Mtu Aero Engines Ag

Bayerische Motoren Werke Aktiengesellschaft

Alexander Buck

Thomas Hess

Christian Liebl

Hans-Peter Hackenberg

Richard Scharl

Daniel Kirchner

Franz-Josef Ertl

Oskar Ostermeir

Manfred Feldmann

Markus Schlemmer

Steffen Schlothauer

Norbert Schinko

Janine Sangl

Marcin Rozak

Franz-Joseph Ertl

Stefan Mandlmeier

Thomas Heß

A guide blade arrangement () for a turbomachine (), including a guide blade airfoil () and a platform (). The guide blade airfoil () is situated at a side () of the platform () facing the gas channel, an opposite side () of the platform () facing away from the gas channel being contoured at least in one area () with elevations () and depressions () that follow one another in the circumferential direction () in relation to a longitudinal axis () of the turbomachine (), and the elevations () and depressions () at the side () facing away from the gas channel being set via a platform thickness (), taken radially in each case, that is variable in the circumferential direction () and that repeatedly increases and decreases with a continuous profile.

Guide blade arrangement for 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

A gas turbine component for a gas turbine is provided. The gas turbine component has a shell portion having an abradable portion () to allow rotor blade ends () of a rotor blade array of the gas turbine to rub into the same. The abradable portion adjoins a neighboring portion () of the shell portion axially at both sides and is additively manufactured together therewith.

A method for manufacturing a turbine casing part having a bearing chamber system including a shell () and at least one bearing receptacle () and further having a protective heat shield () that at least partially encompasses the shell () radially outwardly, the protective heat shield () being additively manufactured integrally with the bearing chamber system by selectively solidifying layer-by-layer a feedstock material () is provided.

Method for additive manufacturing of a gas turbine casing part

The invention relates to a guide vane ring with at least one guide vane ring segment for a turbomachine, including a plurality of guide vanes arranged radially around an axis of rotation, an outer shroud arranged radially on the outer side of the guide vanes, and an inner shroud arranged radially on the inner side of the guide vanes, wherein the outer shroud or the inner shroud has at least one expansion joint, wherein the guide vane ring segment is formed in one piece with the guide vanes, the outer shroud, and the inner shroud and the at least one expansion joint is sealed in each case by at least one sealing device arranged in the respective expansion joint.

Guide vane ring for a turbomachine

A stator vane segment () of a fluid flow machine, having an upstream casing-side attachment () and/or a downstream casing-side attachment (), and a platform (). The attachments are provided on the platform (). The platform () has a first sealing section () and extends in the direction of flow beyond a connection region () that connects the rearward attachment () to the platform (). The first sealing section () that is located in a section () downstream of the connection region () has a first slot () which is continuous in the circumferential direction. The present invention also relates to a turbine having at least one stator vane segment ().

Stator vane segment of a fluid flow machine and turbine

The present invention relates to a blade rim segment for a turbomachine with at least one shroud band which extends along a segment of a circle and is connected in single-piece fashion with at least three blades, which extend radially from the shroud band and are configured to be hollow with at least one channel, wherein the blade rim segment is manufactured in a single piece by casting and directional solidification, and wherein at the outlet openings of the channels of the blades, the shroud band exhibits first reinforcement ribs that surround the opening and run axially, as well as at least one second reinforcement rib between at least the first reinforcement ribs, as well as a corresponding method for manufacturing a blade rim segment.

Blade rim segment for a turbomachine and method for manufacture

A brake disc is provided having ribs arranged between two friction rings, extending radially with side walls standing essentially perpendicular to the friction rings to bound air cooling ducts. At least one of the side walls of one, two, three, or five ribs is inclined with respect to the perpendicular ribs to avoid squealing noise. At least one of the ribs having at least one inclined side wall has a thickness measured in the direction perpendicular to the side wall which differs from the thickness of the perpendicular ribs. When two, three, or five ribs having inclined walls are present, the angles enclosed between these ribs preferably are not all the same. Any imbalance resulting from this non-uniform distribution of ribs having an inclined side wall is essentially eliminated by adding material on selected perpendicular ribs.

Growing community of inventors

Munich, Germany

Alexander Buck