Rotor drive of auxiliary unit of gas-turbine engine, support of units for gas-turbine engine, and gas-turbine engine

FIELD: engines and pumps.

SUBSTANCE: rotor drive of auxiliary unit, which is installed on support of units of gas-turbine engine, which contains rotor shaft drive means, includes tubular shaft rotated with the above means and supported with the first and the second support bearings rigidly connected to the support of the units. Rotor shaft is installed coaxially with tubular shaft, and engagement device with rotation is provided between rotor shaft and tubular shaft. Rotor shaft is supported with the third support bearing rigidly connected to the support of the units. The first and the second support bearings have the size which is less than size of the third support bearing. The other invention of the group refers to the support of gas-turbine engine units, which contains the gears rotating the above drive. One more invention of the group refers to gas-turbine engine containing the shaft and power take-off devices on the shaft, rotary gears of the above support of the units.

EFFECT: inventions allow improving reliability of rotor drive of auxiliary unit.

12 cl, 6 dwg

 

The present invention relates to the field of gas turbine engines and related auxiliary drive unit, in particular a generator of electric current that is installed on the support units.

Gas turbine engine comprises a support auxiliary units, called box units and transmission, such as alternators, fuel and oil pumps, starter, and various other units. They are driven mechanical shaft gas turbine engine, as a rule, the shaft of the pressure vessel in the case of a bypass gas turbine engine.

In gas-turbine engine from a number of these units can be distinguished, at least two of the alternator, one of which provides electrical power to the aircraft, powered turbojet engine, and the other produces an electric current necessary for the operation of the gas turbine engine and is smaller in size. This last alternator, normally an electric Dynamo or alternator with permanent magnets, called specialists PMA, which is short for "Permanent Magnet Alternator". In the further description will call it the alternator. In particular, the generator changes the nogo current produces electrical energy, required for device control and regulation of the gas turbine engine, called FADEC (short for "Full Authority Digital Engine Control", which experts commonly known and which translates as "fully Autonomous digital motor controller").

The rotor of the alternator rotates at very high speed, typically from 18000 to 30000 rpm. At present poorly understood loads (mechanical, Electromechanical, and so on), which is subjected to the alternator during operation. In addition, for maintenance the alternator often disassemble, then again set in place. To do this, first on the shaft assemblies install the rotor, then the rotor on the box units using bolts securing the stator.

Figure 1 shows the device of the drive rotor of the AC generator of the prior art, the rotor of the AC generator includes a shaft 1, which contains the tail section 2, which establish the elements of the induction coil (not shown), rotating inside is not shown in the drawing, the stator (armature) of the alternator. This shaft 1 is driven into rotation of the gear 3 boxes of units and transmission, which, in its PTS who lived, rotates directly or indirectly from the output shaft turbojet engine. In addition, this shaft 1 is mounted on two support bearings 4, 5, permanently United with a fixed box design units and transmissions. The stator of the alternator attached to the structure so that it can be removed independently of the rotor. Thus, the rotor installed in the stator console.

Bearings of the rotor shaft are small, as in the absence of loads that occur during operation of the alternator (with a proper balancing), the rotating elements (balls or rollers) bearing large size will tend not to rotate on the respective rings of the bearing, and to slip on these rings due to the inertia of these bodies, if they are large; because of this slippage, the bearings can wear out and break down faster than worse circulate a lubricant. The bearings of the smaller sizes have a higher relative loads and less prone to slippage, if the alternator is well balanced and is subjected to weak loads.

However, because the alternator is often disassemble and then set in place with the technical about the services, incorrect installation can lead to significant load imbalance at high speeds on the shaft of the installed console rotor of the alternator. These loads can be added magnetic imbalance of the alternator. Due to small size and low resistance to stress in this case also, it may corrupt these bearings, particularly in poor oil circulation between the alternator and transmission units. In addition, strains, bumps and imbalance is transmitted to the gear box units through the transmission gear 3 boxes of aggregates, which is highly undesirable.

The result is a stalemate in determining the size of the supporting bearings of the rotor shaft of the alternator: if they are large, can be damaged due to slippage during normal operation, and a good linear balancing of the alternator, if they are small, it may lead to damage due to the large unexpected (and unexplored) loads, and these loads are transferred to the same on the gear box assemblies.

In the patent GB 2055118 described gas turbine engine containing the shaft, means for selecting the movement on the shaft, causing gear bearing units, which, in turn, is avodat in the movement of the drive rotor accessories.

