FIELD: gas turbine engine.
SUBSTANCE: invention is related to a gas turbine engine of an aircraft containing an outer casing (2) that, together with the internal central part (3), limits the flow path (1) for the passage of a gas flow, in which a low-pressure turbine is located, configured to drive the low-pressure shaft into rotation. Said gas turbine engine contains, in the direction of gas flow, a first propeller (31) and a second propeller (32) located behind the first propeller, wherein the first propeller (31) is driven by said low-pressure shaft, and the second propeller is driven by rotated by an electric motor (70). The second propeller (32) is located at a distance of 1.5 to 4 chord lengths (LC1) of the first propeller (31) and determined between the corresponding axes of the angle setting (A31, A32) of each of the first and second propellers. This gap between the two propellers (31, 32) provides an aerodynamic connection that can effectively contribute to the thrust of the gas turbine engine. This gap is also the result of an aero-acoustic trade-off between: the distance between the two propellers being large enough to limit the intensity of the acoustic interaction bands between the propellers; the distance between the two propellers that is small enough to minimize the dissipation of the velocity profiles at the exit of the first propeller (input propeller) and facilitate their immediate use by deflecting the second propeller (exit propeller).
EFFECT: by configuring the variable interactions between the two propellers, the performance of the gas turbine engine is improved.
12 cl, 11 dwg
