Abstract: A fuel injection device includes a plurality of main burners and pilot burners. Each main burner is connected to a main distribution line, and each pilot burner is connected to a pilot distribution line. A setting device provides fuel to the main fuel line and/or to the pilot fuel line. A control unit adjusts the setting device between a first mode for exclusive pilot burner operation and a second mode for joint pilot burner operation and main burner operation such that, in the first mode, a tank connection is connected to a first line section of the main fuel line, and a second line section of the main fuel line is connected to the pilot supply line to conduct fuel through the main fuel line before it is supplied to the pilot fuel line to cool the main burner.

Abstract: A slicing machine for cutting slices of a food product includes a machine housing including a circular blade configured to rotate in a cutting plane, a stop plate configured to be move, by an adjustment device, perpendicular to the cutting plane, a carriage mounted such that it is movable parallel to the cutting plane, and a machine status display for displaying an actual status of the slicing machine.

Abstract: An air-guiding system between a compressor and a turbine of a gas turbine engine includes an air chamber (5) being delimited by the inner casing of the combustion chamber (4) and first and second seals (7, 8) towards the rotating compressor shaft cone (12). An axial thrust compensation chamber (6) is adjoined to said second seal (8) and respectively loaded with the turbine cooling air (B?, C) branched-off from the compressor air. Due to the higher pressure in said axial thrust compensation chamber with respect to said air chamber, the high axial forces are compensated. The air flowing back into said air chamber through said second seal (8) is guided and separated from components (10) and flowing-off air masses by a flow-guiding means (16) in said air chamber. This results in a high rinsing effect, a reduced vortex formation and finally, a reduced thermal stress.

Abstract: An air-guiding system between a compressor and a turbine of a gas turbine engine includes an air chamber (5) being delimited by the inner casing of the combustion chamber (4) and first and second seals (7, 8) towards the rotating compressor shaft cone (12). An axial thrust compensation chamber (6) is adjoined to said second seal (8) and respectively loaded with the turbine cooling air (B?, C) branched-off from the compressor air. Due to the higher pressure in said axial thrust compensation chamber with respect to said air chamber, the high axial forces are compensated. The air flowing back into said air chamber through said second seal (8) is guided and separated from components (10) and flowing-off air masses by a flow-guiding means (16) in said air chamber. This results in a high rinsing effect, a reduced vortex formation and finally, a reduced thermal stress.