Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Frank Stiehler

Andreas Hartung

Hans Peter Borufka

Patrick Prokopczuk

Martin Pernleitner

Steffen Schlothauer

Christian Liebl

Georg Kempinger

Juergen Kraus

Stephan Klaen

Alois Eichinger

Thomas Koebke

Markus Schlemmer

Manuel Hertter

Lars Schellhorn

Manfred Feldmann

Thomas Hess

Hermann Klingels

Andreas Jakimov

Alexander Ladewig

Julian Weber

André Werner

Christoph Cernay

Manuel Hein

Joachim Wulf

Joachim Lorenz

Hernan Victor Arrieta

Hans-Peter Borufka

Patrick Wackers

Stephan Klän

Johannes Casper

Stephan Prostler

Felix Kern

Stefan Busam

Bernhard Theis

Thomas Heß

Jürgen Kraus

Thomas Köbke

Stephan Pröstler

Peter Borufka

Andre Dr Werner

Manuel Dr Hertter

A bearing chamber housing for supporting a shaft of a turbomachine is provided, the bearing chamber housing including an additively built-up housing wall which bounds an oil chamber of the bearing chamber housing radially outwardly relative to an axis of rotation of the shaft, the housing wall being built up with an oil duct which has an inlet opening toward the oil chamber for admission of oil from the oil chamber into the oil duct, and which has an outlet opening for discharging the oil from the oil duct, the outlet opening being located at a different axial position and at a different circumferential position than the inlet opening, considered relative to the axis of rotation of the shaft, and the oil duct having an extent with both an axial component and a circumferential component, at least over a portion thereof.

Bearing chamber housing for a turbomachine

A moving blade for a turbine or compressor stage of a gas turbine is provided, including a vane () and a radially outer shroud (), for at least one contour point (P) of an outer contour of a profile cross section (P) of the vane at a radial outer gas channel boundary, the wall thickness of the shroud at at least one edge point (P) of the shroud, whose connecting line (V), including the contour point with a normal (N), which is perpendicular to the outer contour of the profile cross section in the contour point, encloses an angle (&#x3c3;), which is no more than 5&#xb0;, is less than a wall thickness of the shroud at the contour point, the wall thickness of the shroud decreasing strictly monotonously along the connecting line.

Gas turbine moving blade

A guide vane arrangement for a turbomachine, wherein the guide vane arrangement has a plurality of adjustable guide vanes that are rotatably mounted around an adjustment axis, at least one inner ring segment that is formed separately from the guide vanes, and a seal carrier that is formed separately from the at least one inner ring segment, wherein the at least one inner ring segment is fastened to one guide vane or to a plurality of guide vanes, and wherein the seal carrier is mounted in a spoke-centered manner with respect to the at least one inner ring segment, so that the seal carrier is movably mounted with respect to the at least one inner ring segment in the direction of at least one adjustment axis of at least one guide vane.

Adjustable guide vane arrangement, guide vane, seal carrier and turbomachine

A method for manufacturing a blade or vane assembly having at least one hollow airfoil () for a gas turbine, profile sections (A, B, C) of this airfoil being configured (S) on the basis of a predetermined desired torsion of the airfoil, and the airfoil being manufactured (S) on the basis of the configured profile sections using an additive manufacturing process (S).

Blade or vane assembly for a gas turbine and method of manufacture thereof

A guide vane according to the invention for a guide vane ring of a turbomachine has a vane element as well as a guide vane plate for its support on an inner ring. The guide vane plate has a cover surface facing the vane element, a base surface lying opposite to the cover surface, and an edge surface joining the cover and base surfaces. In a first region, the edge surface forms a chamfer of the vane plate, and in a second region, which forms the edge of a sector of the guide vane plate that is different from that of the first region, the edge surface runs along a cylindrical surface. A method comprises inserting a plurality of guide vanes according to the invention into respective uptakes in an inner ring.

Guide vane plate with a chamfered and a cylindrical edge region

The present invention relates to a bearing chamber housing for bearing a shaft of a turbomachine, comprising an additively built-up housing section and a cover, which, in each case referred to an axis of rotation of the shaft, connects axially to the housing section and has a radially extending collar, which collar axially bounds an oil space of the bearing chamber housing, wherein the cover is assembled with the housing section and is connected therewith via a weld.

The present invention relates to a bearing chamber housing for bearing a shaft of a turbomachine, having an additively built-up housing wall and a cover of the oil chamber, wherein, in each case referred to an axis of rotation of the shaft, the housing wall bounds radially outwardly an oil chamber of the bearing chamber housing and the cover of the oil chamber disposed on an axial end of the housing wall axially bounds a region of the oil chamber; the region bounds radially inwardly an inner shell of the bearing chamber housing.

The invention relates to a guide vane system for a turbomachine with at least one guide vane, which can be rotatably mounted around an adjustment axis and is arranged with a radially inner end region in a corresponding recess of an inner ring, wherein the arrangement of the guide vane on the inner ring is secured by a securing element in a form-fitting manner. For an especially advantageous securing of this arrangement, it is provided that the securing element is designed as an oblong element, which is arranged at least in a recess and/or through-opening of the radially inner end region of the guide vane directed in the peripheral direction of the turbomachine and is arranged at least in a recess and/or through-opening of the inner ring directed in the peripheral direction of the turbomachine. In addition, the invention relates to a turbomachine, in particular an aircraft engine, and to a method for assembling a guide vane system.

Guide vane system for a turbomachine

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 brush seal for a turbomachine includes a support that has a recess, in which a spring element is clamped axially, which fastens a brush element, where the spring element is axially locked at an undercut in the recess.

Brush seal for a turbomachine

The present invention relates to a turbomachine blade () with a base element, which has a blade part () for flow diversion and a blade root (), a first guide (), fixed on the base element, in which a first element () is movably guided, and a second guide (), fixed on the base element, in which a second element () is movably guided, wherein a dynamic of the first element in the first guide and a dynamic of the second element in the second guide are designed differently, and the first guide () is arranged in a half, nearer to the base root, of a radial height (H) of the base element, and the second guide is arranged in a half, more remote from the blade root, of the radial height of the base element.

Turbomachine blade arrangement with first and second guides with respective movable first and second elements to reduce vibrational response

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 turbomachine blade having a main body () that includes a plane, first attachment surface () having a first rim contour (), a cover () that has a plane, second attachment surface () having a second rim contour () that is welded to the first attachment surface, and a tuning body configuration having at least one tuning body (-) for contacting an inner wall () of the cover by impact therewith, a gap (s) being formed between the first and the second rim contour.

Turbomachine blade having a main body including a plane first attachment surface

The present invention relates to a blade or vane for a turbomachine, having at least one impulse element housing with a first impact cavity, in which an impulse element is arranged with play of movement, wherein the impulse element housing has at least one second impact cavity, which is in alignment with the first impact cavity in a first matrix direction and in which an impulse element is arranged with play of movement, and has at least one third impact cavity, which is in alignment with the first impact cavity in a second matrix direction crosswise to the first matrix direction and in which an impulse element is arranged with play of movement.

Blade or vane for a turbomachine and axial turbomachine

An inner ring for forming a guide blade ring for a turbomachine is disclosed, composed of at least two one-part ring segments having a plurality of openings, closed on the peripheral side, for accommodating journal bearings on the blade side, the outer diameter of the inner ring being at least 12 times larger than its height. Also disclosed are a guide blade ring having this type of inner ring and a turbomachine having this type of guide blade ring.

Growing community of inventors

Bad Liebenwerda, Germany

Frank Stiehler