Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Manuel Hein

Markus Schlemmer

Bernd Kislinger

Oliver Thiele

Rudolf Stanka

Manfred Feldmann

Frank Stiehler

Martin Pernleitner

Manfred Dopfer

Vitalis Mairhanser

Joachim Wulf

Markus Uecker

Christoph Lauer

Wilfried Schuette

Manfred Schill

Norman Cleesattel

Axel Stettner

Marcus Woehler

Philipp Langholf

Wilfried Schütte

Marcus Wöhler

A vane assembly for a turbomachine includes a variable vane (10-15), the vane having at least one first, in particular plane or curved, engagement surface (11; 11') for clamping, in particular without play, an actuator (20) of the vane assembly for adjustment of the vane, this first engagement surface not being inclined toward a longitudinal axis (L) of the vane or being inclined toward it by no more than 15&#xb0;, and/or the vane assembly including a clamp (30; 31) for clamping the actuator against the first engagement surface by at least partially elastically compressing the clamp transversely to the longitudinal axis of the vane and/or by advancing the clamp in a clamp direction (S) that forms an angle of at least 45&#xb0; with the longitudinal axis of the vane.

Variable turbomachine vane

A guide vane segmentfor a turbomachine includes a radially inner shroud platehaving a shroud plate surfacethat is adapted to be configured in the turbomachine to face a rotor bladeadjacent to the guide vane segment, and thereby essentially extend along an outer conical surface Kwhose cone axis coincides with the axis of rotation A of a rotor shaft. In a radially inner region, a rotor bladefor a turbomachine has a base platehaving a base plate surfacethat is adapted to be configured in the turbomachine to face a shroud of a guide vane rowadjacent to the rotor blade and thereby essentially extend along an outer conical surface Kwhose cone axis coincides with the axis of rotation A of a rotor shaft

Run-up surface for the guide-vane shroud plate and the rotor-blade base plate

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 invention relates to a guide vane segment for a gas turbine comprising at least one radially outer shroud and one radially inner shroud, which extend along a respective arc and together form an annular segment, wherein, in the radial direction between the outer shroud and the inner shroud, a plurality of guide vanes are arranged adjacent to one another in the peripheral direction and are joined to the inner shroud and to the outer shroud in a material-bonded manner and, in particular, are joined in a one-piece manner, wherein, in an axial lengthwise direction, the outer shroud comprises an axially front end wall element and an axially rear end wall element in such a way that the outer shroud and the two end walls form a tub-like profile in lengthwise section.

Guide vane segment with radical securing elements

An inner ring according to the invention or an inner ring segment according to the invention for an adjustable guide vane assembly comprises a plurality of uptakes, each for the bearing of an adjustable guide vane. The uptakes here each form an essentially ellipsoidally shaped uptake space for a guide vane head of the respective guide vane. A guide vane according to the invention for an adjustable guide vane assembly has a blade body and a guide vane head. The guide vane head is essentially ellipsoidal in shape and is equipped to be accommodated pivotably in an uptake of an inner ring or inner ring segment of the guide vane assembly.

Ellipsoidal inner central blade storage space

A guide vane arrangement for a turbomachine, particularly a gas turbine, is disclosed. The guide vane arrangement includes an external shroud band, on which at least two guide vanes protrude radially inward. A pair of axial ribs spaced apart from each other in the peripheral direction and disposed between two adjoining guide vanes in the peripheral direction protrude radially outward from a circumferential surface of the external shroud band and/or axially from a radial flange of the external shroud band.

Guide vane arrangement

A sealing device for an integrally bladed rotor basic body of a turbomachine to suppress a gas exchange between a hot gas stream and a cooling air stream in the radial direction in contact areas of adjacent moving blades, including a plurality of sealing elements activatable by centrifugal force, which may be situated in the area of channels which extend from a high-pressure side to a low-pressure side and are peripherally delimited by the moving blades, an integrally bladed rotor basic body having such a sealing device, and a turbomachine having such an integrally bladed rotor basic body.

Sealing device, integrally bladed rotor basic body, and turbomachine

Growing community of inventors

Karlsfeld, Germany

Manuel Hein