Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Johann Geppert

Lothar Albers

Peter Eibelshaeuser

Thomas Binsteiner

Manuel Hertter

Stephen Royston Williams

Heinz Rauschmair

Stefan Herbst

Alexander Scharf

Robert Winsy

Peter Dr Eibelshäuser

A rotor member is described for a gas turbine that is adapted for rotating about a central axis, the rotor member being a blisk having a rotor blade row that extends around the central axis or a rotor disk having a mounting portion for installing rotor blades of a rotor blade row that extends around the central axis, and being axially offset from the rotor blade row and/or the mounting portion and, extending coaxially, having at least one annular and axially asymmetrical sealing fin that has a radially outer tip portion having a front flank facing the rotor blade row and/or the mounting portion, and an opposite flank facing away from the rotor blade row and/or the mounting portion; the front flank being less steep than the opposite flank; a turbine and a compressor having such a rotor member, and a method for manufacturing such a rotor member having at least one sealing fin coating.

Sealing fin having an axially asymmetric tip portion

A rotor stage () for a turbomachine, including a plurality of rotor blades (), a rotor main body () having at least two rotor arms () and a balancing assembly () for balancing the rotor stage (). The rotor arm () configured downstream from the rotor main body () features the balancing assembly (). The balancing assembly () is configured between the axial end region of the rotor arm () and the rotor disk () of the rotor main body (). Furthermore, a rotor drum () for a turbomachine and a rotor () for a turbomachine.

Rotor stage for a turbomachine, rotor drum, and rotor

A bladed rotor for a turbomachine, in particular a gas turbine, having a plurality of blades distributed around the circumference thereof; the blade distribution being made up of a natural-number sector count of first angular sectors and second angular sectors; a first blade count of first blades being arranged in the first angular sectors, and a second blade count of second blades being arranged in the second angular sectors, said second blade count being different from said first blade count; and the sector count being odd (Z=2n+1, n=1, 2, 3, . . . ) and/or greater than two (Z&#x3e;2).

Bladed rotor for a turbomachine

A blade for a continuous-flow machine is disclosed, especially an aircraft engine, whereby, starting from the middle section, the cross section of the blade tip is reduced with respect to the middle section, at least over a front partial section in the direction of the leading edge and over at least a rear section in the direction of the trailing edge, and a continuous-flow machine having at least one row of blades including such blades is also disclosed.

Blade for a continuous-flow machine and a continuous-flow machine

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Tuerkenfeld, Germany

Johann Geppert