Blade and preparation process thereof

A preparation process and blade technology, which is applied in the field of blades and their preparation technology, can solve the problems of limited fatigue fracture capacity of blades, and achieve the effects of improving the surface integrity of blades, increasing fatigue strength, and reducing roughness values

Active Publication Date: 2021-10-01
AECC AVIATION POWER CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, in terms of anti-fatigue manufacturing of aero-engine blades, the existing technology is limited in improving the ability of the blades to undergo fatigue fracture during use, so there is still room for further improvement in the anti-fatigue manufacturing process of aero-engine blades

Method used

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  • Blade and preparation process thereof
  • Blade and preparation process thereof
  • Blade and preparation process thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0037] Take the second-stage high-pressure compressor rotor blade of a certain type of aero-engine as an example, and its material is titanium alloy TA11.

[0038] Before improving the process, the fatigue strength limit test data of the rotor blades of the second stage high pressure compressor are shown in Table 1.

[0039] Table 1 shows the fatigue strength limit test data of the second-stage high-pressure compressor rotor blade (before improvement)

[0040] Table 1

[0041]

[0042]

[0043] "Closed" lifting chart and matching results are shown in figure 1 , Table 2, Table 2 is the matching table of adjacent stress levels.

[0044] Table 2

[0045]

[0046] Median fatigue strength σ -1 :

[0047]

[0048] The standard deviation of fatigue strength sub-sample is:

[0049]

[0050] The coefficient of variation is:

[0051]

[0052] When the confidence level is 95% and the error limit is 5%, the total number of required pairs (the minimum number of obs...

Embodiment 2

[0076] Taking the rotor blade of the eighth-stage high-pressure compressor of a certain type of aero-engine as an example, the material of the rotor blade of the eighth-stage high-pressure compressor is 1Cr16Co5Ni2MoWVNbN.

[0077] Before the improvement process, the fatigue strength limit test data of the eighth-stage high-pressure compressor rotor blades are shown in Table 5, and Table 5 is the fatigue strength limit test data of the eighth-stage high-pressure compressor rotor blades (before improvement).

[0078] table 5

[0079]

[0080] Draw the "closed" lifting diagram according to the test data results in Table 5, see image 3 . According to the up-and-down diagram, the adjacent data with opposite test results are paired, and the maximum likelihood estimation value of fatigue strength σ is calculated * i , and use this value as a random variable for statistical analysis. The pairing results are shown in Table 6, which is the pairing table of adjacent stress levels...

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PUM

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Abstract

The invention discloses a blade and a preparation process thereof. The preparation process comprises the following steps that primary vacuum stress relief annealing is carried out on a blade forge piece after a correction procedure of blade profile forming of a precision forging blade; the blade forge piece is machined; secondary vacuum stress relief annealing is carried out on the machined blade forge piece; and shot blasting and vibration finishing are carried out on the blade forge piece subjected to secondary vacuum stress relief annealing, and preparation is completed.

Description

technical field [0001] The invention relates to an anti-fatigue manufacturing technology of precision forged blades of aero-engines, in particular to a blade and a preparation process thereof. Background technique [0002] Fatigue failure refers to the weaker grains in the high stress concentration area of ​​the mechanical structure, after a certain number of cycles under the action of alternating stress / strain, microscopic cracks are formed, and then develop into macroscopic cracks and continue to expand, eventually leading to material The process of fracture, and the starting point of fatigue cracks usually occurs at the surface or subsurface defects of metal components, especially rotating parts, when there are machining tool marks, non-metallic inclusions, micropores, burns, grinding cracks, When there are defects such as chemical composition segregation, fatigue crack initiation is more likely to be induced. [0003] According to relevant statistics, fatigue failure ac...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C21D9/00C21D1/30C21D1/773C22F1/18C22F1/10B24C1/00B24B1/00F04D29/30F04D29/02
CPCC21D9/0068C21D1/30C21D1/773C22F1/183C22F1/10B24C1/00B24B1/00F04D29/30F04D29/023
Inventor 张义德梁忠效寇录文王波陈媛媛马辉刘亚锋周经纬
Owner AECC AVIATION POWER CO LTD
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