Stator wheel of a turbomachine comprising vanes having different chords

Abstract

A stator wheel of a turbomachine configured to be mounted in an aircraft, the turbomachine extending along an axis, the turbomachine comprising a core flow stream for a first air flow and a bypass flow stream for a second air flow, wherein the stator wheel is configured to be mounted along the axis, the stator wheel comprising a plurality of vanes extending radially from the axis, each vane comprising a leading edge and a trailing edge that together define a chord in a plane of revolution defined relative to the axis, at least two vanes having different chords at a same radial distance, the difference in chords between two adjacent vanes being less than or equal to 25%.

Dependencies are inferred from the claim text.