Abstract: The uniaxial gas turbine system of the present invention has a uniaxial gas turbine, a rotary machine driven by the uniaxial gas turbine, a continuously variable speed transmission of transmitting a drive force from the uniaxial gas turbine to the rotary machine, and a controller of controlling a revolution speed of the uniaxial gas turbine to an optimal revolution speed and controlling a speed variation ratio of the continuously variable speed transmission so as to set a revolution speed of the rotary machine to a desired revolution speed. According to load changes of the rotary machine driven by the gas turbine, the revolution speed of the gas turbine or the rotary machine can be optimized.

Abstract: An output rotational driving power of the engine is split into a first split power and a second split power. The first split power is transmitted to a continuously variable speed transmission that transmits the first split power by a shearing resistance of a fluid. The second split power is transmitted to a differential planetary gear system. An output power of the continuously variable speed transmission is transmitted to the differential planetary gear system to combine the first split power and the second split power in the differential planetary gear system. A variation of a rotating speed of the output rotational driving power is absorbed by the continuously variable speed transmission to adjust an output rotating speed of the differential planetary gear system to a constant speed.

Abstract: A speed change control method of controlling a speed change ratio of a continuously variable transmission mechanism including a traction continuously variable transmission, includes: estimating a tilt angle of a power roller included in the continuously variable transmission based on an input rotating speed and an output rotating speed of the continuously-variable transmission mechanism;

Abstract: A constant speed drive apparatus for an aircraft generator comprises an input shaft for receiving drive torque from an aircraft engine, a traction speed change mechanism of continuously-variable speed change ratio which is coupled to the input shaft, an output shaft for supplying the aircraft generator with drive torque which is changed in speed by the traction speed change mechanism, and a control computer for controlling the speed change ratio of the traction speed change mechanism to maintain the output shaft at a predetermined rotational frequency. With such constitution it is possible to achieve a small and lightweight constant speed drive apparatus having a high transmission efficiency.

Abstract: In a variable mode of operation in which clutches are locked and a clutch and a brake are unlocked, the power of an input shaft is branched to a traction transmission mechanism. By contrast, in a fixed mode of operation in which the clutches are unlocked and the clutch and the brake are locked, the power of the input shaft is not branched to the traction transmission mechanism. In this way, the fixed mode and the variable mode are selectively used, whereby noise reduction and enhanced fuel efficiency can be attained. According to this configuration, it is possible to provide a power transmission apparatus for helicopters in which the number of rotations of a main rotor or a tail rotor is continuously varied while maintaining the number of rotations of an engine constant.

Abstract: An output rotational driving power of the engine is split into a first split power and a second split power. The first split power is transmitted to a continuously variable speed transmission that transmits the first split power by a shearing resistance of a fluid. The second split power is transmitted to a differential planetary gear system. An output power of the continuously variable speed transmission is transmitted to the differential planetary gear system to combine the first split power and the second split power in the differential planetary gear system. A variation of a rotating speed of the output rotational driving power is absorbed by the continuously variable speed transmission to adjust an output rotating speed of the differential planetary gear system to a constant speed.

Abstract: The engines which have output shafts connected to traction speed change mechanisms via freewheel clutches are decelerated or accelerated at a desired speed change ratio and then rotate and drive a collector gear and a main rotor shaft. A part of output torque of the engines is diverted into gears to drive and rotate accessories and a tail rotor. Such an arrangement is useful for a power transmission for a helicopter in that it enables the speed of rotation of the main rotor to be varied while the speed of rotation of the engines is kept constant.

Abstract: Each engine is directly coupled to an engine deceleration device composed of a traction speed change mechanisms and a planetary speed change mechanism, and is decelerated at a desired speed change ratio, and rotate and drive a collector gear and a main rotor shaft. The collector gear rotates and drives accessories and a tail rotor through a second traction speed change mechanism changing speed in inverse number of the speed change ratio of the traction speed change mechanisms. Thus, the rotating speed of the engines can be continuously decelerated at an arbitrary speed change ratio, and an engine deceleration device of small size, light weight, and low loss is realized. At the same time, a power transmission device for helicopters capable of changing the rotating speed of the main rotor at a constant engine rotating speed is realized.