In the patent EP 0200178 the described device of the rotor drive auxiliary equipment installed on the support units of the gas turbine engine containing means of the drive shaft of the rotor comprising a tubular shaft driven by one of the above means and supported by first and second bearings, permanently connected to the support units, and the rotor shaft is coaxial with the tubular shaft and the clutch means in the rotation is established between the rotor shaft and the tubular shaft, and a rotor shaft supported by a third thrust bearing is rigidly connected to the support units, and the first, second and third bearings are the same size.

To resolve the problems inherent in the devices of the prior art, the idea arose to change bearings, namely two bearings with roller bearings or with one roller bearing and one ball bearing in one configuration or in the reverse configuration. None of these combinations has not led to satisfactory results.

In the present invention, an apparatus of driving the rotor of the alternator and General auxiliary unit, which allows you to avoid or at least reduce the transmission of mechanical loads from the generator AC oporn the e bearings of the rotor shaft and gear box assemblies.

In this regard, an object of the present invention is the device of the auxiliary rotor drive Assembly mounted on the support units gas turbine engine which includes means for the drive shaft of the rotor, characterized in that it comprises a tubular shaft, rotating mentioned means and mounted on the first and second support bearings fixedly connected to the support units, while the rotor shaft is coaxially aligned relative to the tubular shaft, and between the rotor shaft and the tubular shaft is made the means of coupling in rotation.

Under the clutch means in the rotation should understand the means of coupling or connection, which acts on the rotor shaft only tangential forces, that is, perpendicular to its axis of rotation. Thus, the rotor shaft is connected with the tubular shaft being coaxially aligned and is driven into rotation this tubular shaft. We are talking about, for example, a splined connection or complementary profiles (for example, prismatic shaft), keyed connection or any other means of tangential connections. This means the clutch in the rotation provides a certain degree of freedom of movement between the tubular shaft and rotor shaft in the longitudinal direction and torsional oscillation. Thus, the connection between the rotor shaft arunchalam shaft has a certain flexibility.

According to the invention the rotor is not still connected directly to the drive means of the bracket units or boxes aggregates and does not pass it loads, shocks or vibrations, the effect of which it may be subjected. Some vibrations are perceived by means of the clutch during rotation, the structure of which essentially absorbs these vibrations due to flexibility in directions other than tangential. Thus, get the separation between the rotor shaft and the drive tool box units, i.e. between the rotor shaft and gear box units and transmission due to the presence of the tubular shaft. A means of coupling in rotation imparts flexibility to the entire site formed by the shaft of the rotor of the alternator and the tubular shaft.

In the private version of the invention is used for the case when the auxiliary unit is an AC generator mounted console and contains a stator fixed to the support units. Indeed, initially solved by the invention of the task was for exactly this case, since the rotor, on the one hand, and the stator, on the other hand, is installed on the box units and are often subjected to disassembly and Assembly, their mutual arrangement depends on their relative positionyou the Oia in-a-box units and transmissions. However, the volume of claims according to the invention is not limited to this auxiliary unit.

Preferably, the rotor shaft is supported by one third thrust bearing, permanently connected to the support units. Forces acting on the rotor can thus be perceived third thrust bearing is installed on the rotor shaft, and transmitted to the fixed bearing design units. Such thrust bearing only feels the load of the rotor of the alternator, and not the load connected with a toothed gear box units and transmission.

Preferably, the clutch means in the rotation was a splined connection type. This means the clutch is easy to use: just insert the rotor shaft containing the slots in the tubular shaft containing slots corresponding form.

Preferably, the third thrust bearing supporting the rotor shaft of the alternator, was the bearing and contained means of drainage of the lubricant on the outer ring.

Such an embodiment differs in the following advantage. Due to the presence of the drainage means the danger of slippage of the balls in the bearing outer ring is reduced, which allows the use of bearing great is th size, better perceiving efforts.

In this case, it is preferable that the third thrust bearing was so-called bearing with three or four contact points.

Preferably, in the outer ring of the third support bearing were made funds depreciation using the oil film.

Preferably, according to a private variant of execution of the present invention the first and second support bearings of the tubular shaft had to be smaller than the third thrust bearing of the rotor shaft of the alternator.

Thus, it is possible to combine the respective advantages of small and large bearings. Small bearings allow the weak to withstand the load exerted on gear box units during normal operation. In addition, a large thrust bearing can easily bear the load associated with poor balancing, in particular, in the case of dismantling and subsequent inaccurate mounting of the alternator, while slippage on a large thrust bearing warned at the expense of the drainage of the lubricant in the case of qualitative balancing.

