Snecma

Anthony Pascal Eloi Louet

Jonathan Evert Vlastuin

Clement Marcel Maurice Dejeu

The invention relates to an aircraft turboprop engine having two unducted propellers, coaxial about a rotation axis (LL), respectively upstream () and downstream (), each propeller comprising an annular row of blades, the blades of the downstream propeller () each having a truncated head and each comprising a leading edge () and a trailing edge (), the radially external ends (AB) of which are distant from each other and are connected by a terminal edge (), characterised in that the terminal edge () of each blade of the downstream propeller () has, at at least two points, tangents in a meridian plane having different slopes, the upstream end (A) of the terminal edge defining a maximum radial dimension (R) of the blade and its downstream end (B) defining a minimum radial dimension (R) of the terminal edge.

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Alfortville, France

Anthony Pascal Eloi Louet