FIELD: engines and pumps.
SUBSTANCE: control device for fan blades orientation of turbo-propeller engine includes a set of blades with adjusted orientation, linked with rotating ring, mechanically connected with turbine rotor, and cylinder aligned according to axis of the rotating ring and linked during rotation with the turbine rotor. Each blade of the set for its orientation control is connected with support of the blade base installed with possibility of rotation on the rotating ring by means of the bevel gear drive. The bevel gear drive contains the first and the second tooth-wheels. The first tooth-wheel is connected with the support of the blade base, and is aligned as per axis radially to the rotating ring. The second tooth-wheel is connected with the rotating ring, is aligned as per axis tangential to the rotating ring, and has counterbalance, that is non-aligned relatively to its axis of rotation. The cylinder stock is connected with each counterbalance by means of the connecting levers to transfer the synchronous angular movement to the set of counterbalances relatively to the axis of rotation of their appropriate tooth-wheel. Each connecting ring has radial link with one end connected with the appropriate counterbalance, and another end connected with the crank lever, and which another lever is connected with the cylinder stock. Another invention of the group relates to the turbo-propeller engine comprising the turbine, having two rotors with opposite rotation, and two sets of fan blades with controlled orientation, connected during rotation with two rotating rings connected with rotors respectively. Orientation control of at least one set of the fan blades is ensured by the above described control device.
EFFECT: group of inventions improves reliability, and reduces weight of the control device of the fan blades.
8 cl, 5 dwg