It is preferable to reduce the risk of imbalances and overheating near the third thrust bearing of the rotor shaft of the alternator from the side of the generator is to install and use the brush strip.

Thus, provide a better seal between the drive rotor of the alternator and the generator that allows you to avoid getting oil in the generator and the resulting imbalance, which will be more discussed below.

Preferably, the rotor shaft of the alternator contains a weakened area, forming the fuse, collapsing in the case of a very large loads on the rotor, in order to avoid transfer of these loads on the gear box units and transmission.

The object of the present invention is also bearing units or box units and transmission containing the above-described drive unit, and a turbojet engine with this box.

The present invention will be more apparent from the following description of the preferred embodiment of the device in accordance with the present invention with reference to the accompanying drawings, in which:

Figure 1 depicts a schematic view in section of a drive device of the prior art.

Figure 2 - schematic view in section of a first variant implementation of the device in accordance with the present invention.

Figure 3 - schematic view in section of a second variant implementation of the device in accordance with the present and the acquisition.

4 is a schematic view of the support bearing of the rotor shaft of the alternator according to the third variant of execution of the device in accordance with the present invention.

5 is a schematic view in section of a fourth variant of the execution device in accordance with the present invention.

6 is a schematic view in section of a fifth variant of the execution device in accordance with the present invention.

In various versions of the common elements designated in the same positions.

As shown in figure 2, a turbojet engine comprises a support 10 units or a box of 10 units and transmission, called by the English term "accessory gear b" or well known in the art reduction AGB, which was described above and will hereinafter be called the box 10. Box 10 is mounted on the periphery of the turbojet engine, for example in the case of a bypass gas turbine engine it is fixed to the outer casing fan. On the shaft of a high pressure gas turbine engine includes means for PTO included in engagement with the shaft, which is connected to the box 10 and is called PTO. This shaft is mounted in the radial direction between the shaft of a high pressure gas turbine engine and box 10, comes into the box and mehaniceskoe.mogu in action many auxiliary units or mechanisms, among them we can distinguish the generator 11 AC, intended for device control and regulation of the gas turbine engine, fuel and oil pumps, starter, alternator provides electrical power to the aircraft powered by gas turbine engine, etc. For this box 10 contains many gears, directly or indirectly related to the PTO shaft of a high pressure gas turbine engine, the gear is arranged to actuate the various units.

The generator 11 AC contains the stator 12, schematically shown in shaded form, and a rotor which includes a shaft 13, driven PTO, and the tail section 14 which is located inside the stator 12. This end section 14 is installed elements of the induction coil (not shown)that communicates with the stator 12 - anchor - for the production of electrical energy in a known manner. Thus, on the shaft 13 of the rotor has a rotor rotating in the stator. In this case, the generator 11 AC is an AC generator with permanent magnets. In this case we are talking about the generator of relatively small size, at least compared with the size of the AC generator is about current, producing electric current in the plane, the rotor rotates at high speed, typically from 18000 to 30000 rpm. This speed allows you to get a stable current and use the AC generator of small size and, thus, to reduce its dimensions.

In this case, the shaft 13 of the rotor is made as a single part together with the rotor. The rotor shaft can also be made as a separate part fixedly connected in rotation with the rotor by any appropriate means.

Box 10 contains means 15 of the drive for the generator 11 AC, in this case, means gearing, i.e. the gear 15 fixedly connected with the shaft associated with the gear box and therefore directly or indirectly with the PTO.

The drive gear 15 is engaged with the toothed wheel 16, or any other appropriate drive means fixedly connected to the tubular shaft 17. In one area, in this case located approximately mid-length of the tubular shaft, the tubular shaft 17 comprises a gear wheel 16. At each of its ends the tubular shaft 17 is supported by the first and second bearings 18, 19. In this case, the bearings 18, 19 are roller bearings, but what they can be and ball bearings. The advantage of roller bearings is that they can withstand higher loads. Its outer ring bearings 18, 19 still connected with a fixed design of the box 10. The tubular shaft 17 is located in the axis of the stator 12 of the generator 11 AC, i.e. in the axis slot of the rotor.

In the area of its inner surface, preferably located on the side opposite to the generator 11 AC tubular shaft 17 contains the splined portion 20 of the coupling or connection. The splined portion 20 of the clutch contains a set of slots uniformly performed around the axis of the tubular shaft 17 and forming, thereby, grooves and protrusions parallel to this axis.

