Mtu Aero Engines Ag

Lothar Albers

Alexander Boeck

Werner Humhauser

Manuel Hertter

Stefan Beichl

Georg Zotz

Vitalis Mairhanser

Alexander Böck

Johann Geppert

Thomas Binsteiner

Stephen Royston Williams

Alexander Scharf

Robert Winsy

Stefan Herbst

Rudolf Pilzweger

Hermann Becker

Stephan Pröstler

The invention relates to a rotor for integration in a turbomachine, with a rotor base body, wherein, on the rotor base body in a rotor outer space of the rotor, at least one blade element or airfoil is mounted, wherein the rotor base body extends in an axial direction of the rotor and comprises a connecting section, which extends in an axial direction of the rotor for connection to at least one further rotor and separates the rotor outer space from a rotor inner space of the rotor, wherein the connecting section comprises, in the axial direction, at a front side, preferably in the axial direction at a downstream-lying front side, a balancing flange, wherein the balancing flange is configured for compensating an imbalance of the rotor and extends in the radial direction in the rotor outer space, at least in sections.

Rotor with a balancing flange, rotor assembly with at least one rotor, and turbomachine with at least one rotor or with a rotor assembly

A rotor () for a turbomachine, in particular for an aircraft engine, having a rotor base body (), on which at least one sealing fin (), which is disposed on a base (), is provided for cooperating with an associated sealing element () of the turbomachine; relative to an axial direction of the rotor (), the base () having a base portion () disposed upstream of the sealing fin () and a base portion () disposed downstream thereof, for supporting masks during the coating of sealing fins; the upstream base portion () and the downstream base portion () having different radial distances (A, A) to a radially outer sealing tip () of the sealing fin (). Also, a turbomachine having at least one such rotor ().

Rotor for a turbomachine, and turbomachine having such a rotor

A turbomachine housing element, having a flow channel for accommodating a rotor blade assembly and a first cavity at least partially produced by primary shaping; the first cavity being adapted for passive thermal insulation and/or the assemblable turbomachine housing element not being adapted for the active circulation of fluid through the first cavity; and/or, between the first cavity and the flow channel, a separate seal being attached to turbomachine housing element; and/or the first cavity extending in the axial direction of the flow channel over at least 20% of a minimum axial length of the turbomachine housing element at the level of the cavity and/or over a minimum axial length of the separate seal and/or being filled with air or a thermally insulating fluid, whose specific thermal conductivity &#x3bb; is at least 10% lower than the specific thermal conductivity &#x3bb; of air.

Turbomachine housing element

The invention relates to a positioning element for a guide vane arrangement of a guide vane stage of a gas turbine, with at least one base section curved in the peripheral direction; a plurality of uptake openings arranged next to each other in the peripheral direction on the base section, whose aperture axis runs substantially in the radial direction and which are designed to take up a respective radially inner guide vane section; a coupling section provided on the base section, which is or can be coupled to a seal carrier of a seal arrangement. According to the invention, it is proposed that at least one recess is provided in the base section, which is arranged between two neighboring uptake openings and runs from inside to outside at least in the radial direction.

Positioning element with recesses for a guide vane arrangement

The invention relates to an inner ring for a guide vane assembly for mounting adjustable guide vanes of a turbomachine, of a compressor stage or turbine stage of a gas turbine, a guide vane assembly for a turbomachine having an inner ring, a turbomachine having an inner ring, and a method for producing an inner ring, wherein the inner ring has a plurality of guide vane bearing mounts, which are each arranged spaced apart in the peripheral direction, recesses, which are each formed for receiving a bearing element, a bearing journal, of a guide vane, wherein, between at least two adjacent guide vane bearing mounts, the inner ring has at least one depression with a wall thickness in a radial direction that is reduced in comparison to a region that abuts the depression and is outside of the depression.

Inner ring for a turbomachine, vane ring with an inner ring, turbomachine and method of making an inner ring

A rotor member is described for a gas turbine that is adapted for rotating about a central axis, the rotor member being a blisk having a rotor blade row that extends around the central axis or a rotor disk having a mounting portion for installing rotor blades of a rotor blade row that extends around the central axis, and being axially offset from the rotor blade row and/or the mounting portion and, extending coaxially, having at least one annular and axially asymmetrical sealing fin that has a radially outer tip portion having a front flank facing the rotor blade row and/or the mounting portion, and an opposite flank facing away from the rotor blade row and/or the mounting portion; the front flank being less steep than the opposite flank; a turbine and a compressor having such a rotor member, and a method for manufacturing such a rotor member having at least one sealing fin coating.

Sealing fin having an axially asymmetric tip portion

An inner ring according to the invention for a guide vane cascade of a turbomachine has a radially outer inner ring surface as well as a plurality of bearing mounts for a respective guide vane plate of a guide vane. The bearing mounts each have an opening in the outer inner ring surface as well as a bottom face lying radially opposite the opening. At least two of the bearing mounts are separated from each other by a separating wall and are connected to each other in a region of their bottom face by a through-opening. A guide vane cascade according to the invention for a turbomachine has an inner ring according to the invention and a plurality of guide vanes inserted into the bearing mounts.

Inner ring and guide vane cascade for a turbomachine

The invention relates to an inner ring system for an inlet guide vane cascade of a turbomachine. The inner ring system comprises an intermediate casing for accommodating structural loads and an inner ring, which is divided axially into a first ring segment and a second ring segment, which together form recesses for bearing radially inner end portions of guide vanes of the inlet guide vane cascade, wherein at least the second ring segment is fixed in place on the intermediate casing by screw connection. The invention further relates to an inner ring and to an intermediate casing for such an inner ring system, as well as a turbomachine that has such an inner ring system.

Inner ring system for an inlet guide vane cascade of a turbomachine

A rotor stage () for a turbomachine, including a plurality of rotor blades (), a rotor main body () having at least two rotor arms () and a balancing assembly () for balancing the rotor stage (). The rotor arm () configured downstream from the rotor main body () features the balancing assembly (). The balancing assembly () is configured between the axial end region of the rotor arm () and the rotor disk () of the rotor main body (). Furthermore, a rotor drum () for a turbomachine and a rotor () for a turbomachine.

Rotor stage for a turbomachine, rotor drum, and rotor

An inner ring of a fluid flow machine includes fixing rings and seal carriers split into at least two fixing ring segments and into at least two seal carrier segments, respectively. The fixing ring segments and the seal carrier segments are arranged with the respective end faces facing each other. A first fixing ring segment has a first ring segment shoulder and a second fixing ring segment has an offset second ring segment shoulder. A first seal carrier segment has a first carrier segment shoulder, and a second seal carrier segment has a second carrier segment shoulder, which is offset with respect to the first carrier segment shoulder. In a separation plane of the inner ring, the first carrier segment shoulder abuts the second ring segment shoulder at the end face. Also in the separation plane, the second carrier segment shoulder abuts the first ring segment shoulder at the end face.

Growing community of inventors

Munich, Germany

Lothar Albers