Aviation engine bearing nut locking structure

A technology for aero-engines and bearing nuts, applied to nuts, threaded fasteners, locking fasteners, etc., can solve the problems of poor assembly, high cost, and low reliability of anti-loosening structures, and improve the reliability of imitation loosening , Excellent assembly effect

Active Publication Date: 2019-03-22
AECC SICHUAN GAS TURBINE RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to meet the needs of the fourth-generation engine, a new mechanical locking structure is designed to solve the problems of low reliability, poor assembly and high cost of the anti-loosening structure of the bearing nut of the aero-engine

Method used

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  • Aviation engine bearing nut locking structure
  • Aviation engine bearing nut locking structure
  • Aviation engine bearing nut locking structure

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Embodiment Construction

[0021] The technical solution of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0022] The design concept of the technical solution of the present invention is: one end of the bearing nut 3 is pressed against the inner ring 5 of the bearing, a number of grooves are opened on the other end of the bearing nut 3 and the journal 4, and a lock plate 1 with multiple teeth inside and outside is designed, and multiple teeth are assembled in the groove. Tooth lock piece 1, the outer teeth 6 and inner teeth 7 of the lock piece 1 prevent the bearing nut 3 from loosening, and the retaining ring 2 is used to fix the lock piece to prevent the lock piece 1 from withdrawing axially. The locking piece is formed to prevent the nut from loosening, and the retaining ring axially fixes the structure of the locking piece. During the working process, the multi-tooth structure of the locking piece constrains each other, and will not vibrate un...

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Abstract

The invention discloses an aviation engine bearing nut locking structure. The aviation engine bearing nut locking structure is characterized in that a plurality of slots are formed in a bearing nut and a shaft neck; the aviation engine bearing nut locking structure includes a locking piece of a ring structure; inner and outer ring surfaces are provided with a plurality of internal teeth and external teeth; the internal and external teeth of the locking piece fit with the slots in the bearing nut and the shaft neck, so that the locking is completed; a retaining ring is also arranged in the bearing nut to fix the annular locking piece so that the annular locking piece can be prevented axial withdrawal. According to the aviation engine bearing nut locking structure, the problem that conventional locking pieces have low looseness prevention reliability is solved; compared with the conventional structural deformation locking pieces, the novel structural locking piece has no bending deformation during assembling and testing, the shearing areas are increased, and the ability of looseness prevention of the bearing nut is improved.

Description

Technical field: [0001] The invention belongs to the technical field of aero-engine bearings, in particular to an aero-engine bearing nut locking structure. Background technique [0002] The bearing nuts of aero-engines cannot be loosened during the entire life cycle of the engine, so as to ensure that the axial compression of the bearings is in a normal working state, and the bearing nuts are prone to self-loosening under the action of alternating loads and vibrations in the working state, so large Some bearing nuts are mechanically locked to ensure that the bearing nuts will not loosen. [0003] Most of the bearing nuts of the third-generation aero-engines are locked with lock pieces or pins. The two locking structures require that the bearing nut groove / hole corresponds to the journal groove / hole. Otherwise, the extrusion end surface of the bearing nut needs to be ground to ensure Assembly of cleats or pins; cleats or pins are destructively disassembled and cannot be reu...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16B37/00F16B39/282
CPCF16B37/00F16B39/282
Inventor 周梦志宁腾飞康亚杰张元兵史家伟
Owner AECC SICHUAN GAS TURBINE RES INST
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