Concentric with the tubular shaft 17 and the inside has the shaft 13 of the rotor of the generator 11 AC. The shaft 13 of the rotor contains a section 21 of the shaft, the opposite end section 14, is inserted in the stator 12, and are designed to be installed inside the tubular shaft 17. At the end of this section of the shaft 21, the shaft 13 of the rotor contains a slotted section 22 of the clutch corresponding to the slotted portion 20 of coupling a tubular shaft 17 and is arranged to connect to the site. Slotted section 22 of the clutch shaft 13 of the rotor shown in the figure is not broken, and in profile, which allows you to better read the drawing.

Slotted with whom estva 20, 22 clutch form a clutch means in rotation. Indeed, during rotation of the tubular shaft 17 splines of the shaft 17 is applied to the spline shaft 13 of the rotor forces, tangential with respect to the shaft 13 of the rotor and perpendicular to its axis of rotation. In particular, the tubular shaft 17 is not effective stresses in the longitudinal direction of the shaft 13 of the rotor or of the torsional oscillation. Therefore, there is a certain degree of freedom of movement and flexibility in the longitudinal movement and rotation-oscillation.

Between the closest to the generator 11, the AC end of the tubular shaft 17, in this case, the end resting on the thrust bearing 19, and by the generator shaft 13 of the rotor is supported by thrust bearing 23. This bearing 23 still connected with its outer ring 25 with a fixed design of the box 10. Preferably the thrust bearing 23 is a ball bearing. It is installed coaxially with the tubular shaft 17.

The shaft 13 of the rotor preferably contains section 24, which supports the inner ring 26 of a support bearing 23 and which has a larger diameter than section 21 of the shaft inside the tubular shaft 17. Starting from the extended section 24, the shaft 13 of the rotor facing the stator 12 of the generator 11 AC and inside of him, when ATmega section 14, inserted in the stator 12 has a diameter that is smaller compared to the advanced section 24.

It should be noted that the front support bearing 23 of the shaft 13 of the rotor of the generator 11 AC from the generator 11 includes a reflector 36. This reflector allows you to avoid ejection of the lubricant of the bearing 23 and even other elements of the drive device in the direction of the generator 11 AC. Indeed, the presence of oil on the end 14 of the shaft 13 of the rotor inserted in the stator 12 of the generator 11 AC, creates an imbalance on the rotor, because, since the space between the rotor and the stator 12 is very limited, the oil is heated and consueta. Such a reflector can be performed rotating to improve its effectiveness. The reflector 36 has the form of a flange, the inner wall which extends without contact shaft 13 of the rotor of the generator 11 AC.

What follows is a description of the operation of the device of the drive shaft 13 of the rotor of the generator 11 AC.

The gear 15 is rotated directly or indirectly PTO shaft, rotates the gear wheel 16 of the tubular shaft 17, supported during its movement in two bearings 18, 19 connected to the fixed structure of the box 10. Through the splined connection 20, 22 of the tubular shaft 17 rotates the rotor of the generator is 11 AC which is supported in its movement splined connection 20, 22 and thrust bearing 23 which is connected with the fixed design of the box 10. The rotation of the end portion 14 of the rotor in the stator 12, an electric current is used to power a turbine engine.

In this embodiment, the drive unit allows to avoid possible transmission of stress or imbalance of the rotor of the generator 11 AC gear box 10. Indeed, some vibrations are absorbed by the splined connection 20, 22, as this type of connection forming means of the clutch in the rotation, has some intrinsic, flexibility. Load generally absorbed at the level of the support bearing 23 of the shaft 13 of the rotor, especially if the bearing is large enough. Thrust bearing 23 perceives only the load from the generator rotor 11 AC and did not perceive any loads connected with the gear box 10. These loads are not transmitted to the transmission gear box 10, and a fixed box design, which does not suffer from absorption of such loads.

Thus, achieve separation between the generator rotor 11 AC and gears of the box 10. In addition, since the bearings 18, 19, to support the living of the tubular shaft 17, disconnected from the generator rotor 11 AC, they are not subjected to loads from the last. Therefore, they may have small dimensions, providing rotation of the tubular shaft with a minimum of friction and with minimum weight.

In this case, preferably, the thrust bearing 23 of the shaft 13 of the rotor of the generator 11 AC were large in comparison with bearings 18, 19, supporting the tubular shaft 17, which are small. Thus, the load from the generator rotor 11 AC mainly perceived by the bearing 23 supporting shaft 13 of the rotor, and in the case of certain vibrations splined connection 20, 22, whereas the bearings 18, 19 of the tubular shaft 17 are subjected to small loads and, therefore, rotate with only slight friction.

