The gear drive rotor helicopter |
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IPC classes for russian patent The gear drive rotor helicopter (RU 2146636):
 The node of the planetary gear / 2145396
The invention relates to the nodes of the planetary gear, in particular to the nodes of the planetary gear with multi-level stepped arrangement of satellites for transmission of the helicopter
 Helicopter gearbox / 2250180
Proposed gearbox of helicopter main rotor includes two drive gears and one driven gear mounted on shaft of main rotor drive. Engines are mounted for rotation towards each other. Driven gear of main rotor shaft is directly connected with one drive gear; it is connected with other drive gear through idler.
 Coaxial helicopter reduction gearbox / 2309874
Proposed reduction gearbox for coaxial helicopter includes drive shaft, two coaxial driven shafts (inner and outer), gear train and planetary mechanisms which are kinematically interconnected; each mechanism includes sun gear wheel fitted on drive shaft and epicycle fitted on outer driven shaft. Gear train mechanism has idler units placed in carrier which is rigidly secured on inner driven shaft; number of satellites exceeds number of idler units by one; number of teeth of sun gear wheel and epicycle of gear train mechanism is multiple of number of idler units; total number of teeth of these members in planetary mechanism is multiple of number of satellites.
 Multi-flow reducer for rotorcraft / 2402710
System of reducer consists of multitude of three-step modules (26A, 26B, 26C) of power tooth gear dividing flow of torque; each module transmits torque from high-speed engine to shaft (24) of lifting screw. A packaged design of a conic flat tooth gear of the first step (S1) facilitates installation of the engine in various positions along all axes. On the second step (S2) units of hollow shafts ensure equal balance of load. On the third step (S3) each unit of the hollow shaft includes multitude of small gears engaging an output tooth gear (28) of the last step.
 Helicopter reduction gearbox / 2541566
Invention relates to aviation, specifically to helicopter transmission designs. Helicopter reduction gearbox includes case where following parts are located: bevel gear wheels connected with shafts of helicopter rotors, bevel gear forming engagements with mentioned bevel gear wheels of rotor shafts and connected with shaft mounted on tapered rolling bearings and with gear wheel fitted on this shaft. Inner rings of tapered bearings are fixed in axial direction relative to shaft, and outer rings are installed with thrust against case and sleeve beads in "tensioned" pattern. Outer bearing ring installed adjacent to crown of bevel gear has possibility of hard contact with case bead, and outer ring of the other bearing has possibility to rest on inner bead of sleeve. The latter is located in case hole with groove to interact with key connected with surface of the mentioned sleeve. Sleeve surface extends from case by its outside thread. Nut end can contact with reduction gear case from outside. The nut is made as closed cup with grooves in one of which tooth of locking device is placed. The locking device is attached to helicopter reduction gearbox case.
 Coaxial-rotor helicopter gearbox / 2541569
This gearbox comprises housing to accommodate spinning hollow vertical and coaxial shafts. Rotor is fitted on one end of every said shaft. Sump is arranged in housing case and coupled via bearings and tapered gearing with second ends of hollow shafts of upper and lower rotors. Note here that vaned pump wheel is fitted on upper rotor shaft its vanes being arranged at angle α relative to its radius and provided with orifices arranged regularly on its lower end surface, axes of said orifices being parallel with pump wheel axis. Vanes on sump inner surface are arranged at angle α relative to its radius directed opposite inclination of the vanes of said pump wheel. Chamber case is filled with lubricant and communicated via channel, clearances and orifices with bearings and gearings.
