Patent ID: 8764392
Filing Date: 2014-07-01
Classification: F01D,Y10T

Abstract:
1. A rectifier stage of an axial turbine engine compressor, comprising: an outer shroud and an inner shroud, both being concentric; a series of blades arranged radially and fastened at tips thereof to the outer shroud; a series of cutouts arranged about the inner shroud, each cutout being configured such that a root of a corresponding blade protrudes through the inner shroud from the outer side of the inner shroud to the inner side of the inner shroud; at least one opening located at the root of each blade, each opening being on the inner side of the inner shroud; and a spiral ring having at least one overlapping loop, the spiral ring passing through the openings of each blade so as to prevent the root of each blade from escaping from the respective cutout of the inner shroud, and so as to form a connection between the blade roots; and wherein the diameter of the ring when non-operational is slightly smaller than the diameter of the virtual circle going passing through the openings, such that the ring is tensioned when in place and pulls all the blades equally towards a middle of the inner shroud.