Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Marcus Woehler

Martin Pernleitner

Rudolf Stanka

Manfred Dopfer

Klaus Wittig

Norman Cleesattel

Markus Schlemmer

Bernd Kislinger

Christoph Lauer

Wilfried Schuette

Manfred Schill

Manuel Hein

Oliver Thiele

Kaspar Wolf

Carsten Schoenhoff

Christoph Bichlmaier

Wilfrid Schuette

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 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 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 rotor for a turbomachine, in particular for a jet engine, having a blade ring which includes multiple differently designed rotor blades () having blade platforms () engaged flush with one another, the blade ring including at least two groups of differently designed rotor blades (), each group of rotor blades () being assigned blade platforms (), each of which is engageable flush with a matching blade platform () of at least one other group of rotor blades () and not with a blade platform () of the same group of rotor blades (). A method for manufacturing a blade ring of a rotor for a turbomachine is also provided.

Rotor for a turbomachine

A system for specifying an installation position of adjacent rotor blades of a blade row of a turbomachine is disclosed. The system has a plurality of axial securing elements, which have at least two sections with different profile areas for the arrangement in each case between a groove base of a rotor shaft and a blade root, which are joined together by a connecting web at a groove distance from one another, and which have counter-contours on the blade root side for forming in each case a positive-fit pair with the profile areas. Also disclosed are a securing element and a rotor blade for this type of system, a turbomachine having a rotor which has this type of system, and a method for manufacturing this type of rotor.

System for specifying an installation position of rotor blades, securing element, rotor blade, turbomachine, and method

Growing community of inventors

Inning am Ammersee, Germany

Marcus Woehler