Alstom Technology Limited

Abb Research Ltd.

Alstom (switzerland) Ltd

Abb Alstom Power (switzerland) Ltd.

Alstom

Abb Management Ag

General Electric Technology Gmbh

Ansaldo Energia IP UK Limited

Christian Steinbach

Klaus Dobbeling

Bettina Paikert

Peter Jansohn

Thomas R Ruck

Weiqun Geng

Hans Peter Knopfel

Stefano Bernero

Thomas Ruck

Stefan Tschirren

Peter Stuber

Daniel Burri

Martin Andrea Von Planta

Andreas Abdon

Timothy Albert Griffin

Christian Oliver Paschereit

Thomas Sattelmayer

Peter Flohr

Dieter Winkler

Douglas Pennell

Wolfgang Polifke

Rolf Dittmann

Wolfgang Franz Dietrich Mohr

Jurgen Haumann

Ken-Yves Haffner

Gijsbertus Oomens

Jonathan Lloyd

Slawomir Slowik

Martin Valk

Allen Michael Pfeffer

Franz B&uuml;chi

Peter Dubach

Jurgen Hoffmann

Richard Straessle

Uwe Hoferer

Philippe Jean-Michel Paelinck

Charles Soothill

Jérôme André Aubry

Nicolas Ulibarri

Thomas Sattelamayer

Johannes Santner

Wolfgang Franz Mohr

Jerome Andre Aubry

A combustion device () includes at least one combustion chamber () with a plurality of burners (B, . . . , Bn) operating in parallel which produce in each case a flame (F, . . . , Fn) which reaches into the combustion chamber (), wherein each of the burners (B, . . . , Bn), via a fuel distribution system (), is supplied with a fuel from a fuel supply (), which fuel distribution system () includes control elements (V, . . . , Vm) for manual or controlled regulating of the fuel supply and/or fuel composition of individual burners (B, . . . , Bn) and/or groups of burners (B, . . . , B; Bn&#x2212;2, . . . , Bn). In a method of using the combustion device, a quick optimization or homogenization is achieved by a function (F) of the flame temperatures of the burners (B, . . . , Bn) being provided in dependence upon the positions of the control elements (V, . . . , Vm) of the fuel distribution system (), which function has been calibrated by measurements of the flame temperatures at a plurality of predetermined positions of the control elements (V, . . . , Vm) of the fuel distribution system (), and in that by the calibrated function (F) the positions of the control elements (V, . . . , Vm) of the fuel distribution system (), which are optimum for a predetermined distribution of the flame temperatures of the burners (B, . . . , Bn), are determined and adjusted.

Method for operating a combustion device

In a method for reducing the NOx emissions from a burner arrangement comprising a plurality of burners (B, . . . , Bn), in particular in a gas turbine, which burners (B, . . . , Bn) are operated in parallel and each burner supplied fuel by means of combustion air to form a flame (F, . . . , Fn), an effective drop is achieved in a simple way by virtue of the fact that at a predetermined time the flame temperatures of individual burners (B, . . . , Bn) or burner groups or differences between the flame temperatures of individual burners (B, . . . , Bn) or burner groups are measured directly or indirectly. The fuel supply to those burners or burner groups whose flame temperature exceeds a predetermined value for the flame temperature is selectively throttled in order to homogenize the flame temperatures of the burners (B, . . . , Bn).

Method for reducing the NOx emissions from a burner arrangement comprising a plurality of burners, and burner arrangement for carrying out the method

Power plant characteristics are operated in a flexible manner by controlling the power consumption of a COcapture and compression system. The impact of COcapture and compression on the capacity of a power plant can be minimized to maximize the electric power the plant can deliver to the power grid and the impact of COcapture and compression on the average plant efficiency can be reduced, by an operating method and a power plant, in which the power consumption of the COcapture system is used to control the net output of the plant.

