Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Markus Uecker

Thomas Uihlein

Wolfgang Eichmann

Karl-Heinz Manier

Manfred Feldmann

Rudolf Stanka

Falko Heutling

Dieter Freno

Manuel Hein

Jens Wittmer

Benedikt Heidenreich

Rolf Gerstner

A rotor blade () for a rotor blade assembly () of a turbomachine () is provided, having an inner rotor blade platform () which extends axially from the rotor blade () with respect to a longitudinal turbomachine axis () and has two opposite circumferential end faces () and a free axial end () whose cross section is radially inwardly and radially outwardly bounded by circular arcs of two concentric circles. The inner rotor blade platform () has a cross section of connection () with the rotor blade () which is bounded radially inwardly by an inner connecting line () and radially outwardly by an outer connecting line (). Each of the connecting lines () has a central portion () having a convex curvature.

Rotor blade and rotor blade assembly for a turbomachine

The invention relates to a guide vane segment for aircraft gas turbine, which extend along a respective circular arc and together form an annular section, wherein, in the radial direction between the outer shroud and the inner shroud, a plurality of guide vanes are arranged adjacently in the peripheral direction, the outer shroud and the two sealing walls form a trough-like profile in longitudinal section, wherein, at the axially front or/and rear sealing wall element(s), at least one relief gap with a main section is provided, which extends substantially radially inward, starting from a radial outer edge of the respective front or/and rear sealing wall element(s) along the sealing wall element. According to the invention, it is proposed that the relief gap has at least one additional section that adjoins the main section radially inward, wherein the additional section is formed by at least one curved subsection.

Guide vane segment with curved relief gap

A guide vane arrangement for a turbomachine, particularly a gas turbine, is disclosed. The guide vane arrangement includes an external shroud band, on which at least two guide vanes protrude radially inward. A pair of axial ribs spaced apart from each other in the peripheral direction and disposed between two adjoining guide vanes in the peripheral direction protrude radially outward from a circumferential surface of the external shroud band and/or axially from a radial flange of the external shroud band.

Guide vane arrangement

For producing a component, especially a gas turbine component, coated with a wear-protection, corrosion-protection or erosion-protection coating, a method includes the following steps: providing a component () to be coated on a component surface (); at least partially coating the component () on its component surface with an at least two-layered protective coating (), which includes at least one relatively soft layer () and at least one relatively hard layer (); and then surface densifying the at least partially coated component on its coated component surface by ball blasting or shot peening.

Method for producing a component covered with a wear-resistant coating

A turbomachine is disclosed. The turbomachine includes a rotor, a plurality of blades arranged side by side on the rotor in a circumferential direction, and a plurality of sealing apparatuses each disposed on a respective blade shaft of the plurality of blades. Each of the plurality of sealing apparatuses includes first and second bottom plates protruding in a respective axial direction on the respective blade shaft and first and second bulkheads which extend in a radial direction along the respective blade shaft and form a double-walled seal in the axial direction. A respective rounded or parabolic transitional cross-section from the bottom plates to the bulkheads is provided and at least one of the bulkheads is offset with respect to a blade root edge of the respective blade shaft in a direction toward a radial longitudinal axis of the respective blade shaft.

Sealing apparatus at the blade shaft of a rotor stage of an axial turbomachine

A blade of a turbomachine such as a gas turbine includes a blade vane with a blade tip and a blade base. A blade tip armor cladding is applied on the blade tip. A coating covers at least the armor cladding and includes at least one multilayer coating system, and preferably plural such coating systems stacked repetitively on one another. Each coating system includes at least two different layers stacked successively on one another, with one layer of a metal material closer to the blade tip and one layer of a ceramic material farther from the blade tip.

Turbomachine blade with a blade tip armor cladding

A wear-resistant coating, in particular an erosion-resistant coating for a component that is exposed to fluidic loads, is disclosed. The wear-resistant coating has one or more multilayer systems applied repeatedly to the surface to be coated, where each of the applied multilayer systems has at least four different layers. A first layer of each multilayer system facing the surface to be coated is made of a metallic material adapted to the composition of the component surface to be coated. A second layer applied to the first layer of each multilayer system is made of a metal alloy material adapted to the composition of the component surface to be coated. A third layer applied to the second layer of each multilayer system is made of a gradated metal-ceramic material and a fourth layer applied to the third layer of each multilayer system is made of a nanostructured ceramic material.

Growing community of inventors

Munich, Germany

Markus Uecker