Mtu Aero Engines Ag

Florian Neuberger

Franz-Josef Ertl

Kaspar Wolf

Martin Pernleitner

Georg Kempinger

Daniel Kirchner

Christian Roth

Julia Schmidt-Petersen

Stephan Doeppl

David Strunck

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

An adjustment lever adjusts a stator vane of a turbomachine. The adjustment lever has: a first connection site, of a plurality of connection sites, the first connection site being configured to join to an adjustment ring; a second connection site, of the connection sites, the second connection stie being configured to join to the stator vane; and a joining member arranged between the first connection site and the second connection site. The joining member is shaped having at least two struts which adjoin at least one of the connection sites.

Adjustment lever for a turbomachine

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 lever for adjusting an adjustable vane of a turbomachine, wherein the lever has a fulcrum for the rotatable mounting of the lever about an axis of rotation, a first load arm with a first adjusting connection point for at least indirect connection to an adjustable vane and a first force arm with a first actuating connection point for connection to an adjusting device, wherein the lever further has a first strut, which connects the first adjusting connection point and the first actuating connection point to each other and thereby extends in an arc-shaped manner about the axis of rotation.

Growing community of inventors

Dorfen, Germany

Florian Neuberger