Abstract: A two-substance atomizing device for atomizing a fluid in a gas stream includes: a fluid supply branch including a nozzle orifice; a gas supply branch configured concentrically about the fluid supply branch; a concentric second gas branch branching from the gas supply branch and disposed upstream of the nozzle orifice, the nozzle orifice terminating in the gas supply branch; an axially symmetric mixing channel disposed in axial extension of the fluid supply branch and including a discharge orifice; an annular injection orifice in communication with the gas supply branch and disposed near the discharge orifice; and an adjustment device configured to adjust a cross section of the injection orifice.

Abstract: The invention relates to a burner for combustors of gas turbines, the burner having an atomizer nozzle for atomisation of fuel in the combustion air and having a primary and secondary flow channel. In the burners, mostly used in aircraft engines, an extensively homogenous distribution of the air-fuel mixture is to be achieved in the combustor to reduce emissions. The flow channels opening into the combustor are separated from a first component arranged concentrically in relation to the burner axis and having a sleeve-shaped atomizer lip extending cylindrically or conically, and the external secondary flow channel is bounded externally and radially by a second annular component arranged concentrically and having an internal wall extending to converge and diverge. The second component forms an area with the most narrow flow cross-section, and the first component is arranged radially inwards and ends with the atomizer lip at the axial height of the cross-section or upstream thereof.

Abstract: The present invention provides dual-fuel burners for the oxidation of liquid and of gaseous fuel with air. A dual-fuel burner is provided with an atomizer nozzle which generates a divergent spray cone of liquid fuel, and with an annular atomizer lip as an impact member for the liquid fuel spray cone. The dual-fuel burner has a primary channel for a first air stream through the spray cone and the inside of the atomizer lip, and a secondary channel for a second air stream over the outside of the atomizer lip with a common, coaxial mouth at an atomizer edge thereof. A channel for the gaseous fuel leads into the inside of the atomizer lip between the primary and secondary channels and discharges into one or both of the primary and secondary channels upstream of the atomizer edge.

Abstract: A system is provided for cooling especially the backplate of a flame tube of a combustion chamber for gas turbine engines, of the type having at least one burner arranged on the backplate and having a fuel nozzle and at least one swirler arranged coaxially with the fuel nozzle for the supply of combustion air. The backplate is cooled with compressed air diverted from a compressor and ducted to a head end of the combustion chamber. The backplate forms at least one cooling air duct to carry the compressed air supplied for backplate cooling, and the cooling air duct communicates at its outlet end at the burner with the flame tube such that the compressed air issuing from the cooling air duct enters into combustion in the primary zone. At its outlet end the cooling air duct can communicate with the air inlets of at least one swirler.

Abstract: A combustion chamber apparatus 1 for a gas turbine has a pilot stage and a main stage for low-emission lean-burn operation. The pilot stage is separate from the main stage and is formed by a flame tube 2 with an upstream first fuel injector 3a and with a secondary combustion zone 7a. The main stage includes a vaporization chamber 4 and a combustion chamber 5, and a second fuel injector 3b is provided at an upstream end of the vaporization chamber 4. The vaporization chamber 4 produces a homogenous fuel-air mixture which will not burn until it is in the combustion chamber 5. In lean-burn operation of the apparatus, the separate arrangement of the two chambers 4, 5 significantly reduces the formation of nitrogen oxides. For use in aircraft gas turbine engines, the apparatus has an annular shape with several main and pilot stages.

Abstract: A burner for gas turbine engines is provided in which a ring-shaped swirling device is coaxially assigned to a fuel nozzle. The swirling device forms tangential ducts for an adjustable feeding of combustion air between profiles arranged along the circumference. In this case, the profiles are to be formed by corresponding sections of components which are arranged to be axially movable relative to one another. One respective section of a profile is to be a hollow body in which the corresponding other section engages in a movable manner. With the burner, a combustion is made possible that is low in pollutants while the swirling efficiency and the rotational swirl development are optimal.

Abstract: A burner for gas turbine engines is provided in which a ring-shaped swirling device is coaxially assigned to a fuel nozzle. The swirling device forms tangential ducts for an adjustable feeding of combustion air between profiled surfaces arranged along the circumference. Two components, which are axially adjustable relative to one another, are to form, on mutually opposite faces, the ducts between profiles and recesses which are arranged offset relative to one another along the circumference, in such a manner that, when at least one component is adjusted, the profiles can be moved into the recesses for a reduction of the duct cross-sections or can be moved out of the recesses for an enlargement of the duct cross-sections.