Mtu Aero Engines Ag

Benjamin Hanschke

Benjamin Linke

Alexander Halcoussis

Michael Junge

Axel Stettner

Astrid Kraus

Francesca Storti

Moritz Thon

Amadeusz Rekosiewicz

A blade has an internal blade profile, and a jet deflection portion adjoining the internal blade profile. Each blade profile of the jet deflection portion has a center of gravity. The centers of gravity are joined by a thread line, which is a space line, starting from the internal blade profile. A total deviation of the space line in relation to the reference line is described by an nth order polynomial based on radial distance from the blade profile to a reference point. The thread line is selected and designed such that a compressive stress is produced in the region of the leading edge of the blade during operation.

Blade for a turbomachine, and turbomachine having at least one blade

A blisk has at least one blade, with a blade airfoil and a blade root; a platform, the blade being integrally attached to the platform; and a fillet arranged on the blade root and between the blade airfoil and the platform. The fillet merges into the blade at a blade connection. The fillet merges into the platform at a platform connection. The fillet extends with a longitudinal extent around the blade root and a transverse extent from the platform to the blade airfoil. The fillet has a variable radius along the transverse extent. The variable radius has, at least in a first section of the fillet, a minimum radius which, at least in the first section, is spaced apart from the platform by at least 15% of the transverse extent along the transverse extent of the fillet.

Blisk

The invention relates to a blisk segment for a gas turbine, comprising at least one first blade having an airfoil, a leading edge, a trailing edge, a blade root, a suction side and a pressure side, a pedestal, and a first fillet having a device for influencing crack growth. The robustness of the gas turbine is improved in accordance with the invention in that, at the leading edge of the first blade, at least on the first fillet, a first surface structure is arranged and interacts with the crack-influencing device for influencing crack growth and for flow influencing.

Blisk for a gas turbine

The invention relates to an airfoil for a compressor of a turbomachine, which extends starting from a blade root between a leading edge and a trailing edge to a blade tip, wherein the leading edge has a leading-edge thickness and the airfoil has a maximum profile thickness, the ratio of which to each other represents a relative leading-edge thickness, and the airfoil has a leading-edge wedge angle.

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Munich, Germany

Benjamin Hanschke