Multi-flow reducer for rotorcraft

FIELD: machine building.

SUBSTANCE: 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.

EFFECT: reduced weight and dimension, equal distribution of load and simple and inexpensive production.

8 cl, 8 dwg

The level of technology

The present invention relates to multi-threaded reducer, and more specifically to the reducer with flow distribution of torque to many threads for the aircraft.

System gearbox transmits power from the gas turbine engine to the propeller or propeller aircraft. A typical system may direct power from several gas turbine engines on a single screw or propeller. Since the rotational speed of the screw or propeller is substantially lower than the frequency of rotation of the gas turbine engine, the rotational speed of a gas turbine engine, it is necessary to lower using a reducer system. When decreasing the output speed of the gas turbine engine torque is increased through a number of intermediate stages and the shafts of the gearbox before final transmission to the screw or propeller.

One system according to the prior art includes a number of gear wheels arranged with the possibility of separation of the flow of torque. Torque is normally transmitted single-threaded gear, is transmitted via two gears to separate thereby the original thread torque that is transmitted to the gear. The combined weight of these two separated flows of torque less mA the son of one of the original stream gear. Despite the fact that this system of separation of flow torque over the prior art in some situations could increase the ratio of the horsepower/weight, especially when the total used capacity in horsepower was significant, and there were plenty of input streams of different drive motors, this traditional approach, however, requires a relatively surround system with a relatively substantial mass.

Many of the traditional system of gears and system with separation of the flow of torque are heavy and bulky due to uneven load distribution. Uneven load distribution occurs when the system gearbox is not uniformly share the load. This requires increasing the size of each gear is higher than the optimal in order to ensure the possibility proportionate to the load even in the absence of a uniform load distribution.

In addition, the typical system of gears with the separation of the flow of torque, in spite of its effectiveness, usually designed for one platform aircraft due to the relatively large volume, it is necessary inherent in traditional designs. Each platform aircraft must be designed taking into account the particular situation of motors connected with a specific reducer system.

Accordingly, it is desirable to provide a system of gear with the separation of the flow of torque to the number of threads, which is relatively simple and inexpensive to manufacture, having a smaller weight and dimensions, providing uniform distribution of loads, including independent redundant threads loads and at the same time possessing the ability to adapt to different platforms aircraft.

The invention

In accordance with the present invention, the reducer system with separation of the flow of torque to the many threads provides many multithreaded three modules of the power gears, each of which transmits torque from the high-speed motor on a common shaft rotor. In each module of the flow separation torque of the first stage includes spiralnotebook bevel gear transmission; the second stage includes a cylindrical spur gear; and the third step includes a herringbone gear.

Each module of the flow separation torque is driven high speed input shaft of the gas turbine engine. At the first stage and the input shaft rotates around the axis of rotation of the input shaft, with the shaft installed the small Konica is some gear wheel, located in engagement with a flat bevel gear wheel, forming a first bevel gear transmission. Flat bevel gear wheel mounted on the shaft of the first stage, which rotates around the axis of rotation. The shaft of the first stage is located on the last weekend of the toothed wheel and at least partially within its perimeter to provide a compact layout.

This arrangement of high-speed input mainly allows you to place the engines in different positions for all axes. That is, the angle of engagement of a truncated cone in a conical transmission will have to change just to change the position of the motor on the Z-axis or vertically relative to the reducer system. Bevel gear can also be positioned in any position along the azimuth on a flat bevel gear wheel to accommodate the engine in any mounting position along the axes X and Y relative to the reducer system.

On the second level near the perimeter of the output gears of the last stage with the possibility of rotation around respective axes are many nodes hollow shafts. This location allows you to set each node of the hollow shaft in a common plane so that they are easy to place in a relatively flat housing. Nodes hollow shafts rotate with the equivalent hours of the Auteuil and include a hollow shaft, having torsional flexibility and angular compliance to provide the necessary synchronization for node gearbox, at the same time maintaining the proper distribution of the load during the operation of the gearbox. Nodes hollow shafts, as part of the second stage reduction, ensure equal load balance between all gears power transmission.

On the third level, each node of the hollow shaft includes first and second helical gear wheel which engages with last weekend gear. Each module of the flow separation torque thereby transmit power from one high-speed input shaft to set the gears with the last output gear for substantial torque transmission, which is usually desirable in the embodiment, the rotary-wing aircraft large capacity in a relatively flat reducer system for creating multiple threads load, where the failure of one module does not result in failure of the entire system.