[object Object]

A combustion chamber of a combustion system has a combustion space, a support structure, a support element, and a heat shield. The heat shield has at least two segments, and each segment includes a liner element facing the combustion space and has an edge region, a gap communicating with the combustion space being formed between edge regions of adjacent segments, and a retaining device. The retaining device fixes the respective liner element on the support structure via the support element and forms a flange region that fits over the edge region of the respective liner element. The retaining device forms a first cooling passage with the support element and has at least one through-opening in the flange region. A cooling gas flows through the through.opening from the first cooling passage to the edge region.

Combustion chamber of a combustion system

A combustion chamber of a combustion system comprises a combustion space, a support structure, a heat shield, and at least one through-opening. The heat shield has at least two segments, and each segment has an edge region, a gap communicating with the combustion space being formed between edge regions of adjacent segments, and a retaining device. The adjacent segments include a support element disposed in a bottom region of the gap. The retaining device fixes the respective liner element on the support structure via the respective support element. The at least one through-opening communicates with the gap so as to enable a cooling gas to flow through the through-opening. The at least one through-opening is disposed in at least one of the respective edge region and the support element at the bottom region of the gap.

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 premix burner, for example for a gas turbine, having a conical swirl generator () and a cylindrical mixing section () which follows it in the direction of flow, includes a high-pressure atomizer nozzle () with one or more fuel feed passages. The high-pressure atomizer nozzle () includes at least two outlet passages, through which liquid fuel enters the swirl generator (), these passages being arranged off-center with respect to the longitudinal axis of the nozzle and being configured in such a way that the spray cone () of the fuel is oriented at an angle (&#x3b2;) with respect to the longitudinal axis of the swirl generator () which is smaller than the cone half-angle (&#x3b1;) of the swirl generator (). The outlet passages in particular have an internal geometry with a conically narrowed section.

Burner for a gas turbine

In a fuel lance by means of which fuels can be injected, via at least two separate passages, into a combustion chamber alternately or simultaneously at an injection location arranged substantially at the lance tip, reliable operation is achieved, without the risk of flashbacks and also without coking, by virtue of the fact that the fuel lance, in addition to fuel, also passes purge air to the injection location, and that the purge air, at the injection location, is routed between the two fuel systems, in such a manner that these systems are shielded from one another by the purge air.

Apparatus for injecting a fuel-air mixture into a combustion chamber

Method for injecting a fuel-air mixture into a combustion chamber

An aerodynamically stabilized premixing burner includes a swirl generator for the production of a rotating combustion air flow, and a device for the introduction of at least one fuel into this combustion air flow. The burner is advantageously provided with a device for the introduction of an axial air flow into the center of the generated rotational flow. This axial air flow is controllable in order to affect the position and intensity of the flame-stabilizing recirculation zone at the burner mouth.

Process for operation of a burner with controlled axial central air mass flow

Premix burner arrangement for operating a combustion chamber

Combined pressure atomizing nozzle

In a method for burning a liquid fuel in a combustion system ( ) which comprises a combustion chamber ( ) and at least one injection nozzle ( ) through which liquid fuel is injected into the combustion chamber ( ) in the form of a fuel spray ( ) and is burnt there with combustion air being added, disturbance-free operation in a simple manner is distinguished in that, in order to actively suppress hydrodynamic instabilities in the combustion chamber ( ), the injected fuel spray ( ) is modulated by having an electrical voltage applied to it during the injection process, governed by a selected time function.

Method for combustion of a liquid fuel in a combustion system, and a combustion system for carrying out the method

A premix burner consisting essentially of a swirl generator for a combustion air stream or another gaseous oxidizing medium and of conduits for injecting fuel into the swirl flow thus generated. As a result of a discontinuous cross-sectional widening at the transition to the combustion space, the swirl flow bursts open and a backflow bubble is formed, which serves for flame stabilization. For use under extreme thermal conditions, the burner front is provided with a heat shield which is fastened to a carrier structure in such a way as to allow, as unimpeded as possible, differential thermal expansions. The carrier structure is preferably provided with orifices, through which cooling air for the impact cooling of the heat shield flows. In a preferred variant, the fuel gas supply is designed as pipes which are led through orifices of the swirl generator without any fixed connection. As a result of this design, thermal stresses in the material of the burner are avoided as far as possible.

Premix burner

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Birmenstorf, Switzerland

Christian Steinbach