Machining method of low-pressure compressor casing

A processing method and compressor technology are applied in the field of aero-engine to achieve the effects of low processing cost and high efficiency

Active Publication Date: 2018-09-04
重庆天骄航空动力有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, this spinning method cannot be directly used to m

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  • Machining method of low-pressure compressor casing
  • Machining method of low-pressure compressor casing
  • Machining method of low-pressure compressor casing

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Embodiment Construction

[0030] The present invention will be further described below in conjunction with the accompanying drawings.

[0031] see figure 1 , figure 2 , image 3 and Figure 4 , a method for processing a casing of a low-pressure compressor, comprising the following steps:

[0032] The first step is blank inspection: the blank material is D6AC high-strength steel, annealed at 800°C for 2-3 hours, and the size, surface roughness, and tensile strength of the blank workpiece are tested;

[0033] The second step, turning datum: use CNC vertical lathe to process the rough workpiece datum to ensure the flatness of the datum plane is 0.05mm (millimeters);

[0034] The third step, spinning: first clamp the mold on the powerful CNC spinning machine and apply lubricant, then install the blank workpiece on the mold and carry out spinning step by step according to the set CNC program to obtain the wall thickness δ and roundness control For workpieces within 0.1mm, a small amount of margin is r...

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Abstract

The invention relates to a machining method of a low-pressure compressor casing. The method comprises the following steps that 1, a blank is inspected; 2, a benchmark is turned; 3, spinning is carriedout, wherein the blank is subjected to drawing and spinning by using a powerful numerical control spinning machine, so that a workpiece is obtained, wherein the wall thickness delta and the roundnessof the workpiece are controlled to be within 0.1 mm, and a small amount of allowance is reserved at the two ends of the workpiece to be used for subsequent mechanical machining; 4, the workpiece is cleaned, wherein a lubricant on the surface of the workpiece is cleared; 5, heat treatment is carried out, wherein the spinning stress is eliminated through the heat treatment; 6, a finish turning is carried out on a front end of the workpiece and a rear end of the workpiece; 7, the end face holes at the two ends of the workpiece is drilled and bored; 8, stamping of blade-type grooves is carried out, wherein a numerical-control punching machine is used for equidistantly stamping the blade-shaped grooves on the workpiece in the radial direction and fine trimming is carried out, so that the position degree of the blade-shaped groove is ensured to be 0.2 mm, and the contour degree of the blade-shaped groove is 0.05 mm; 9, magnetic particle testing is carried out; and 10, checking and storing are carried out. According to the method, the requirements of case deformation control, surface quality control and cost control can be met.

Description

technical field [0001] The invention relates to an aero-engine, in particular to a processing method for a casing of a low-pressure compressor. Background technique [0002] At present, the casing of the low-pressure compressor of the aero-engine is processed by turning + milling. The removal allowance is large, and the residual internal stress of the workpiece is large, resulting in large deformation of the workpiece. At the same time turning and milling are more costly. [0003] CN 107717029A discloses "a high-efficiency milling process method for split casings", which adopts the trochoidal milling tool path, large depth of cut, small width of cut, and fast feed process parameters. The steps are: high-efficiency milling tool path planning; Adopt the method of large depth of cut, small width of cut, and high feed speed to optimize cutting parameters; high-efficiency milling tool path planning includes: select the tool path of helical feed and cycloidal opening of pre-proce...

Claims

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Application Information

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IPC IPC(8): B23P15/00
Inventor 林大凯翟会民李俊儒吕静
Owner 重庆天骄航空动力有限公司
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