Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Almecon Technologie Gmbh

Klaus Pirker

Markus Schlemmer

Rudolf Stanka

Bernd Kislinger

Christoph Lauer

Hans-Peter Borufka

Lukasz Sosnowka

Ralph Kropp

Marcin Regulski

Lorenz Vinke

Waldemar Wiebe

The invention relates to a sealing assembly for a fluid kinetic machine, in particular for an aircraft engine, for sealing a radial gap between a rotor and a stator, including at least one sealing support for retaining and/or fixing at least one sealing element, wherein the sealing support includes a first and a second radial web extending in a radial extension direction as well as an axial web extending in an axial extension direction, firmly bonded to the radial webs, and the radial webs form a receptacle for receiving an element of the stator. Therein, the radial webs are formed as sheet elements formed elongated in radial direction, wherein a radially interior end of the radial webs is respectively firmly bonded, in particular welded, to a radially exterior surface of the axial web.

Sealing assembly for a fluid kinetic machine, method for producing a sealing assembly as well as fluid kinetic machine

The invention relates to a seal arrangement for a turbomachine, especially for an aircraft engine, for sealing a radial gap between a rotor and a stator, comprising at least one seal carrier for the supporting and/or fastening of at least one seal element, wherein the seal carrier comprises a radial crosspiece extending in a radial direction of extension and an axial crosspiece, formed as a single piece with the latter and extending in an axial direction of extension, wherein the seal element is arranged at a radially inner-lying bearing surface of the axial crosspiece, and a front ring or a front ring segment, viewed in the flow direction, and/or a rear ring or a rear ring segment, each with a radially running crosspiece.

Seal arrangement for a turbomachine, method for manufacturing a seal arrangement and turbomachine

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

The turbomachine includes a mid turbine vane frame, with an annular compartment formed between the mid turbine vane frame and a low-pressure turbine casing being sealed by means of at least two ring seals, wherein one ring seal is in contact with the mid turbine vane frame and the other ring seal is in contact with the low-pressure turbine casing and a radial annular overlap is thereby created with the first-mentioned ring seal.

Turbomachine

Described is a material sample for testing material properties under biaxial load as well as a method therefor. The material sample has a circular disk shape and, for rotation about the center line thereof, is provided with an integrally formed hub. The edge of the material sample and the hub are thicker than the ring section of the material sample located in between. In one embodiment, the ring section is designed with an annular concave fillet concentric to the hub and the concave fillet may extend from the edge to the hub and have a continuous curvature over its width. In the method, it is rotated about its center line at least at 100,000 rpm, preferably at 150,000 rpm&#xb1;10,000 rpm.

Material sample for testing biaxial stress conditions

A rotor comprising several blades rotating together with the rotor, particularly running blades, and the blades forming at least one blade ring, is disclosed. The blades within the, or each, blade ring are arranged at a different distance from one another.

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St. Lambert, Canada

Klaus Pirker