In addition, load, usually occur due to imprecision during disassembly and Assembly of the generator 11 AC. In this case, the installation is carried out by introducing the shaft 13 of the rotor inside the tubular shaft 17 and its support bearing 23, and then the stator 12 set around the end 14 of the rotor. The shaft 13 of the rotor inside the tubular shaft 17 is without difficulty because of possible inaccuracies in the longitudinal direction does not matter, since the introduction of slotted teaching the TKA 22 of the shaft 13 of the rotor slotted site may be incomplete or to be too strong. Indeed, for normal transmission of motion is not necessary that the slots were strictly against each other. In addition, the angular inaccuracies will be absorbed by the splined connection 20, 22 due to its flexibility or, in extreme cases, thrust bearing 23 supporting shaft 13 of the rotor.

According to the second variant of execution, shown in figure 3, the drive rotor of the generator 11 AC similar to the device shown in figure 2, except that the thrust bearing 23' of the shaft 13 of the rotor of the generator 11 AC is a ball bearing and its outer ring 25' includes means 27 drainage of grease. In this case, these means include at least one channel 27, is made in the thickness of the outer ring 25', in its Central part. It is preferable to perform a variety of channels 27, evenly distributed around the circumference of the outer ring 25'. For grease, in this case oil, indeed was given through the channels 27, the support bearing balls 23' should not block the entrance channels. This thrust bearing 23' are in the form of so-called "bearing with three contact points", well known in the art. This bearing includes the outer ring 25', the inner surface of which is formed, for example, two segments or half-rings, which have radio is, greater than the radius of the balls, and which are connected via the Central line, containing the openings of the channels 27. Thus, the balls can't get in contact with the outer ring 25' along this line, but only along two different lines, each of which is located on the segment or semicircle. Thus, each ball is in contact with two points of the outer ring 25' and in any case, one point of the inner ring 26 located on its Central line. Hence the expression "three contact points.

Preferably the thrust bearing 23' is the so-called "bearing with four contact points", i.e. the inner ring 26' is also a ring with drainage means (not shown). These funds may be made either to remove grease or, on the contrary, for grease in the bearing 23', and in this case it is removed through the drainage means 27 of the outer ring 25'. In this latter case, the oil is fed at the level of the inner ring 26' by centrifugation and removed at the level of the outer ring 25'.

Such bearings with four contact points are described in patents FR 2740187 and FR 2841305, registered in the name of the applicant.

Thus, lubrication of the bearing 23'coming, for example, through the nozzles, is removed through the channels 27, the holes which never overlap Shari is AMI, for removal of grease on the outside of the outer ring is provided by the system 28 removal of grease, for example, in the form of channels, operating on the principle of pumping or suction. Remove grease may also occur as a result of rotation of the balls in the outer ring 25', which causes the lubricant to pass into the channels 27 due to the action of centrifugal force, without the need of having any special removal system. Grease does not accumulate between the balls and the outer ring 25', so the beads do not slip on the outer ring 25'. Thus, it reduces the possibility of damage of the support bearing 23' from slipping, which, as it supports the rotor is protected.

Therefore, due to the use of a support bearing 23' with the means 27 drainage of lubricant, designed to maintain the shaft 13 of the rotor of the generator 11 AC drive rotor has not only the above-mentioned advantages, i.e. the separation between the rotor and the gear transmission box 10, which prevents the transmission of loads between the two elements, but also an additional advantage in that the thrust bearing 23' is protected, protecting, thus, the generator rotor 11 AC and, therefore, the generator 11 AC. Thus the m be protected gear box and the generator 11 AC.

In addition, due to the availability of funds 27 drainage of grease balls support bearing 23' less eager to slippage in the outer ring 25', which allows you to use a thrust bearing 23' larger size, which better absorbs the load of the rotor.

According to a third preferred variant of execution, shown in figure 4, the drive rotor of the generator 11 AC similar to the device shown in figure 3, except that the thrust bearing 23 supporting the shaft 13 of the rotor of the generator 11 AC, contains not only means 17 drainage of grease on the outer ring 25", but also means 29 depreciation between the outer ring 25 and the fixed design of the box 10. These funds 29 contain oil film between the outer ring 25 and the fixed design of the box 10. This means depreciation oil film known in the art under the English name "squeeze film". In particular, the outer side of the outer ring 25 is installed plate 31, which together with the outer ring 25" forms a space into which of the drainage channels 27 enters the oil. It does not matter what the pressure of the oil in such channels 27 is not significant as it heads the second is to maintain the level of the oil film 30 of a certain pressure. As shown by the arrows 32, 33, the oil can be removed through the space remaining between the edges of the outer ring 25" on either side of the ring 25". Alternatively, you can provide other means of removal, for example, to the outside of the outer ring 25", comparable with the means 28 removal of the scenarios shown in figure 3.

