CN112697691A - Research method for corrosion damage distribution rule of aviation alloy steel in service environment - Google Patents
Research method for corrosion damage distribution rule of aviation alloy steel in service environment Download PDFInfo
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Abstract
The invention discloses a research method for corrosion damage distribution rule of aviation alloy steel in service environment, which comprises the following steps of S1: aiming at the characteristics of an alloy steel material blade material of an aircraft engine compressor and a specific airport environment, designing an accelerated corrosion test scheme, and carrying out accelerated corrosion tests of different equivalent calendar years on an alloy steel material test piece; s2: after accelerated corrosion of each equivalent calendar year, detecting and photographing corrosion damage of each test piece to obtain a macroscopic corrosion image of each test piece; s3: qualitatively describing and analyzing the appearance corrosion condition of the test piece after accelerated corrosion; s4: and constructing an evolution model of the corrosion damage appearance of the alloy steel material of the air compressor of the aircraft engine, and carrying out quantitative statistics and analysis on the corrosion damage parameters of the test piece after accelerated corrosion of different equivalent calendar years. The research method can accurately predict and evaluate the corrosion evolution law of the aero-engine compressor blade in a specific service environment.
Description
Technical Field
The invention relates to the technical field of corrosion damage of aviation alloy steel, in particular to a research method of a corrosion damage distribution rule of aviation alloy steel in a service environment.
Background
As the corrosion has great influence on the service life of the aviation equipment, the foreign developed aviation countries attach high importance to the influence of environmental factors on the corrosion of the aviation equipment and develop targeted research earlier. The study of aeronautical equipment corrosion and fatigue corrosion in countries such as the united kingdom, the united states, australia and the north atlantic convention group has been beginning in succession from the last 60 years.
After the seventies of the last century in China, because flight accidents caused by corrosion occur successively in relevant models of air force in China, the national aviation industry only starts to pay attention to the corrosion problem of aviation equipment, and then relevant researches on the corrosion, corrosion fatigue, service life and the like of the aviation equipment are carried out. However, due to the lack of systematic knowledge of the problems of corrosion of aviation equipment and service life of the equipment, and the lack of relevant literature, domestic research is in a more advanced stage. The problem continues to the eighties, and under the promotion of the pre-research topic of the air weight point and the requirements of related models, the related aviation academies in China carry out extensive research on the aspects of aircraft structure corrosion resistance design technology, environment spectrum and load/environment spectrum compiling technology, accelerated test environment spectrum compiling and accelerated test technology, calendar life evaluation technology and the like in sequence, and certain progress is made. However, for the current related research work, many problems in the basic research aspect of China still need to be solved urgently, and some students utilize the existing data to compile an environment spectrum and develop an acceleration test, but because the exposure corrosion result of the blade test piece is too little, the test result is too different from the natural corrosion result, the corrosion condition of the test piece in the natural environment cannot be accurately reflected, the accurate corrosion damage kinetic rule of the aviation equipment under the service condition cannot be established, and further the accurate prediction and evaluation on the corrosion evolution rule of the aircraft structural part in the real service environment cannot be made.
Disclosure of Invention
Aiming at the existing problems, the invention aims to provide a method for researching the corrosion damage distribution rule of an aviation alloy steel in a service environment, an accelerated corrosion test scheme is designed according to the characteristics of aviation alloy steel materials and specific service airport environments thereof, an accelerated corrosion test is carried out on an alloy steel material test piece of an aviation engine compressor blade, corrosion damage data is detected, research on the distribution rule is carried out according to the damage data obtained by detection, and therefore, accurate prediction and evaluation are carried out on the corrosion evolution rule of the aviation engine compressor blade in the real service environment.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
a research method for corrosion damage distribution rule of aviation alloy steel service environment is characterized by comprising the following steps,
s1: aiming at the characteristics of an alloy steel material blade material of an aircraft engine compressor and a specific airport environment, designing an accelerated corrosion test scheme, and carrying out accelerated corrosion tests of different equivalent calendar years on an alloy steel material test piece;
s2: after accelerated corrosion of each equivalent calendar year, detecting and photographing corrosion damage of each test piece to obtain a macroscopic corrosion image of each test piece;
s3: qualitatively describing and analyzing the appearance corrosion condition of the test piece after accelerated corrosion;
s4: and constructing a corrosion damage evolution model of the alloy steel material of the air compressor of the aircraft engine, and carrying out quantitative statistics and analysis on corrosion parameters of the test piece after accelerated corrosion in calendar years with different equivalent weights.
Further, the specific operation of step S1 includes the following steps,
s101: calculating action strength and action rule of typical environmental factors according to subsequent service environment of equipment equipped on alloy steel material blades of an aircraft engine compressor, on the basis, selecting typical strong corrosion environmental factors according to a corrosion damage equivalent conversion relation theory and an implementation method of test piece materials and the like, and designing and constructing a laboratory simulation accelerated corrosion test scheme of the test piece materials; the alloy steel material of the aero-engine compressor is 1Cr11Ni2W2Mov forged stator blade material;
s102: grouping, numbering and preprocessing the test pieces;
s103: constructing an accelerated corrosion test environment;
s104: and (4) carrying out accelerated corrosion on the test pieces of different groups in different equivalent calendar years according to the accelerated corrosion test scheme of the step (S101).
Further, the specific operation of constructing the accelerated corrosion test environment in step S103 includes the following steps,
s1031: preparing a NaCl solution with the concentration of 5% by using 95 parts of distilled water and 5 parts of NaCl (analytically pure);
s1032: adding a proper amount of dilute H2SO4The pH of the etching solution was adjusted to 4.0 ± 0.2.
