Aircraft turboprop engine comprising two coaxial propellers

The invention relates to an aircraft turboprop engine having two unducted propellers, coaxial about a rotation axis (LL), respectively upstream (12) and downstream (14′), each propeller comprising an annular row of blades, the blades of the downstream propeller (14′) each having a truncated head and...

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Bibliographic Details
Main Authors Anthony Pascal Eloi Louet, Jonathan Evert Vlastuin, Clement Marcel Maurice Dejeu
Format Patent
LanguageEnglish
Published 26.08.2020
Subjects
AEROPLANES
AIR INTAKES FOR JET-PROPULSION PLANTS
AIRCRAFT
AVIATION
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
COSMONAUTICS
GAS-TURBINE PLANTS
HEATING
HELICOPTERS
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
PERFORMING OPERATIONS
TRANSPORTING
WEAPONS
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Summary:The invention relates to an aircraft turboprop engine having two unducted propellers, coaxial about a rotation axis (LL), respectively upstream (12) and downstream (14′), each propeller comprising an annular row of blades, the blades of the downstream propeller (14′) each having a truncated head and each comprising a leading edge (20′) and a trailing edge (22′), the radially external ends (A2, B1) of which are distant from each other and are connected by a terminal edge (21′), characterised in that the terminal edge (21′) of each blade of the downstream propeller (14′) 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 (R2) of the blade and its downstream end (B1) defining a minimum radial dimension (R3) of the terminal edge.
Bibliography:Application Number: GB20150009158