Abstract: The present invention relates to a method for operating a lean premix burner of an aircraft gas turbine, where fuel and primary supporting air are supplied by means of a supporting burner (pilot burner) arranged centrically to the burner axis, where secondary air surrounding the supporting burner is supplied, and where fuel and air are supplied by means of a main burner, characterized in that the primary supporting air is supplied in an amount of 5 vol % to 10 vol % of the total air quantity, that the secondary supporting air is supplied in an amount of 5 vol % to 20 vol % and that 35 vol % to 75 vol % of the total air quantity are supplied via the main burner in the partial load range and in the full load range.

Abstract: A device for mixing fuel and air of a jet engine includes at least one air-carrying duct and at least one further fuel-carrying duct. Guide elements extending over the duct height and distributed over the circumference of the duct are provided at least in the air-carrying duct, in the area of which guide elements a twist can be imparted to the air flowing in the air-carrying duct in order to improve mixing between the air and the fuel downstream of the ducts. The guide elements are provided at a trailing edge with at least one downstream extending projection and/or upstream extending recess designed at least approximately or at least in some areas with a sharp edge.

Abstract: This invention relates to a lean premix burner of a gas-turbine engine with an annular central body 2, which, while being essentially concentric to a burner center axis 1, is connected to a film applicator 3, which conically widens at the fuel exit side, as well as to an outer ring 4 concentrically arranged to the burner center axis 1 and surrounding at least the film applicator 3 at a certain distance, characterized in that an annular flow-guiding element 6 is provided in an annular duct 5 formed between the outer ring 4 and the film applicator 3 which, in the axial direction of the annular duct 5, is at least partly situated outside of the outer ring 4.

Abstract: This invention relates to a lean premix burner of a gas-turbine engine with an annular central body 2, which, while being essentially concentric to a burner center axis 1, is provided with an annular duct 4 connected to a supply line 3 and with a film applicator 5 which conically widens at the fuel exit side and into whose radially inward area at least one fuel exit opening 6 issues which is connected to the annular duct, characterized in that the film applicator 5 has, adjacently to and downstream of the fuel exit openings 6 in the area facing the fuel exit side 8, a step-like, annular protruding area 7 disposed radially to the burner center axis.

Abstract: A fuel injector includes pilot and main fuel injectors. The pilot fuel injector includes at least one pilot air swirler and the main fuel injector includes a main air blast fuel injector located between inner main and outer main air swirlers. A first air splitter is located between the pilot and inner main air swirlers and a second air splitter is located between the pilot and inner main air swirlers. The first air splitter has a downstream portion converging to a downstream end. The second air splitter has a downstream portion diverging to a downstream end. The second air splitter downstream end is downstream of the first air splitter downstream end and the ratio of the distance from the first air splitter downstream end to the second air splitter downstream end to the diameter of the second air splitter downstream end is in the range of 0.22 to 0.30.

Abstract: A gas-turbine burner for a gas turbine includes a fuel nozzle 1 having several fuel exit holes 23, which are each connected to a fuel line 5, 7, 29, 30, through which fuel can be passed selectively Between individual fuel exit holes 23, different static pressures of the airflow are provided between fuel lines flown by fuel and fuel lines not flown by fuel.

Abstract: This invention relates to a lean premix burner of a gas-turbine engine with an annular central body 2, which, while being essentially concentric to a burner centre axis 1, is connected to a film applicator 3, which conically widens at the fuel exit side, as well as to an outer ring 4 concentrically arranged to the burner centre axis 1 and surrounding at least the film applicator 3 at a certain distance, characterized in that an annular flow-guiding element 6 is provided in an annular duct 5 formed between the outer ring 4 and the film applicator 3 which, in the axial direction of the annular duct 5, is at least partly situated outside of the outer ring 4.

Abstract: This invention relates to a lean premix burner of a gas-turbine engine with an annular central body 2, which, while being essentially concentric to a burner centre axis 1, is provided with an annular duct 4 connected to a supply line 3 and with a film applicator 5 which conically widens at the fuel exit side and into whose radially inward area at least one fuel exit opening 6 issues which is connected to the annular duct, characterized in that the film applicator 5 has, adjacently to and downstream of the fuel exit openings 6 in the area facing the fuel exit side 8, a step-like, annular protruding area 7 disposed radially to the burner centre axis.

Abstract: A gas-turbine burner for a gas turbine includes a fuel nozzle 1 having several fuel exit holes 23, which are each connected to a fuel line 5, 7, 29, 30, through which fuel can be passed selectively Between individual fuel exit holes 23, different static pressures of the airflow are provided between fuel lines flown by fuel and fuel lines not flown by fuel.

Abstract: A gas turbine combustion chamber with a burner 7, includes means for the supply of fuel and an atomizer 6, wherein the means for the supply of fuel are provided such that the fuel is injected in areas with maximum airflow velocity.

Abstract: A gas turbine combustion chamber with a burner 7, includes means for the supply of fuel and an atomizer 6, wherein the means for the supply of fuel are provided such that the fuel is injected in areas with maximum airflow velocity.

Abstract: The invention relates to a highly substituted carboxyalkyl starch which is obtained by a special slurry method. A conversion of starch with halogenated acids is thereby effected in an organic-aqueous reaction medium in the presence of alkali hydroxide. This starch is used in the chemical industry field.