Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Christian Liebl

Thomas Hess

Frank Stiehler

Daniel Kirchner

Richard Scharl

Andreas Jakimov

Joachim Bamberg

Steffen Schlothauer

Manuel Hertter

Thomas Koebke

Georg Schlick

Stefan Schneiderbanger

Alexander Ladewig

Juergen Kraus

Georg Kempinger

Alexander Buck

Alois Eichinger

Karl-Heinz Dusel

Klaus Semmler

Katrin Friedberger

Johannes Casper

Karl Blumenschein

Laura Buerger

Hans-Georg Lottprein

Jürgen Kraus

Thomas Köbke

Laura Bürger

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 gas turbine component for a gas turbine is provided. The gas turbine component has a shell portion having an abradable portion () to allow rotor blade ends () of a rotor blade array of the gas turbine to rub into the same. The abradable portion adjoins a neighboring portion () of the shell portion axially at both sides and is additively manufactured together therewith.

Gas turbine component

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.

An apparatus for laser materials processing including a laser () for generating a laser beam and a laser head () which is movable along at least one spatial direction and is connected to the laser via a light guide, and which emits a laser beam () capable of processing a material. The present invention also relates to an apparatus for selective laser melting or selective laser sintering having an apparatus for laser materials processing.

Apparatus for laser materials processing

The invention relates to a method for the additive manufacture of at least one region of a component. Here, at least the following steps are carried out: a) layer-wise application of at least one powder-form component material onto a component platform in the region of a build-up and joining zone; b) layer-wise and local solidifying of the component material by selective exposure of the component material by at least one high-energy beam in the region of the build-up and joining zone, with the formation of a component layer; c) layer- wise lowering of the component platform by a pre-defined layer thickness; and d) repeating steps a) to c) until the component region or the component has been completely fabricated.

Method and device for the additive manufacture of at least one component region of a component

A seal segment assembly for a turbomachine, in particular a gas turbine, including a first seal carrier and a second seal carrier, that are adjacently disposed in the circumferential direction, the first seal carrier having a first carrier base and at least one first sealing member that is joined to the first carrier base, and the second seal carrier having a second carrier base and at least one second sealing member that is joined to the second carrier base, the first sealing member and the second sealing member being formed by a plurality of cavities, that are adjacently disposed in the circumferential direction and in the axial direction, in particular evenly spaced, the cavities extending in the radial direction from the particular carrier base. The first carrier base and the second carrier base are intercouplable or are intercoupled in the circumferential direction by a mating connection assembly.

Seal segment assembly including mating connection for a turbomachine

A method for manufacturing a turbine casing part having a bearing chamber system including a shell () and at least one bearing receptacle () and further having a protective heat shield () that at least partially encompasses the shell () radially outwardly, the protective heat shield () being additively manufactured integrally with the bearing chamber system by selectively solidifying layer-by-layer a feedstock material () is provided.

Method for additive manufacturing of a gas turbine casing part

The invention relates to a guide vane ring with at least one guide vane ring segment for a turbomachine, including a plurality of guide vanes arranged radially around an axis of rotation, an outer shroud arranged radially on the outer side of the guide vanes, and an inner shroud arranged radially on the inner side of the guide vanes, wherein the outer shroud or the inner shroud has at least one expansion joint, wherein the guide vane ring segment is formed in one piece with the guide vanes, the outer shroud, and the inner shroud and the at least one expansion joint is sealed in each case by at least one sealing device arranged in the respective expansion joint.

Guide vane ring for a turbomachine

The invention relates to a repair method for a component and includes the steps of removal of a damaged region of the component with the formation of at least one separating surface; arrangement of the component in a processing chamber of a device for the additive restoration of at least the region of the component that has been removed; determining first structural data of the component disposed in the processing chamber; providing second structural data of the component; determining third structural data based on the first and the second structural data; and additive restoration of the component region that has been removed on the at least one separating surface of the component. In addition, the invention relates to a device for the additive repair of a component.

Repair method for the additive repair of a component

An apparatus and method for the generative production of a component includes a movably dispensing structure for the disposal of a starting material layer; a bonding device, such as a laser, for the local bonding of this starting material layer to a cross section of the component being produced; a platform for supporting the component being produced, which can be displaced counter to a direction of layer buildup in a motor-driven manner; a position sensing device for sensing a position or change in position, such as vibration, of the platform in the direction of layer buildup with the capability of sensing interference as to whether the movement of the dispensing structure is not free of interference on the basis of the sensed position or change in position.

Apparatus and method for generative production of a component

The present invention relates to a method for manufacturing components, in particular components of turbomachines, such as aircraft engines, wherein an additive method is used at least partially for the manufacture of the component (), wherein at least one surface region () of the additively manufactured portion of the component () is provided with a smoothing layer (), which is deposited by vapor deposition. In addition, the invention relates to a correspondingly manufactured component of a turbomachine.

Surfacing of additively manufactured components and corresponding manufactured components of a turbomachine

The invention relates to a compressor, particularly a high pressure compressor, of a gas turbine, particularly of a gas turbine aircraft engine, having at least one rotating blade ring on the rotor side, and having at least one guide blade ring on the stator side, wherein the, or each, guide blade ring is formed of a plurality of guide blade segments, and wherein each guide blade segment is formed of a plurality of individual blades. According to the invention, adjacent individual blades () are permanently connected to each other within each guide blade segment () of at least one guide blade ring on opposing surfaces positioned radially outward, whereas the same are not connected to each other on opposing surfaces positioned radially inward.

Growing community of inventors

Bockhorn, Germany

Christian Liebl