Abstract: In a method of compressing a gas, a compression which is simple to realize is achieved in that, in a first step, a foam (21) is formed from the gas and a liquid, in which foam (21) 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 (19, 20) 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 (19, 20).

Abstract: A method and apparatus for operating a gas turbine installation combustion chamber with liquid fuel, by means of which the NOX are similar to those for gaseous fuels. The liquid fuel (38) is evaporated in two steps in an evaporative reactor (12). The liquid fuel (38) is first atomized to a fuel vapor/liquid fuel mixture (61) by direct heat exchange with a first heat exchange medium (21). The evaporation of the remaining residue of the liquid fuel (38) takes place by indirect heat exchange with a second heat exchange medium (51). An evaporative reactor (12) is arranged which accommodates, at its inlet end, a dual-fluid nozzle (22) connected both to a liquid fuel line (19) and to a supply line (20) for a first heat exchange medium (21).

Abstract: A burner for operating a unit for generating a hot gas consists essentially of at least two hollow partial bodies (1, 2) 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 (1,2) form tangential air inlet ducts (5, 6) for the inlet flow of combustion air (7) into an internal space (8) prescribed by the partial bodies (1, 2). The burner has at least one fuel nozzle (11). In order to control flow instabilities in the burner, the inside of the burner outlet (17) has a plurality of nozzles (32) along the periphery of the burner outlet (17) for introducing axial vorticity into the flow, the nozzles (32) for injecting air (34) being arranged at an angle to the flow direction (30).

Abstract: In a gas turbine having a device for the fuel injection, which injects fuel into a mixing device (12), the injected fuel being mixed with combustion air in the mixing device (12), and in which the gas turbine also has a combustion chamber (16) arranged downstream of the mixing device (12), the length of the combustion chamber being LBK and the length of the mixing device being LMix, in order to suppress thermoacoustic vibrations the premix combustion chamber (10) containing the combustion chamber (16) and the mixing device (12) is designed in such a way that an acoustic pressure fluctuation which occurs in the premix combustion chamber (10) at the combustion-chamber outlet (20) is superimposed in phase opposition on an entropy-wave-induced pressure fluctuation at a certain frequency to be damped.