Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Wilfried Schuette

Martin Pernleitner

Manfred Dopfer

Michael Junge

Axel Stettner

Rudolf Stanka

Markus Schlemmer

Reinhold Meier

Bernd Kislinger

Hans-Peter Hackenberg

Alexander Halcoussis

Manuel Hein

Klaus Wittig

Marcus Woehler

Oliver Thiele

Kaspar Wolf

Daniel Theurich

Carsten Schoenhoff

Hannes Wolf

Martin Becker

Georg Moosrainer

Wolfgang Horn

A curved contour of the lateral surface of a blade arrangement includes in at least one meridian section on mutually opposite sides of a blade airfoil an intersection point that is closer to the blade airfoil front edge, and an intersection point that is closer to the blade airfoil rear edge, and a best-fit line of least square distances from the curved contour. The curved contour includes first and/or the second contour section which meet specified conditions.

Gas turbine blade arrangement

The invention relates to a blade for a turbomachine, comprising a blade element with a suction side and a pressure side, which extend between a leading edge and a trailing edge of the blade element, as well as a blade root for connection of the blade at a main rotor body, wherein the blade comprises a crack-affecting device, which, in the radial direction, has an altered cross-sectional geometry in comparison to an aerodynamically optimized blade profile. The invention further relates to a rotor for a turbomachine having at least one such blade, a turbomachine having at least one such blade, and/or with such a rotor as well as a method for producing a blade.

Blade and rotor for a turbomachine and turbomachine

The invention relates to a guide vane segment for an aircraft gas turbine, comprising at least a radially outer shroud and a radially inner shroud, which extend along a respective circular arc and together form a ring segment, wherein, in the radial direction, between the outer shroud and the inner shroud, a plurality of guide vanes are arranged next to one another in the peripheral direction (UR), the vanes being materially joined with the inner shroud and the outer shroud, in particular joined in one piece. At least two securing ribs are arranged next to one another are formed on the trailing end face for at least one guide vane, wherein an intermediate space delimited by the two securing ribs in the peripheral direction (UR) is formed, this space tapering from radially outside to radially inside.

Vane segment with peripheral securing

The present invention relates to a rotating blade for a turbomachine, in particular a compressor stage or a turbine stage of a gas turbine, particularly of an aircraft engine, having a blade element for deflecting the flow, with a pressure side and a suction side, these sides being joined by a leading edge and a trailing edge, wherein a stacking axis of the blade element, in the radial direction over a radius r from a root of a blade element at r=0 to a tip of a blade element at r=H, has a course x(r) in a first downstream direction perpendicular to the radial direction and parallel to a principal axis of the turbomachine and has a course y(r) in a second direction perpendicular to the radial direction and to the first direction.

Rotating blade

A damper () for damping a blade movement of a turbomachine (), and to a method for producing the damper (). The damper () has at least one side surface (') which can be brought into frictional contact with a friction surface of the turbomachine () in order to damp a blade movement. The side surfaces (&#x2032;) are asymmetrically convex in shape.

Damping means for damping a blade movement of a turbomachine

A securing device () for axially securing a blade root () of a blade in a groove () of a turbine engine. The outer contour () of the securing device () that faces a groove wall, in particular a groove base (), is curved at least in some regions, the outer contour () having three different radii (R, R, R) in some regions.

Securing device for axially securing a blade root of a turbomachine blade

A milling tool which is used to mill recesses, in particular, circular-shaped grooves, in a workpiece is provided. The milling tool () is disposed on a disk-shaped or plate-shaped base body () and on at least one cutting body () arranged on the outer periphery of the base body (). The cutting body or each cutting body () is inclined in relation to the disk-shaped base body or the plate-shaped base body ().

Milling tool and method for milling recesses

Growing community of inventors

Oberhaching-Furth, Germany

Wilfried Schuette