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(57) Abstract: The invention relates to the structures of the main gearbox of the helicopter powered by two or more engines. The drive gear of the helicopter main rotor includes an input shaft for transmitting power from the engine and multiple speed transmission with a device dividing the input torque into parts equal to the number of engines. The latter is in the form of a common shaft and bevel gears, the number of pairs being equal to the number of the input shaft of the gearbox. When all the engines on a single mode in the gearbox from each engine receives equal torques. In case of shutdown or failure of one engine to another engine translates into increased capacity to provide helicopter flight. When this torque is distributed equally. In three-engine scheme when working on high-power one or two engines are stressed all the kinematic chains equally. Increases reliability of the gearbox and operation of the helicopter. 2 Il. The invention relates to structures of aircraft, namely the designs of the main gearbox of the helicopter powered by two or more engines. Closest to the claimed is the drive gear of the helicopter main rotor containing a few steps to transfer the power from the motors, which are connected with the input shaft of the gearbox, the steps include gear and device for dividing torque into parts equal to the number of engines [2]. A disadvantage of the known constructions is the presence of a large number of elements of the intermediate gear, which increases the weight of the gearbox, complicates its design and therefore does not provide sufficient reliability, the efficiency of manufacture of the gearbox and operation of the helicopter. The technical problem solved by the invention is to improve the reliability of the gearbox and operation of the helicopter by simplifying the design and reducing the weight of the heads of the screws helicopter with an input shaft for transmitting power from the engine, containing several stages of reduction and the device dividing the input torque into parts equal to the number of engines according to the invention the device of the division made in the form of a common shaft and bevel gears, of which the driven wheels mounted on a common shaft, and wheel on the input shaft of the gearbox, and the number of pairs of bevel gears in the unit of division is equal to the number of the input shaft of the gearbox. The running gear of the drive rotor helicopter with the device fission in the form of a common shaft and bevel gears when driven bevel gears mounted on a common shaft, and the bevel gear fixed on the input shaft of the gearbox, allows forming device fission power closing kinematic chain, which comes into operation in the event of an outage of one or several motors with one working and which is not loaded with all engines operative. The need for a "circuit" applied to the gearbox torque multi-motor drive due to the need for uniform load in all gears (pairs of gears) gear in the case, when cratsley (emergency) torque. Replacing the intermediate bevel and cylindrical gears trailing chain existing in the construction of the prototype, a common shaft connecting the driven gears additional bevel gears that are included in each kinematic chain from the entrance to the gearbox, allows you to combine ("looping") single kinematic chain multi-motor drive in a common system, which prevents overloading of the individual gears, even when working with high (emergency) torque (in the case of disconnection of one or two engines) and reduces the likelihood of their failure. In addition, this design decision, where the number of bevel gears in the device dividing the input torque is equal to the number of the input shaft of the gearbox, i.e. United with them engines, from which the drive gear makes it possible to reduce the number of gears that reduce the weight of the gearbox and increases its reliability. In Fig. 1 shows a diagram of the three-step gear driven by two motors; Fig. 2 - powered by three engines. Torque from the right engine is transmitted through the input shaft 1 and a pair of conical memory is 8 third stage. Torque from the second engine through the input shaft 9, a pair of bevel gears 10, 11, cylindrical transmission including gears 12, 13, 14 is transmitted to the wheel gears 15, 16 third stage reduction. Leading gears 7, 8, 15, 16 are in engagement with the common slave wheel 17 (external or internal gears), mounted on the shaft 18 of the rotor of the helicopter. On the same shaft 1 with a leading gear wheel 2 installed leading bevel wheel 19, and on the same shaft 9 also established a leading bevel wheel 20 so that the mating with them the driven wheels 21 and 22 were on a common shaft 23 and have the same frequency and direction of rotation. In the scheme of transfer of torque from the three engines of the third kinematic chain consists of an input shaft 24, gear 25, 26, 27, 28, 29 and wheel gears 30, 31, which are in engagement with the common slave wheel 17 of the shaft 18 of the rotor. On the same shaft with the gear wheel 25 is placed a gear wheel 32 which engages with a driven wheel 33. Closing kinematic chain includes a tapered pair containing gears 32-33, 19-21, 20-22, i.e., the number of which equals the number of input shaft 1,encovi, and the driven wheels 21, 22, 33 mounted on a common shaft 23. When all the engines on a single mode in the gearbox from each engine receives equal torques, thus closing the kinematic chain (pair, including gears 32-33, 19-21, 20-22) is unloaded. In case of shutdown or failure, for example, the right engine in the power plant and connected to the input shaft 1 gear (Fig. 1) left engine translates into increased capacity to provide helicopter flight. Torque to be transmitted to the left of the kinematic chain of the drive rotor from the input shaft 9 of the transmission including gears 10-11, 12-13-14, 15-16-17), and a transmission including gears 20-22, 21-19 on the right chain (2-3, 4-5-6, 7-8-17). When this torque is distributed equally, i.e., is divided among all kinematic chains, which prevents overloading of individual kinematic chains operating at high engine power. In three-engine scheme when working on high-power one or two engines are stressed all the kinematic chains equally, thereby also preventing overload. Sources of information1. "V propeller helicopter with an input shaft for transmitting power from the engine, contains several steps and includes a device dividing the input torque into parts equal to the number of engines, characterized in that the device of the division made in the form of a common shaft and bevel gears, of which the driven wheels mounted on a common shaft, and wheel on the input shaft of the gearbox, and the number of pairs of bevel gears in the unit of division is equal to the number of the input shaft of the gearbox.
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