Alstom Technology Limited

Alstom (switzerland) Ltd

Ansaldo Energia IP UK Limited

Alstom

Ansaldo Energia Switzerland Ag

H2 IP UK Limited

Thomas R Ruck

Timothy Albert Griffin

Christian Steinbach

Peter Jansohn

Peter Stuttaford

Douglas Pennell

Michael Thomas Maurer

Stephen Wilder Jorgensen

Donald Gauthier

Hans Peter Knoepfel

Joshua R McNally

Pawel Matys

Bernard Tam-Yen Sam

Marc Paskin

Martin Andrea Von Planta

Sasha Savic

Wolfgang Weisenstein

Weiqun Geng

Slawomir Slowik

Christoph Gaupp

Torsten Strand

Michele Pereti

Hanspeter Knöpfel

Peter John Stuttaford

Stephen W Jorgensen

Douglas Pennel

Roland HÄFLIGER

Systems and methods for dual-fuel operation of a gas turbine combustor are provided. An exemplary gas turbine combustor may comprise one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly, one or more of which may be configured to supply either a gaseous or a liquid fuel to the combustion liner, depending on whether gaseous fuel operation or liquid fuel operation of the combustor is desired.

Fuel injection locations based on combustor flow path

Gas turbine combustion systems and fuel cartridge assemblies are provided. An exemplary combustion system may comprise a combustor including one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly. An exemplary fuel cartridge assembly may comprise first and second fuel manifolds which are connected to respective fuel circuits which supply fuel, such as liquid fuel, through a plurality of fuel passages within the fuel cartridge assembly or to other locations within an associated combustor. The fuel cartridge assembly may further include a plurality of fuel injector tips located at a tip plate of the fuel cartridge assembly through which fuel may be supplied to an associated combustor.

Gas turbine fuel components

A premixing burner has a swirl generator with at least two burner shells () which jointly enclose an axia conically widening swirl space and delimit tangential air inlet slits () through which combustion supply air passes into the swirl space in which an axially propagating swirl flow is formed, and with fuel injection devices at least partially along the tangentially running air inlet slits (). The fuel injection devices include a fuel line () separate from the burner shell () and which is firmly attached to the burner shell () so as to be longitudinally movable with respect to the burner shell () and releasable perpendicularly to the surface of the burner shell (). In the burner shell (), orifices () are provided, into which issue fuel injectors () which are provided along the fuel line () and which project beyond the circumferential edge of the fuel line ().

Premixing burner for generating an ignitable fuel/air mixture

A premix burner for producing an ignitable fuel/air mixture has a swirl generator with at least two burner shells (B) which complement one another to form a throughflow body, which in each case have a first burner shell section () with a partial cone shape and together enclose an axially conically widening swirl space and which mutually define, in the axial cone longitudinal direction, tangential air inlet slots (LS), through which the combustion feed air (L) passes into the swirl space, in which an axially spreading swirl flow forms, and includes fuel feeds which are arranged at least in sections along the tangentially running air inlet slots (LS). A second burner shell section () curved in opposition to the first burner shell section (), in each case designed in a partial cone shape, is added flush to the first burner shell section (), a third burner shell section () adjoins the second burner shell section () flush, the third burner shell section () having a curvature tangentially adapted to the second burner shell section (), and the third burner shell section () defines, on the one side in each case, one of the tangential air inlet slots (LS) and provides a leading edge () serving for the combustion feed air (L).

Premix burner for operating a combustion chamber

A burner () which is useful for operating a heat generator includes a first upstream swirl generator () capable of swirling a combustion air stream, a device for injecting at least one fuel into the combustion air stream from the upstream swirl generator (), an exit ring () located at the downstream end of the burner () at the edge to the combustion chamber () where the fuel is burnt, and preferentially a mixing section () downstream from the upstream swirl generator () having a downstream end, having at least one transfer duct () for transferring downstream a flow of combustion air and fuel formed in the upstream swirl generator (), and having a mixing tube () downstream from the at least one transfer duct () and receiving flow from the at least one transfer duct (), wherein the downstream end of the mixing section borders the combustion chamber () and is formed by the exit ring (). Pilot mode operation of such a burner () is advantageously and economically made possible by providing a pilot burner system () in the exit ring () for injecting liquid fuel () into the combustion chamber ().

Premixed exit ring pilot burner

The invention relates to a premix burner with high flame stability for use in a heat generator, preferably in the combustion chamber of a gas turbine. Modern, lean-operated premix burners enable very low noxious emissions, but sometimes operate very close to the extinction limit. To increase the stability of the lean premix combustion by increasing the distance between flame temperature and extinction limit temperature the invention proposes to equip the burner in the mixing zone ( ) with a net-like structure ( ) for the premixing of combustion air and fuel. According to a preferred embodiment, the net-like structure ( ) consists of a plurality of layers of individual wire mesh fabrics ( ) arranged at a distance from each other. The wire mesh fabrics ( ) are preferably equipped with an oxidation-promoting, catalytically active surface. It was found that the net structure ( ) positively influences the thermoacoustic behavior of the burner and dampens and insulates pressure waves from the combustion chamber ( ), and in this way reduces the excitation of pressure waves in the combustion chamber ( ).

Premix burner with high flame stability having a net-like structure within the mixing section

Premix burner arrangement for operating a combustion chamber

The invention relates to a premix burner with high flame stability for use in a heat producer, preferably in the combustion chamber of a gas turbine. Modern lean operated premix burners make possible very low pollutant emissions, but sometimes operate very close to the extinction limit. To increase the stability of the lean premix combustion by increasing the distance between the flame temperature and the extinction limit temperature, it is proposed according to the invention to arrange a downstream combustion gas mixing section ( ) for the burner, which mixing section ( ) projects at least partially into the combustion chamber ( ) and enables combustion gases from the combustion chamber ( ) access to the fuel/air mixture ( ) by means of combustion gas inlet openings ( ). The added combustion gases ( ) are mixed with the fuel/air mixture ( ), and in this manner increase its temperature. This increase in temperature results in a significant increase in the flame speed, as a consequence of which the extent of the flame front ( ) and the extinction limit temperature of the burner decrease.

Burner with high flame stability

A premix burner arrangement with catalytic combustion provides a fuel/air mixture to a combustion chamber of a gas turbine arrangement. The premix burner arrangement includes a premix burner, at least one fuel addition unit, and air inlet openings arranged in such a way that at least one of gaseous and liquid fuel can be mixed with combustion inlet air inside the premix burner to form a fuel/air mixture. The fuel/air mixture exits from the premix burner downstream in the direction towards a combustion chamber positioned after the premix burner arrangement and can be ignited inside the combustion chamber. A catalyzer unit is provided before the entrance of the fuel/air mixture into the combustion chamber. Part of the fuel/air mixture can be introduced into and passed through the catalyzer unit before the catalyzed part of the fuel/air mixture flows together with the remaining portion of the fuel/air mixture into the combustion chamber.

Premix burner arrangement with catalytic combustion and method for its operation

According to the invention, in burners having a swirl generator ( ), a mixing tube ( ) and a combustion chamber ( ), the transition from the mixing tube ( ) to the combustion chamber ( ) is designed with a variable radius over the circumference of the mixing tube ( ). As a result, it is possible to form the flame in various shapes&mdash;from a circle to an ellipse with a ratio of width to height of 3 at most. The number of burners in a gas turbine may thus be advantageously reduced. Burners of existing gas turbines may be converted in a simple manner.

Burner for a heat generator

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Rekingen, Switzerland

Thomas R Ruck