Kevin Weston Mcmahan

Jr Lewis Berkley Davis

A passive flow modulation device according to an embodiment includes: a pressure sensitive main valve controlling a flow of a cooling fluid from a first area to a second area through an orifice; and a temperature sensitive pilot valve coupled to the pressure sensitive main valve, the temperature sensitive pilot valve configured to open at a predetermined temperature in the first area, causing a pressurization of the pressure sensitive main valve, wherein the pressurization of the pressure sensitive main valve actuates the pressure sensitive main valve to an open position, allowing the cooling fluid to flow from the first area to the second area through the orifice.

Passive flow modulation of cooling flow into a cavity

The present disclosure is directed to a gas turbine including a primary compressor, a combustion section disposed downstream from the primary compressor and a turbine disposed downstream from the combustion section. A pipe assembly defines an extraction-air circuit between an extraction port of the primary compressor and an inlet port of the turbine. The gas turbine further includes an extraction-air conditioning system. The extraction-air conditioning system includes a secondary compressor having an inlet and an outlet. Both the inlet and the outlet are fluidly coupled to the extraction-air circuit at respective locations defined along the pipe assembly between the extraction port of the primary compressor and the inlet port of the turbine.

Gas turbine with extraction-air conditioner

A segmented annular combustion system with dual fuel capability includes an alternating arrangement of fuel injection modules and integrated combustor nozzles. The fuel injection module includes a bundled tube fuel nozzle portion and fuel injection lances, which are fluidly coupled via conduits to respective fuel plenums. A liquid fuel cartridge is disposed within the bundled tube fuel nozzle portion, within one of the plurality of fuel injection lances, or within both the bundled tube fuel nozzle portion and one of the plurality of fuel injection lances. A gas turbine having the segmented annular combustion system is also provided.

Segmented annular combustion system with dual fuel capability

Hot gas path (HGP) components for turbine systems are disclosed. The HGP component may include a body including a forward end, an aft end, and an inner portion positioned adjacent a hot gas flow path for the turbine system. The body may also include an outer portion formed radially opposite the inner portion, and a plurality of nozzles extending through the outer portion. Additionally, body may include an intermediate portion formed between the inner portion and the outer portion, and a plurality of venturi extending through the intermediate portion. The plurality of venturi may be in fluid communication with the plurality of nozzles.

Hot gas path components including plurality of nozzles and venturi

Airfoils including a plurality of nozzles and venturi. The airfoils may include a body including an inner wall defining a high pressure fluid chamber, and a plurality of high pressure nozzles extending through the inner wall. Each high pressure nozzle may be in fluid communication with the high pressure fluid chamber. The airfoil body may also include an intermediate wall positioned adjacent to and surrounding the inner wall to define a low pressure fluid chamber formed between the intermediate wall and the inner wall, and a plurality of low pressure venturi extending through the intermediate wall. Each low pressure venturi may be in fluid communication with the low pressure fluid chamber. Additionally, the airfoil body may include an outer wall positioned adjacent to and surrounding the intermediate wall to define a cooling channel formed between the intermediate wall and the outer wall.

Airfoils including plurality of nozzles and venturi

A bypass valve for a combustor, including: a housing; an opening in the housing; a pneumatically actuated component within the housing; a passage coupling the opening in the housing and a duct of the combustor; a chamber formed by the housing and the pneumatically actuated component, the chamber containing a volume of air; and a control valve for controlling a pressure within the chamber to selectively displace the pneumatically actuated component to open and close the passage.

Pneumatically-actuated bypass valve

A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral portions in which: a base portion is made from a first material; and a top portion is made from a second material. The airfoil may include a connector securing the base portion to the top portion of the airfoil, wherein the connector comprises a wire-lock connector that includes: a tab extending from one of the base portion and the top portion; a complimentary slot for receiving the tab formed in the other one of the base portion and the top portion; a first groove formed in a side of the tab; a second groove formed in a side of the slot; a retaining aperture formed cooperatively via an alignment of the first and second grooves upon the tab being received into the slot; and a retaining wire housed within the retaining aperture.

