General Electric Company

Christian Lee Vandervort

Emil Donald Jarczynski

Todd Garrett Wetzel

Samir Armando Salamah

Wayne Nigel Owen Turnbull

Venkat Eswarlu Tangirala

Wei Tong

Anthony John Dean

Narendra Digamber Joshi

Adam Rasheed

Joel Meier Haynes

Ronald Scott Bunker

Konrad Roman Weeber

James Michael Fogarty

Robert Russell Mayer

Richard Scott Bourgeois

Ahmed Mostafa ELKady

Frederick John Rink, Jr

John Wesley Griffith

Gary Michael Itzel

Christopher Charles Glynn

Kishore Ramakrishnan

Krishan Lal Luthra

Robert Joseph Iasillo

Parag Prakash Kulkarni

Fei Han

Kevin Richard Kirtley

Kapil Kumar Singh

Kenneth Edward Seitzer

Joseph Vincent Citeno

Charles E Steber

David Michael Chapin

Edward Randall Furlong

Jeffrey Scott Goldmeer

William Hunter Boardman, Iv

Rodger O Anderson

Richard Edwin Warren, Jr

Krishnakumar Venkatesan

William James Lawson

Gary D Mercer

Pierre Francois Pinard

Ahmed Mostafa ElKady

Qingguo Zhang

Je-Hoon Kim

Krishna Kumar Venkatesan

Peirre Francois Pinard

Julian D Burrow

Edward J Lin

Donald Bruce Potter

Sherif Mohamed

Deepali Nitin Bhate

Shiva Kumar Srnivasan

Balasubramanyam Preetham

A method for starting and operating a NMHC fueled gas turbine combined cycle power plant includes injecting gaseous NMHC fuel into a gaseous NMHC fuel treatment system, injecting at least one of auxiliary steam, HRSG steam, or HRSG water into the gaseous NMHC fuel treatment system, and mixing the at least one of auxiliary steam, HRSG steam, or HRSG water with the gaseous NMHC fuel in the NMHC fuel treatment system to form a gaseous NMHC fuel mixture. The method further includes injecting the gaseous NMHC fuel mixture into a gaseous NMHC fuel distribution system, and providing the gaseous NMHC fuel mixture through the gaseous NMHC fuel distribution system to a combustor of the NMHC fueled gas turbine.

Methods for startup and operation of gas turbine combined cycle power plants using NMHC fuels

A turbine assembly is provided. The turbine assembly includes a gas turbine engine including at least one hot gas path component formed at least partially from a ceramic matrix composite material. The turbine assembly also includes a treatment system positioned to receive a flow of exhaust gas from the gas turbine engine. The treatment system is configured to remove water from the flow of exhaust gas to form a flow of treated exhaust gas, and to channel the flow of treated exhaust gas towards the at least one hot gas path component. The at least one hot gas path component includes a plurality of cooling holes for channeling the flow of treated exhaust gas therethrough, such that a protective film is formed over the at least one hot gas path component.

Turbine engine assembly and method of assembling the same

A turbine system and method of operating is provided. The system includes a compressor configured to generate a compressed low-oxygen air stream and a combustor configured to receive the compressed low-oxygen air stream and to combust a fuel stream to generate a post combustion gas stream. The turbine system also includes a turbine for receiving the post combustion gas stream to generate a low-NOexhaust gas stream, a heat recovery system configured to receive the low-NOexhaust gas stream and generate a cooled air stream and an auxiliary compressor configured to generate an oxygen and water vapor deficient cooled and compressed air stream. A portion of the oxygen and water vapor deficient cooled and compressed air stream is directed to the combustor to generate an Oxygen and HO deficient film on exposed portions of the combustor, and another portion is directed to the turbine to provide a cooling flow.

Gas turbine engine and method of operating thereof

A nozzle for assemblies and gas turbines is provided. The nozzle exhibits destabilized flame holding characteristics, i.e., the nozzle is unable to stabilize flame up to an equivalence ratio of about 0.65. As a result, flame heat release is delayed resulting in lower peak flame temperatures and correspondingly lower NOx levels. Flame stabilization capability is retained for higher equivalence ratios to support operation of the combustor in other regions of the load range.

Fuel nozzle and assembly and gas turbine comprising the same

A combustion system premixer includes one or more streamwise vortex generators configured to passively redirect surrounding high velocity air into at least one of wake and vortex regions within a combustion system fuel nozzle in response to air passing through the premixer. The streamwise vortex generators operate to minimize turbulent flow structures, thus improving air/fuel mixing, and enhancing resistance to flame-holding and flash-back within the premixer.

System and method for premixer wake and vortex filling for enhanced flame-holding resistance

A system for removing heat from a turbine includes a component in the turbine having a supply plenum and a return plenum therein. A substrate that defines a shape of the component has an inner surface and an outer surface. A coating applied to the outer surface of the substrate has an interior surface facing the outer surface of the substrate and an exterior surface opposed to the interior surface. A first fluid channel is between the outer surface of the substrate and the exterior surface of the coating. A first fluid path is from the supply plenum, through the substrate, and into the first fluid channel, and a second fluid path is from the first fluid channel, through the substrate, and into the return plenum.

