Compressor for an engine
AssigneeMTU Aero Engines AG
InventorsSergio Elorza Gomez, Werner Humhauser, Roland Matzgeller
Life of this patent
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Abstract
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.
Claims15
A compressor, for an engine, which 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, wherein the rotating blade cascade and the guide vane cascade each have an aspect ratio of a mean height to a mean chord length of a blade or vane, wherein the compressor stages are configured and arranged where a value of a ratio between the aspect ratio of the second rotating blade cascade and the aspect ratio of the penultimate guide vane cascade for the entire rotating blade cascade and guide vane cascade of the compressor is greater than 2.0.
A compressor, for an engine, which 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, wherein the rotating blade cascade and the guide vane cascade each have an aspect ratio of a mean height to a mean chord length of a blade or vane, wherein the compressor stages are configured and arranged where a value of a ratio between the aspect ratio of the second rotating blade cascade and the aspect ratio of the last rotating blade cascade for the entire rotating blade cascade and guide vane cascade of the compressor is greater than 2.0.
A compressor, for an engine, which 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, wherein the rotating blade cascade and the guide vane cascade each have an aspect ratio of a mean height to a mean chord length of a blade or vane, wherein the compressor stages are configured and arranged where a value of a ratio between an aspect ratio of the first guide vane cascade and an aspect ratio of the penultimate guide vane cascade for the entire rotating blade cascade and guide vane cascade of the compressor is greater than 2.8.
Dependencies are inferred from the claim text.