Mtu Aero Engines Ag

Klaus Wittig

Martin Pernleitner

Manfred Dopfer

Dieter Freno

Marcus Woehler

Lutz Friedrich

Tino Hummel

Rudolf Stanka

Detlef Korte

Markus Brettschneider

Bernd Kislinger

Christian Eichler

Wilfried Schuette

Norman Cleesattel

Kaspar Wolf

Carsten Schoenhoff

Christoph Bichlmaier

Wilfrid Schuette

Johannes Linhard

Carsten Schönhoff

Wilfried Schütte

Marcus Wöhler

A rotor for a turbomachine has at least one blade and has at least one rotor main part, which has at least one recess, in which a blade root of the least one blade is interlockingly received, wherein the blade root comprises at least one depression, in which at least one protrusion of the at least one rotor main part, which protrusion delimits the at least one recess in regions is received, wherein the at least one depression is delimited by a first delimiting face on the blade root side and the at least one protrusion is delimited by a second delimiting face on the rotor main part side. At least the first delimiting face has at least one elevation which narrows a gap at least in regions, which extends between the first delimiting face and the second delimiting face.

Rotor for a turbomachine and turbomachine

A stator vane for a turbomachine, including an airfoil having a leading edge and a trailing edge, which are interconnected by a suction side and a pressure side, the airfoil extending substantially in a radial direction between an inner platform and an outer platform, wherein, when viewed in an axial direction of the turbomachine toward the trailing edge, the trailing edge extends so as to be inclined at a first angle to the pressure side radially on an outside in relation to the radial direction at a circumferential position at which the trailing edge meets the outer platform, and wherein the first angle between the trailing edge and a tangent to the outer platform at a transition from the outer platform to the trailing edge is between 72° and 84°.

Stator vane for a turbomachine

An intermediate element is for a blade/rotor disk connection in a rotor of a fluid flow machine. The intermediate element is adapted to a shape of a blade root of a blade and to a blade root slot in a rotor disk for receiving the blade root such that, when arranged between the blade root and rotor disk, the intermediate element prevents contact between the blade root and rotor disk. The intermediate element has, on an outer surface that faces the rotor disk, at least one protrusion to reduce an air flow parallel to an axis of rotation of the rotor between the rotor disk and the intermediate element; and on an inner surface that faces the blade root, a recess that corresponds to the at least one protrusion.

Intermediate element for a blade/rotor disc connection in a rotor of a turbomachine, associated rotor for a turbomachine, and turbomachine

A gas turbine has a rotor blade. The rotor blade has a blade root connected to an airfoil. The blade root has a root contour with respect to a cross-sectional view. From a lower end of the blade root, the blade root contour has convex contour portions and concave contour portions. From the lower end along the blade root contour between a convex contour portion and an adjoining concave contour portion, there is a contour portion as a flank portion that is load-bearing. From the lower end along the blade root contour between a concave contour portion and an adjoining convex contour portion, there is a contour portion as a flank portion that is not load-bearing in operation. At least one of the concave contour portions has a first arc portion, a second arc portion, and a straight portion disposed between the two arc portions.

Rotor blade with blade root contour having a straight portion provided in a concave contour portion

A rotor blade for a gas turbine, in particular an aircraft gas turbine, having a blade root element and a stream deflection portion adjoining the blade root element () in the longitudinal direction of the blade (RR); respective centroids () of blade cross-sectional areas of the stream deflection portion residing on a common stacking axis (). It is provided that, starting from a first centroid () of a first blade cross-sectional area adjoining the blade root element (), the stacking axis () extend within a cone () whose apex resides within the first centroid (), and whose cone height (KH) extends orthogonally to the plane of the blade cross-sectional area; the angle (&#x3b2;) of the cone () being greater than 0&#xb0; and smaller than or equal to 4&#xb0;; preferably greater than or equal to 0.5&#xb0; and smaller than or equal to 2&#xb0;.

Stacking of rotor blades on centroids

A shroud segment () for disposition on a blade of a turbomachine is provided, in particular a gas turbine, the shroud segment having a stiffening structure raised above a shroud segment surface (), the stiffening structure including at least three interconnected ribs (), and a first end portion of the ribs () being connected to an upstream sealing tip () of the shroud segment (), and a second end portion of these ribs () being connected to a downstream sealing tip () of the shroud segment (). The angles (W, W, W) between the direction of the axis of rotation (a) of the blade and the longitudinal orientations () of the ribs (), as viewed in the direction of flow () through the turbomachine, are between zero degrees and eighty degrees. The present invention also relates to a blade () of a turbomachine.

Shroud segment for disposition on a blade of a turbomachine, and blade

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

Growing community of inventors

Roehrmoos, Germany

Klaus Wittig