Thus, according to the present invention suggests a system of gear with the separation of the flow of torque to the number of threads, which is relatively simple and inexpensive to manufacture, having a smaller weight and dimensions, providing equal division of naruto is, includes redundant threads loads, and at the same time adaptable to different platforms aircraft.

Brief description of drawings

Various characteristics and advantages of the present invention will be obvious to experts in the art from the following detailed description of preferred at the present time variant implementation. The drawings that accompany the detailed description can be briefly described as follows:

figure 1 is a General perspective view illustrative options rotary-wing aircraft for use with the present invention;

2 is a partially phantom image illustrative options rotary-wing aircraft, illustrating its transmission;

figure 3 is a perspective view of the reducer system according to the present invention;

4 is a perspective view of the reducer system in figure 3 with the enlarged image of one module of the flow separation torque of the present invention;

5 is a top view of the system of the gearbox according to the present invention;

6 is a lateral oblique projection system of the gearbox according to the present invention;

7 is a partially phantom view of one module of the flow separation torque in figure 4 to illustrate the hollow shaft mounted therein;

Fig is a perspective view of the systems of the gear with the separation of the flow of torque with a different location of the chassis according to the present invention.

A detailed description of the preferred option implementation

Figure 1 schematically shows a rotary-wing aircraft 10 having the node 12 of the main rotor. The aircraft 10 includes a housing 14 of an aircraft having an elongated tail portion 16, on which is mounted a steering screw 18. The node 12 of the main rotor is driven around the axis of rotation of the screw through the system 20 of the gearbox one or more engine E. it Should be understood that the configuration of the helicopter, the Sikorsky CH-53, shown in the disclosed embodiment, the embodiment is only for illustration, and the present invention can be applied to other aircraft.

As shown in figure 2, the system 20 of the gearbox is a three-stage power gear with a split flow of torque, which passes the flow of torque from a variety of high-speed motor E on the shaft 24 of the rotor of the node 12 of the main rotor. The system 20 of the reduction gear is preferably mounted in the body 21, which supports the transmission gear and the shaft 24 of the rotor. It should be understood that the gear system of the present invention can be used in various buildings and structures.

The system 20 of the gearbox in the first place, but not only, designed for single-rotor aircraft with three d is the motor, typical rotary-wing aircraft of high capacity. It should be understood that the present invention can use any number of engines. The system 20 of the gearbox allows easy installation of multiple engines on the hull, due to the flexible modular design and arrangement of gear wheels.

As shown in figure 3, the system 20 of the gearbox, basically, includes many modules 26 of the flow separation torque, each of which has three stages S1, S2 and S3. Each stage includes many links L1-Ln. Each link represents a gear-wheel, which divide the flow of torque from each engine E (figure 2). Each link is preferably constructed on the basis of the transmitted part of the total load on that link. That is, due to the equal load sharing, each link should not excessively to pay for the increased load, as required still to ensure transfer unevenly divided load. In the shown embodiment, for example only, three steps provide the following reduction: the first step - gear ratio RR1=1,968, input/output frequency - 6574/3341 rpm; the second stage - gear ratio RR2=1,681, input/output frequency - 3341/1977 rpm; the third stage - transmit is offered against RR3=11,106, input/output frequency - 1977/178 rpm

Each engine E passes the flow of torque to the corresponding module 26A, 26C, 26C separation of the flow of torque through the corresponding high-speed input shaft 28A, 28C, 28C. The number of modules 26 of the flow separation torque in the system 20 of the gearbox depends on the configuration of the aircraft, the number of engines and transmitted power. The modules 26 of the flow separation torque are located around the perimeter of the output gear 28 of the last stage, which combines the power flows from each module and transmits power through the shaft 24 of the rotor to the node 12 of the screw.

Because the modules 26A, 26C, 26C of the flow separation torque is essentially the same, the detail will be described only module 26A of the flow separation torque, however, it should be understood that this description applies equally to the modules 26A, 26C and 26C of the flow separation torque. That is, although the detail will be described only one module that divides the flow of torque from the engine E, a gear on each engine, essentially the same and, in addition, it should be understood that the present invention can be used any number of engines. Each module 26A, 26C, 26C of the flow separation torque of the first article the stump S1 preferably includes a spiral bevel gearing; the second step S2 preferably includes a cylindrical spur gearing; and a third step S3 preferably includes herringbone gearing.

