Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Andreas Hartung

Markus Schlemmer

Frank Stiehler

Martin Pernleitner

Karl-Hermann Richter

Herbert Hanrieder

Manfred Schill

Gerhard-Heinz Roesele

Manfred Feldmann

Hans-Peter Hackenberg

Malte Krack

Timo Theurich

Hermann Klingels

Hans Peter Borufka

Michael Junge

Patrick Prokopczuk

Patrick Wackers

Claudia Stoehr

Adrian Ehrenberg

Claudia STÖHR

Gerhard-Heinz Rösele

An arrangement reduces oscillation (vibration) of an oscillatory structure. The arrangement has a structure having at least one mode in at least one direction; and an oscillation-reducing device (vibration-reducing device). The oscillation-reducing devices has a housing formed by or provided on the structure, a cavity, and a body configured for making impact contacts with the housing and disposed in the cavity in such a manner that the body is configured to make impact contacts with the housing at least temporarily for as long as the structure is excited in the at least one mode in the at least on direction.

Arrangement for reducing oscillation

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.

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 blade arrangement for a turbomachine, in particular a gas turbine, with a first blade, which has a first blade body and a first platform, and a second blade, which is adjacent in the peripheral direction, and has a second blade body and a second platform. A first wall of the first blade and a second wall of the second blade bound a blade cavity, in which a damper with a wall-side contact surface is arranged. This contact surface has at least one first surface portion, which is convexly curved in a first direction, which, in at least one contact position, contacts the first wall in the first surface portion and is parallel to at least one portion of an edge of the first platform, said edge facing the second platform.

Blade arrangement with damper for turbomachine

The present invention relates to a turbomachine assembly with an annular flow cascade, which has a plurality of blades, which are arranged distributed in a peripheral direction, and a detuning device for different detuning of natural frequencies of the blades, wherein the detuning device has a ring that revolves in the peripheral direction, or wherein the detuning device has all detuning elements that are arranged at the blade, which follow one another in a row in the peripheral direction, and are designed in such a way that, during operation, first blades of the flow cascade each contact at most one, in particular, no movable detuning element of the detuning device.

Turbomachine assembly with a detuning device for different detuning of natural frequencies of the blades

A combination including a seal (-) for sealing a gap (s) between blade platforms () of two adjacent blades of a turbomachine and a reducer (-) for reducing vibrations of at least one of the blades, the seal including at least one rib () having a rib thickness and at least one wall () having a wall thickness that is smaller than the rib thickness and/or the reducer including a tuning-element guide housing () having at least one cavity () in which at least one tuning element () is disposed with play for impacting contact with the tuning-element guide housing.

Combination for sealing a gap between turbomachine blades and for reducing vibrations of the turbomachine blades

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

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

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.

The present invention relates to a turbomachine blade or vane arrangement having a first turbomachine blade or vane, a second turbomachine blade or vane adjacent to it, and at least one tuning element guide housing with at least one cavity, in which at least one tuning element is arranged with play of movement for impact contact with the tuning element guide housing, with the tuning element guide housing being arranged at least in part in a recess, in particular in a frame, of the first turbomachine blade or vane, where the second turbomachine blade or vane has at least one first rib for securing the tuning element guide housing arranged in the recess.

Turbomachine blade assembly

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 ().

A blade for a turbomachine, in particular a compressor or turbine stage of a gas turbine, having at least one matrix having a first impact chamber () in which at least one impulse element () is disposed with play, at least one second impact chamber () whose volumetric centroid is offset from a volumetric centroid of the first impact chamber () along a first matrix axis (A) and in which at least one impulse element () is disposed with play, and at least one third impact chamber () whose volumetric centroid is offset from the volumetric centroid of the first impact chamber () along a second matrix axis (B) transversely to the first matrix axis (A) and in which at least one impulse element () is disposed with play, the first matrix axis (A) and an axis of rotation (R) of the turbomachine forming an angle of at least 60&#xb0; and no more than 120&#xb0; is provided.

Turbomachine blade

The present invention relates to a bladed rotor for a gas turbine, with a body and a plurality of rotating blades where contact regions of a cylindrical surface of the body and front faces of the rotating blades are joined together cohesively. At least one of these contact regions and/or at least one of these front faces has at least one blind hole, in which at least one impulse body is arranged with play of movement and which is sealed and rotating blades are joined with the cylindrical surface. Alternatively, the body and rotating blades are manufactured integrally with one another by machining, and at least one blind hole extends from an inner surface of the body facing away from the blade out to one of the rotating blades, at least one impulse body being disposed with play of movement in this hole, and this hole is sealed.

Bladed gas turbine rotor

The invention relates to a turbomachine including: a guide baffle, whose sguide blades are situated on c guide blade carriers; and an adjacent moving baffle including smoving blades; the guide baffle nincluding impulse bodies which are situated in a cavity system of the guide baffle with movement play with respect to the impulse contact; the moving baffle nincluding impulse bodies which are situated in a cavity system of the moving baffle with movement play with respect to the impulse contact; and quotient of sum of the masses of all impulse bodies of the guide baffle divided by the difference (s&#x2212;c) of the number sof all guide blades minus the number c of all guide blade carriers amounts to at least 1.5 times quotient of sum of the masses of all impulse bodies of the moving baffle divided by the number sof all moving blades 

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Munich, Germany

Andreas Hartung