Structure for aviation gas turbine rotor supporting point ball bearing axial pre-load

An axial load, fulcrum ball technology, used in engine lubrication, engine components, turbine/propulsion lubrication, etc., can solve problems such as main bearing slippage, slippage damage, engine normal, reliable work threats, etc.

Inactive Publication Date: 2013-03-20
AECC SHENYANG ENGINE RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] In the existing aviation gas turbine engines, the axial load of the rotor generally changes direction during operation. At the moment before and after the direction change, the bearings will appear light load and zero load. If anti-skid measures are not adopted, most of the main bearings will It will slip and cause slipping damage, which poses a threat to the normal and reliable operation of the engine

Method used

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  • Structure for aviation gas turbine rotor supporting point ball bearing axial pre-load
  • Structure for aviation gas turbine rotor supporting point ball bearing axial pre-load

Examples

Experimental program
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Embodiment 1

[0017] This embodiment provides a structure for pre-applying axial load of the fulcrum ball bearing of the aviation gas turbine rotor, which is characterized in that: the structure for pre-applying the axial load of the fulcrum ball bearing of the aviation gas turbine rotor includes the main Bearing 1, auxiliary bearing 2, disc spring 3, adjusting pad 4;

[0018] Among them: the auxiliary bearing 2 is fixed on the rotor of the gas turbine, and shares the inner ring of the bearing with the main bearing 1, the outer ring is fixed on the stator by means of floating or clearance fit, one end of the disc spring 3 is pressed against the end face of the outer ring of the auxiliary bearing 2, and the other end is It is tight against the end face of the adjustment pad 4, and the adjustment pad 4 is fixed on the stator.

[0019] In order to prevent the two ends of the disc spring from collapsing or wearing due to the large stress, the two ends of the disc yellow 3 need to be chamfered a...

Embodiment 2

[0024] This embodiment provides a structure for pre-applying axial load of the fulcrum ball bearing of the aviation gas turbine rotor, which is characterized in that: the structure for pre-applying the axial load of the fulcrum ball bearing of the aviation gas turbine rotor includes the main Bearing 1, auxiliary bearing 2, disc spring 3, adjusting pad 4;

[0025] Among them: the auxiliary bearing 2 is fixed on the rotor of the gas turbine, and shares the inner ring of the bearing with the main bearing 1, the outer ring is fixed on the stator by means of floating or clearance fit, one end of the disc spring 3 is pressed against the end face of the outer ring of the auxiliary bearing 2, and the other end is It is tight against the end face of the adjustment pad 4, and the adjustment pad 4 is fixed on the stator.

[0026] In order to prevent the two ends of the disc spring from collapsing or wearing due to the large stress, the two ends of the disc yellow 3 need to be chamfered a...

Embodiment 3

[0031] This embodiment provides a structure for pre-applying axial load of the fulcrum ball bearing of the aviation gas turbine rotor, which is characterized in that: the structure for pre-applying the axial load of the fulcrum ball bearing of the aviation gas turbine rotor includes the main Bearing 1, auxiliary bearing 2, disc spring 3, adjusting pad 4;

[0032] Among them: the auxiliary bearing 2 is fixed on the rotor of the gas turbine, and shares the inner ring of the bearing with the main bearing 1, the outer ring is fixed on the stator by means of floating or clearance fit, one end of the disc spring 3 is pressed against the end face of the outer ring of the auxiliary bearing 2, and the other end is It is tight against the end face of the adjustment pad 4, and the adjustment pad 4 is fixed on the stator.

[0033] In order to prevent the two ends of the disc spring from collapsing or wearing due to the large stress, the two ends of the disc yellow 3 need to be chamfered a...

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Abstract

A structure for aviation gas turbine rotor supporting point ball bearing axial pre-load includes a main bearing, an auxiliary bearing, a disc spring, and an adjustable pad, wherein the auxiliary bearing is fixed on a gas turbine rotor and shares a bearing inner ring with the main bearing, the outer ring is fixed on a stator in the manner of floating or clearance fitting, one end of the disc spring sticks tightly against the outer ring end face of the auxiliary bearing, the other end of the disc spring sticks tightly against the end face of the adjustable pad, and the adjustable pad is fixed on the stator. The structure has the advantages of being applicable to different aviation gas turbines, meeting the need of rotor supporting point ball bearing axial pre-load, improving the loading condition of the ball bearing, and improving the reliability of the ball bearing. The structure is simple in structure, easy for assembly, and high in environmental adaptability and reliability, can pre-add a large axial force, can apply different preload according to the requirements of different gas turbine axial forces; and effectively improves the applicability of the main bearing.

Description

technical field [0001] The invention relates to the field of aviation gas turbines, in particular to a structure for pre-loading the axial load of the fulcrum ball bearing of the rotor of the aviation gas turbine. Background technique [0002] In the existing aviation gas turbine engines, the axial load of the rotor generally changes direction during operation. At the moment before and after the direction change, the bearings will appear light load and zero load. If anti-skid measures are not adopted, most of the main bearings will It will slip and cause slipping damage, which poses a threat to the normal and reliable operation of the engine. [0003] Therefore, on the main bearings of aviation gas turbines, special attention should be paid to prevent the bearings from slipping. At present, in most designs, in order to reduce bearing slippage, either the method of reducing the resistance to the movement of the roller-cage can be used, or the method of increasing the drag fo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/06
Inventor 金海黄耀宇张彦军刘仕运贾瑞琦
Owner AECC SHENYANG ENGINE RES INST
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