Further, the specific operation of step S4 includes the following steps,
s401: selecting an erosion parameter for defining erosion damage;
s402: constructing a corrosion damage morphology evolution model of an alloy steel material of an aircraft engine compressor, and obtaining a quantitative relation between corrosion parameters by the corrosion damage morphology evolution model;
s403: acquiring corrosion parameter data;
s404: according to a statistical analysis method, the distribution conditions of the corrosion parameters under the same corrosion age in different distribution forms are contrastively analyzed, and the dynamic law of the corrosion parameters is analyzed.
Further, the erosion parameters used to define the erosion damage in step S401 include the length, width and depth of the erosion damage surface.
Further, the corrosion damage shape evolution model in the step S402 includes a hemispherical damage model and a semi-ellipsoidal damage model.
Further, the specific operation of establishing the corrosion damage morphology evolution model in step S402 includes the following steps,
s4021: the nature of the initiation and the expansion of the corrosion damage of the alloy steel material is random process behavior, the process follows Faraday's law and combines with the Archimedes formula, and the pitting expansion model can be obtained as
In the formula, V represents pitting damage volume, t represents pitting period and is a time unit; m is atomic weight, IpDenotes the current density in the electrochemical process of pitting corrosion, IpoRepresents the current density constant in the electrochemical process of pitting corrosion; n is the valence, F is the Faraday constant, p is the material density, EaRepresents activation energy, R is an ideal gas constant, and T is absolute temperature;
s4022: establishing a hemispheroidal damage model with an evolving corrosion damage morphology
Wherein a represents a damage radius of the corrosion damage, then
S4023: to pair
Integrating to obtain the relation of the damage radius of the corrosion damage hemisphere damage model along with the change of the corrosion period
In the formula, a0The size of damage nucleation representing corrosion damage is related to the microstructure of the material and is usually between 5 and 10 mu m;
s4024: establishing a semi-ellipsoid damage model of corrosion damage morphology evolution
In the formula, w, l and h respectively represent short axis, long axis and depth damage parameters of the damaged surface of the corrosion damage;
s4025: as the fractal characteristics of the damage three-dimensional morphology parameters of the corrosion damage gradually appear in the expansion process, the proportion relation between the damage three-dimensional morphology parameters can be deduced to gradually trend towards a fixed value, so that
h/l＝ε，εIf greater than 0, then
h＝lε；
S4026: when the three corrosion parameters of the corrosion damage are different, substituting the two equations in the step S5025 into
In (1) obtaining
S4027: in pair type
Integrating to obtain an evolution rule of a corrosion parameter l of the corrosion damage;
s4028: to pair
h/l is equal to epsilon, epsilon is more than 0, and the steps S5026 and S5027 are repeated, so that the evolution law of the corrosion parameters w and h of the corrosion damage can be obtained;
s4029: when two of the three corrosion parameters of the corrosion damage are the same, assuming that w is h, the two parameters are the same
Integrating the parameters to obtain an evolution rule of a corrosion parameter l of the corrosion damage; and obtaining the evolution law of the corrosion parameters w and h of the corrosion damage in the same way.
Further, the distribution form described in step S404 includes a normal distribution, a Gumbel distribution, a Weibull distribution, and a lognormal distribution.
Further, when the depth of the damaged surface follows Gumbel distribution, the probability distribution density function is
A distribution function of
Then
Wherein D is a random variable of the maximum erosion depth; p (D is less than or equal to D)m) The maximum depth of corrosion does not exceed the value DmThe probability of (d); μ and σ are the location and scale parameters, respectively;
when the depth of the damaged surface follows normal distribution, the probability density function is
A distribution function of
Then
Where μ "is the average of the maximum etch depths over all etch regions; sigma2Is the variance;
when the depth of the damaged surface obeys the two-parameter Weibull distribution, the probability density function is
A distribution function of
Then
Wherein m is a shape parameter, a is a scale parameter,
is a true scale parameter;
when the depth of the damage surface follows the log normal distribution, the size of the corrosion damage is logarithmically lg D, and X is lgD, the probability density function is
A distribution function of
Then
In the formula, sigma 'and mu' are respectively the variance and mean value of the corrosion depth after logarithm;
and according to the quantitative relation among the corrosion parameters obtained in the step S402, further obtaining a probability density function and a distribution function when the length and the width of the corrosion damage surface obey normal distribution, Gumbel distribution, Weibull distribution and lognormal distribution.
Further, the specific operation of analyzing the dynamics of the corrosion parameter in step S404 includes,
s4041: arranging the actual measured values of the corrosion depth in the order from small to large, wherein the No. 1 value is the minimum measured value D of the corrosion depth1The measured value of the corrosion depth of No. i is DiStatistical probability P of No. i dataiIs shown as
Wherein i is 1, 2, 3, …, N, N is the number of the measured values of the corrosion depth;
s4042: respectively calculating the corrosion depth corresponding to Gumbel, normal, lognormal and Weibull distribution
And ln Di；
S4043: according to the calculation result of the step S5042, by utilizing Origin graphic tool software, Gumbel, normal, lognormal and Weibull distribution fitting is adopted for testing;
s4044: carrying out statistical analysis on the corrosion depths under different corrosion years to finally obtain the overall change trend of the corrosion depth of the test piece along with the increase of the corrosion equivalent years;
s4045: and (4) repeating the steps S4041-S4044 according to the quantitative relation among the corrosion parameters to obtain the overall change trend of the length and the width of the corrosion damage surface of the test piece along with the increase of the corrosion equivalent age.
