A two-propeller turboprop having first and second sets (26a, 26b) of adjustable-pitch fan blades driven in rotation by a rotor of a power turbine, two hydraulic actuators (40, 42) for controlling the pitch of the fan blades and centered on a longitudinal axis of the turboprop, and a device for feeding fluid to the hydraulic actuators, said device comprising: a fluid manifold constrained to rotate with a rotor of the turboprop and comprising a cylindrical portion that is provided on an outside surface with at least two annular fluid-circulation grooves that are longitudinally spaced apart, each fluid-circulation groove presenting at least one outlet orifice opening out radially to the inside of the cylindrical portion of the fluid manifold; a fluid-admission support secured to a stationary portion of the turboprop and comprising a cylindrical portion that is arranged around the cylindrical portion of the fluid manifold, being coaxial therewith and provided with at least two distinct fluid passages opening out to respective fluid-admission tubes and each leading radially to the inside of the cylindrical portion of the support in a respective one of the fluid-circulation grooves of the manifold; and a tub constrained to rotate with the fluid manifold and comprising a central portion that is arranged inside the cylindrical portion of the manifold, being coaxial therewith, and provided on an outside surface with at least two longitudinal fluid-flow channels each fed with fluid via a respective one of the outlet orifices of the fluid manifold, each fluid-flow channel having a longitudinal end leading to a chamber (40a, 42a) of a control actuator (40, 42), the cylindrical portion of the fluid manifold is extended at one of its longitudinal ends by a radial portion provided with at least two ducts for passing fluid, each fluid-passing duct opening into a fluid-flow channel of the tub and leading to a control actuator chamber. a fluid manifold constrained to rotate with a rotor of the turboprop and comprising a cylindrical portion that is provided on an outside surface with at least two annular fluid-circulation grooves that are longitudinally spaced apart, each fluid-circulation groove presenting at least one outlet orifice opening out radially to the inside of the cylindrical portion of the fluid manifold; a fluid-admission support secured to a stationary portion of the turboprop and comprising a cylindrical portion that is arranged around the cylindrical portion of the fluid manifold, being coaxial therewith and provided with at least two distinct fluid passages opening out to respective fluid-admission tubes and each leading radially to the inside of the cylindrical portion of the support in a respective one of the fluid-circulation grooves of the manifold; and a tub constrained to rotate with the fluid manifold and comprising a central portion that is arranged inside the cylindrical portion of the manifold, being coaxial therewith, and provided on an outside surface with at least two longitudinal fluid-flow channels each fed with fluid via a respective one of the outlet orifices of the fluid manifold, each fluid-flow channel having a longitudinal end leading to a chamber (40a, 42a) of a control actuator (40, 42), the cylindrical portion of the fluid manifold is extended at one of its longitudinal ends by a radial portion provided with at least two ducts for passing fluid, each fluid-passing duct opening into a fluid-flow channel of the tub and leading to a control actuator chamber.