CN114912307A - High-cycle fatigue life prediction method for nickel-based single crystal superalloy - Google Patents

High-cycle fatigue life prediction method for nickel-based single crystal superalloy Download PDF

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CN114912307A
CN114912307A CN202210368515.1A CN202210368515A CN114912307A CN 114912307 A CN114912307 A CN 114912307A CN 202210368515 A CN202210368515 A CN 202210368515A CN 114912307 A CN114912307 A CN 114912307A
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stress
single crystal
nickel
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赵子华
张平发
田兆
梁振宇
孟扬
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Abstract

The invention discloses a high cycle fatigue life prediction method of a nickel-based single crystal superalloy, which comprehensively considers the shape and position of a defect and the influence of a tip plasticity zone, constructs a D parameter which is composed of the shape factor and the position factor of the defect and considers the tip plasticity zone, and constructs a life prediction model according to the D parameter. The method can realize effective prediction of the high cycle fatigue life of the nickel-based single crystal superalloy containing the defects.

Description

High-cycle fatigue life prediction method for nickel-based single crystal superalloy
Technical Field
The invention belongs to the field of fatigue life prediction, and particularly relates to a high cycle fatigue life prediction method of a nickel-based single crystal superalloy.
Background
The nickel-based single crystal superalloy has the advantages of high-temperature strength, strong oxidation resistance, excellent fatigue resistance and the like, and is a main selected material for advanced aeroengine turbine blades. High cycle fatigue is a common failure mode during turbine blade service. Stress is concentrated at the cast defect of the nickel-based single crystal, and fatigue cracks are initiated at the defect.
The stress concentration degree at the defect is not only related to the size of the defect, but also related to the shape and the position to the surface of the defect, and according to the finite element analysis result, the closer to the surface, the more serious the stress concentration degree is for the same defect.
The defect may be considered a crack. When subjected to an applied load, the crack tip forms a plastic zone, and the presence of the plastic zone reduces the stiffness of the material, corresponding to the growth of the crack. Therefore, the plastic region needs to be taken into account when considering the effect of the defect size on the stress concentration level.
The prior model for predicting the high-cycle fatigue life of the nickel-based single crystal containing the defect only considers the influence of the size of the defect, so that a stress concentration parameter is constructed, the parameter reflects the influence of the shape, size, position and plastic region of the defect on the stress concentration degree of the defect, and the parameter is very meaningful for predicting the high-cycle fatigue life of the nickel-based single crystal containing the defect.
Disclosure of Invention
In order to achieve the above object, the present invention proposes a new parameter D and uses the parameter for life prediction. The parameters comprehensively consider the influences of the shape, size and position of the defect and also consider the influence of the plastic zone of the crack tip. The invention adopts the following technical scheme:
a method for predicting the high-cycle fatigue life of a nickel-based single crystal superalloy is based on a D parameter, wherein the expression of the D parameter is as follows:
Figure BDA0003582990230000021
wherein L is a positional stress intensity factor, S is a roundness-constituting shape factor, a is a defect size, and σ is y For yield strength, σ is the stress.
Further, the method comprises the following steps:
(1) carrying out a high-cycle fatigue test to obtain the service life, the stress and a fracture;
(2) measuring a defect area of a crack initiation defect defect Defect perimeter C defect Defect size a, defect-to-surface distance d defect Fracture diameter d;
(3) determining the stress intensity factors L and d of the position by finite element analysis defect The relation of/d:
L＝f(d defect /d)；
(4) construction of roundness composition shape factor S:
Figure BDA0003582990230000022
(5) constructing a D parameter according to the steps (1) to (4);
(6) and establishing a service life prediction model according to the parameter D.
Further, the life prediction model is as follows:
lgN f ＝α-βlg(I)
Figure BDA0003582990230000023
ΔD＝D max -D min
Figure BDA0003582990230000024
in the formula, N f Fatigue life is considered; sigma max Maximum tensile stress; sigma min Is the minimum tensile stress; when the stress is negative, σ min ＝0；ΔD th Represents the minimum value among the values of the Δ D parameters of each specimen, Δ σ ═ σ ∑ σ max -σ min And alpha and beta are fitting parameters.
Compared with the prior art, the invention has the beneficial effects that:
aiming at the problem of predicting the high-cycle fatigue life of the nickel-based single crystal, the invention provides a new life prediction parameter D, which considers the influences of the shape, the position and the plastic zone of the defect, establishes a life prediction model according to the parameter and realizes the effective prediction of the low-cycle fatigue life of the nickel-based single crystal.
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FIG. 1 shows [001] oriented high cycle fatigue fracture of DD6 Ni-based single crystal superalloy at 850 ℃;
FIG. 2 is a comparison of the predicted life and the test life of the DD6 Ni-based single crystal superalloy with high cycle fatigue at 850 ℃ according to the method of the present invention.
