General Electric Company

Plug Power Inc.

Alan S Feitelberg

Narendra Digamber Joshi

Joel Meier Haynes

David Joseph Najewicz

Raul Eduardo Ayala

David Louis Burrus

Sanjay M Correa

Ching-Jen Tang

Steven George Goebel

Stephen Lan-Sun Hung

Vinod Kumar Pareek

Mark Christopher Schmidt

Stephen L Hung

Milton Bradford Hilt

Roointon Erach Pavri

Alan Whitehead

Kevin Michael Elward

Robert Lee Hillis

John Francis Love

Richard Benjamin Schiefer

Richard Arthur Symonds

An oxidizer that is usable with a fuel cell includes a catalyst, an inlet to communicate an oxidant flow, an injection tube to communicate an anode exhaust flow, a mixing tube and a divergent nozzle. The injection tube communicates the anode exhaust flow from the fuel cell into the oxidizer to produce a combined flow in which the anode exhaust flow is oriented in substantially the same direction as the oxidant flow and surrounded by the oxidant flow. The mixing tube is connected to the inlet to receive the combined flow and mix the oxidant flow and the anode exhaust flow mix together to produce a mixed flow. A cross-sectional flow area of the mixing tube is sized to prevent flashback. The divergent nozzle communicates the mixed flow to the catalyst.

Oxidizer for a fuel cell system

A gas turbine engine combustor can downstream of a pre-mixer has a pre-mixer flowpath therein and circumferentially spaced apart swirling vanes disposed across the pre-mixer flowpath. A primary fuel injector is positioned for injecting fuel into the pre-mixer flowpath. A combustion chamber surrounded by an annular combustor liner disposed in supply flow communication with the pre-mixer. An annular trapped dual vortex cavity located at an upstream end of the combustor liner is defined between an annular aft wall, an annular forward wall, and a circular radially outer wall formed therebetween. A cavity opening at a radially inner end of the cavity is spaced apart from the radially outer wall. Air injection first holes are disposed through the forward wall and air injection second holes are disposed through the aft wall. Fuel injection holes are disposed through at least one of the forward and aft walls.

Gas turbine engine combustor can with trapped vortex cavity

The addition of a magnesium compound to an ash bearing fuel results in a reduction in the formation of deposits in the turbine and extending the interval between turbine washes when burning the ash bearing fuel in a turbine compared to burning the ash bearing fuel in a turbine without the addition of a magnesium compound. The additive is desirably effective with ash bearing fuel having less than 0.5 ppm vanadium by weight, less than 1 ppm sodium and potassium combined by weight, and greater than about 25 ppm ash by weight or greater than 2 ppm calcium by weight. The additive is blended with the ash bearing fuel to give a mass ratio of magnesium to ash of between about 0.5 to 1 and about 3 to 1, and desirably about 1 to 1 on a mass basis after mixing.

Fuel composition and method for extending the time between turbine washes when burning ash bearing fuel in a turbine

The ammonia content of fuel gas in an IGCC power generation system is reduced through ammonia decomposition, thereby reducing the NO emissions from the plant. The power generation system includes a gasifier, a gas turbine and at least one catalytic reactor arranged between the gasifier and the gas turbine. The catalytic reactor may be either a three stage or two stage device. The three stage reactor includes a first catalyst which promotes water-gas-shift, a second catalyst which promotes CO methanation, and a third catalyst which promotes ammonia decomposition. The two stage reactor includes a first catalyst which promotes water-gas-shift and CO methanation and a second catalyst which promotes ammonia decomposition. The plural catalytic stages may be disposed in a single vessel or successively disposed in individual vessels, and the catalysts may be in a pelletized form or coated on honeycomb structures.

Staged catalytic ammonia decomposition in integrated gasification combined cycle systems

An optimized combustor cooperating with a compressor in driving a gas turbine comprises a cylindrical outer combustor wall having an upstream fuel entry region and a downstream turbine entry region. An array of mixing holes are disposed about the periphery of the outer combustor wall adjacent to the fuel entry region so as to lower No,production therein. An array of dilution holes are medially disposed within the outer combustor wall to provide an entry for dilution air to the combustor.

Reduced emissions gas turbine combustor

An apparatus for applying heat to a rotatable workpiece is disclosed. A rotating lathe is provided for mounting a workpiece, for example a quartz tube, thereto so as to enable rotation of the workpiece. At least one translatable burner is coupled to a fuel source and an oxygen source for producing a flame. The burner is directed such that flame impinges upon the workpiece mounted on the rotating lathe. A first pulse control valve is coupled to and positioned between the translatable burner and the fuel source. A second pulse control valve is coupled to and positioned between the translatable burners and the oxygen course. The first and second pulse control valves are pulsed at a predetermined frequency to prevent the formation of a steady thermal boundary layer about the workpiece to improve the rate of heat transfer between the flame and the workpiece.

Pulsed fuel-oxygen burner and method for rotatable workpieces

A combustor cooperating with a compressor in driving a gas turbine includes a cylindrical outer combustor casing. A combustion liner, having an upstream rich section, a quench section and a downstream lean section, is disposed within the outer combustor casing defining a combustion chamber having at least a core quench region and an outer quench region. A first plurality of quench holes are disposed within the liner at the quench section having a first diameter to provide cooling jet penetration to the core region of the quench section of the combustion chamber. A second plurality of quench holes are disposed within the liner at the quench section having a second diameter to provide cooling jet penetration to the outer region of the quench section of the combustion chamber. In an alternative embodiment, the combustion chamber quench section further includes at least one middle region and at least a third plurality of quench holes disposed within the liner at the quench section having a third diameter to provide cooling jet penetration to at least one middle region of the quench section of the combustion chamber.

Rapid-quench axially staged combustor

The ammonia content of fuel gas in an IGCC power generation system is reduced through ammonia decomposition, thereby reducing the NO.sub.x emissions from the plant. The power generation system includes a gasifier, a gas turbine and at least one catalytic reactor arranged between the gasifier and the gas turbine. The catalytic reactor may be either a three stage or two stage device. The three stage reactor includes a first catalyst which promotes water-gas-shift, a second catalyst which promotes CO methanation, and a third catalyst which promotes ammonia decomposition. The two stage reactor includes a first catalyst which promotes water-gas-shift and CO methanation and a second catalyst which promotes ammonia decomposition. The plural catalytic stages may be disposed in a single vessel or successively disposed in individual vessels, and the catalysts may be in a pelletized form or coated on honeycomb structures. Alternatively, fluidized bed reactors may be used. The reactions are carried out either adiabatically or non-adiabatically. Heat from the water-gas-shift and CO methanation reactions may be used to generate steam, which can be injected downstream or sent to a steam turbine. Preferably, a second catalytic reactor is provided in parallel with the first reactor so that the two reactors can alternately receive fuel gas from the gasifier.

Growing community of inventors

Niskayuna, NY, United States of America

Alan S Feitelberg