Oil film 30 forms a means of cushioning for support bearing 23". An additional advantage of such a device is the depreciation part of the loads on the thrust bearing 23 and providing additional protection and, therefore, protection of generator rotor 11 AC. Oil film 30 is created by the flow of oil through the drain channels 27 and is therefore easy to use. It further contributes to the separation between the generator rotor 11 AC and box 10, because not only the gear box 10 to be disconnected and, therefore, isolated from the rotor, but the oil film 30 also isolates and, therefore, separates the rotor and fixed the design of the box 10. Thus, at the same time gear and stationary design of the box 10 are isolated from the rotor.

Provided by plate 34 locks the rotation of the outer ring 25 is mounted on the ring 25 and nepo is vignau design of the box 10 from the generator 11 AC in order to prevent any turning of the ring 25 around the axis of the generator rotor 11 AC.

The inner ring 26 can be performed in the classical way, or contain a means of lubrication, for example, being made of two half-rings.

According to the fourth preferred variant of execution, shown in figure 5, the drive of the generator rotor 11 AC similar to the device according to the previous variants of execution, except that the shaft 13' of the generator rotor 11 AC has an additional distinctive feature. In this embodiment, the shaft 13' of the rotor in its section 21 of the shaft inside the tubular shaft 17, contains a weakened section 35 of smaller diameter, forming a relief area 35. Thus, in the case of a very high loads on the rotor and, consequently, on its shaft 13 safety section 35 is broken and completely disconnect the rotor from the tubular shaft 17 and, consequently, from the gear box 10. In this case we are talking about additional means of protection, which prevents damage to the box 10 in the case of too high load on the generator rotor 11 AC. This relief area 35 is calibrated depending on the maximum loads that the specialist deems acceptable for rotor GE is erator 11 AC and it collapses in case of too high loads that exceed a certain thus acceptable threshold load.

According to the fifth preferred variant implementation, shown in Fig.6, the drive rotor of the generator 11 AC similar to the device according to the previous variants of execution, except that the seal between the drive rotor of the generator 11 AC and the generator 11 is provided not by the reflector 36 as in the previous embodiments, execution, and brush strip 36'. Such brush strip 36' includes a ring 37 attached to a fixed structure of the box 10 near the support bearing 23 between the bearing 23 and the generator 11 AC, from which in the direction of the internal space densely made the hairs 38, for example, of carbon or ceramics. Such brush strip 36' set statically on the fixed structure of the carton 10, with the bristles 38 are in contact with the shaft 13 of the rotor (the length exceeds the distance between the ring 37 and the surface of the shaft 13 of the rotor). Thus, avoid the appearance of imbalance on the rotor due to the presence of oil between the rotor and the stator 12 of the generator 11 AC, and this further improves the operation of the device drive generator 11 AC, which is under argueta smaller loads.

Various options for the conduct can be combined with each other individually, in part or in entirety, as it was mentioned above that every single variant execution is on one particular item. The advantages of each option, perform complement each other and combined with each other, responding to the requirements of the separation and protection of the gear box 10 and the generator rotor 11 AC, as well as reducing stresses to which they are exposed.

1. The device of the auxiliary rotor drive Assembly mounted on the support units gas turbine engine which includes means for the drive shaft of the rotor comprising a tubular shaft, rotating mentioned means and supported by first and second bearings, permanently connected to the support units, while the rotor shaft is coaxial with the tubular shaft, and between the rotor shaft and the tubular shaft is made the means of coupling in rotation when the rotor shaft is supported by the third support bearing, permanently connected to the support units, and first and second bearings have a size less than the size of the third support bearing.

2. The device according to claim 1, wherein the auxiliary unit is an AC generator, containing a stator fixed n the support units.

3. The device according to claim 1, in which the clutch means in the rotation is splined connection type.

4. The device according to claim 1, in which the third thrust bearing is a ball bearing and includes means for drainage of grease on the outer ring.

5. The device according to claim 4, in which the third support bearing is the so-called bearing with three contact points or with four contact points.

6. The device according to claim 4, containing tools amortization oil film, made in the outer ring of the third support bearing.