As shown in figure 4, the module 26A of the flow separation torque is driven high-speed input shaft 28A. This high-speed input shaft 28A is rotated around the axis of the first rotation of the input shaft, and has a small bevel gear wheel 30, which is a bevel gearing 34 flat bevel gear wheel 32. Flat bevel gear wheel 32 rotates on its axis F rotation, which runs essentially parallel to the axis of rotation of the screw (figure 3) and transversely to the axis of the first rotation of the input shaft. The first bevel gearing 34 forms a first step S1 to convert rotation of the input shaft about the axis I of the rotation of the flat gears about the axis F. it Should be understood that the present invention will be useful for other locations of the teeth on the gears, such as the preferred location of spiral bevel gears.

This arrangement of high-speed input mainly allows you to set the engines at various positions along all axes. That is, the angle of bevel gearing in the conical gear I have is ü only to change the position of the engine in the vertical or Z-axis with respect to the system 20 of the gearbox (see 3). Bevel gearing 34 may also be located in any position in azimuth on a flat bevel gear wheel 32, to accommodate the engine in any mounting position along the axes X and Y with respect to system 20 of the gearbox. This input is the first step allows you to easily create a rotorcraft with many engines where the engines can be placed in various positions on the fuselage.

Flat bevel gear 32 mounted on the shaft 36 of the first stage, which rotates around the axis F rotation. The shaft 36 of the first stage supports the first cylindrical spur gear 38 and the second cylindrical spur gear 40, spaced along the length of the shaft. The shaft 36 of the first stage preferably is located above the output gear 28 of the last stage and at least partially within its perimeter to provide a compact layout. That is, the axis F rotation is located at a radius less than the radius defined by the output gear 28 last stage relative to the axis of rotation of the screw (figure 5).

At the second stage S2 is set the first node 40A of the hollow shaft, the second node 40B of the hollow shaft, the third node 40C of the hollow shaft and the fourth node 40D hollow shaft, which is arranged to rotate around the respective axes Q1-Q4, PR is walking near the perimeter of the output gear 28 of the last stage. That is, the axis Q1-Q4 are installed on a common radius that is larger than the radius defined by the output gear 28 of the last stage (figure 5). This location allows you to set each node 40A-40D of the hollow shaft in a common plane P (6)which is provided in the housing 21 of the gearbox (figure 2).

Preferably, each of the first node 40A and the fourth node 40D hollow shaft includes a corresponding second cylindrical spur gears 42A and 42D, which are in engagement with the first cylindrical spur gear 38, while the second node 40B of the hollow shaft and the third node 40C of the hollow shaft includes a corresponding straight-toothed bevel gears V, S second stage, which are in engagement with the second cylindrical spur gear 40.

Gears between the cylindrical spur gears 42A, 42D of the second stage and the first cylindrical spur gear 38, and between the cylindrical spur gear 44, S second stage and second cylindrical spur gear 40 have equivalent gear ratio so that the nodes 40A-40D hollow shafts rotate with equivalent frequency. Straight-toothed spur gears 42A, 42D of the second stage preferably have a larger diameter than Pramogu the s cylindrical gears W, S second stage, therefore, spur bevel gears V, S second stage can be placed under cylindrical spur gears 42A, 42D of the second stage that allows you to make the design more compact (figure 5). That is straight-toothed spur gears 42A, 42D of the second stage determines the overlapping offset cylindrical spur gears W, S second stage.

Each node 40A-40D of the hollow shaft includes a hollow shaft 46A-46D, which is torsion flexible and pliable in the angular direction of the element, which provides the necessary synchronization gears when assembling the gearbox, at the same time maintaining proper distribution of the load during operation. To obtain the equivalent of the flow separation torque in proportion 50/50 between all gears hollow shafts 46A-46D have the same torsional properties. Preferably, the hollow rollers 46A-46D is identical to (7) for ease of Assembly and maintenance. Hollow shafts 46A-46D, as part of the second stage reduction, ensure equal load balance between all gears power transmission.

At the third step S3, each node 40A-40D of the hollow shaft includes a first helical gear AA-48aD and the second helical gear 48bA-48bD, is the quiet are in engagement with the output gear 28 last stage, which preferably is a helical gear. Each module, thus, transmits the power flow from one high-speed input shaft 28A of eight (8) on the gears with the output gear 28 of the last stage to provide a substantial flow of torque is typically desirable option for rotary-wing aircraft heavy vehicles, to obtain a relatively flat system 20 of the gearbox, which has many threads load and in which the failure of one module does not result in failure of the entire system.

