Mtu Aero Engines Ag

Roland Matzgeller

Werner Humhauser

Sergio Elorza Gomez

The invention relates to a compressor for an engine, wherein the compressor has compressor stages arranged in succession in a flow direction of the compressor and each compressor stage has a rotating blade cascade and a guide vane cascade arranged downstream of the rotating blade cascade and the rotating blade cascade and the guide vane cascade each have an aspect ratio.

Compressor for an engine

The present invention relates to a compressor stage for a gas turbine, in particular, an aircraft engine, having a row of rotating blades () and a row of guide vanes (), which is adjacent downstream, wherein the choke point &#x3c3; and the aspect ratio AR, which is defined by the quotient between average channel height (h) and average chord length (l), satisfy the condition&#x3c3;&#x3e;&#x2212;1.33&#xb7;AR+5.16.

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Vierkirchen, Germany

Roland Matzgeller