7. The device according to claim 1, in which a number of third thrust bearing from the supporting unit has a brush gasket designed to seal the auxiliary unit to the lubrication device.

8. The device according to claim 1, in which the rotor shaft contains a plot forming the fuse, calibrated with destruction in case of too high load on the rotor.

9. The device according to claim 1 in which the said tool drive shaft of the rotor is a gear.

10. Bearing assemblies for gas turbine engine containing gears, torque drive device according to one of claims 1 to 9.

11. Gas turbine engine containing the shaft, means the power take-off shaft, the rotating gear support agregate is in paragraph 10.



 

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33 cl, 10 dwg

FIELD: electricity.

SUBSTANCE: cable bundle (3) positioning and retaining station on the turbojet engine (1) housing (2) includes bundle supports (3) standardized for directions perpendicular to the turbojet engine (1) axis (4) and bundle supports standardised for directions parallel to the turbojet engine (1) axis (4).

EFFECT: reduction of manufacturing cycle cost and time.

14 cl, 10 dwg

FIELD: engines and pumps.

SUBSTANCE: invention refers to aviation and particularly to devices for restraint and arrangement of auxiliary equipment in turbojet engines. The device consists of two coaxial rings (12, 14) assembled one into another and connected to each other with hollow radial poles (16, 18, 20 and 22). The pipelines and electrical wires run inside poles. At least one of the side poles (16, 18) bears a removable panel (24, 26) on its side, which after dismounting facilitates an access to the equipment of the turbojet engine arranged radially inside the interior ring (12) in one line with the radial pole (16, 18). Such design of the device provides an access to the equipment, installed in a turbojet engine.

EFFECT: facilitating access to equipment, assembled in a turbojet engine due to arrangement of a restraining device and of auxiliary equipment.

10 cl, 5 dwg

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: invention relates to units of drives of gas-turbine engines of aircraft and ground application. Proposed device contains fastening members and movable member telescopically connected with casing. Movable member is on accessory gear box and secured by pressure flange for displacement along end face of box. Clearance is formed between mating surfaces of flange and movable member.

EFFECT: improved reliability of connection of casing and accessory gear box by providing their rigid connection and sealing of inner spaces.

3 dwg

FIELD: aircraft engineering; gas turbine engines.

SUBSTANCE: invention relates to units of drives of gas-turbine engines of aircraft and ground application. Proposed device to transmit torque from compressor shaft to box of auxiliaries of gas-turbine engine includes spur gear wheel and bevel gear spaced and connected by seat surfaces and splines. Bevel gear is mounted on separate bearing support. Inductor is fitted in inner space of spur gear.

EFFECT: improved reliability of engine by provision of accurate signal from device checking frequency of rotation of compressor rotor.

1 dwg

Gas-turbine unit // 2245448

FIELD: power engineering.

SUBSTANCE: proposed gas-turbine unit has low-pressure compressor, intermediate air cooler, high-pressure compressor, regenerator, combustion chamber, gas turbine wherefrom spent gas is conveyed to regenerator coupled with exhaust pipe that uses energy of exhaust gases and is provided with nozzle and intake chamber for cooling down atmospheric air arriving from intermediate air cooler. Proportion of exhaust pipe parts is chosen to ensure desired proportion of sizes of gas-turbine components.

EFFECT: enhanced reliability of gas-turbine unit and ability of its off-line operation.

1 cl, 1 dwg

FIELD: aircraft engineering; gas turbine engines.

SUBSTANCE: invention relates to units of drives of gas-turbine engines of aircraft and ground application. Proposed device to transmit torque from compressor shaft to box of auxiliaries of gas-turbine engine includes spur gear wheel and bevel gear spaced and connected by seat surfaces and splines. Bevel gear is mounted on separate bearing support. Inductor is fitted in inner space of spur gear.

EFFECT: improved reliability of engine by provision of accurate signal from device checking frequency of rotation of compressor rotor.

1 dwg

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: invention relates to units of drives of gas-turbine engines of aircraft and ground application. Proposed device contains fastening members and movable member telescopically connected with casing. Movable member is on accessory gear box and secured by pressure flange for displacement along end face of box. Clearance is formed between mating surfaces of flange and movable member.

EFFECT: improved reliability of connection of casing and accessory gear box by providing their rigid connection and sealing of inner spaces.

3 dwg

FIELD: engines and pumps.