As shown in Fig, another system 20' of the gearbox contains the alternate node 50 of the housing. Since in the present invention the gears are preferably located on a relatively large diameter around the main output gear (figure 5), the node 50 of the housing can be adapted for use under various constraints on the size. For example only, the gear system 20 may include three independent housing 52A, B, C models of gears mounted on a common housing 54, which defines a plane P, which has nodes hollow shafts each module (6). Load from node 12 of the main rotor, which is transmitted through the shaft 24 of the rotor, served on a separate node 56 reference RA is s propeller shaft. The division supports minimizes the transmission of deformations under external loads on the node 12 of the main rotor, the transmission gear. Thus, there is an easier site housing, which minimizes the displacement gear wheels and increases the lifetime of the system.

It should be understood that the relative positioning, such as "front", "rear", "upper", "lower", "above", "below", etc. refer to the normal operational spatial position of the vehicle and should not be considered limiting.

It should be understood that although in the shown embodiment has been disclosed a specific arrangement of components, the present invention extends to other location options.

Although in the description have been shown, described and claimed a specific sequence of steps, it should be understood that according to the present invention, these steps may be performed in any order, separately or jointly, unless otherwise noted.

The above description is illustrative and not limiting. In light of the above ideas, there are various modifications and variations of the present invention. We have described above the preferred variants of the present invention, however, experts recognize that certain modifications are included in the scope of the present invention. So the m way it should be understood that within the applied formulas of the present invention can be implemented in ways other than specifically described above. Therefore the true scope and content of the present invention defined by the attached claims.

1. The reducer system containing the output gear wheel of the last stage, which determines the axis of rotation of the rotor;
conical flat toothed wheel mounted on the shaft of the first stage to rotate around the axis of rotation of the bevel gear, with the said axis of rotation of the bevel gear runs parallel to the aforementioned axis of rotation of the rotor and located at a radial distance from the axis of rotation of the rotor is smaller than the radius defined by the aforementioned output toothed wheel last stage; the first cylindrical spur gear mounted on said shaft of the first stage; a second cylindrical spur gear mounted on said shaft of the first stage; the first node of the hollow shaft, having a cylindrical gear wheel of the second stage which engages with the said the first cylindrical spur gear wheel, thus referred to the first node of the hollow shaft mounted for rotation around the first axis of rotation of the hollow shaft; a second node Polo is on the shaft, with the cylindrical gear of the second stage being in engagement with said second cylindrical spur gears, while the aforementioned second node of the hollow shaft mounted for rotation around the second axis of rotation of the hollow shaft; the third node of the hollow shaft, having a cylindrical gear wheel of the second stage being in engagement with said second cylindrical spur gear wheel, with said third node of the hollow shaft mounted for rotation around a third axis of rotation of the hollow shaft; and a fourth node of the hollow shaft, having a cylindrical gear wheel of the second stage, which is in engagement with the first-mentioned cylindrical spur gear wheel, with this referred to the fourth node, a hollow shaft mounted for rotation about a fourth axis of rotation of the hollow shaft, with the aforementioned first, second, third and fourth axis of rotation of the hollow shaft located on a common radius greater than the radius defined by the aforementioned output gear last step.

2. The system of the gearbox according to claim 1, in which each of the said first, second, third and fourth nodes of the hollow shaft includes a hollow shaft with an equivalent torsional properties.

3. The system of the gearbox according to claim 1, in which each of the said first, second, third and otwartego nodes of the hollow shaft mounted in a common plane of the housing, defined under the said output gear last stage opposite the rotor shaft.

4. The system of the gearbox according to claim 1, in which the aforementioned output gear wheel of the last stage supports the rotor shaft site rotor.

5. The system of the gearbox according to claim 1, in which the aforementioned output gear wheel of the last stage drives the node rotor rotary-wing aircraft.

6. The system of the gearbox according to claim 1, further containing a first helical gear and a second helical gear mounted on said first node of the hollow shaft for rotation together therewith; a first helical gear and a second helical gear mounted on said second node of the hollow shaft for rotation together therewith; a first helical gear and a second helical gear mounted on said third node of the hollow shaft for rotation together therewith; a first helical gear and a second helical gear mounted on said fourth node hollow shaft for rotation with it.

7. The system of the gearbox according to claim 6, in which the aforementioned output gear wheel of the last stage is zazemlenie with said first helical gear and said second helical gear, mounted on said first node of the hollow shaft, with said first helical gear and said second helical gear mounted on said second node of the hollow shaft, with said first helical gear and said second helical gear mounted on said third node of the hollow shaft, and with said first helical gear and said second helical gear mounted on said fourth node of the hollow shaft.

8. The reducer system according to claim 7, in which the aforementioned output gear wheel of the last stage is the herringbone gear.