An aircraft turbomachine, comprising: - a gas generator equipped with a turbine comprising a turbine shaft with an axis of rotation, and - a main fan propeller driven in rotation by a main shaft, this propeller being located upstream of a first annular splitter nose for separating two annular flow ducts for an internal primary flow and an external secondary flow respectively, - a secondary fan propeller (S') driven in rotation by a secondary shaft, this propeller being located in the flow duct for the primary flow, and - a power transmission module, comprising ∘ a torque input configured to be connected to a turbine shaft, ∘ a first torque output coupled to the main shaft, and ∘ a second torque output coupled to the secondary shaft, this power transmission module comprising a mechanical reducer comprising a sun gear forming said torque input, and planet gears carried by a planet carrier, each of these planet gears comprising a first toothing meshed with the sun gear, each of the planet gears comprising at least three independent toothings (120a, 120b, 120c) and comprising: - a second toothing meshed with an element forming one of the first and second torque outputs (110b, 110c), and - a third toothing meshed with another element, said other element forming the other of the first and second torque outputs (110b, 110c) when said planet carrier is stationary, or that other element being a stationary ring gear (12b, 12c) when said planet carrier is movable and forms the other of the first and second torque outputs (110b, 110c). - a gas generator equipped with a turbine comprising a turbine shaft with an axis of rotation, and - a main fan propeller driven in rotation by a main shaft, this propeller being located upstream of a first annular splitter nose for separating two annular flow ducts for an internal primary flow and an external secondary flow respectively, - a secondary fan propeller (S') driven in rotation by a secondary shaft, this propeller being located in the flow duct for the primary flow, and - a power transmission module, comprising ∘ a torque input configured to be connected to a turbine shaft, ∘ a first torque output coupled to the main shaft, and ∘ a second torque output coupled to the secondary shaft, ∘ a torque input configured to be connected to a turbine shaft, ∘ a first torque output coupled to the main shaft, and ∘ a second torque output coupled to the secondary shaft, this power transmission module comprising a mechanical reducer comprising a sun gear forming said torque input, and planet gears carried by a planet carrier, each of these planet gears comprising a first toothing meshed with the sun gear, each of the planet gears comprising at least three independent toothings (120a, 120b, 120c) and comprising: - a second toothing meshed with an element forming one of the first and second torque outputs (110b, 110c), and - a third toothing meshed with another element, said other element forming the other of the first and second torque outputs (110b, 110c) when said planet carrier is stationary, or that other element being a stationary ring gear (12b, 12c) when said planet carrier is movable and forms the other of the first and second torque outputs (110b, 110c). - a second toothing meshed with an element forming one of the first and second torque outputs (110b, 110c), and - a third toothing meshed with another element, said other element forming the other of the first and second torque outputs (110b, 110c) when said planet carrier is stationary, or that other element being a stationary ring gear (12b, 12c) when said planet carrier is movable and forms the other of the first and second torque outputs (110b, 110c).