Rolls-royce Deutschland Ltd & Co. Kg

Rolls-royce Corporation

Technische Universitat Darmstadt

Frank Heinichen

Thomas Giersch

Erik Johann

John Dodds

Sven Schrape

Bernhard Mück

Jens Nipkau

Bernd Becker

Patrick Grothe

Maximilian Juengst

Bernhard Mueck

Maximilian Jüngst

A blade wheel of a turbomachine, which blade wheel has a multiplicity of blades which are suitable and provided for extending radially in a flow path of the turbomachine, wherein the blades form a blade entry angle and a blade exit angle. Provision is made whereby the blade wheel forms N blocks of blades, where N&#x2265;2, wherein the blades of a block have in each case the same blade entry angle and the same blade exit angle, and the blades of at least two mutually adjacent blocks have a different blade entry angle and/or a different blade exit angle. According to a further aspect of the invention, partial gaps that the blades form in relation to an adjacent flow path boundary are varied in mutually adjacent blocks.

Wheel of a fluid flow machine

A structural subassembly for a compressor of a turbomachine, which has a rotor having a plurality of blades, which extend radially in a flow path of the turbomachine, and a compressor casing, which forms a flow path boundary, which delimits the flow path through the turbomachine radially on the outside. In this subassembly, the compressor casing has casing structuring adjoining the rotor. It is envisaged that the compressor casing has a plurality of circumferential segments, which extend in the circumferential direction, wherein only one or only some of the circumferential segments forms or form casing structuring.

Structural assembly for a compressor of a fluid flow machine

The present invention relates to a stator of an axial compressor stage of a turbomachine featuring a radially outer blade ring forming an outer ring surface, a radially inner blade ring forming an inner ring surface, and several stator blades connected to the blade rings. It is provided that the outer ring surface and/or the inner ring surface has at least in a partial area a changing radius relative to a central axis of the stator both in the axial direction and in the circumferential direction.

Stator of an axial compressor stage of a turbomachine

The present invention relates to a rotor of an axial compressor stage of a turbomachine featuring a rotor assembly with a rotary axis, forming on its circumference a blade ring with a radially outer ring surface, and several rotor blades arranged on the blade ring. It is provided that the ring surface between two adjacent rotor blades has at least in a partial area a changing radius relative to the rotary axis of the rotor assembly both in the axial direction and in the circumferential direction.

Rotor of an axial compressor stage of a turbomachine

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Berlin, Germany

Frank Heinichen