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Method for predicting crack initiation life of high temperature alloy containing inclusion powder

A technology of life prediction and superalloy, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as high cost, reverse thrust life, and inability to predict

Active Publication Date: 2018-06-12
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

On the one hand, the method of scanning electron microscope in-situ stretching and in-situ fatigue is relatively expensive, and on the other hand, this method can only infer the life through the fracture surface and cannot be predicted

Method used

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  • Method for predicting crack initiation life of high temperature alloy containing inclusion powder
  • Method for predicting crack initiation life of high temperature alloy containing inclusion powder
  • Method for predicting crack initiation life of high temperature alloy containing inclusion powder

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Embodiment

[0047] The component whose life expectancy is to be predicted is a flat-shaped component whose length and width are both 10 mm, and there is a circular aluminum oxide inclusion with a radius R of 100 microns in its center, and its geometric form is as follows: figure 2 shown. The component matrix material is FGH95 powder superalloy, its elastic modulus is E=193GPa, and Poisson’s ratio is 0.3; the central inclusion is set as a common alumina hard spherical inclusion in powder superalloy, and its elastic modulus is E 2 =400GPa, Poisson's ratio 0.3. Assuming that the member is subjected to far-field uniaxial tensile alternating loads, the maximum tensile strain is 0.8%, and the cycle characteristics are pulsating loads, that is, the maximum far-field tensile strain is 0.8%, and the minimum strain is 0.

[0048] 1. Define the damage variable field D(x i ,N):

[0049]

[0050] 2. Define the characteristic parameter Y as a function of the following strain components:

[0051...

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Abstract

The invention belongs to the technical field of life prediction, and relates to a method for predicting crack initiation life of a high temperature alloy containing inclusion powder. The method comprises the steps of defining a damage variable field D(xi, N) describing the crack initiation process around inclusions; defining a characterization parameter; defining a cyclic characteristic parameterR; defining a damage variable field rate equation; predicting the crack initiation life. The invention provides the method for predicting the crack initiation life of the high temperature alloy containing the inclusion powder, and the method can predict the service life of powder high temperature alloy parts, establish a fatigue failure performance criterion for the powder high temperature alloy parts, and further provide a basis for safety assessment during process of aeroengine component design.

Description

technical field [0001] The invention belongs to life prediction technology, and relates to a method for predicting the life of crack initiation of powder superalloy containing inclusions. Background technique [0002] The design and manufacture of aero-engines is the key technology of modern aircraft, and its development level represents the overall level of the national aviation industry. The turbine disk is a key component of an aero-engine, and it is subjected to high centrifugal load, thermal load, aerodynamic load, vibration load and corrosion and oxidation of the environmental medium during operation, and has strict requirements on material properties. Powdered superalloy is an ideal material for aero-engine turbine disks. It has excellent properties: fine powder, extremely fast cooling rate, uniform alloy composition, and no macro-segregation, so the performance of the part is stable and the thermal deformation performance is good. However, due to its process charact...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/17G06F30/23
Inventor 赵凯王依兵刘新灵徐元铭杨东有
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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