Detailed Description
The idea, specific structure and technical effects of the present invention will be described clearly and completely with reference to the following embodiments, so as to fully understand the objects, features and effects of the present invention.
A method for predicting the high cycle fatigue life of a nickel-based single crystal superalloy adopts the following technical scheme:
firstly, the defect can be regarded as a crack, and according to the principle of fracture mechanics, the tip of the crack has a plastic zone, and the presence of the plastic zone reduces the rigidity of the material, so that the crack needs to be equivalently increased in length by an amount r y Comprises the following steps:
Figure BDA0003582990230000031
wherein σ y For yield strength, K is the stress intensity factor, which is expressed as:
Figure BDA0003582990230000032
where Y is the geometry factor, σ is the stress, and a is the defect size.
According to the formulas (1) and (2), the following can be obtained:
Figure BDA0003582990230000033
secondly, there is a stress concentration near the defect, and the degree of stress concentration is related to the shape of the defect. Thus, the roundness is used to form the shape factor, as shown in equation (4):
Figure BDA0003582990230000041
wherein S is a roundness-forming form factor, area defect Is a defect area, C defect The defect perimeter.
Furthermore, the stress concentration level near the defect is also related to the position of the defect. The defect position characteristic is represented by the ratio of the distance from the defect to the surface to the diameter of the fracture, and the mathematical relationship between the stress concentration coefficient and the distance from the defect to the edge of the fracture is determined through finite element analysis, so as to obtain an expression of a position stress intensity factor L (namely the stress concentration coefficient at the defect), as shown in formula (5):
L＝f(d defect /d) (5)
wherein L is the position stress intensity factor, d defect D is the fracture diameter for the defect-to-surface distance.
Introducing the roundness forming shape factor S and the position stress intensity factor L to substitute Y in the formula (3), a new stress intensity factor expression can be obtained, namely, the parameter D:
Figure BDA0003582990230000042
the specific implementation steps are as follows:
the first step is as follows: designing and processing a high cycle fatigue test piece, and testing under different stress levels to obtain fatigue data and fractures of the test piece.
The second step: measuring area of defect causing crack initiation defect Circumference C defect Dimension a, defect-to-surface distance d defect And a fracture diameter d. The definition of defect size here is: the maximum value of the distance between any two points in the defect.
The third step: determining a position stress intensity factor L and a defect-to-surface distance d by finite element analysis defect And a mathematical relationship between the fracture diameter d.
The fourth step: the parameters D of each test piece were calculated as described above.
The fifth step: and (4) constructing a service life prediction model by using the parameter D obtained by calculation in the step four, thereby predicting the high cycle fatigue life.
Example one
Taking 850 ℃ 001 oriented nickel-based single crystal superalloy DD6 as an example, the specific application process of the invention is as follows:
(1) the [001] oriented nickel-based single crystal superalloy DD6 fatigue test is carried out at 850 ℃, the test loads are 900MPa, 800MPa, 850MPa, 680MPa, 675MPa, 600MPa, 580MPa and 575MPa respectively, and the stress ratio is 0.05. The test results are shown in table 1.
TABLE 1 fatigue test results
Figure BDA0003582990230000051
(2) And acquiring a macroscopic image of the fracture and the microscopic morphology of the defect at the crack initiation part by a scanning electron microscope, such as the image shown in FIG. 1. The perimeter, area and length of the fracture source region defect, the distance from the fracture source region defect to the surface and the diameter of the fracture of different test pieces are measured, and the test results are shown in table 2.
TABLE 2 fracture measurement results
Figure BDA0003582990230000052
Figure BDA0003582990230000061
(3) Through finite element analysis, the relation between the stress intensity factor L of the position and the defect position is determined as follows:
Figure BDA0003582990230000062
(4) and calculating the parameter D of each test piece. The results are shown in Table 3.
TABLE 3 results of parameter calculation
Figure BDA0003582990230000063
(5) And constructing a life prediction model.
Based on the parameter D, the following life prediction model is constructed here
lgN f ＝α-βlg(I) (10)
Figure BDA0003582990230000064
Figure BDA0003582990230000071
In the formula, N f Fatigue life is considered; sigma max Maximum tensile stress; sigma min Is the minimum tensile stress; when the stress is negative, σ min ＝0；ΔD th Represents the minimum value among the values of the Δ D parameter of each sample, Δ σ ═ σ max -σ min And alpha and beta are fitting parameters.
The predicted fatigue life and actual fatigue life ratio is shown in fig. 2, and it can be seen that the predicted life is basically within a triple line, and has higher precision, which indicates that it is effective to construct a life prediction model through the D parameter.
The above description is only exemplary of the present invention and should not be taken as limiting the scope of the present invention, and any modifications, equivalents, improvements and the like that are within the spirit and principle of the present invention should be included in the scope of the present invention.

