Rolls-Royce Deutschland Ltd & Co. Kg

Waldemar Lazik

Thomas Doerr

Imon-Kalyan Bagchi

Carsten Clemen

Leif Rackwitz

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.

Device for mixing fuel and air of a jet engine

This invention relates to a lean premix burner of a gas-turbine engine with an annular central body, which, while being essentially concentric to a burner center axis, is provided with an annular ductconnected to a supply lineand with a film applicatorwhich conically widens at the fuel exit side and into whose radially inward area at least one fuel exit openingissues which is connected to the annular duct, characterized in that the film applicatorhas, adjacently to and downstream of the fuel exit openingsin the area facing the fuel exit side, a step-like, annular protruding areadisposed radially to the burner center axis.

Lean premix burner of a gas-turbine engine provided with a concentric annular central body

This invention relates to a lean premix burner of a gas-turbine engine with an annular central body, which, while being essentially concentric to a burner center axis, is connected to a film applicator, which conically widens at the fuel exit side, as well as to an outer ringconcentrically arranged to the burner center axisand surrounding at least the film applicatorat a certain distance, characterized in that an annular flow-guiding elementis provided in an annular ductformed between the outer ringand the film applicatorwhich, in the axial direction of the annular duct, is at least partly situated outside of the outer ring

Lean premix burner of a gas-turbine engine provided with a flow-guiding element

A gas-turbine burner for a gas turbine includes a fuel nozzlehaving several fuel exit holes, which are each connected to a fuel line, through which fuel can be passed selectively Between individual fuel exit holes, different static pressures of the airflow are provided between fuel lines flown by fuel and fuel lines not flown by fuel.

Gas-turbine burner for a gas turbine with purging mechanism for a fuel nozzle

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

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Teltow, Germany

Waldemar Lazik