Mtu Aero Engines Ag

Mtu Aero Engines Ag & Co. Kg

Stephan Klaen

Frank Stiehler

Hermann Klingels

Norbert Schinko

Christian Scherer

Uwe Vogel

Thomas Hess

Markus Schlemmer

Manuel Hertter

André Werner

Julian Weber

Christoph Cernay

Janine Sangl

Stefan Busam

Bernhard Theis

Disclosed is a turbomachine having an annular flow duct and a housing structure surrounding the flow duct and a multiplicity of guide vanes and rotor blades which are arranged in the flow duct. The rotor blades are rotatably accommodated in the housing structure whereas the guide vanes are fixed in the housing structure, a plurality of guide vanes forming an annular guide vane ring. The housing structure has a seal in the region of the radially inner flow duct boundary in order to prevent hot gas escaping from the flow duct, which seal is arranged on guide vane roots of the guide vanes of the guide vane ring via a seal support and forms a seal against a rotatable seal surface, the seal support being formed from an intermetallic material, in particular a TiAl material.

Seal support of titanium aluminide for a turbomachine

A seal configuration () for a turbo machine having a rotor (), wherein the seal configuration () has a sealing element () to create a seal with respect to the rotor () in an installed position and a supporting device (). The supporting device () has, in at least one section of the supporting device, a material () that melts when it comes into contact with the rotating rotor () in the installed position. A turbo machine having a seal configuration () is also provided.

Seal configuration for a turbo machine

A ceramic component for a turbomachine, the ceramic component () being configured to be destroyed in response to a contacting with another component () of the turbomachine that moves relative to the ceramic component (). A turbomachine component pairing and a turbomachine including such a ceramic component.

Ceramic component for a turbomachine

A brush seal for a gas turbine, in particular an aircraft engine, is disclosed. The brush seal includes a support ring which has a support plate and a support structure, where the support structure is arranged downstream with respect to the support plate. The brush seal also includes bristles which are arranged upstream with respect to the support ring, where ends of the bristles protrude radially inward beyond the support plate. The support structure yields when a scraping force acting radially outward occurs on a first lateral surface of the support structure, where the first lateral surface is directed radially inward, and the support structure does not yield when an axial operating force occurs on a second lateral surface of the support structure.

Brush seal

The invention relates to a mixing device and a turbofan engine having such a mixing devicefor mixing a first gas flowwith a second gas flowin a turbofan engine, having an actuating deviceand walls, which bound a channelfor the first gas flowand a channellying radially outside for the second gas flow, the actuating devicecomprising a coupling elementthat is coupled to the walls (), the actuating devicebeing designed to pivot the wallsbetween a first position and a second position disposed radially outside relative to the first position, the actuating devicecomprising an adjusting ringthat can be rotated between a first rotating position and a second rotating position in the peripheral direction and that is joined to the coupling element

Mixing device and turbofan engine having such mixing device

A thrust deflecting device for deflecting a thrust stream is disclosed, which includes a flap system having a plurality of deflecting flaps, each of which is pivotable around its yaw axis, the flap system being situated between parallel control surfaces such as baffle plates which, together with the flap system, form a box structure, which is pivotable around a pivot axis running in the direction of the transverse axis for the purpose of deflecting the thrust stream in the pitch direction, an aircraft engine also being disclosed.

Thrust deflecting device and aircraft engine

The invention relates to a guide vane arrangement and a method for mounting a guide vane. The guide vane arrangement has at least one guide vane having a radially inner journal, which engages in a borehole of a bushing. The bushing is disposed in a borehole of an inner ring segment. The journal is connected to the bushing in a rotation-resistant manner and a slide mounting is provided between the bushing and the inner ring borehole. For mounting the guide vane in an inner ring segment, the journal of the guide vane is introduced into the borehole of the bushing. Further, the journal is fastened to the bushing in a rotation-resistant manner, and the bushing is slide-mounted with the inner ring segment. The slide mounting is conducted prior to or simultaneously with or after the fastening of the journal to the bushing in a rotation-resistant manner.

Growing community of inventors

Berlin, Germany

Stephan Klaen