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Machining process deformation solving method for low-pressure turbine disc

A solution method, a low-pressure turbine technology, is applied in the field of deformation solution in the machining process of the low-pressure turbine disk, which can solve the problems of easy deformation of the low-pressure turbine disk, and achieve the effect of avoiding deformation.

Active Publication Date: 2021-01-29
无锡航亚科技股份有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The technical problem to be solved by the present invention is to provide a solution to the deformation of the low-pressure turbine disk during machining, so as to solve the technical problem that the low-pressure turbine disk is easily deformed during the machining process in the prior art

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  • Machining process deformation solving method for low-pressure turbine disc
  • Machining process deformation solving method for low-pressure turbine disc
  • Machining process deformation solving method for low-pressure turbine disc

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Embodiment Construction

[0019] The specific embodiments of the present invention will be further described below in conjunction with the accompanying drawings. It should be noted here that the descriptions of these embodiments are used to help understand the present invention, but are not intended to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below may be combined with each other as long as they do not constitute a conflict with each other.

[0020] see Figure 1-5 , the present invention provides a solution to the deformation of the machining process of the low-pressure turbine disc, comprising the following steps:

[0021] Step 1: Turning process step route control, turning adjustment margin distribution is divided into 4 processes (see figure 1 ), the finish turning process margin of 0.5mm is divided into 4 cuts and two sections, of which the first two cuts each process 0.15mm and a total of 0.3mm, and t...

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Abstract

The invention discloses a machining process deformation solving method for a low-pressure turbine disc. The method comprises the following steps that finish-turning is performed in the procedures of turning step route control, clamping control in a broaching process, process control in a shot-blasting procedure and the like; 0.2mm allowance is reserved for a benchmark and a related matching surface after finish-turning is finished; after broaching, the roundness of the side edge of a mortise and the disc center is repaired to serve as a follow-up benchmark; after milling is finished, the innerside and the outer side of the deformed portion of an installation edge are repaired; and after shot blasting is finished, an assembly surface and assembly holes are finally and finely machined in place, and therefore the technical problem that the low-pressure turbine disc deforms in the machining process is effectively solved.

Description

technical field [0001] The invention relates to the technical field of low-pressure turbine disk machining technology for new materials of aero-engines, in particular to a method for solving the deformation of the low-pressure turbine disk during machining. Background technique [0002] The turbine disk is the most critical core rotating part in the aero-engine. Its working conditions are harsh, and it needs to withstand the double superposition of high temperature and high pressure. The manufacturing process is complex and the technical requirements are high. It has long been one of the problems restricting the development of aero-engines in my country; At present, the low-pressure turbine disk is a large-diameter, thin-walled and easily deformed part, which is easily deformed by factors such as improper clamping force, uneven cutting force, high-speed broaching and shot peening during processing. Contents of the invention [0003] The technical problem to be solved by the...

Claims

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Application Information

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IPC IPC(8): B23P15/00
CPCB23P15/00Y02E10/20
Inventor 崔腾姚煜张颖玉姜功宇闫晨
Owner 无锡航亚科技股份有限公司