RU177741U1 - SUPPORTING THE ROTOR OF THE AIRCRAFT GAS TURBINE ENGINE (GTE) WITH GREASE LUBRICANT - Google Patents

Abstract

The utility model relates to the field of gas turbine engine building and can be used in aircraft engines having severe restrictions on overall dimensions and mass. The use of grease as opposed to liquid allows to significantly simplify the design of the rotor support engine due to the absence of the need for an oil system. The technical result achieved in the claimed utility model, is to increase the service life of the support of an aircraft gas turbine engine (GTE), and therefore, always engine, by improving the lubrication conditions of the bearing due to the uniform and intensive supply of lubricant to the contact areas of the bearing elements and the forced removal of spent lubricant in the discharge cavity, which does not affect the operation of the bearing. The technical result is achieved by the fact that the rotor support of the aircraft gas turbine engine (GTE) with grease containing a hollow shaft, housing, bearing with outer and inner rings, a cage and rolling elements, one channel for the cooler, made in the hollow shaft, reserve grease-filled bowl, cooling cavities communicated with exhaust cooler discharge cavities with the same medium pressure. A new model in the utility model is that the grease reservoir is made inside the hollow shaft and communicates with the bearing cavities through one channel made in the hollow shaft, the cavity The discharge of the used grease is performed outside the bearing and communicated with the bearing through the channels for removing the used grease. A completed reservoir with grease in the rotor and communicated with the floor by means of a bearing through a single channel made in the rotor, it allows intensively and uniformly supplying lubricant to all bearing elements under the action of centrifugal forces, by pushing a new portion of grease to all elements and surfaces of the bearing and placing the discharge cavity of the used lubricant outside the bearing, which does not render negative impact on his work.

Description

SUPPORTING THE ROTOR OF THE AIRCRAFT GAS TURBINE ENGINE (GTE) WITH GREASE LUBRICANT

The utility model relates to the field of gas turbine engine building and can find application in aircraft engines having severe restrictions on overall dimensions and weight.

The use of grease, unlike liquid grease, can significantly simplify the design of the rotor support motor due to the absence of the need for an oil system.

Known cooled bearings (Copyright certificate No. 1712696 A1; class F16C 37/00, published 02.15.1992), including a housing mounted on a shaft bearing with outer and inner rings, a cage and balls, a reservoir for lubricating the bearing, a cooling channel.

The main disadvantage of the design described is the ineffective lubrication of the bearing elements, due to the fact that only grease is used, which is previously placed in the bearing cavity, the used grease and wear products do not leave the bearing cavity, which worsens its operation.

Known shaft support, selected as a prototype (RF Patent No. 85588; class F16C 37/00, published August 10, 2009), comprising a hollow shaft, a housing, a bearing with outer and inner rings, a cage and rolling elements, one channel for a cooler, made in a hollow shaft, a grease reservoir, cooling cavities communicated with the discharge cavities of the spent cooler with the same medium pressure.

The main disadvantage of the design described is the ineffective lubrication of the bearing elements due to the fact that the aggregate state of the grease is not taken into account, which affects the efficiency of its getting into the contact areas of the bearing elements, and

it also makes it impossible to circulate spent lubricant inside the bearing, while the presence of spent lubricant in the area of operation of the bearing elements impairs the operation of the entire structure.

The technical result achieved in the claimed utility model is to increase the service life of the support of an aircraft gas turbine engine (GTE), and, consequently, the entire engine, by improving the lubrication of the bearing due to the uniform and intensive supply of lubricant to the contact areas of the bearing elements and the forced removal of spent lubricant in the discharge cavity, which does not affect the operation of the bearing.

The technical result is achieved in that the rotor support of an aircraft gas turbine engine (GTE) with grease, containing a hollow shaft, a housing, a bearing with outer and inner rings, a cage and rolling elements, one channel for the cooler made in the hollow shaft, a reservoir with a grease lubrication, cooling cavities communicated with the discharge cavities of the spent cooler with the same medium pressure.

New in the utility model is that the grease reservoir is made inside the hollow shaft and communicated with the bearing cavities through a single channel made in the hollow shaft, the spent lubricant discharge cavities are made outside the bearing and communicated with the bearing through the exhaust grease channels.

The made reservoir with grease in the rotor and communicated with the bearing cavities through at least one channel made in the rotor allows the lubricant to be intensively and uniformly supplied to all bearing elements under the action of centrifugal forces, by pushing a new portion of the grease to all elements and surfaces bearing and placement

cavity discharge of used grease outside the bearing does not have a negative impact on its operation.

The accompanying drawing shows the claimed rotor support of an aircraft gas turbine engine (GTE) with grease.

The rotor support of an aircraft gas turbine engine (GTE) with grease contains a hollow shaft 1, a housing 2, a bearing 3 with an outer 4 and an inner 5 rings, a cage 6 and rolling elements 7.

The channel for the cooler 8 is made in the hollow shaft 1.

The cooling cavities 9 are in communication with the exhaust cavities 10 of the spent cooler. The discharge cavities 10 of the cooler have the same medium pressure.

The reservoir with grease 11 is made inside the hollow shaft 1 and communicated with the cavities 12 of the bearing 3 through the channel 13, made in the hollow shaft 1.

The grease discharge cavities 14 are made outside the bearing 3 and communicated with the bearing 3 by means of exhaust grease exhaust channels 15.

The rotor support of an aircraft gas turbine engine (GTE) with grease operates as follows.

Compressed air from the intermediate stage of the compressor or from the engine inlet enters through the channel for cooler 8, thereby cooling the elements of the bearing 3.

Next, the exhaust air is discharged into the cavity 10, which maintains the same pressure of the medium from both ends of the bearing 3, which eliminates the removal of grease from the air from the cavities of the bearing 3.

Grease reservoir 11 is full. When the rotor rotates under the action of centrifugal force, the lubricant is pushed through the channel 13 to the contact areas of the rolling elements 7, the outer 4 and inner 5 rings, and the bearing cage 6.

Next, the lubricant is displaced into the discharge cavity 14 through the exhaust channel 15.

Thus, the proposed design of the support for an aircraft gas turbine engine (GTE) allows to increase the service life, and therefore the entire engine, by improving the lubrication of the bearing due to the uniform and intensive supply of lubricant to the contact areas of the bearing elements and the forced removal of spent lubricant in the discharge cavity, not affecting the operation of the bearing.

Claims (1)

The rotor support of an aircraft gas turbine engine (GTE) with grease, comprising a hollow shaft, a housing, a bearing with outer and inner rings, a cage and rolling elements, one channel for a cooler made in the hollow shaft, a grease reservoir, and cooling cavities communicated with discharge cavities of the spent cooler with the same medium pressure, characterized in that the grease reservoir is made inside the hollow shaft and communicates with the bearing cavities through one channel made into the floor On the shaft, the exhaust grease discharge cavities are made outside the bearing and communicated with the bearing through the channels for exhaust grease removal.

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