System and method for removing heat from a turbine

A combustor system for use in a turbine engine is provided. The turbine engine includes turbine assembly that includes a fluid inlet, a fluid outlet, and a combustion gas path defined therebetween. The combustor system includes a first combustor assembly and a second combustor assembly. The first combustor assembly is coupled to the turbine assembly for channeling a first flow of combustion gases through the turbine assembly. The first combustor assembly is oriented adjacent to the turbine assembly inlet to channel the first flow of combustion gases to the turbine assembly through the turbine assembly inlet. The second combustor assembly is coupled to the turbine assembly along the combustion gas path for channeling a second flow of combustion gases through the turbine assembly.

Gas turbine engine including secondary combustion chamber integrated with the stator vanes in the turbine/expansion section of the engine and a method of operating the same

A system and method of reducing gas turbine nitric oxide emissions includes a first combustion stage configured to burn air vitiated with diluents to generate first combustion stage products. A second combustion stage is configured to burn the first combustion stage products in combination with enriched oxygen to generate second combustion stage products having a lower level of nitric oxide emissions than that achievable through combustion with vitiated air alone or through combustion staging alone.

System and method using low emissions gas turbine cycle with partial air separation

An engine contains at least one pulse detonation combustor which is surrounded by a bypass flow air duct, through which bypass air flow is directed. The bypass air duct contains at least one converging-diverging structure to dampen or choke the upstream propagation of shock waves from the pulse detonation combustor through the bypass flow air duct. The bypass air also serves to cool the outer surfaces of the pulse detonation combustor. The bypass air flow is controlled in tandem with the heat release from the PDC to provide the appropriate amount of thermal energy to a downstream energy conversion device, such as a turbine. A mixing plenum is positioned downstream of the pulse detonation combustor and bypass flow air duct.

Pulse detonation engine bypass and cooling flow with downstream mixing volume

A pulse detonation (PD) assembly includes a number of PD chambers adapted to expel respective detonation product streams and a number of barriers disposed between respective pairs of PD chambers. The barriers define, at least in part, a number of sectors that contain at least one PD chamber. A hybrid engine includes a number of PD chambers and barriers. The hybrid engine further includes a turbine assembly having at least one turbine stage, being in flow communication with the PD chambers and being configured to be at least partially driven by the detonation product streams. A segmented hybrid engine includes a number of PD chambers and segments configured to receive and direct the detonation product streams from respective PD chambers. The segmented hybrid engine further includes a turbine assembly configured to be at least partially driven by the detonation product streams.

Pulse detonation assembly and hybrid engine

A turbine disk assembly including a rotatable cylindrical member rotatably coupled to a shaft and a plurality of turbine blades extend circumferentially outward from said cylindrical member. The turbine blades include at least two different geometrical shapes, a first of the geometrical shapes is configured to facilitate extracting power from a first pulsed detonation combustor product stream. A second of said geometrical shapes is configured to facilitate extracting power from a second pulsed detonation combustor product stream that is different from the first pulsed detonation combustor product stream.

Methods and apparatus to facilitate generating power from a turbine engine

A swirler having cross-sectional area comparable to the area of a detonation chamber is placed upstream of the detonation chamber to enhance the fuel-air mixing. The swirler has a first region and a second region, each of which induces swirl in the flow through the swirler. Each region induces a different direction of swirl in the flow. The residual net swirl present in the flow downstream of the swirler is controlled by the relative properties of each region of the swirler. The swirler also provides high optical blockage to inhibit the upstream propagation of flow due to the detonation shockwave.

Swirling flows and swirler to enhance pulse detonation engine operation

A pulse detonation engine comprises a primary air inlet; a primary air plenum located in fluid communication with the primary air inlet; a secondary air inlet; a secondary air plenum located in fluid communication with the secondary air inlet, wherein the secondary air plenum is substantially isolated from the primary air plenum; a pulse detonation combustor comprising a pulse detonation chamber, wherein the pulse detonation chamber is located downstream of and in fluid communication with the primary air plenum; a coaxial liner surrounding the pulse detonation combustor defining a cooling plenum, wherein the cooling plenum is in fluid communication with the secondary air plenum; an axial turbine assembly located downstream of and in fluid communication with the pulse detonation combustor and the cooling plenum; and a housing encasing the primary air plenum, the secondary air plenum, the pulse detonation combustor, the coaxial liner, and the axial turbine assembly.

Pulse detonation engines and components thereof

A method and system for actively controlling thrust pressure in a steam turbine is disclosed. The method may comprise monitoring a thrust pressure affecting a thrust fitting in a steam turbine, and adjusting the thrust pressure to maintain a desired thrust pressure on the thrust fitting in the steam turbine.

Variable pressure-controlled cooling scheme and thrust control arrangements for a steam turbine

Apparatus () controls net thrust in a steam turbine (T) in response to changes in the operating condition of the turbine. The turbine includes a thrust bearing (B) positioned between low and intermediate pressure sections (LP, IP) of the turbine and a high pressure section (HP) thereof. Sensors () for sense thrust loads on the thrust bearing. A number of control valve (CV-CV) are used to balance pressures occurring at locations within the high pressure section of the turbine. A controller () is responsive to the sensors sensing a change within the turbine indicative of a significant change in net thrust to energize one or more of the control valves and to adjust the pressure within the high pressure section of the turbine so to maintain net thrust within an acceptable range of thrust values.

System to control axial thrust loads for steam turbines

Growing community of inventors

Voorheesville, NY, United States of America

Christian Lee Vandervort