RU2293193C1 - Gas-turbine engine support unit - Google Patents

Abstract

FIELD: power and transport engineering.

SUBSTANCE: invention relates to bearing support lubrication systems of gas-turbine engines and it can be used to fed oil to bearing, for instance, interrotor bearings of high-temperature aircraft gas-turbine engines. According to invention gas-turbine engine support unit contains bearing with roller, inner race and cage, support unit being made to supply oil to bearing. At least channel is made additionally in inner race of bearing to supply oil to path of bearing inner race, ratio of channel is 20°≤α≤90° where α is angle between axis of channel and axis of rotation of bearing. Ratio of B/L=1.1-5.0 is true for bearing of support unit where B is width of cage and L is width of roller. Oil can be fed to path of inner race of bearing in support unit of gas-turbine engine through grooves made in bearing inner holder by grinding wheel.

EFFECT: improved reliability of bearing and, consequently, engine itself by improving conditions of lubrication of bearings and its cooling, increased service life of engine.

2 cl, 2 dwg

Description

The invention relates to power and transport engineering, in particular to lubrication systems for bearing bearings of gas turbine engines, and can be used to supply oil to bearings, for example, inter-rotor bearings of high-temperature aircraft gas turbine engines.

Widely known are various devices for supplying oil to bearings of a bearing from a common oil system of a gas turbine engine (GTE) containing oil-injecting nozzles of a jet type. Each nozzle contains a housing with a nozzle channel for supplying oil to the working bodies of the bearing, connected to the oil line of the engine, and the holes of the nozzle channels have a calculated size in accordance with the requirements and conditions of lubrication (Shtoda A.V. et al. “Design of aircraft engines”, ed. VVIA, 1959, p.114-117).

These designs are justified for engines operating in low temperature modes.

However, the bearing supports of rotors, especially turbine rotors of modern high-temperature gas turbine aircraft engines, are exposed to temperatures of the order of 300 ° C due to the supply of heat from the hot gases of the working engine to them, and after its shutdown, from massive to high temperature turbine parts.

Known support node for a gas turbine engine, comprising a bearing with a roller, an inner ring and a cage, connected by oil supply channels to the shaft. This solution uses a bearing containing a so-called “with wings” separator, as well as channels made in the sleeve and allowing oil to be supplied to the bearing (RF patent No. 2038513, IPC 6: F 04 D 29/04, publication date 1995.06.27 ) is an analogue.

The disadvantage of this solution is that the oil does not fall on the inner ring of the bearing, but is captured by the “wings” of the separator, which perform the function of trapping oil. Thus, only the rollers and the outer bearing ring are lubricated, which does not provide effective bearing lubrication and heat dissipation.

A gas turbine engine support assembly is also known in which oil is supplied to a bearing with a roller, an inner ring and a cage as follows. Through the holes made in the pin of the toe of the low-pressure turbine, oil enters the annular manifolds and through the nozzles is fed into the bearing in the axial direction (RF patent No. 2144995, F 02 C 7/06, publication date - 2000.01.27) - prototype.

The disadvantage of this design is that the oil from the nozzles is thrown by centrifugal forces directly to the outer ring of the bearing, and the oil enters the inner ring of the bearing in a small amount, insufficient to ensure reliable operation of the bearing and the engine as a whole.

The technical result, the achievement of which the claimed invention is directed, is to increase the reliability of the bearing and, consequently, the entire engine by improving the lubrication conditions of the bearing and its cooling and providing increased engine life.

The specified technical result is achieved in that the support unit of the gas turbine engine comprises a bearing with a roller, an inner ring and a cage, wherein the support assembly is configured to supply oil to the bearing, and at least one channel for supplying oil to the inner ring of the bearing is additionally made the treadmill of the inner ring of the bearing, and for the channel, the relation 20 ° ≤α≤90 ° is fulfilled, where α is the angle between the axis of the channel and the axis of rotation of the bearing.

For the bearing of the support assembly, the ratio B / L = 1.1-5.0 can be fulfilled, where B is the width of the separator, L is the width of the roller.

In the node of the supports of the gas turbine engine, oil can be supplied to the treadmill of the inner ring of the bearing in the grooves of the grinding wheel exit made in the inner ring of the bearing.

The claimed invention is characterized in that in order to achieve the claimed technical result, it is necessary that at least one channel for supplying oil to the treadmill of the inner ring of the bearing is additionally made in the inner ring of the bearing, and the ratio 20 ° ≤α≤90 ° is fulfilled for the channel , where α is the angle between the channel axis and the axis of rotation of the bearing, and for the bearing the ratio B / L = 1.1-5.0 can be fulfilled, where B is the width of the separator, L is the width of the roller, and the oil supply to the treadmill of the inner ring the hem nick can be made in performed in the inner ring of the bearing of the grinding wheel output grooves.

This implementation is due to the following:

To ensure the effectiveness of bearing lubrication, the lubricant must be supplied to all working surfaces of the bearing, for example, to the bearing roller. The inner ring of the bearing, especially in the case of guide rails, is located in the zone of oil “starvation” and to ensure its lubrication, a direct supply of oil to its working surface is required, which is ensured by the implementation of oil supply channels in it.

Oil flows through the channels under the action of centrifugal forces. The effectiveness of the oil flow rate depends on the angle between the axis of the channel and the axis of rotation of the bearing, and therefore the engine.

The implementation of at least one of the channels at an angle of 20 ° ≤α≤90 °, where α is the angle between the axis of the channel and the axis of rotation of the bearing, allows to obtain the claimed technical result, which can be optimized by the fact that the oil supply directly to the inner ring the bearing can be implemented in the grooves of the grinding wheel exit made in the inner ring of the bearing.

