FIELD: machine building.
SUBSTANCE: invention relates to gas turbine engine (1) straightener blade. Said blade comprises a plurality of blade sections (35) stacked along radial axis Z. On a bottom portion of the blade, from 0 to 50% of the total height thereof, leading edge (BA) of each section protrudes in front of the leading edge of the section corresponding to the total height, and the maximum thicknesses are located at positions spaced apart from leading edge (BA) of at least 50% of the chord.
EFFECT: invention is aimed at improving the efficiency of straightener blades.
9 cl, 9 dwg
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