Rolls-Royce Deutschland Ltd & Co. Kg

Bmw Rolls-Royce Gmbh

Thomas Schillinger

Predrag Todorovic

Neil M Evans

The invention relates to a propelling nozzle for a turbofan engine on a supersonic aircraft, the propelling nozzle including: a propelling nozzle wall, a duct, which is radially outwardly bounded by the propelling nozzle wall, and a central body arranged in the duct. According to the invention, the central body is connected to the propelling nozzle wall via at least one brace.

Propelling nozzle for a turbofan engine on a supersonic aircraft

An exhaust nozzle of a gas turbine engine which includes an outer nozzle wall, a flow channel which is limited radially outwards by the nozzle wall, a centerbody arranged in the flow channel, and exactly one strut connecting the centerbody to the nozzle wall. The strut is connected to the nozzle wall by means of a connecting structure that is displaceable in the axial direction of the outer nozzle wall. At least one actuator is provided interacting with the connecting structure or the outer nozzle wall for displacing the strut in the axial direction.

Exhaust nozzle of a gas turbine engine

In connection with a turbine rotor disk in whose disk grooves air-cooled turbine blades have been inserted, at least two cooling air channels, respectively extending from the same disk front face, terminate in each disk groove. The outlet openings of two cooling air channels in each disk groove preferably lie essentially next to each other in a common sectional plane, which is normal to the disk axis. Because of this it is possible to supply a larger cooling air flow without drastically increasing the weakening, or respectively the stress of the disk in the groove bottom.

Turbine impeller disk with cooling air channels

In connection with a turbine rotating disk with disk grooves, constituted by disk fingers, for receiving turbine blades, as well as with measures for guiding a cooling air flow from a chamber located in front of the disk to one behind the disk, a cooling air transfer channel is provided in at least some of the disk fingers, which respectively starts at the front disk face, and makes a transition into a cooling air exhaust channel, also essentially extending in the radial direction in the disk finger, whose outlet opening on the rear disk face side lies closer to the disk axis than the disk ring section, which has the disk grooves and is widened in the disk axial directions. By means of this it is possible to convey a larger cooling air flow which, in an advantageous manner, indirectly aids the cooling of the disk in the area of the disk grooves.

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Berlin, Germany

Thomas Schillinger