The invention has the beneficial effects that:
according to the service environment of the aero-engine compressor blade, the service environment spectrum is compiled, on the basis, according to a corrosion damage equivalent conversion relation theory and an implementation method, a laboratory simulation accelerated corrosion test environment spectrum of the engine compressor blade material is compiled, according to the accelerated corrosion test environment spectrum, a simulation accelerated corrosion test is developed and corrosion damage data are detected, according to the corrosion damage data obtained through detection, research on the distribution rule is developed, and finally the corrosion damage distribution rule of a 1Cr11Ni2W2Mov forged piece stator blade test piece in the service environment is obtained and better accords with Gumbel distribution.
Drawings
FIG. 1 is an original shape of a 1Cr11Ni2W2Mov stator blade in the invention;
FIG. 2 is an environmental spectrum of an accelerated corrosion test of a stator blade of a 1Cr11Ni2W2Mov forged piece in the invention;
FIG. 3 is an appearance diagram of 1 equivalent corrosion age in group 1 corrosion test of a 1Cr11Ni2W2Mov forged stator blade in the invention;
FIG. 4 is an appearance diagram of 1 equivalent corrosion age in group 2 corrosion test of 1Cr11Ni2W2Mov forged stator blade in the invention;
FIG. 5 is an appearance diagram of 1 equivalent corrosion age in group 3 corrosion test of 1Cr11Ni2W2Mov forged stator blade in the invention;
FIG. 6 is an appearance diagram of 1 equivalent corrosion age in group 4 corrosion test of 1Cr11Ni2W2Mov forged stator blade in the invention;
FIG. 7 is an appearance diagram of 1 equivalent corrosion age in group 5 corrosion test of a 1Cr11Ni2W2Mov forged stator blade in the invention;
FIG. 8 is an appearance diagram of the 1 equivalent corrosion age of the 6 th group corrosion test of the 1Cr11Ni2W2Mov forged stator blade in the invention;
FIG. 9 is an appearance diagram of 1 equivalent corrosion age in group 7 corrosion test of 1Cr11Ni2W2Mov forged stator blade in the invention;
FIG. 10 is an appearance diagram of 1 equivalent corrosion age in group 8 corrosion test of 1Cr11Ni2W2Mov forged stator blade in the invention;
FIG. 11 is an appearance diagram of the 1 equivalent corrosion age of the 9 th group of corrosion tests of the 1Cr11Ni2W2Mov forged stator blade in the invention;
FIG. 12 is an appearance diagram of the 10 th group of 1Cr11Ni2W2Mov forged stator blades in the corrosion test with 1 equivalent corrosion age in the invention;
FIG. 13 is a schematic diagram illustrating the definition of parameters of pitting topography in accordance with the present invention;
FIG. 14 is a microscopic measurement of corrosion damage depth according to the present invention;
FIG. 15 is a graph showing a distribution rule of corrosion depth at 3 years of accelerated corrosion in the present invention;
FIG. 16 is a diagram illustrating a distribution rule of corrosion depth in 6 years of accelerated corrosion according to the present invention;
FIG. 17 is a graph showing a distribution rule of corrosion depth in 10 years of accelerated corrosion according to the present invention;
FIG. 18 is a graph showing correlation coefficients of corrosion depth at different corrosion ages according to the present invention;
FIG. 19 is a graph of etch depth versus etch time in accordance with the present invention;
FIG. 20 is a graph showing correlation coefficients of surface length parameters of corrosion damage in different corrosion periods according to the present invention.
Detailed Description
In order to make those skilled in the art better understand the technical solution of the present invention, the following further describes the technical solution of the present invention with reference to the drawings and the embodiments.
A method for researching a corrosion damage distribution rule of an aviation alloy steel in a service environment comprises the following steps,
s1: aiming at the characteristics of an alloy steel material blade material of an aircraft engine compressor and a specific airport environment, designing an accelerated corrosion test scheme, and carrying out accelerated corrosion tests of different equivalent calendar years on an alloy steel material test piece;
specifically, S101: calculating action strength and action rule of typical environmental factors according to subsequent service environment of equipment equipped on alloy steel material blades of an aircraft engine compressor, on the basis, selecting typical strong corrosion environmental factors according to a corrosion damage equivalent conversion relation theory and an implementation method of test piece materials and the like, and designing and constructing a laboratory simulation accelerated corrosion test scheme of the test piece materials;
the test piece adopted in the invention is a 1Cr11Ni2W2Mov forged stator blade test piece of an aeroengine, the detailed conditions are shown in the following table 1, the original morphology is shown in the attached drawing 1, and the accelerated corrosion test environment spectrum is shown in the attached drawing 2.
TABLE 1 details of the blade test piece
| Name (R) | Heat treatment process | Number of pieces | Remarks for note |
| 1Cr11Ni2W2Mov | Forging piece | 88 | Stator blade |
S102: grouping, numbering and preprocessing the test pieces;
the 88 test pieces are randomly and evenly divided into 11 groups of 8 test pieces, and the number in each group is 01-08. The equivalent corrosion years of 1Cr11Ni2W2Mov stator blades are respectively represented by two digits from 00 to 10, the number of a specific blade test piece under the equivalent corrosion years is represented by 01 to 08, 05 to 06 represent the number 6 blade test piece under the 5 th equivalent corrosion year, and the like.