Claims (3)

1. A method for predicting the high-cycle fatigue life of a nickel-based single crystal superalloy is characterized in that the method for predicting the life is based on a D parameter, and the expression of the D parameter is as follows:
Figure FDA0003582990220000011
wherein L is a positional stress intensity factor, S is a roundness-constituting shape factor, a is a defect size, and σ is y For yield strength, σ is the stress.
2. The method for predicting the high cycle fatigue life of the nickel-based single crystal superalloy as claimed in claim 1, comprising the steps of:
(1) carrying out a high-cycle fatigue test to obtain the service life, the stress and a fracture;
(2) measuring a defect area of a crack initiation defect defect Perimeter of defect C de f ect Defect size a, defect-to-surface distance d defect Fracture diameter d;
(3) determining the stress intensity factors L and d of the position by finite element analysis defect The relation of/d:
L＝f(d defect /d)；
(4) construction of roundness composition shape factor S:
Figure FDA0003582990220000012
(5) constructing a D parameter according to the steps (1) to (4);
(6) and establishing a service life prediction model according to the parameter D.
3. The method for predicting the high cycle fatigue life of the nickel-based single crystal superalloy according to claim 2, wherein the life prediction model is:
lgN f ＝α-β1g(I)
Figure FDA0003582990220000013
ΔD＝D max -D min
Figure FDA0003582990220000014
in the formula, N f Fatigue life is considered; sigma max Maximum tensile stress; sigma min Is the minimum tensile stress; when the stress is negative, σ min ＝0；ΔD th Represents the minimum value among the values of the Δ D parameters of each specimen, Δ σ ═ σ ∑ σ max -σ min And alpha and beta are fitting parameters.
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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117556569A (en) * 2024-01-11 2024-02-13 中国航发四川燃气涡轮研究院 Single crystal blade thermal-mechanical fatigue prediction method considering crystal orientation deflection angle
CN118533463A (en) * 2024-07-24 2024-08-23 中国航发湖南动力机械研究所 Nickel-based superalloy dirty white spot defect damage tolerance design method
CN118533463B (en) * 2024-07-24 2024-11-05 中国航发湖南动力机械研究所 Nickel-based superalloy dirty white spot defect damage tolerance design method

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117556569A (en) * 2024-01-11 2024-02-13 中国航发四川燃气涡轮研究院 Single crystal blade thermal-mechanical fatigue prediction method considering crystal orientation deflection angle
CN117556569B (en) * 2024-01-11 2024-03-19 中国航发四川燃气涡轮研究院 Single crystal blade thermal-mechanical fatigue prediction method considering crystal orientation deflection angle
CN118533463A (en) * 2024-07-24 2024-08-23 中国航发湖南动力机械研究所 Nickel-based superalloy dirty white spot defect damage tolerance design method
CN118533463B (en) * 2024-07-24 2024-11-05 中国航发湖南动力机械研究所 Nickel-based superalloy dirty white spot defect damage tolerance design method

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