Disassembling method for double-tightness chuck

A chuck and tightness technology, which is applied to the supporting elements of the blade, preventing leakage, and engine components, can solve the problem that the double-tightness chuck cannot be decomposed, and achieves the effect of eliminating friction and interference and stabilizing the decomposition process.

Active Publication Date: 2019-01-11
AECC AVIATION POWER CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The purpose of the present invention is to provide a disassembly method of a double-tightn

Method used

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  • Disassembling method for double-tightness chuck
  • Disassembling method for double-tightness chuck
  • Disassembling method for double-tightness chuck

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Embodiment Construction

[0051] Below in conjunction with accompanying drawing, the present invention is described in detail.

[0052] Such as figure 1 , figure 2 As shown, a disassembly device for a double-tightness chuck provided by the present invention includes a lifting mechanism 1, a body 2, a rotating mechanism 3, an outer ring lifting mechanism 4, a backing plate 5, a gripping mechanism 6 and an auxiliary gripping mechanism 7, wherein , the backing plate 5 is placed under the outer ring lifting mechanism 4, and the turbine disk to be separated is placed in the cavity between the backing plate 5 and the outer ring lifting mechanism 4; the grasping mechanism 6 and the auxiliary grasping mechanism 7 are installed outside In the central hole of the ring lifting mechanism 4, the body 2 is installed on the upper surface of the outer ring lifting mechanism 4, and the body 2 is also connected with the lifting mechanism 1.

[0053] specifically:

[0054] Such as image 3 As shown, the lifting mech...

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Abstract

The invention provides a disassembling device and method for a double-tightness chuck. The disassembling device comprises a lifting mechanism, a body, a rotating mechanism, an outer ring lifting mechanism, a base plate and a grabbing mechanism. The body is arranged below the lifting mechanism, the grabbing mechanism is arranged below the body, and the body, the lifting mechanism and the grabbing mechanism are fixedly connected. The outer ring lifting mechanism is mounted at one end of the grabbing mechanism in a sleeving mode and connected with the body, and the other end of the grabbing mechanism makes contact with a chuck body in the to-be-separated double-tightness chuck. The base plate is arranged below the outer ring lifting mechanism. A turbine disc in the to-be-separated double-tightness chuck is placed in a cavity between the base plate and the outer ring lifting mechanism and fixed to the base plate. The rotating mechanism is arranged on the upper surface of the outer ring lifting mechanism. According to the disassembling device and method for the double-tightness chuck, the chuck pre-deforms through a disassembling hydraulic device, the synchronous double-tightness over-positioning chuck is disassembled in steps, friction and interference between parts during relative motion decomposing are eliminated, and the disassembling process is stable, accurate, reliable, and free of bumping.

Description

technical field [0001] The invention belongs to the technical field of aero-engine assembly, and in particular relates to a method for disassembling a double-tightness chuck. Background technique [0002] In recent years, the chuck (i.e. the integrated structure of the front sealing plate of the turbine rotor and the baffle) has been widely used in domestic advanced aero-engine research products. It is not only the axial positioning baffle of the turbine blade but also the Rotating non-contact gas sealing device, this structure simplifies the turbine components, reduces the number of parts, weight and improves the cooling effect of the disc, which has significant advantages in improving the performance of aircraft engines. [0003] From the analysis of the assembly structure of the chuck and the turbine disk, the chuck and the turbine disk are connected in a "pressure cooker cover" type, and the axial fit tightness is 1.07-1.31mm (that is, the amount of deformation of the ch...

Claims

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Application Information

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IPC IPC(8): F01D5/30F01D11/04F01D25/00
CPCF01D5/30F01D11/04F01D25/00
Inventor 王满贤孟繁翎吕军刚郗育钊杨翠玲王幸张绍军齐玮凤
Owner AECC AVIATION POWER CO LTD
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