The pretreatment comprises the steps of checking the appearance and the appearance of a test piece, photographing and checking whether the original state of the surface of the test piece has no damage (including whether a coating is foamed, wrinkled, peeled and cracked; loosened, deformed, cracked and the like).
Carefully removing oil stains on the surface of the test piece, scrubbing the test piece by using gasoline, washing the test piece twice by using absolute ethyl alcohol after drying, washing the test piece by using distilled water or deionized water, washing the test piece by using a drying oven or naturally drying the test piece in the air, and taking a picture of the appearance of the test piece. The blade test piece is not allowed to be immersed into the solution in advance before the test is started, and the test is not allowed to be carried out on non-homogeneous materials and non-homogeneous coatings in the same tank solution. The test pieces are vertically hung on a test bracket of the periodic infiltration environment test box by nylon wires, and the test pieces are ensured not to be contacted or covered with each other and other metals and water-absorbing materials, so that the contact corrosion which is not required by the test is prevented from occurring.
S103: constructing an accelerated corrosion test environment;
specifically, the accelerated corrosion solution is a NaCl solution with a pH value of 4.0 +/-0.2 and a concentration of 5%, and the preparation method comprises the following steps:
s1031: preparing a NaCl solution with the concentration of 5% by using 95 parts of distilled water and 5 parts of NaCl (analytically pure);
s1032: adding a proper amount of dilute H2SO4The pH of the etching solution was adjusted to 4.0 ± 0.2.
S104: and (4) carrying out accelerated corrosion on the test pieces of different groups in different equivalent calendar years according to the accelerated corrosion test scheme of the step (S101).
Specifically, the alloy steel test pieces were subjected to dry-wet alternation 335 times under the environmental spectrum conditions as shown in fig. 2, wherein each time of soaking is 1.82 minutes, baking is 10.47 minutes, and the corrosion test time of each accelerated corrosion is 68.61 hours for 1 year. The method comprises the steps of respectively carrying out accelerated corrosion tests of 1-10 equivalent corrosion years on 10 grouped 1Cr11Ni2W2Mov stator blades (the 0 th group does not carry out corrosion tests and is a control group), carrying out 1 equivalent corrosion year test on the 1 st group of blade test pieces, carrying out 2 equivalent corrosion year tests on the 2 nd group of blade test pieces, and so on until the 10 th group of blade test pieces carry out 10 equivalent corrosion year tests.
Further, step S2: after accelerated corrosion of each equivalent calendar year, detecting and photographing corrosion damage of each test piece to obtain a macroscopic corrosion image of each test piece;
specifically, after each corrosion test period is finished, according to the requirements of GB/T16545-2015, if corrosion exists and the corrosion is slight, the test piece is slightly mechanically cleaned by a soft brush in running water to remove corrosion products which are not firmly adhered or loose; if the corrosion depth of the blade test piece is larger, the corrosion products are more, the adhesive force is strong, and the corrosion products are difficult to remove by a simple cleaning method, the following method can be adopted for treatment: soaking the fabric in concentrated nitric acid (HNO3) with the concentration of 40 percent for 1 minute at the temperature of between 20 and 25 ℃, then brushing the fabric by using a soft brush and washing the fabric by using deionized water;
after each equivalent corrosion age, firstly observing and quantitatively detecting the shape and size of corrosion damage of each blade test piece, and photographing and storing.
Further, step S3: qualitatively describing and analyzing the appearance corrosion condition of the test piece after accelerated corrosion;
specifically, when the corrosion time limit of equivalent 1 equivalent is reached according to the compiled accelerated corrosion test environment spectrum test, the statistics of the appearance corrosion conditions of the blade test piece are shown in the following table 2 and attached figures 3-12.
TABLE 2 Corrosion appearance statistics for 1 equivalent corrosion year of accelerated corrosion test on blade specimens
From the corrosion test result of 1 equivalent corrosion year of the above test piece, the blade surface body basically has no corrosion, only a part of the test piece is distributed with more disperse tawny rust and a small amount of spots, and a certain rust exists in a certain test piece. The reason is that the surface of the blade test piece is contacted with tenons of other blades due to improper protection measures (a plurality of test pieces are in the same packaging bag) in the transportation process of the blade, the initial state of the surface is damaged, partial regions are scratched, metal matrixes in the scratched regions are exposed and are easy to rust, and for example, corrosion damage positions with deep colors can be obviously seen from the blade test pieces such as 01-08, 02-06 and 04-02.
And when the corrosion time of the blade test piece is 1 equivalent, the appearance corrosion condition of the blade test piece is counted in a mode of counting the appearance corrosion condition of the blade test piece when the corrosion time of the blade test piece is 2-10 equivalent.
Further, step S4: and constructing a corrosion damage evolution model of the alloy steel material of the air compressor of the aircraft engine, and carrying out quantitative statistics and analysis on corrosion parameters of the test piece after accelerated corrosion in calendar years with different equivalent weights.
Specifically, S401: selecting an erosion parameter for defining erosion damage;
usually, three shape parameters of the length, width and depth of the surface of the corrosion damage are adopted to define the corrosion damage, and each parameter is specifically defined as: defining the maximum dimension of the damage surface parallel to the axial direction of the test piece as the damage length, and expressing the maximum dimension as L; the maximum dimension of the damage surface perpendicular to the axial direction of the test piece is defined as the damage width and is represented by W; the maximum size of the damage that develops perpendicular to the surface of the test piece to the depth of the test piece is defined as the depth of the damage, D, and the units of 3 parameters are μm, and the corrosion damage is defined as shown in fig. 13.
