Mtu Aero Engines Ag

Hans-Peter Hackenberg

Alexander Buck

Andreas Hartung

Karl Maar

Franz-Josef Ertl

Michael Junge

Daniel Theurich

Oskar Ostermeir

Manfred Feldmann

Hermann Klingels

Werner Humhauser

Rudolf Stanka

Markus Schlemmer

Norbert Huebner

Erich Steinhardt

Jochen Gier

Alexander Halcoussis

Wilfried Schuette

Stefan Hagen Weber

Axel Stettner

Joerg Frischbier

Hannes Wolf

Malte Krack

Martin Becker

Timo Theurich

Knut Werner

Franz-Joseph Ertl

Claudia Stoehr

Wolfgang Horn

Claus Riegler

Eckart Heinrich

Klaus Peter Rued

Jörg Frischbier

Claudia STÖHR

Wilfried Schütte

Rotor blade () to be arranged in a gas conduit () of a turbomachine (), having a rotor blade airfoil (), which radially inwardly has a chord length S, radially outwardly has a chord length S, and in a radial position rinbetween has a chord length S, the chord length Sin the radial position rbeing at least equal to the chord length Sradially inwardly (S<S), and the chord length Sradially outwardly corresponding at most 0.9 times the chord length Sin the radial position rinbetween (Sa<0.9 S).

Rotor blade for a turbomachine, associated turbine module, and use thereof

A guide blade arrangement () for a turbomachine (), including a guide blade airfoil () and a platform (). The guide blade airfoil () is situated at a side () of the platform () facing the gas channel, an opposite side () of the platform () facing away from the gas channel being contoured at least in one area () with elevations () and depressions () that follow one another in the circumferential direction () in relation to a longitudinal axis () of the turbomachine (), and the elevations () and depressions () at the side () facing away from the gas channel being set via a platform thickness (), taken radially in each case, that is variable in the circumferential direction () and that repeatedly increases and decreases with a continuous profile.

Guide blade arrangement for a turbomachine

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 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 rotor assembly may be used in a gas turbine. The rotor assembly includes rotor segments arranged in succession in an axial direction and interconnected in the axial direction by a tie-rod, and a rotor segment disposed forwardly in the axial direction having a first contact surface and a rotor segment disposed rearwardly in the axial direction having a second contact surface. The first and second contact surfaces are at least partially in contact with each other, are substantially annular in shape, and extend in a radial direction and in a circumferential direction. The first contact surface and/or the second contact surface extend at least partially obliquely relative to the radial direction. An angle is formed between the first contact surface and the second contact surface when viewed in a sectional plane defined by the axial direction and the radial direction.

Rotor arrangement for a gas turbine with inclined axial contact surfaces formed on rotor segments, gas turbine and aircraft gas turbine

A gas turbine component, in particular a stator vane cluster (), having at least one radial flange () with a radial slot () for spoke-type centering of a gas turbine element, in particular an inner ring (), the radial slot () having a first slot flank (), a slot base () adjoining the same, and a second slot flank () adjoining the same, the slot base () being asymmetric with respect to a mid-plane (M) which extends radially and perpendicularly to the circumferential direction and centrally between the two slot flanks ().

Gas turbine component

An airfoil for disposition and exposure to flow in a hot gas duct of a turbomachine is provided. The airfoil has a suction-side wall and a pressure-side wall with respect to its exposure to the flow in the gas duct, the side walls converging in an upstream end region toward a leading edge and converging in a downstream end region toward a trailing edge. The airfoil further has a cavity structure therein which is enclosed between an inner wall surface of the suction-side wall and an inner wall surface of the pressure-side wall when viewed in a cross-sectional plane axially parallel to a longitudinal axis of the turbomachine. When viewed in the cross-sectional plane, at least one of the inner wall surfaces, normalized to a mean camber line of the airfoil as a reference, extends with a change in curvature into at least one of the end regions in such a way that a clearance width of the cavity structure is increased at the at least one end region.

Airfoil for a turbomachine

The invention relates to a blade for a turbomachine, comprising a blade element with a suction side and a pressure side, which extend between a leading edge and a trailing edge of the blade element, as well as a blade root for connection of the blade at a main rotor body, wherein the blade comprises a crack-affecting device, which, in the radial direction, has an altered cross-sectional geometry in comparison to an aerodynamically optimized blade profile. The invention further relates to a rotor for a turbomachine having at least one such blade, a turbomachine having at least one such blade, and/or with such a rotor as well as a method for producing a blade.

Blade and rotor for a turbomachine and turbomachine

A turbofan aircraft engine having a primary duct (C), including a combustion chamber (BK), a first turbine (HT) disposed downstream of the combustion chamber, a compressor (HC) disposed upstream of the combustion chamber and coupled (W) to the first turbine, and a second turbine (L) disposed downstream of the first turbine and coupled (W) via a speed reduction mechanism (G) to a fan (F) for feeding a secondary duct (B) of the turbofan aircraft engine. A square of a ratio of a maximum blade diameter (D) of the fan to a maximum blade diameter (D) of the second turbine is at least 3.5, in particular at least 4.

Turbofan aircraft engine

Growing community of inventors

Olching, Germany

Hans-Peter Hackenberg