For a particular bearing, the channels made in it can have both the same diameter and different diameters. This depends on the design of the GTE support assembly, on the recommended oil flow through the bearing and on the number of channels made in the inner race of the bearing, and the mutual radial angular arrangement of the channels on both sides can be different, i.e. the axis of the channels can be located both in one and in different planes.

The implementation of the bearing unit of the support of the ratio B / L = 1.1-5.0, where B is the width of the separator, L is the width of the roller, allows you to further ensure the compactness of the design of the entire oil line and increase the capture and retention of oil in the bearing.

When the angle of inclination of the channels is less than 20 ° and more than 90 ° to the axis of rotation of the bearing, it will reduce the reliability of the bearing due to increased losses in speed and additional oil consumption, as well as due to a significant increase in dimensions and complication of the entire bearing assembly.

To ensure a better capture and retention of oil in the bearing, the B / L ratio should be in the range of 1.1 to 5.0. A ratio of less than 1.1 will not ensure oil recovery, and if the ratio is greater than 5.0, the oil, without falling into the bearing, will be displaced to the drain, which will significantly increase the dimensions of the structure and worsen the strength characteristics of the gas turbine engine support assembly.

The supply of oil through the holes made in the inner ring of the bearing and extending into the grooves of the exit of the grinding wheel ensures the integrity of the treadmill and the bearing guide rails, which increases the resource and optimizes the strength characteristics, and therefore the reliability of the bearing assembly.

The claimed solution is illustrated by the drawings presented in figures 1 and 2, where in figure 1 is a node of the support of a gas turbine engine (GTE), in figure 2 is an enlarged view A of figure 1.

The GTE support assembly, for example, the GTE turbine support assembly, includes a bearing 1 with a roller 2, an inner ring 3 and a separator with “wings” 4, grooves 5, 6 and oil supply channels 7 and 8, turbine shaft 9, nozzle 10, oil manifold 11 mounted on the housing of the turbine support and the tip of the turbine 12. In the inner ring 3 of the bearing are additionally made channels 13 and 14, which serve to supply oil to the bearing 1. Channels 13 and 14 are made in the inner ring 3 of the bearing 1 with the formation between their axes and axis rotation of the bearing angles 20 ° -90 °, for example 45 °. The channels 13 and 14, made in the inner ring of the bearing 1, can be connected to the channels of the shaft 7 and 8 either directly (in the absence of a pin), or through the shaft 9 and, accordingly, through the channels 5 and 6, made in the shaft 9.

The channels 13 and 14 can be made in such a way that they connect the shaft 9 with the grooves of the output of the grinding wheel (grooves) 15 and 16, made in the inner ring 3 and forming a cavity between the inner ring 3 of the bearing 1 and the roller 2.

The device operates as follows.

Through the nozzle 10 of the oil manifold 11, mounted on the housing of the turbine support, oil is supplied under pressure from the oil pump (not shown in the drawing) into the internal cavity of the shaft 9, where an oil bath is formed due to its structural design, for example, a spacer ring. Further, due to the centrifugal forces arising from the rotation of the shaft 9 of the turbine, for example, a low pressure turbine, oil enters through the openings in the shaft 9 into the space formed by the outer surface of the shaft and the inner surface of the toe 12 of the low pressure turbine. Next, the oil moves into the radial channels made in the toe 12 of the low pressure turbine under the inner ring 13 of the bearing 1.

Next, the oil is fed into the inner ring 3 of the bearing through the channels 13 and 14, made in the inner ring 3, while the oil is supplied at an angle to the vertical axis and enters the roller 2 and the inner ring 3 of the bearing, for example inter-rotor bearing. The "wings" of the separator 4 hold the oil in the bearing 1, which increases the efficiency of lubrication and heat transfer.

The advantage of this solution is as follows:

- the oil enters not only the rollers and the outer ring of the bearing, but also more directly on the treadmill of the inner ring of the bearing, which provides better lubrication compared to the prototype, in which the oil falls only on the rollers and the outer ring;

- the use of a separator with wings allows you to more fully use the oil, as the oil is more fully trapped and held in the bearing;

- accordingly, a more efficient heat removal from the bearing rings is provided, which increases the reliability and service life of the bearing in the assembly and the engine as a whole.

As shown by comparative tests of the support assembly of the gas turbine engine with the inventive bearing with channels made in the inner ring and the bearing of the prototype (RF patent No. 2144995).

The bearing with 8 channels (4 per side) with a diameter of 1 mm, made at an angle of 45 degrees to the axis of rotation of the bearing and the ratio B / L = 2.5, has a ring temperature of 10 ° C lower than that of the prototype, and quality control of workers of the surfaces of the claimed bearing and prototype showed that the bearing according to the claimed solution has less wear on the working surfaces, which increases the reliability of the bearing assembly and engine life.

Claims (2)

1. A support assembly for a gas turbine engine, comprising a bearing with a roller, an inner ring and a cage, and configured to supply oil to the bearing, characterized in that at least one channel for supplying oil to the treadmill of the inner race is additionally provided in the inner ring of the bearing bearing rings, and for the channel, the relation 20 ° ≤α≤90 ° is fulfilled, where α is the angle between the channel axis and the axis of rotation of the bearing, and for the bearing, the ratio B / L = 1.1-5.0, where B is the width of the separator , L is the width of the roller. 2. The support assembly according to claim 1, characterized in that the oil is supplied to the treadmill of the inner ring of the bearing in the grooves of the exit of the grinding wheel made in the inner race of the bearing.

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