S402: constructing a corrosion damage morphology evolution model of an alloy steel material of an aircraft engine compressor, and obtaining a quantitative relation between corrosion parameters by the corrosion damage morphology evolution model; the corrosion damage shape evolution model comprises a semi-sphere damage model and a semi-ellipsoid damage model.
Specifically, S4021: the nature of the initiation and the expansion of the corrosion damage of the alloy steel material is random process behavior, the process follows Faraday's law and combines with the Archimedes formula, and the pitting expansion model can be obtained as
In the formula, V represents pitting damage volume, t represents pitting period and is a time unit; m is atomic weight, IpDenotes the current density in the electrochemical process of pitting corrosion, IpoRepresents the current density constant in the electrochemical process of pitting corrosion; n is the valence, F is the Faraday constant, p is the material density, EaRepresents activation energy, R is an ideal gas constant, and T is absolute temperature;
s4022: establishing a hemispheroidal damage model with an evolving corrosion damage morphology
Wherein a represents a damage radius of the corrosion damage, then
S4023: to pair
Integrating to obtain the relation of the damage radius of the corrosion damage hemisphere damage model along with the change of the corrosion period
In the formula, a0The size of damage nucleation representing corrosion damage is related to the microstructure of the material and is usually between 5 and 10 mu m;
s4024: establishing a semi-ellipsoid damage model of corrosion damage morphology evolution
In the formula, w, l and h respectively represent short axis, long axis and depth damage parameters of the damaged surface of the corrosion damage;
s4025: as the fractal characteristics of the damage three-dimensional morphology parameters of the corrosion damage gradually appear in the expansion process, the proportion relation between the damage three-dimensional morphology parameters can be deduced to gradually trend towards a fixed value, so that
If h/l is equal to epsilon, epsilon is more than 0, then
h＝lε
S4026: when corrosion damagesWhen the corrosion parameters are different from each other, the two equations in step S5025 are substituted
In (1) obtaining
S4027: in pair type
Integrating to obtain an evolution rule of a corrosion parameter l of the corrosion damage;
s4028: to pair
h/l is equal to epsilon, epsilon is more than 0, and the steps S5026 and S5027 are repeated, so that the evolution law of the corrosion parameters w and h of the corrosion damage can be obtained;
s4029: when two of the three corrosion parameters of the corrosion damage are the same, assuming that w is h, the two parameters are the same
Integrating the parameters to obtain an evolution rule of a corrosion parameter l of the corrosion damage; and obtaining the evolution law of the corrosion parameters w and h of the corrosion damage in the same way.
Further, step S403: acquiring corrosion parameter data;
specifically, the erosion damage morphology parameter data of the erosion blade test piece under different equivalent erosion years are obtained through observation and measurement by adopting a Cochstmad microscope, and in the method, the erosion damage depth is selected as a research object for explanation (the research methods of the length and the width are completely the same).
The measured corrosion damage depth parameter data under typical cycle is shown in the following tables 3-6. The microscopic measurement is shown in FIG. 14.
TABLE 3 blade equivalent accelerated corrosion 7 years corrosion damage measurement data
| Serial number | Di(μm) | Serial number | Di(μm) | Serial number | Di(μm) | Serial number | Di(μm) |
| 1 | 48.294 | 6 | 83.799 | 11 | 96.818 | 16 | 132.28 |
| 2 | 69.822 | 7 | 88.067 | 12 | 97.585 | 17 | 141.436 |
| 3 | 70.933 | 8 | 90.729 | 13 | 117.524 | 18 | 144.515 |
| 4 | 72.766 | 9 | 91.421 | 14 | 117.984 | 19 | 159.542 |
| 5 | 80.341 | 10 | 96.615 | 15 | 118.047 | 20 | 161.931 |
TABLE 4 blade equivalent accelerated corrosion 8 years corrosion damage measurement data
| Serial number | Di(μm) | Serial number | Di(μm) | Serial number | Di(μm) | Serial number | Di(μm) |
| 1 | 26.374 | 6 | 111.413 | 11 | 144.365 | 16 | 181.127 |
| 2 | 70.927 | 7 | 113.395 | 12 | 152.135 | 17 | 182.894 |
| 3 | 71.613 | 8 | 120.691 | 13 | 152.182 | 18 | 225.911 |
| 4 | 95.298 | 9 | 126.527 | 14 | 155.828 | 19 | 252.252 |
| 5 | 101.246 | 10 | 137.883 | 15 | 159.21 | 20 | 252.534 |
TABLE 5 blade equivalent accelerated corrosion Corrosion Damage measurement data at 9 years
| Serial number | Di(μm) | Serial number | Di(μm) | Serial number | Di(μm) | Serial number | Di(μm) |
| 1 | 83.547 | 6 | 102.41 | 11 | 137.686 | 16 | 182.063 |
| 2 | 86.453 | 7 | 108.421 | 12 | 143.268 | 17 | 185.97 |
| 3 | 89.327 | 8 | 117.951 | 13 | 165.617 | 18 | 197.914 |
| 4 | 92.291 | 9 | 129.021 | 14 | 174.676 | 19 | 225.473 |
| 5 | 93.861 | 10 | 135.706 | 15 | 178.106 | 20 | 259.378 |
TABLE 6 blade equivalent accelerated corrosion 10 years corrosion damage measurement data
| Serial number | Di(μm) | Serial number | Di(μm) | Serial number | Di(μm) | Serial number | Di(μm) |
| 1 | 78.731 | 6 | 117.902 | 11 | 159.233 | 16 | 199.724 |
| 2 | 92.508 | 7 | 133.999 | 12 | 179.696 | 17 | 218.775 |
| 3 | 96.11 | 8 | 147.639 | 13 | 182.51 | 18 | 219.937 |
| 4 | 99.427 | 9 | 154.103 | 14 | 183.733 | 19 | 220.206 |
| 5 | 105.663 | 10 | 155.248 | 15 | 189.787 | 20 | 226.639 |
Further, step 4504: according to a statistical analysis method, the distribution conditions of the corrosion parameters under the same corrosion age in different distribution forms are contrastively analyzed, and the dynamic law of the corrosion parameters is analyzed.
