FIELD: mechanical engineering; gas-turbine engines.
SUBSTANCE: invention relates to fans and compressors of gas-turbine engines. Blade 14 includes convexity of chords on leading edge between root part 20 and end 22 being swept-forward at end. In other design version chords are increased in length at distance outwards from root part 20 to convexity of blade 14.
EFFECT: provision of good delivery of flow and capacity at high velocity.
20 cl, 3 dwg
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