Abstract: A fuel lance for liquid and/or gaseous fuels for use in a combustion chamber includes a liquid fuel pipe extending along a lance center line and defining a liquid fuel passage, a gas pipe surrounding the liquid fuel pipe and forming therebetween a gas passage, and a lance outer shell surrounding the gas pipe and forming an air passage around the gas pipe for cooling air and atomizer air. At least one air/fuel nozzle is provided in a peripheral side of the lance outer shell at a downstream end of the fuel lance for air flow out of the air passage into the combustion chamber. At least one gas nozzle is provided in the gas pipe for gas flow out of the gas passage into the air passage, the gas nozzle is positioned relative to the air/fuel nozzle so that gas from the gas nozzle flows with air from the air passage through the at least one air/fuel nozzle into the combustion chamber.

Abstract: In a drum rotor for an axial flow turbomachine, the blades are fastened via their roots (22) in circumferential blade grooves (1-13) with support indentations at the side. A circumferential forward groove (0), which is not fitted with blades, is located upstream of the first blade groove (1). This forward groove (0) is fitted with axially split closing segments (24).

Abstract: In order to clamp blades (1, 2, n) of turbomachines to influence the blade vibration occuring in such machines, the shroud plates (1a, 2a, na) are dimensioned in such a way that they are in contact with one another in the installed condition without clearance and without contact force or else they are dimensioned so that they exhibit a gap (3) relative to each other. A prestressed or pretorsioned, clearance-free connection occures between the shroud plates (1a, 2a, na) due to plastic deformation of the shroud plates (1a, 2a, na) in the region of their boundries or of the gap (3).

Abstract: In the case of saddle-type rotor blades of axial-flow turbomachines, the locking blade (6a), without its root part engaging in the fir trees (2) on the radially outer part of the rotor disk (1), is located under a large prestress between its neighboring blades (6b, 6c). It is fastened in the root part by means of axial pins (7). The blade root (4') of the locking blade (6a) is dimensioned more narrowly in the region of its fir trees (2') in its axial extension than that (4) of the neighboring blades (6b, 6c). By this means, a removal recess (10) is produced on both the inlet and outlet sides, in each of which a compression jack (11) can be introduced for pressing apart the neighboring blades (6b, 6c). The locking blade, relieved of loads in this manner, can be removed without being destroyed.

Abstract: In order to damp blade vibrations, the shroud plates of the blades are equipped with magnet inserts.