Mtu Aero Engines Ag

Daniel Kirchner

Thomas Hess

Christian Liebl

Alexander Buck

Richard Scharl

Manfred Feldmann

Alois Eichinger

Steffen Schlothauer

Georg Kempinger

Kaspar Wolf

Florian Neuberger

Wolfgang Bickmeier

Thomas Flatscher

Johannes Geisler

Stephan Doeppl

Thomas Heß

A bearing chamber housing () for bearing a shaft () of a turbomachine (), including a housing outer shell () that delimits an oil chamber () of the bearing chamber housing () radially outwardly in relation to a rotational axis () of the shaft (), and a housing inner shell () for bearing the shaft (). The housing inner shell () is radially connected to the housing outer shell () via support ribs () that in each case extend axially, at least in part, and the housing inner shell (), the housing outer shell (), and two support ribs () that are next-adjacent to one another jointly delimit a cavity () that is axially open at the rear, and thus lead into a rear opening (). The rear opening (), viewed in tangential sections, has a clearance () in each case that constitutes at least 50% of a circumferential distance () between the next-adjacent support ribs ().

Bearing chamber housing 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.

Gas turbine component

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

A liner element of a hot-gas-conveying duct of a turbine intermediate case of a gas turbine, in particular of an aircraft gas turbine, the liner element includes a central portion having at least one first reinforcement portion projecting in a direction away from the duct and extending substantially straight between an axial forward end and an axial rearward end; at least one of the two axial ends being adjoined by a second reinforcement portion projecting in a direction away from the duct and extending inclinedly or curvedly relative to the straight-line extent of the first reinforcement portion; the first reinforcement portion and the second reinforcement portion together forming a reinforcing element; the entire reinforcing element being disposed within the outer surface of the central portion, in particular in such a way that the reinforcing element is spaced apart from the first connecting portion and from the second connecting portion.

Liner element for a turbine intermediate case

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 turbomachine includes a seal device for sealing a gap between two components, with a plurality of sealing elements tippable in the direction of a relative displacement of the components. The sealing elements are mounted on one of the components and bridge the gap where the device has prestressing elements, by which the tippable sealing elements are prestressed against a respective sealing edge of the components. The prestressing elements are each supported at a front support point and a back support point of the component on the mounting side, these points being distanced from one another in the axial direction and in the radial direction of the turbomachine where the front support point is disposed radially outside and the back support point is disposed radially inside with respect to the mounting.

Turbomachine having a seal device

The invention relates to a mid-frame () for a gas turbine, having at least one outer casing element () and having a plurality of duct segments (), which are arranged in succession in the radial direction on the inside of the outer casing element () and in the peripheral direction of the casing element () and by which segments, in each case, at least one duct () through which a gas can flow is delimited at least in the radial direction at least partially, wherein a ring element () that is common to the duct segments () and is formed in one piece is provided, by means of which the duct segments () are held at the outer casing element ().

Growing community of inventors

Munich, Germany

Daniel Kirchner