1. The rectifier (20) of the gas turbine engine, containing many blades (22) located around the ring (29) centered on the axis of the gas turbine engine, with each blade (22) having a leading edge (23) and passing between the end of the legs (25) and the end of the head (26), and the leading edge (23) at the end of the legs (25) of each blade (22) is located at the entrance of the leading edge (23) at the end of the head (26) of the blade relative to the air flow, and the offset of the leading edge (23) between its two ends, exceeds 10% of the height of the blade (22), measured in the direction of the axis (X) of gas turbines engine, characterized in that the tangent set-up curve formed by the position in the tangent direction (Y) to the ring (29) of the centers of gravity of the successive blade sections (27) along the height of the blade (22) is a curve constantly increasing towards the back (E) of the blade (22), said curve near the end of the head (26) of the blade (22) having a strong inclination towards the back (E) compared to the rest of the curve, and the curve having an average inclination near the end of the head (26) of the blade exceeding at least , 1.2 times the average slope of the curve into parts, co from 30 to 90% of the height of the scapula. 2. The rectifier according to claim 1, in which part of the inclination near the end of the head (26) is from 90 to 100% of the height of the blade (22). 3. The rectifier (20) of the gas turbine engine according to claim 1, wherein the leading edge (23) of each blade (22) contains at least one part located at the outlet of the leading edge (23) at the end of the blade head (26) with respect to the direction air flow. 4. The rectifier according to claim 3, wherein said part is included in the leading edge zone (23) located between 60 and 100% of the height of the blade (22). 5. The rectifier according to claim 3, wherein the point of the leading edge (23) located in the direction of the leading edge position
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