Abb Research Ltd.

Alstom (schweiz) Ag

Abb Search Ltd.

Klaus D&ouml;bbeling

Christian Oliver Paschereit

Ephraim J Gutmark

Dieter Winkler

Wolfgang Polifke

Bettina Paikert

Wolfgang Weisenstein

Fulvio Magni

Lothar Reh

Gerhard M&uuml;ller

Yunhong Wang

Geoffrey Engelbrecht

Johannes Buss

A burner for operating a heat generator, includes a swirl generator ( ) for a combustion air flow ( ) means for injecting at least one fuel into the combustion air flow. A mixing section is arranged downstream of this swirl generator, which mixing section has, within a first section in the flow direction, a number of ducts in a transition piece ( ) for the transfer of a flow formed in the swirl generator into a mixing tube ( ) connected downstream of this transition piece. A combustion space ( ) is arranged downstream of this mixing tube. The swirl generator ( ) is integrated into an inlet flow cross section ( ) which is essentially closed by the swirl generator, and is subjected to the combustion air flow ( ).

Burner for heat generator

In a method for reliably removing liquid fuel from the fuel system of a gas turbine after shutting down the same, in the case of which fuel system liquid fuel is fed via at least a first feeder line in normal operation of the gas turbine to a burner and injected there into a combustion chamber via fuel nozzles, a high reliability against explosion and coking is achieved in a simple way by virtue of the fact that the liquid fuel is flushed from the fuel system by the use of an inert auxiliary medium.

Method for reliably removing liquid fuel from the fuel system of a gas turbine, and a device for carrying out the method

A description is given of a method for feeding liquid and/or gaseous fuels to gas turbines, by means of which method the same feed path to the burner of the gas turbine can be used for both fuels, the liquid fuel being processed before being fed to the burner. This processing takes place in a fuel pre-evaporator which, for the purpose of processing the liquid fuel, has an evaporator tube,, which is made of a material with good thermal conductivity, interacts with a heating device (,) and, at its one end, is connected to a feed device (,) for a flushing gas, and, at its other end, is connected to a fuel feed and discharge appliance (,).

Method for feeding a gas turbine with both liquid and gaseous fuels

In a method of compressing a gas, a compression which is simple to realize is achieved in that, in a first step, a foam (,) is formed from the gas and a liquid, in which foam (,) the sonic velocity is markedly lower than in the gas and in the liquid taken by themselves, in that, in a second step, the foam is directed at supersonic velocity through a nozzle (,) and the gas located in the foam is thereby compressed, and in that, in a third step, the compressed gas and the liquid are separated from one another behind the nozzle (,).

Supersonic centrifugal compression and separation of liquid and gas mixture

A method and apparatus for operating a gas turbine installation combustion chamber with liquid fuel, by means of which the NO,are similar to those for gaseous fuels. The liquid fuel (,) is evaporated in two steps in an evaporative reactor (,). The liquid fuel (,) is first atomized to a fuel vapor/liquid fuel mixture (,) by direct heat exchange with a first heat exchange medium (,). The evaporation of the remaining residue of the liquid fuel (,) takes place by indirect heat exchange with a second heat exchange medium (,). An evaporative reactor (,) is arranged which accommodates, at its inlet end, a dual-fluid nozzle (,) connected both to a liquid fuel line (,) and to a supply line (,) for a first heat exchange medium (,).

Appliance for operating a gas turbine installation combustion chamber with liquid fuel

A burner for operating a unit for generating a hot gas consists essentially of at least two hollow partial bodies (,) which are interleaved in the flow direction and whose center lines extend offset relative to one another in such a way that adjacent walls of the partial bodies (,) form tangential air inlet ducts (,) for the inlet flow of combustion air (,) into an internal space (,) prescribed by the partial bodies (,). The burner has at least one fuel nozzle (,). In order to control flow instabilities in the burner, the inside of the burner outlet (,) has a plurality of nozzles (,) along the periphery of the burner outlet (,) for introducing axial vorticity into the flow, the nozzles (,) for injecting air (,) being arranged at an angle to the flow direction (,).

Burner

In a gas turbine having a device for the fuel injection, which injects fuel into a mixing device (,), the injected fuel being mixed with combustion air in the mixing device (,), and in which the gas turbine also has a combustion chamber (,) arranged downstream of the mixing device (,), the length of the combustion chamber being L,and the length of the mixing device being L,, in order to suppress thermoacoustic vibrations the premix combustion chamber (,) containing the combustion chamber (,) and the mixing device (,) is designed in such a way that an acoustic pressure fluctuation which occurs in the premix combustion chamber (,) at the combustion-chamber outlet (,) is superimposed in phase opposition on an entropy-wave-induced pressure fluctuation at a certain frequency to be damped.

Growing community of inventors

Windisch, Switzerland

Klaus Döbbeling

Growing community of inventors

Windisch, Switzerland

Klaus D&ouml;bbeling

Klaus Döbbeling