Device and method for screwing rear shaft nut of high pressure turbine of aero-engine

A technology of aero-engine, rear axle nut, applied in the field of devices for tightening or loosening screw parts

Active Publication Date: 2020-01-03
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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  • Device and method for screwing rear shaft nut of high pressure turbine of aero-engine
  • Device and method for screwing rear shaft nut of high pressure turbine of aero-engine
  • Device and method for screwing rear shaft nut of high pressure turbine of aero-engine

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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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PUM

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Abstract

The invention relates to a device and method for screwing a rear shaft nut of a high pressure turbine of an aero-engine. The screwing device comprises an inner stopping tool, an outer rotating tool and a torsion bar, wherein the inner stopping tool comprises a first clamping part, the first clamping part can be fixed into a rear shaft of the high pressure turbine so as to fix the rear shaft of thehigh pressure turbine, the outer rotating tool comprises a second clamping part and a rotating part, the second clamping part can be clamped on the rear shaft nut, the rotating part drives the secondclamping part so as to rotate and screw the rear shaft nut, one end of the torsion bar is connected with the inner stopping tool, and the other end of the torsion bar is fixed so as to bear the rotating torque borne by the inner stopping tool and keep a rear shaft of the high pressure turbine fixed in the screwing process. The screwing device and screwing method have the advantages that precisionis high and operation is simple and convenient.

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 Figure 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 necess...

Claims

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Application Information

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Patent Type & Authority Applications(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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