Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Almecon Technologie Gmbh

Mtu Aero Engines Ag & Co. Kg

Markus Schlemmer

Andreas Hartung

Oliver Thiele

Manfred Feldmann

Martin Pernleitner

Bernd Kislinger

Karl-Hermann Richter

Rudolf Stanka

Herbert Hanrieder

Manuel Hein

Gerhard-Heinz Roesele

Frank Stiehler

Inga Mahle

Markus Brettschneider

Manfred Schill

Klaus Pirker

Nina Wolfrum

Bartlomiej Pikul

Marcin Rozak

Hermann Klingels

Manfred Dopfer

Norbert Schinko

Julian Weber

Hans-Peter Hackenberg

Alexander Buck

Janine Sangl

Stephan Klaen

Wilfried Schuette

Christoph Lauer

Michael Junge

Marcus Woehler

Norman Cleesattel

Malte Krack

Ralph Kropp

Stephan Prostler

Patrick Wackers

Julia Schmidt-Petersen

Stephan Klän

Timo Theurich

Lukasz Sosnowka

Otto Liebscher

Lorenz Vinke

Claudia Stoehr

Waldemar Wiebe

Marcin Regulski

Adrian Ehrenberg

Eckart Henrich

Claudia STÖHR

Stephan Pröstler

An arrangement reduces oscillation of an oscillatory structure. The arrangement has: a structure having at least one mode in at least one direction; and an oscillation-reducing device. The oscillation-reducing device includes a housing on the structure; a cavity; and a body. The body is configured to make impact contact with a first surface portion and a second surface portion of an inner wall of the housing and disposed is in the cavity such that the body can make impact contact with the first surface portion and the second surface portion of the inner wall of the housing at least temporarily for as long as the structure is excited in the at least one mode in the at least one direction. The first surface portion or the second surface portion of the inner wall of the housing has a curved profile.

Arrangement for reducing oscillation

An integrally bladed rotor for a turbomachine, in particular a compressor or turbine stage of a gas turbine, to which at least one separately formed impulse element housing (′) is fastened by at least one fastening element (′) which engages for this purpose into an opening () of the impulse element housing and into an opening () of the rotor, the impulse element housing having at least one cavity () in which at least one impulse element () is accommodated with play.

Integrally bladed turbomachine rotor

A sealing apparatus for a turbomachine, including a stator vane component, which includes an inner shroud element and a flow-directing element connected to the inner shroud element. The sealing apparatus includes a sealing component, which has a seal-carrier ring element coupled to the stator vane component. The seal-carrier ring element includes at least one ring body element and at least one projection, which is connected in one piece to the at least one ring body element, protrudes from the at least one ring body element in the radial direction of the sealing apparatus, and is inserted into at least one opening, which extends through the inner shroud element. Other aspects relate to a seal-carrier ring element for a sealing apparatus, and to a turbomachine which includes at least one sealing apparatus and/or at least one seal-carrier ring element.

Sealing apparatus for a turbomachine, seal-carrier ring element for a sealing apparatus, and turbomachine

A guide vane segment for a turbomachine stage that has an inner ring segment () and a plurality of guide vanes () that are configured on the inner ring segment; a detuning region (V) of the inner ring segment extending in each case from a trailing edge () of at least one guide vane (), in particular of at least 50% of the guide vanes (), axially toward a leading edge () of the guide vane () over at most 50% of a width (B) of the inner ring segment () and/or at most 5 mm and/or circumferentially on both sides, in each case over at most 25% of a spacing (A) between adjacent guide vanes (), at and/or in which at least one cavity () is configured which contains at least one impulse element () with clearance of motion for providing impact contacts.

Guide vane segment

The invention relates to a guide vane segment for an aircraft engine, having at least one guide vane element, having at least one flange formed in a radial extension direction (R) of the guide vane element and at least one positioning member projecting from the flange in the radial extension direction (R), and at least one seal carrier, which is arranged at the flange and is aligned relative to the guide vane element by way of the positioning member, wherein the flange has a supporting surface on which the seal carrier is supported, wherein a partial surface of the positioning member is adjacent to the flange at a transition from the flange to the positioning member, and respective surface normal lines of the supporting surface and of the partial surface enclose between them an angle (&#x3b1;) that is different from a zero angle.