Hybrid rotor blades for turbine engines

A flow modulator for a fuel nozzle, including: a fixed outer tube, the fixed outer tube including a set of apertures; a movable inner tube concentrically positioned within the fixed outer tube, the movable inner tube including a set of apertures; and a pneumatically actuated component for displacing the movable inner tube within the fixed outer tube to selectively align the set of apertures of the fixed outer tube with the set of apertures of the movable inner tube.

Pneumatically-actuated fuel nozzle air flow modulator

A segmented annular combustion system includes an alternating arrangement of fuel nozzles and integrated combustor nozzles. The fuel nozzles deliver fuel to the primary combustion zones. The integrated combustor nozzles include an inner liner segment, an outer liner segment, and a fuel injection panel extending between the liner segments. The fuel injection panel includes injection outlets on one or both side walls to deliver a combustible mixture to the secondary combustion zones. Each fuel injection panel, which provides a boundary between adjacent primary and secondary combustion zones, includes an aft end that defines a turbine nozzle. The segmented annular combustion system is part of a gas turbine.

Segmented annular combustion system with axial fuel staging

A segmented annular combustion system includes integrated combustor nozzles, each of which has a fuel injection panel disposed radially between an inner liner segment and an outer liner segment. The fuel injection panel includes an aft end portion, a first side wall, a second side wall, premixing channels defined between the first side wall and the side wall, and injection outlets defined along at least one of the first side wall and the second side wall. The aft end portion defines a turbine nozzle portion. An interior portion between the first side wall and the second side wall includes walls that extend between the first and second side walls, thereby partitioning the interior portion into discrete air cavities. The air cavities and the liner segments may be cooled by impingement inserts or panels.

Cooling of integrated combustor nozzle of segmented annular combustion system

The present disclosure is directed to an integrated combustor nozzle for a segmented annular combustion system. The integrated combustor nozzle includes an outer liner segment, an inner liner segment, and a fuel injection panel extending radially between the outer liner segment and the inner liner segment. The fuel injection panel includes a first side wall, a second side wall, and a plurality of premixing channels between the first and second side walls, each of the premixing channels having an outlet on one of the first and second side walls. The aft end of the fuel injection panel defines a turbine nozzle.

Integrated combustor nozzle for a segmented annular combustion system

A combustor for a gas turbine, including: a combustor chamber; a casing enclosing the combustor chamber and defining an area therebetween for passing compressor discharge air into the combustor chamber for use in combustion; and at least one passive bypass valve for selectively extracting a portion of the compressor discharge air from the area between the combustor chamber and the casing to adjust a temperature in the combustor.

Combustion bypass passive valve system for a gas turbine

Embodiments of the present disclosure provide injection systems for fuel and air. According to one embodiment, an injection system can include a mixing zone embedded within a surface of a turbine nozzle and positioned between a first outlet and a second outlet, the turbine nozzle separating a combustor of a power generation system from a turbine stage of the power generation system, wherein the first outlet is oriented substantially in opposition to the second outlet; a first injection conduit for delivering a carrier gas to the mixing zone through the first outlet; and a second injection conduit for delivering a fuel to the mixing zone through a second outlet; wherein the carrier gas and the fuel intermix within the mixing zone upon leaving the first injection conduit and the second injection conduit.

Injection systems for fuel and gas

Embodiments of the present disclosure provide an apparatus comprising: a reaction chamber positioned between a first turbine stage of a power generation system and a turbine stage of the power generation system, wherein the turbine stage comprises a turbine nozzle and a turbine blade row; a plurality of injectors positioned on a wall of the reaction chamber; and a conduit in fluid communication with the plurality of injectors, wherein the conduit delivers at least one of fuel from a fuel supply line to the reaction chamber through the plurality of injectors.

Injecting apparatus with reheat combustor and turbomachine

Aspects of the present disclosure provide an apparatus including: an injector in fluid communication with an aft section of a reheat combustor in a power generation system, the aft section being positioned downstream of a combustion reaction zone in the reheat combustor, and positioned upstream of a turbine stage of the power generation system, wherein the turbine stage includes a turbine nozzle and a turbine blade row; and a conduit in fluid communication with the injector, wherein the conduit delivers at least one of a fuel from a fuel supply line and a carrier gas to the injector.

Injector apparatus and reheat combustor

Growing community of inventors

Greenville, SC, United States of America

Stanley Kevin Widener