Mtu Aero Engines Ag

Mtu Motoren-Und Turbinen-Union Munchen Gmbh

Oskar Ostermeir

Alexander Buck

Hans-Peter Hackenberg

Wolfgang Kruger

Franz-Josef Ertl

Franz-Joseph Ertl

The present invention relates to an adjustment assembly for the adjustment of adjustable blades or vanes of a turbomachine, having an adjustment ring for coupling to the adjustable blades or vanes of a blade or vane ring and having an adjusting mechanism, which has a coupling rod for coupling to a further blade or vane ring as well as a lever and a push rod, wherein the lever is rotatably mounted at a pivot and has a load arm as well as a force arm, wherein the load arm of the lever is coupled to the push rod and its force arm is coupled to the coupling rod, on different sides of the lever, so that an offset of the coupling rod via the lever and the push rod is converted to a rotation of the adjustment ring around the ring axis thereof.

Adjustment assembly for adjustable blades or vanes of a turbomachine

A gas turbine component, in particular a stator vane cluster (), having at least one radial flange () with a radial slot () for spoke-type centering of a gas turbine element, in particular an inner ring (), the radial slot () having a first slot flank (), a slot base () adjoining the same, and a second slot flank () adjoining the same, the slot base () being asymmetric with respect to a mid-plane (M) which extends radially and perpendicularly to the circumferential direction and centrally between the two slot flanks ().

Gas turbine component

An airfoil for disposition and exposure to flow in a hot gas duct of a turbomachine is provided. The airfoil has a suction-side wall and a pressure-side wall with respect to its exposure to the flow in the gas duct, the side walls converging in an upstream end region toward a leading edge and converging in a downstream end region toward a trailing edge. The airfoil further has a cavity structure therein which is enclosed between an inner wall surface of the suction-side wall and an inner wall surface of the pressure-side wall when viewed in a cross-sectional plane axially parallel to a longitudinal axis of the turbomachine. When viewed in the cross-sectional plane, at least one of the inner wall surfaces, normalized to a mean camber line of the airfoil as a reference, extends with a change in curvature into at least one of the end regions in such a way that a clearance width of the cavity structure is increased at the at least one end region.

Airfoil for a turbomachine

Guide vane ring of a turbine of a gas turbine engine

Growing community of inventors

Kottgeisering, Germany

Oskar Ostermeir