Mtu Aero Engines Gmbh

Mtu Motoren-und Turbinen-union Muenchen, Gmbh

Other

Mtu Motoren-und Turbinen-union Munchen Gmbh

Ulrich Knott

Karl-Hermann Richter

Erwin Bayer

Werner Humhauser

Hans Juergen Schmuhl

Karlheinz Manier

Siegfried Boettcher

Horst Friedrich

Josef Reischl

Roberto Furlan

Klaus Breitschwerdt

Thomas Uihlein

Piotr Kowalczyk

The present invention relates to methods for joining a rotationally asymmetrical part, preferably a turbine blade, which is made of a monocrystalline material, to a part, preferably a rotor core, which is made of polycrystalline material, having the method steps of: &#x2014;joining the rotationally asymmetrical part to an adapter piece made of polycrystalline material by means of rotational friction welding, and &#x2014;joining the adapter piece to the part made of polycrystalline material. The present invention also relates to a turbine blisk having a rotor core made of polycrystalline material and turbine blades made of monocrystalline material.

Methods for joining a monocrystalline part to a polycrystalline part by means of an adapter piece made of polycrystalline material

A method for hardfacing a metal component surface (), especially a shroud surface of a turbine blade made of a TiAl alloy, with at least one metal material (), in particular a Co&#x2014;Cr alloy. The hardfacing coating is produced separately from the component surface and is then joined to the component surface in a high-temperature soldering process. A turbine blade including such a hardfacing coating, primarily in a shroud region ().

Method for coating a turbine blade

A method and apparatus for the fabrication and/or repair of an integrally bladed rotor, specifically of an integrally bladed gas turbine rotor, is disclosed. At least one rotor blade is joined to a main rotor body for fabrication and/or repair. The joining is carried out by diffusion welding.

Method and apparatus for producing and/or repairing an integrally bladed rotor by inductive diffusion welding

A worked nozzle ring for a gas turbine, in particular an aircraft engine, having at least one shroud and at least one blade sheet arranged thereon, whereby, in order to create a worked nozzle ring that is easy to manufacture, the blade sheet comprises, at the frontal side, at least one two-dimensionally profiled connecting space region that is placed in a profiled opening formed in the shroud by beam cutting and is connected therewith.

Nozzle ring for a gas turbine

A worked nozzle ring for a gas turbine, in particular an aircraft engine, having at least one shroud and at least one blade sheet arranged thereon, whereby in order to create a worked nozzle ring that is easy to manufacture, the blade sheet comprises, at the frontal side, at least one two-dimensionally profiled connecting space region that is placed in a profiled opening formed in the shroud by means of beam cutting and is connected therewith.

Nozzle ring for a gas turbine and method of manufacture thereof

In a method of repairing worn blade tips of compressor or turbine blades, the worn blade tip (4) is first removed from the remaining blade portion (2) at a standardized height (h). The actual geometry of the end of the remaining blade portion (2) at the height (h) is measured, for example by optical digital image processing means. A repair part (4') is cut from a plate or sheet of repair material having a thickness (d) essentially corresponding to the difference between the nominal finished height (H) of the repaired turbine blade (1) and the standardized height (h) of the remaining blade portion (2) undergoing repair. The repair part (4') is cut to have a contour corresponding to the measured actual geometry of the end of the remaining blade portion (2) at the standardized cut-off height (h), for example using a laser cutting process CNC-controlled by the acquired data representing the actual blade geometry. Finally, the repair part (4') is attached to the end of the remaining blade portion (2), for example by welding or soldering, and preferably by induction soldering with a solder foil (5) interposed between the repair part (4') and the remaining blade portion. The resulting repair is a smooth transition from the remaining blade portion to the repair part, substantially matching the original new blade shape, without requiring finish machining of the joint.

Methods of repairing worn blade tips of compressor and turbine blades

A blade for a rotor, especially a turborotor, is made of two hollow blade foot sections having matching seam surfaces to form a hollow blade with a thickened foot that is butt-welded with its blade foot sole (7) to an integral welding stub of a rotor hub or disk. The two hollow blade foot sections are soldered to each other along a radially outer seam section (5) between the seam surfaces and welded to each other along a radially inner seam section (6) between the seam surface. The radially inner seam section extends from said blade foot sole. The welded seam normally ends in the thickened blade foot section (6) and is thus shorter than the soldered seam section (5).

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Munich, Germany

Ulrich Knott