Tightening device and tightening method of aeroengine high-pressure turbine rear axle nut

An aero-engine and rear axle nut technology, which is used in the field of devices for tightening or loosening threaded parts

Active Publication Date: 2021-08-17
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Based on the above requirements, the existing manual tightening devices and methods are difficult to accurately and efficiently tighten the rear axle nut 43, which has become a major difficulty in the assembly process of aero-engines

Method used

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  • Tightening device and tightening method of aeroengine high-pressure turbine rear axle nut
  • Tightening device and tightening method of aeroengine high-pressure turbine rear axle nut
  • Tightening device and tightening method of aeroengine high-pressure turbine rear axle nut

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Embodiment Construction

[0030] A variety of different implementations or examples for implementing the described subject technical solutions are disclosed below. In order to simplify the disclosure, the following describes the specific examples of each component and arrangement, of course, these are only examples, not limiting the protection scope of the present invention. For example, the description that the first feature described later in the description is formed on or above the second feature may include an embodiment in which the first and second features are formed through direct contact, and may also include an embodiment in which the first and second features are formed between the first and second features. Embodiments of additional features such that there may be no direct relationship between the first and second features. Additionally, reference numerals and / or letters may be repeated in different instances in these disclosures. This repetition is for brevity and clarity and does not i...

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Abstract

The present invention relates to a tightening device and a tightening method for a rear shaft nut of a high-pressure turbine of an aero-engine, wherein the tightening device includes an inner stop frock, and the inner stop frock includes a first clamping part, and the first clamping part It can be fixed in the rear shaft of the high-pressure turbine to fix the rear shaft of the high-pressure turbine; the externally rotating tooling includes a second clamping part and a rotating part, and the second clamping part can be clamped with the rear axle nut. The rotating part drives the second clamping part to rotate and tighten the rear axle nut; the torsion bar, one end of the torsion bar is connected to the inner stop tooling, and the other end is fixed to load the inner stop tooling against the rotation torque to keep the high pressure turbine rear shaft stationary during tightening. The above-mentioned tightening device and tightening method have the advantages of high precision, easy operation and the like.

Description

technical field [0001] The invention relates to a device and method for tightening or loosening a threaded part, in particular to a device and method for tightening a high-pressure turbine rear shaft nut of an aero-engine. Background technique [0002] The rotor part of the core machine of the aero-engine is composed of a high-pressure compressor rotor and a high-pressure turbine rotor. The high-pressure combined rotor is equipped with bearings and sealing grating rings. Due to structural design needs, such as Image 6 As shown, the shaft end of the rear shaft 4 of the high-pressure turbine rotor is designed with an external thread, and a large-sized rear shaft nut 43 is assembled there. The function of the rear shaft nut 43 is to compress the bearing outer ring and The rear shaft seals the grate gear ring 41 tightly. The tightening torque requirement of the rear axle nut 43 is usually greater than 800N.m; during the tightening process of the rear axle nut 43, it is necessa...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23P19/06
CPCB23P19/06
Inventor 连宇臣陈津陈勤潘泽宇周烁
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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