RU126056U1 - GAS-TURBINE ENGINE SUPPORT ASSEMBLY - Google Patents

Abstract

1. A support assembly for a gas turbine engine, comprising a shaft, a housing in which an outer ring of the bearing is mounted with a guaranteed clearance, a cage with sockets in which the rolling elements are installed, and oil supply channels made in the housing and the outer ring of the bearing, while oil supply channels in the outer the bearing ring is inclined in the direction of rotation of the shaft, characterized in that it contains two centrifugal wheels with oil drainage elements mounted on the shaft from the ends of the bearing, the oil drainage elements of which are inclined in the direction of rotation of the shaft, while the oil supply channels in the housing are also inclined in the direction of rotation of the shaft and are aligned with the oil supply channels in the outer ring of the bearing. 2. A gas turbine engine support assembly according to claim 1, characterized in that the side surfaces of the separator sockets are made inclined in the direction of rotation of the rolling elements. The gas turbine engine support assembly according to claim 2, characterized in that the width of the separator socket exceeds the diameter of the rolling body. A gas turbine engine support assembly according to claim 3, characterized in that the separator sockets are staggered relative to each other. The gas turbine engine support assembly according to claim 1, characterized in that the oil exhaust elements are made in the form of blades or grooves.

Description

The utility model relates to the field of aircraft engine and power engineering, mainly to the lubrication systems of bearing bearings of gas turbine engines, and can be used to supply and drain oil in bearings, for example, high-temperature aircraft gas turbine engines.

A known node of a support for a gas turbine engine, comprising a shaft, a housing in which the outer ring of the bearing is installed with a guaranteed clearance, a cage, in the slots of which the rolling bodies are installed, and oil supply channels made in the housing and the outer ring of the bearing. The axis of the oil supply channels in the housing and the outer ring of the bearing are made in the radial direction (Skubachevsky Aircraft gas turbine engines. Design and calculation of parts. - M .: Mashinostroenie, 1969. - 544 p. (P. 467 Fig. 11.09).

Closest to the proposed is a support unit for a gas turbine engine, comprising a shaft, a housing in which the outer ring of the bearing is installed with a guaranteed clearance, a cage with sockets in which the rolling elements are installed, and oil supply channels made in the housing and the outer ring of the bearing, while oil supply the channels in the outer ring of the bearing are inclined in the direction of rotation of the shaft (copyright certificate No. 377571, IPC F16C 33/10, publ. 06/29/1973).

In known solutions, oil is supplied from above through the outer ring of the bearing. Oil is diverted to the oil sump only due to the action of centrifugal forces through the gaps between the separator and the outer ring.

In addition, the known solutions have a limited supply of oil to the inner ring of the bearing, because oil for cooling through the separator practically does not enter the contact zone due to the small gap between the rolling body and the separator and because of the radial arrangement of the grooves in the separator.

The technical result, which is achieved by the claimed utility model, is to increase the reliability and durability of the support of a gas turbine engine and, therefore, the entire engine by improving the lubrication conditions and enhancing the cooling of the bearing, by ensuring uniform supply of oil to the contact areas of the outer ring of the bearing and rolling elements and forced removal of oil from the contact zone of the inner ring of the bearing and rolling elements.

An additional technical result is the improvement of the conditions for supplying oil to the inner ring of the bearing.

The technical result is achieved in that the gas turbine engine support assembly comprising a shaft, a housing in which the outer ring of the bearing is mounted with a guaranteed clearance, a cage with sockets in which the rolling elements are installed, and oil supply channels made in the housing and the outer ring of the bearing, the oil supply channels in the outer ring of the bearing are inclined in the direction of rotation of the shaft, unlike the known one, it contains two centrifugal wheels with oil drainage elements mounted on the shaft from the ends of the bearings a, oil return elements which are inclined in the rotational direction, wherein the oil supply passages in the housing are also inclined in the direction of rotation of the shaft and coaxial with the oil supply channels in the outer ring of the bearing.

To improve the supply of oil to the inner ring of the bearing, the side surfaces of the separator seats can be made inclined in the direction of rotation of the rolling elements, while the width of the separator socket can exceed the diameter of the rolling element.

To fix the cage in the bearing in the axial direction, the cage seats can be staggered relative to each other.

The oil drainage elements can be made in the form of blades or grooves.

The claimed solution is illustrated by drawings, which depict:

figure 1 - design of the node support the shaft of the gas turbine engine;

figure 2 is a section aa of the structure of the support of figure 1;

figure 3 - a centrifugal wheel with elements of the drainage of oil;

figure 4 - separator with sockets.

The gas turbine engine support assembly (Fig. 1) comprises a shaft 1, a bearing with an inner 2 and an outer 3 rings, a cage 4, in which sockets 5 are installed rolling elements 6, and a housing 7 (or a sleeve), in which an outer 3 is installed with a guaranteed clearance bearing ring.

In the housing 7 and the outer 3 ring of the bearing, coaxial oil supply channels 8 and 9 are made, respectively, while their axes are inclined in the direction of rotation of the shaft 1 (figure 2).

On the shaft 1 from the side ends of the bearing are installed two centrifugal wheels 10 with elements 11 of the oil drain. Elements 11 drain oil made, for example, in the form of blades or grooves, and tilted in the direction of rotation of the shaft 1 (figure 3).

The lateral surfaces 12 of the separator sockets 5 are made oblique in the direction of rotation of the rolling elements 6 (FIG. 2). In this case, the width o of the sockets 5 of the separator 4 may exceed the diameter d of the rolling body, due to which cavities 13 are formed, which in the separator 4 can be staggered order relative to each other (figure 4).

The node support works as follows.

When the engine is running, oil under pressure is supplied to the channels 8 of the housing 7 and then through the channels 9 in the outer 3 ring of the bearing to the cavity between the outer ring and the separator 4. At the sockets 5 of the separator 4, the oil passes into the cavity between the separator 4 and the inner 2 ring of the bearing, which centrifugal forces created by the elements 11 of the oil drain of the centrifugal wheels 10 are thrown into the oil sump shaft support.

The utility model increases the reliability and durability of the support of a gas turbine engine, reduces heat dissipation in the contact areas of the rolling bodies with the outer and inner rings of the bearing, which increases the efficiency of the support of the gas turbine engine as a result of uniform supply of oil to the contact zone and its forced removal from the rolling support.

Claims (5)

1. A support assembly for a gas turbine engine, comprising a shaft, a housing in which an outer ring of the bearing is mounted with a guaranteed clearance, a cage with sockets in which the rolling elements are installed, and oil supply channels made in the housing and the outer ring of the bearing, while oil supply channels in the outer the bearing ring is inclined in the direction of rotation of the shaft, characterized in that it contains two centrifugal wheels with oil drainage elements mounted on the shaft from the ends of the bearing, the oil drainage elements of which are inclined in the direction of rotation of the shaft, while the oil supply channels in the housing are also inclined in the direction of rotation of the shaft and are aligned with the oil supply channels in the outer ring of the bearing. 2. The support node of a gas turbine engine according to claim 1, characterized in that the side surfaces of the separator sockets are made inclined in the direction of rotation of the rolling bodies. 3. The support node of the gas turbine engine according to claim 2, characterized in that the width of the separator socket exceeds the diameter of the rolling body. 4. The gas turbine engine support assembly according to claim 3, characterized in that the separator sockets are staggered relative to each other. 5. The support node of the gas turbine engine according to claim 1, characterized in that the elements of the oil drain are made in the form of blades or grooves.

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