Specifically, prior art studies have shown that the distribution patterns of the corrosion damage parameters of the aircraft alloy steel material include normal distribution, Gumbel distribution, Weibull distribution, and lognormal distribution.
In the present invention, the depth of the damaged surface is taken as an example, and the method of investigating the length and width of the etched surface is exactly the same as the method of investigating the depth of the damaged surface.
Specifically, when the depth of the damaged surface follows Gumbel distribution, the probability distribution density function is
A distribution function of
From the formula (2)
Wherein D is a random variable of the maximum erosion depth; p (D is less than or equal to D)m) The maximum depth of corrosion does not exceed the value DmThe probability of (d); μ and σ are the position and scale parameters, respectivelyCounting;
linear transformation of formula (3) can be obtained
Order to
Then equation (4) can be converted to Z ═ B · D + a (5)
In the formula (5), A and B are constants.
When the depth of the damaged surface follows normal distribution, the probability density function is
A distribution function of
Can be obtained by the following formula (7),
where μ "is the average of the maximum etch depths over all etch regions; sigma2Is the variance; since it is meaningless that the maximum corrosion depth is negative or + ∞, the lower limit of the integral variable is 0, the upper limit is the maximum corrosion depth possible for corrosion pits in the component, and the maximum value is the geometric thickness of the component.
Obtained by converting the formula (8)
Let Z equal phi-1[P(D≤Dm)]，
Then formula (9) can be changed to Z ═ B · D + a (10)
When the lesion surface depth follows a two-parameter Weibull distribution, the probability density function is
A distribution function of
It can be obtained from the formula (12),
wherein m is a shape parameter, a is a scale parameter,
is a true scale parameter;
linear transformation of formula (13) can be obtained
Order to
Then, the formula (14) can be converted to Z ═ B · ln (d) + a (15)
When the depth of the damage surface follows the log normal distribution, the size of the corrosion damage is logarithmically lg D, whether the variable lg D conforms to the normal distribution or not is verified, and X is enabled to be lg D (16)
The probability density function is
A distribution function of
It can be obtained from the formula (18),
obtained by converting the formula (19)
Let Z equal phi-1[P(X≤Xm)]，
Formula (20) can be converted to Z ═ B · X + a, i.e. Z ═ B · lg (d) + a (21)
Where σ 'and μ' are the variance and mean of the etch depth logarithmized, respectively.
The four distributed linear equations above are listed in table 7 below.
TABLE 7 Linear regression equation for each distribution
And according to the quantitative relation among the corrosion parameters obtained in the step S402, further obtaining a probability density function and a distribution function when the length and the width of the corrosion damage surface obey normal distribution, Gumbel distribution, Weibull distribution and lognormal distribution.
Furthermore, the specific operation of analyzing the dynamics of the corrosion parameters includes,
s4041: arranging the actual measured values of the corrosion depth in the order from small to large, wherein the No. 1 value is the minimum measured value D of the corrosion depth1The measured value of the corrosion depth of No. i is DiStatistical probability P of No. i dataiIs shown as
Wherein i is 1, 2, 3, …, N, N is the number of the measured values of the corrosion depth;
s4042: respectively calculating the corrosion depth corresponding to Gumbel, normal, lognormal and Weibull distribution
And ln Di；
S4043: according to the calculation result of the step S5042, by utilizing Origin graphic tool software, Gumbel, normal, lognormal and Weibull distribution fitting is adopted for testing;
s4044: and (4) carrying out statistical analysis on the corrosion depths under different corrosion years to finally obtain the overall change trend of the average corrosion depth of the test piece along with the increase of the corrosion equivalent years.
The statistical analysis is carried out on the corrosion damage surface depth under different corrosion years, the result is shown in the following table 8, the distribution test and linear equation are shown in the following table 9, the distribution rule test graphs of the corrosion depth when the corrosion is accelerated for 3 years, 6 years and 10 years are shown in attached figures 15-17, and the correlation coefficient graphs of different distributions are shown in attached figure 18.
TABLE 8 correlation coefficient of distribution form of erosion depth data
TABLE 9 distribution test and Linear equation
As can be seen from Table 8 and FIG. 18, the etch pit depths of the respective periods follow the four distributions of Gumbel, Normal, Weibull and lognormal, but the respective periods and the four distributions have slightly different functional dependencies. It can be seen from fig. 7-6 that the test pieces after the first cycle accelerated corrosion test and the four distribution functions all have poor correlations, and only the correlation between the first cycle pit depth and the Weibull distribution is better than the correlation between the other three distributions. The correlation coefficient between the cycle which is better in the correlation with other distributions except the Gumbel distribution and the Gumbel distribution is also larger in 5 cycles out of the last 9 cycles, and the corrosion pit depth distribution of the test piece is more consistent with the Gumbel distribution as a whole. As can be seen from tables 7 to 4, the standard deviation of the logarithmic distribution was the smallest in the 1 st to 5 th cycles and the 9 th cycle among the 10 th cycles of the test piece, and the standard deviation of the normal distribution was the smallest in the 6 th to 10 th cycles except the 9 th cycle.
