Mtu Aero Engines Ag

Audi Ag

Christoph Lauer

Jochen Hofmann

Rudolf Stanka

Martin Pernleitner

Markus Schlemmer

Markus Brettschneider

Manfred Dopfer

Bernd Kislinger

Christian Mergl

Manfred Schill

Manuel Hein

Klaus Pirker

Stephan Lorenz

Marcus Woehler

Norman Cleesattel

Oliver Thiele

Hans Stricker

Stefan Rauscher

Michael Höppel

Hartmut Beyersdorfer

Markus Treichl

Alexander Kammenhuber

Marcus Wöhler

Markus Hirschmann

Yannick Dr Muller

Winfried Lauer

Described is a turbine center frame for a gas turbine, in particular an aircraft gas turbine, the turbine center frame having a radially inner wall and a radially outer wall bounding an annular space through which hot gas flows and each having a contour facing the annular space, the contours describing an inner annular space curve along the inner wall and an outer annular space curve along the outer wall. At least one vane element extends in the radial direction through the annular space and has an axial leading edge and an axial trailing edge, the vane element having an outer axial width. The outer annular space curve or/and the inner annular space curve have at least one curve section having an inflection point of the respective annular space curve or/and a point of maximum slope of the respective annular space curve, the curve section being located in the region of the leading edge or trailing edge as considered with respect to the outer axial width or/and the inner axial width and having a length projected parallel to the axial direction which length is up to 20% of the respective axial width, and the curve section intersecting the piercing point where the leading edge or the trailing edge pierces the outer wall or the inner wall.

Turbine center frame having a specifically designed annular space contour

The present invention relates to a module for a turbomachine, having a guide vane arrangement and a seal carrier, which is arranged, with reference to a longitudinal axis of the module, radially inside an inner platform of the guide vane arrangement, wherein, in each case with reference to the longitudinal axis of the module, when considered in an axial section, the seal carrier has a radially extending seal carrier wall and a sealing web extending axially away from it, which forms a labyrinth seal together with the inner platform of the guide vane arrangement, wherein the seal carrier wall and the sealing web are made up in one piece with each other, i.e., they are built up additively together.

Additively manufactured module for a turbomachine

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

A device for influencing the temperatures in inner ring segments of a gas turbine is provided, which includes in the circumferential direction of the gas turbine, at least one outer shell assembly having a plurality of outer ring segments and at least one inner shell assembly having a plurality of inner ring segments. The inner ring segments are equal to or greater in number than the outer ring segments. An outer ring segment gap is between each two adjacent outer ring segments. An inner ring segment gap is between each two adjacent inner ring segments. An outer ring segment gap, or at least a radial cooling air passage, is located opposite each inner ring segment gap in the radial direction of the gas turbine.

Device and method for influencing the temperatures in inner ring segments of a gas turbine

The present invention relates to a gas turbine, in particular an aircraft engine gas turbine having a shaft and a bladed turbine rotor joined therewith that has a first rotor segment which has a downstream rotating cascade of the turbine rotor and bounds a first space in the radial direction, this first space communicating with a first gas passage disposed in the shaft, and has a second rotor segment axially adjacent to the first rotor segment, which has at least one second rotating cascade of the turbine rotor and bounds in the radial direction a second space axially adjacent to the first space, this second space communicating with a second gas passage, wherein the first rotor segment has at least one first discharge opening for the discharge of gas from the first space upstream of the furthest downstream rotating cascade.

Gas turbine

An adapter for connecting a fluid line to a housing section of a turbomachine is disclosed. A lower and an upper pair of flanges are arranged offset from each other about a channel axis of a fluid channel and are arranged without a space between each other in a direction of the channel axis, where the feed-throughs of the upper pair of flanges are open circumferentially.

Adapter and turbomachine

A component support of the turbomachine, in particular an aircraft engine, is described, which includes at least two essentially annular components on the stator side, which are in axial contact with each other and are preferably oriented coaxially to the machine axis, the first component having a plurality of radial, groove-like recesses, which are laterally overlapped by the second component with its projection-like bearing sections, and an uncontoured support ring surface section being provided between the adjacent bearing sections, a turbomachine also being described.

Component support and turbomachine

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Munich, Germany

Christoph Lauer