Guide vane segment for a turbomachine

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

An impulse body module a turbine stage of a gas turbine includes a holder component of one-piece construction, with a base and surrounding side walls arranged at the base, wherein the side walls and the base define a holding chamber; an insert component, of one-piece construction, which is inserted into the holding chamber of the holder component, wherein the holder component and the insert component accommodated therein define a number of mutually separated cavities, and wherein an impulse body, in particular a sphere, is accommodated in each cavity; and a closure component of one-piece construction, which is joined to the holder component in a material-bonded manner where the holding chamber is closed and the insert component is surrounded by the holder component and the closure component. The holder component has at least one base projection in the region of its base, which extends away from the holding chamber.

Pulse body module with bearing protection

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

An impulse element module for a turbomachine, in particular a turbine stage of a gas turbine, preferably an aircraft gas turbine, including a single-unit receptacle component having a base and side walls that extend peripherally thereon, the side walls and the base bounding a receiving space; a single-unit insert component having a form that is inserted into receiving space of receptacle component; together, the receptacle component and the insert component accommodated therein being designed to define a plurality of spaced apart cavities; and an impulse element, in particular a sphere, being accommodated in each cavity; and a single-unit sealing component that is joined in a material-to-material bond to the receptacle component in a way that allows the receiving space to be sealed and the insert component to be surrounded by the receptacle component and the sealing component.

Impulse element module for a turbomachine

A guide vane segment for a turbomachine stage that has an inner ring segment () and a plurality of guide vanes (-) that are configured on the inner ring segment; at and/or in at least one detuning region (A; B) of the inner ring segment, that extends circumferentially in a portion of the inner ring segment that, from one end face () of the inner ring segment to an inner guide vane () that is circumferentially adjacent to an outermost guide vane () adjacent to the end face and/or extends at most over an outermost third of a length (L) of the inner ring segment bounded by an end face () of the inner ring segment, at least one cavity () is configured which contains at least one impulse element () with clearance of motion for providing impact contacts.

Disclosed is a sealing ring for a turbomachine, which is constructed so as to be fastened at a radially inner region of a plurality of guide vanes and rotate around a rotor shaft. The sealing ring comprises a ring part that extends in the axial direction and has a plurality of stiffened portions in succession in the peripheral direction. Further disclosed is a seal for a turbomachine that comprises such a sealing ring as well as a brush and/or run-in coating sealing ring that is to face a rotor shaft, and a method for the manufacture of a sealing ring.

Stabilized sealing ring for a turbomachine

A turbomachine blade assembly including a turbomachine blade (), in particular for a gas turbine, and at least one tuning element container including a housing () attached to the turbomachine blade and an insert () disposed in a recess () of this housing. A wall () of the insert spaces apart two first cavities (), which each accommodate at least one tuning element () provided for impacting contact with the housing () and the insert ().

Turbomachine blade assembly

A blade channel of a turbomachine that is delimited in the circumferential direction of the turbomachine by a pressure side of an airfoil and by an opposite suction side of an adjacent airfoil that, in the radial direction of the turbomachine, is delimited by two opposing side walls, and whose extent in the axial direction of the turbomachine is delimited by leading edges and by trailing edges of airfoils; at least one of the side walls being provided with localized contours, of which at least two are formed as elevations and at least two as depressions; a saddle surface being formed between the contours that, in one rotation, alternately merges into an elevation and a depression; a blade cascade having such blade channels, as well as a turbomachine having such a blade cascade.

Blade channel, blade cascade and turbomachine

The invention relates to a guide vane cluster for a turbomachine, in particular for a turbojet engine, having at least two vanes that are joined together by way of at least one common platform for the radial delimiting of a flow channel of the turbomachine, wherein each vane has a vane element with a suction side and a pressure side that are joined together by a leading edge and a trailing edge, wherein the at least two vanes have different trailing edge wall thicknesses at least in a corresponding radial lengthwise extension region.

Growing community of inventors

Mainburg/Sandelzhausen, Germany

Markus Schlemmer