According to the analysis, the numerical values of the 1Cr11Ni2W2MoV forged stator blade test piece in the statistical sense of the corrosion depth under each corrosion cycle are obtained, as shown in the table 10, and the change trend of the numerical values along with the corrosion equivalent age is shown in the attached figure 19.
TABLE 101 statistical data of corrosion damage depth of Cr11Ni2W2MoV stator blade
| Equivalent corrosion age (year) | Mean value of statistical significance (mum) |
| 2 | 117.5275 |
| 3 | 141.7718 |
| 4 | 152.7455 |
| 5 | 199.7479 |
| 6 | 199.28 |
| 7 | 231.4249 |
| 8 | 238.8028 |
| 9 | 270.1722 |
| 10 | 276.9336 |
As can be seen from fig. 19, the average value of the corrosion pit depth of the blade specimen increases linearly with the increase of the corrosion equivalent age, the fitting linear equation is D-20.45Y +80.5, and the correlation coefficient R-0.977. And after the 10 th period is finished, the average value of the corrosion depths obtained by measuring the individual corrosion damage depths of the surface of the test piece is about, so that the corrosion has certain influence on the surface state of the blade.
The definition of the length parameter and the width parameter of the corrosion damage surface has relative significance, and the numerical values of the length parameter and the width parameter of the corrosion damage surface have a proportional relation on the quantitative relation, so that the research on the distribution rule by selecting one of the length parameter and the width parameter is representative, and the two parameters do not need to be analyzed simultaneously. The distribution pattern of the length of the surface of the corrosion damage was investigated in the same manner as the depth of the surface of the corrosion damage, and the results are shown in table 11 below, and the distribution correlation coefficient distribution of the length parameter distribution of the surface of the corrosion damage at different corrosion ages is shown in fig. 20.
TABLE 11 correlation coefficient of parametric distribution of surface length of corrosion damage
The fitting of the normal distribution law over a typical age yields a linear equation as shown in table 12 below.
TABLE 12 distribution test and Linear equation
| Corrosion time/year | Fitted linear equation | Coefficient of correlation (R) |
| 6 | Z＝68.099·L-6.872 | 0.9878 |
| 7 | Z＝51.971·L-18.375 | 0.9918 |
| 8 | Z＝41.818·L-17.859 | 0.9835 |
| 9 | Z＝36.721·L-20.869 | 0.9965 |
| 10 | Z＝33.988·L-19.336 | 0.9917 |
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (10)
1. A research method for corrosion damage distribution rule of aviation alloy steel service environment is characterized by comprising the following steps,
s1: aiming at the characteristics of an alloy steel material blade material of an aircraft engine compressor and a specific airport environment, designing an accelerated corrosion test scheme, and carrying out accelerated corrosion tests of different equivalent calendar years on an alloy steel material test piece;
s2: after accelerated corrosion of each equivalent calendar year, detecting and photographing corrosion damage of each test piece to obtain a macroscopic corrosion image of each test piece;
s3: qualitatively describing and analyzing the appearance corrosion condition of the test piece after accelerated corrosion;
s4: and constructing a corrosion damage evolution model of the alloy steel material of the air compressor of the aircraft engine, and carrying out quantitative statistics and analysis on corrosion parameters of the test piece after accelerated corrosion in calendar years with different equivalent weights.
2. The method for researching the corrosion damage distribution rule of the aviation alloy steel service environment as claimed in claim 1, wherein the specific operation of the step S1 includes the following steps,
s101: calculating action strength and action rule of typical environmental factors according to subsequent service environment of equipment equipped on alloy steel material blades of an aircraft engine compressor, on the basis, selecting typical strong corrosion environmental factors according to a corrosion damage equivalent conversion relation theory and an implementation method of test piece materials and the like, and designing and constructing a laboratory simulation accelerated corrosion test scheme of the test piece materials; the alloy steel material of the aero-engine compressor is 1Cr11Ni2W2Mov forged stator blade material;
s102: grouping, numbering and preprocessing the test pieces;
s103: constructing an accelerated corrosion test environment;
s104: and (4) carrying out accelerated corrosion on the test pieces of different groups in different equivalent calendar years according to the accelerated corrosion test scheme of the step (S101).
3. The method for researching the corrosion damage distribution rule of the aviation alloy steel in service environment as claimed in claim 2, wherein the specific operation of constructing the accelerated corrosion test environment in the step S103 comprises the following steps,
s1031: preparing a NaCl solution with the concentration of 5% by using 95 parts of distilled water and 5 parts of NaCl (analytically pure);
s1032: adding a proper amount of dilute H2SO4The pH of the etching solution was adjusted to 4.0 ± 0.2.
4. The method for researching the corrosion damage distribution rule of the aviation alloy steel service environment as claimed in claim 1, wherein the specific operation of the step S4 includes the following steps,
s401: selecting an erosion parameter for defining erosion damage;
s402: constructing a corrosion damage morphology evolution model of an alloy steel material of an aircraft engine compressor, and obtaining a quantitative relation between corrosion parameters by the corrosion damage morphology evolution model;
s403: acquiring corrosion parameter data;
s404: according to a statistical analysis method, the distribution conditions of the corrosion parameters under the same corrosion age in different distribution forms are contrastively analyzed, and the dynamic law of the corrosion parameters is analyzed.
