Abstract: A combustion chamber for a gas turbine, in particular for motor vehicles, with an atomizer nozzle for the fuel fed to a pre-chamber, in which the inlet cross section for the primary air is changed by the longitudinal movement of a deflection member extending through the inlet opening of the combustion chamber. The deflection member serves as a flame holder for the stabilization of the combustion in the primary air zone while the air-atomizing nozzle is constructed ring-shaped and is provided with swirl slots in such a manner that the mixture of the fuel and of the atomizing air enters as an annular jet the primary air inlet channel, impinges approximately perpendicularly onto the primary air flow, penetrates the same and uniformly mixes with the same on its way to the inlet into the primary zone. The quantity of the primary air to be supplied is thereby automatically adjustable.

Abstract: A combustion chamber with an evaporator that projects into the combustion zone of the flame tube and includes a coaxial channel and to which air and fuel are supplied separately; a deflection surface is thereby arranged at the end of the evaporator channel which deflects the fuel/air mixture on all sides essentially opposite to the main flow direction prevailing in the channel; an annular channel partly surrounding the evaporator channel adjoins the deflection surface which is in communication by way of discharge openings with a mixing zone disposed upstream of the combustion zone, as viewed in the main flow direction; the mixing zone is formed by an annular space between an outer wall of the evaporator and an intermediate wall of the flame tube, in which are arranged radial webs within a first and a second plane, whereby the discharge openings of the annular channel terminate between the radial webs.

Abstract: A method for operating a gas turbine installation and an apparatus for carrying out the method, particularly for a vehicle gas turbine installation, in which the air is compressed and heated up by utilizing the exhaust gas heat of the gas turbine installation, fuel is combusted under supply of compressed air with an excess of air, the resulting gas is thinned out and cooled off by admixture of compressed heated air, and the produced gas is then permitted to expand for producing an output; a more or less large quantity of non-preheated air is thereby admixed to the preheated primary air prior to the entry into the combustion zone at least within the lower partial load range, preferably as a function of load, in order to control the temperature in the combustion space.

Abstract: A film-evaporating combustion chamber with an evaporator pipe whose inner wall surfaces are wetted with a fuel film from a fuel supply installation, and in which the evaporating fuel is seized by a swirling combustion air flow sweeping along the inner diameter of the evaporator pipe so as to mix the film with the combustion air; the fuel supply installation is thereby equipped with at least one feedline which extends from the inside toward the inner wall of the evaporator pipe and whose discharge opening is located substantially in front of the inner wall.

Abstract: A film evaporating combustion chamber, especially for vehicle gas turbines, which includes a radial guide cascade as guide wheel connected upstream of the inlet aperture of an evaporator pipe, which serves for producing a swirl of the combustion air; a pipe-shaped air guide housing encloses the evaporator pipe and an adjoining reaction chamber; the combustion air axially entering into the air guide housing is fed to the radial guide cascade from the outside by way of a deflection device inserted into the air guide housing and the air, after leaving the blade channels of the radial guide cascade, is then deflected in the axial direction.