SUBSTANCE: invention refers to aviation and particularly to devices for restraint and arrangement of auxiliary equipment in turbojet engines. The device consists of two coaxial rings (12, 14) assembled one into another and connected to each other with hollow radial poles (16, 18, 20 and 22). The pipelines and electrical wires run inside poles. At least one of the side poles (16, 18) bears a removable panel (24, 26) on its side, which after dismounting facilitates an access to the equipment of the turbojet engine arranged radially inside the interior ring (12) in one line with the radial pole (16, 18). Such design of the device provides an access to the equipment, installed in a turbojet engine.

EFFECT: facilitating access to equipment, assembled in a turbojet engine due to arrangement of a restraining device and of auxiliary equipment.

10 cl, 5 dwg

FIELD: electricity.

SUBSTANCE: cable bundle (3) positioning and retaining station on the turbojet engine (1) housing (2) includes bundle supports (3) standardized for directions perpendicular to the turbojet engine (1) axis (4) and bundle supports standardised for directions parallel to the turbojet engine (1) axis (4).

EFFECT: reduction of manufacturing cycle cost and time.

14 cl, 10 dwg

FIELD: engines and pumps.

SUBSTANCE: invention is intended for feeding electric power to equipment from gas turbine engine. The proposed system comprises an electronic control device to control, at least, one parameter containing the data on originating variation in consumed power, a control valve controlled by aforesaid system and feeding air take off the engine operated in transient conditions and a pneumatic device receiving aforesaid taken-off air to actuate the aircraft onboard equipment. The latter can represent an air turbine or generator with built-in pneumatic circuitry.

EFFECT: use of engine pneumatic power to drive aircraft onboard equipment.

33 cl, 10 dwg

Air engine design // 2355902

FIELD: engine engineering, aviation.

SUBSTANCE: in accordance with the present invention fillet fairing is installed inside bypass channel of the external engine circuit in order to avoid outer thickness of auxiliary mechanisms and gear boxes and to actuate them. The external circuit channel is between engine housing and inner circuit of compressor/engine turbine. The fillet fairing dimensions are enough to accommodate auxiliary mechanisms. At the same time the external circuit channel is correspondingly made axisymmentrical to avoid or compensate any blocking effect from fillet fairing within the channel limits when air flows. In addition the fillet fairing may be provided for placing engine oil tank as well as filter/heat exchanger mechanisms foreseen for engine. Under the above circumstances it is essential that elongated cylindrical engine profile is maintained so that reduced cross section is required allowing for the engine to keep a reduced glider of air craft. As a result acoustic shock waves profile is improved.

EFFECT: elimination of outer thickness when auxiliary mechanisms are placed.

FIELD: engines and pumps.

SUBSTANCE: proposed unit consists of gas turbine and reduction gear accommodated inside container and coupled via transfer shaft, reduction gear output shaft carrying the pump. Input device is arranged between said reduction gear and engine so that device front face wall part seats on reduction gear, while device read face wall part is located on gas turbine engine. Note here that both aforesaid parts are linked up axially and radially by sealed telescopic couplings with the remaining part of input device fixed container. Inlet inspection window is made in input device front face wall. Input device lower wall is made flat and horizontal. In operation, sealed telescopic couplings allow the engine and reduction gear to move relative to input device with no loss in tightness on the latter.

EFFECT: higher reliability, reduced weight and overall dimensions, easier mounting and control.

3 dwg

FIELD: machine building.

SUBSTANCE: unit consists of gear box of gas turbine and of at least one starter/generator mechanically coupled with gear box. The gear box consists of gears with several pinions. The starter/generator contains a generating block with a rotor, forming an inductance coil and stator forming an anchor; further, the stator/generator contains an actuating block with the stator forming the inductance coil and rotor forming an anchor connected to the inductance coil of the generating block. The rotor of the generating block and the rotor of the actuating block are arranged on a common shaft with a pinion engaging the gear of the gear box on both sides of this pinion. The invention facilitates integration of the starter/generator into the gear box of the gas turbine.

EFFECT: reduced volume and dimensions, ensuring easy disassembly.

23 cl, 8 dwg

FIELD: engines and pumps.

SUBSTANCE: auxiliary mechanism drive of two-shaft gas turbine engine comprising high- and low-pressure shafts incorporates first mechanical transmission between high-pressure shaft and drive box, and hydraulic transmission between low-pressure shaft and drive box. Auxiliary mechanisms are arranged in drive box, while hydraulic transmission is mounted to allow auxiliary mechanism drive rpm being equal to high-pressure shaft rpm.

EFFECT: possibility to take off power from high- and low-pressure shafts without varying auxiliary mechanism rpm.

14 cl, 3 dwg

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