5. The method for researching corrosion damage distribution law of aviation alloy steel service environment as claimed in claim 4, wherein the corrosion parameters for defining corrosion damage in step S401 include length, width and depth of corrosion damage surface.
6. The method for researching the corrosion damage distribution rule in the aviation alloy steel service environment as claimed in claim 5, wherein the corrosion damage morphology evolution model in the step S402 includes a hemispherical damage model and a semi-ellipsoidal damage model.
7. The method for researching corrosion damage distribution law of aviation alloy steel service environment as claimed in claim 6, wherein the specific operation of establishing the corrosion damage shape evolution model in the step S402 includes the following steps,
s4021: the nature of the initiation and the expansion of the corrosion damage of the alloy steel material is random process behavior, the process follows Faraday's law and combines with the Archimedes formula, and the pitting expansion model can be obtained as
In the formula, V represents pitting damage volume, t represents pitting period and is a time unit; m is atomic weight, IpDenotes the current density in the electrochemical process of pitting corrosion, IpoRepresents the current density constant in the electrochemical process of pitting corrosion; n is the valence, F is the Faraday constant, p is the material density, EaRepresents activation energy, R is an ideal gas constant, and T is absolute temperature;
s4022: establishing a hemispheroidal damage model with an evolving corrosion damage morphology
Wherein a represents a damage radius of the corrosion damage, then
S4023: to pair
Integrating to obtain the relation of the damage radius of the corrosion damage hemisphere damage model along with the change of the corrosion period
In the formula, a0The size of the damage nucleation representing the corrosion damage is usually 5 to 10 μ depending on the microstructure of the materialmTo (c) to (d);
S4024: establishing a semi-ellipsoid damage model of corrosion damage morphology evolution
In the formula, w, l and h respectively represent short axis, long axis and depth damage parameters of the damaged surface of the corrosion damage;
s4025: as the fractal characteristics of the damage three-dimensional morphology parameters of the corrosion damage gradually appear in the expansion process, the proportion relation between the damage three-dimensional morphology parameters can be deduced to gradually trend towards a fixed value, so that
If h/l is equal to epsilon, epsilon is more than 0, then
h＝lε；
S4026: when the three corrosion parameters of the corrosion damage are different, substituting the two equations in the step S5025 into
In (1) obtaining
S4027: in pair type
Integrating to obtain an evolution rule of a corrosion parameter l of the corrosion damage;
s4028: to pair
h/l is equal to epsilon, epsilon is more than 0, and the steps S5026 and S5027 are repeated, so that the evolution law of the corrosion parameters w and h of the corrosion damage can be obtained;
s4029: when two of the three corrosion parameters of the corrosion damage are the same, assuming that w is h, the two parameters are the same
Integrating the parameters to obtain an evolution rule of a corrosion parameter l of the corrosion damage; and obtaining the evolution law of the corrosion parameters w and h of the corrosion damage in the same way.
8. The method for researching corrosion damage distribution law of aviation alloy steel in service environment according to claim 7, wherein the distribution form in step S404 includes normal distribution, Gumbel distribution, Weibull distribution and lognormal distribution.
9. The method for researching corrosion damage distribution rule of aviation alloy steel in service environment as claimed in claim 8, wherein when the depth of damaged surface obeys Gumbel distribution, the probability distribution density function is
A distribution function of
Then
Wherein D is a random variable of the maximum erosion depth; p (D is less than or equal to D)mThe maximum depth of corrosion does not exceed the value DmThe probability of (d); μ and σ are the location and scale parameters, respectively;
when the depth of the damaged surface follows normal distribution, the probability density function is
A distribution function of
Then
In which μ "is over all the etched regionsAverage of maximum etch depth; sigma'2Is the variance;
when the depth of the damaged surface obeys the two-parameter Weibull distribution, the probability density function is
A distribution function of
Then
Wherein m is a shape parameter, a is a scale parameter,
is a true scale parameter;
when the depth of the damage surface follows the log normal distribution, the size of the corrosion damage is logarithmically lg D, and X is lgD, the probability density function is
A distribution function of
Then
In the formula, sigma 'and mu' are respectively the variance and mean value of the corrosion depth after logarithm;
and according to the quantitative relation among the corrosion parameters obtained in the step S402, further obtaining a probability density function and a distribution function when the length and the width of the corrosion damage surface obey normal distribution, Gumbel distribution, Weibull distribution and lognormal distribution.
10. The method for researching corrosion damage distribution law of aviation alloy steel service environment as claimed in claim 9, wherein the specific operation of analyzing the dynamics law of corrosion parameters in step S404 includes,
s4041: arranging the actual measured values of the corrosion depth in the order from small to large, wherein the No. 1 value is the minimum measured value D of the corrosion depth1The measured value of the corrosion depth of No. i is DiStatistical probability P of No. i dataiIs shown as
Wherein i is 1, 2, 3, …, N, N is the number of the measured values of the corrosion depth;
s4042: respectively calculating the corrosion depth corresponding to Gumbel, normal, lognormal and Weibull distribution
And ln Di；
S4043: according to the calculation result of the step S5042, by utilizing Origin graphic tool software, Gumbel, normal, lognormal and Weibull distribution fitting is adopted for testing;
s4044: carrying out statistical analysis on the corrosion depths under different corrosion years to finally obtain the overall change trend of the corrosion depth of the test piece along with the increase of the corrosion equivalent years;
s4045: and (4) repeating the steps S4041-S4044 according to the quantitative relation among the corrosion parameters to obtain the overall change trend of the length and the width of the corrosion damage surface of the test piece along with the increase of the corrosion equivalent age.
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