Mtu Aero Engines Ag

Kaspar Wolf

Florian Neuberger

Martin Pernleitner

Georg Kempinger

Daniel Kirchner

Wilfried Schuette

Klaus Wittig

Marcus Woehler

Stephan Doeppl

Wilfried Schütte

Marcus Wöhler

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

The invention is directed to a method for cleaning powder residues of an additive layer build-up method away from an at least partly additively manufactured component by a cleaning device, wherein a machine plate and the component arranged thereon are excited to mechanical oscillation during a cleaning process by a vibration actuator of the cleaning device with a set resonant frequency of the machine plate. According to the invention, before the cleaning process is carried out, a resonant frequency of the machine plate is set to the set resonant frequency by an arrangement of a mass element on a securing element of the machine plate.

Method for avoiding resonance damage during cleaning of an at least partly additively manufactured component, cleaning device, mass element, and system

Described is a heat-protection element () for a gas turbine (), in particular an aircraft gas turbine, the heat-protection element () being adapted to at least partially surround a bearing chamber () of the gas turbine () and having at least one connecting portion () which is disposed in an axially forward region (VB) and connectable or connected by a material-to-material bond to a protective element () of a seal carrier, in particular a seal carrier with a carbon seal, at least one supporting portion () which is disposed in an axially central region (MB) and adapted to support the heat-protection element () radially on the bearing chamber (), an end portion () which is disposed in an axially rearward region (HB) and forms a free end () of the heat-protection element () and which is configured such that the end portion surrounds () the bearing chamber () in a contactless manner.

Heat-protection element for a bearing chamber of a gas turbine

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

Munich, Germany

Kaspar Wolf