Mtu Aero Engines Gmbh

Mtu Aero Engines Ag

Deutsches Zentrum Fur Luft-und Raumfahrt E.v.

Tim Schneider

Sergio Elorza Gomez

Alexander Hergt

Ulrich Siller

Described is a method for operating a compressor of a turbomachine, in which, when considered in the direction of a main flow, an, in particular, radially averaged degree of reaction has dropped in a front compressor area from a maximum to a minimum, is held constant or virtually constant across a central compressor area up into a rear compressor area, an, in particular, radially averaged degree of reaction being adjusted in the rear compressors area which is closer to the minimum than to the maximum, and a residual swirl of at least 47&#xb0; is present in the middle section, and a compressor and a turbomachine.

Method for operating a compressor of a turbomachine comprising providing a plurality of stages in a front compressor area, a rear compressor area, and allowing a swirl in the rear compressor area

Disclosed is a method for operating a compressor of a turbomachine, in which, when viewed in the direction of a main flow, a slowly dropping degree of reaction being raised in one compressor area more quickly than previously dropped and the raised degree of reaction then being reduced again in a subsequent compressor area more slowly that it was previously raised, a compressor of a turbomachine including at least one degree of reaction rising more quickly in one compressor area in comparison to adjacent compressor areas with respectively a dropping degree of reaction, whereby a sawtooth-shaped curve of the degree of reaction results, and a turbomachine including a compressor of this type.

Method, compressor and turbomachine

A turbomachine including at least one blade-row group that is arranged in the main flow path and at least two rows of blades that are adjacent to each other in the main flow direction, each row having a plurality of blades (), whereby a narrow cross section and a degree of overlap between the blades of the upstream row of blades and the blades of the downstream row of blades vary starting at the center of the main flow path in the direction of at least one main flow limiter.

Turbomachine

A blade group arrangement for a turbomachine in order to form a blade-row group, whereby a front blade and a rear blade each form an overlapping area that has a contraction ratio of at least 1.2, and it also relates to a turbomachine having such a contraction ratio between a front blade and a rear blade.

Blade group arrangement as well as turbomachine

A turbomachine is disclosed having at least one blade row group, which is situated in a main flow path and has at least two adjacent blade rows, viewed in the main flow direction, each blade row having a plurality of blades, the rear edges of the blades of the upstream blade row and the front edges of the blades of the downstream blade row in the peripheral direction being situated at an edge distance which varies starting from a main flow path center in the direction of at least one main flow limitation, the periphery-side edge distance increasing or decreasing on both sides.

A turbomachine including at least one blade-row group that is arranged in the main flow path and at least two rows of blades that are adjacent to each other in the main flow direction, each row having a plurality of blades, whereby the trailing edges of the blades of the upstream row of blades and the leading edges of the blades of the downstream row of blades are arranged at an axial edge distance that decreases from the center of the main flow path in the direction of at least one main flow limiter.

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Dachau, Germany

Tim Schneider