CN113466041A - Turbine blade seepage mechanical property test evaluation method - Google Patents
Turbine blade seepage mechanical property test evaluation method Download PDFInfo
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Abstract
The application belongs to the field of turbine blades of gas turbines, and particularly relates to a turbine blade seepage mechanical property test evaluation method. The method comprises the following steps: the method comprises the following steps of firstly, demand analysis, including: determining the concerned part of the turbine blade according to the service working condition; determining a performance analysis indicator for the turbine blade; step two, experimental design, including: performing test piece design according to the concerned part of the turbine blade, wherein the test piece comprises a standard test piece and a structural feature piece; determining test items and loading conditions of each standard test piece and each structural feature piece according to the performance analysis indexes of the turbine blade; respectively testing each standard test piece and each structural characteristic piece, and acquiring test data; and thirdly, carrying out quantitative evaluation on the single performance and the comprehensive performance based on the test data. The turbine blade mechanical property seepage layer test evaluation method can comprehensively reflect the quantitative evaluation of mechanical properties of the seepage layer required by the actual use of the turbine blade.
Description
Technical Field
The application belongs to the field of turbine blades of gas turbines, and particularly relates to a turbine blade seepage mechanical property test evaluation method.
Background
Turbine blades of aero-engines and gas turbines work under the conditions of high temperature and complex load, and have higher requirements on mechanical properties. The power device for the aircraft and the ship which are in service in the marine corrosive atmosphere environment also considers the problem of corrosion protection. The aluminide diffusion and infiltration layer is a common high-temperature corrosion resistant process at present, and has a good application prospect on the turbine blade. Based on the existing research data, the mechanical properties of parts are influenced while the corrosion resistance of the infiltration layer is improved, so that the mechanical properties of the infiltration layer need to be researched and evaluated in the development stage in order to ensure the service safety of the turbine blade.
At present, the influence of surface engineering processes such as a permeable layer and the like on mechanical properties is researched by adopting some universal evaluation methods, the service working condition characteristics of the blade cannot be truly reflected, and a special evaluation method completely adapting to the actual use requirement of the turbine blade is not provided; the prior art only focuses on a certain single performance of the blade, and no scheme for carrying out system test and evaluation capable of comprehensively reflecting multiple potential failure modes of the turbine blade exists; in the existing research, only the blade body with harsh service temperature is concerned, other parts such as the blade root and the like are ignored, and the blade root also has failure risk caused by the brittleness problem of the middle temperature zone of the infiltrated layer, so that attention is paid; the prior art is mostly qualitative comparative research, and no quantitative evaluation method for comprehensive mechanical properties exists.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a turbine blade seeping layer mechanical property test evaluation method to solve at least one problem in the prior art.
The technical scheme of the application is as follows:
a mechanical property test evaluation method for turbine blade seeping layers comprises the following steps:
the method comprises the following steps of firstly, demand analysis, including:
determining the concerned part of the turbine blade according to the service working condition;
determining a performance analysis indicator for the turbine blade;
step two, experimental design, including:
performing test piece design according to the concerned part of the turbine blade, wherein the test piece comprises a standard test piece and a structural feature piece;
determining test items and loading conditions of each standard test piece and each structural feature piece according to the performance analysis indexes of the turbine blade;
respectively testing each standard test piece and each structural characteristic piece, and acquiring test data;
and thirdly, carrying out quantitative evaluation on the single performance and the comprehensive performance based on the test data.
Optionally, in the first step, the turbine blade includes a rotor blade and a stator blade, the portion of interest of the rotor blade includes a blade body and a blade root, and the portion of interest of the stator blade includes a blade body.
Optionally, in the first step, the performance analysis indexes of the turbine blade comprise a layer penetration performance, a tensile performance, a durability performance, a low cycle fatigue performance and a high cycle fatigue performance.
Optionally, in the second step, the standard test pieces include a rotor blade standard test piece and a stator blade standard test piece, and the structural features include a rotor blade airfoil film hole structural feature, a rotor blade root corner structural feature, and a stator blade airfoil film hole structural feature.
Optionally, the test items of each standard test piece and the structural feature include:
the tensile property test of the standard test piece without the permeation layer comprises the following steps: the tensile property test of the standard test piece of the non-permeable layer rotor blade and the tensile property test of the standard test piece of the non-permeable layer stator blade are carried out;
the tensile property test of the standard test piece with the permeable layer comprises the following steps: the tensile property test of the standard test piece of the rotor blade with the permeable layer and the tensile property test of the standard test piece of the stator blade with the permeable layer are carried out;
the endurance test of the standard test piece without the permeation layer comprises the following steps: the endurance characteristic test of the standard test piece of the non-permeable layer rotor blade and the endurance characteristic test of the standard test piece of the non-permeable layer stator blade;
the test of the endurance quality of the standard test piece with the permeable layer comprises the following steps: the endurance characteristic test of the standard test piece of the rotor blade with the permeable layer and the endurance characteristic test of the standard test piece of the stator blade with the permeable layer are carried out;
the high cycle fatigue characteristic test of the standard test piece without the seeping layer comprises the following steps: testing the high cycle fatigue property of the standard test piece of the non-permeable layer rotor blade;
the high cycle fatigue characteristic test of the standard test piece with the seeping layer comprises the following steps: testing the high cycle fatigue property of a standard test piece of the rotor blade with the infiltrated layer;
the low cycle fatigue characteristic test of the standard test piece without the seeping layer comprises the following steps: the low cycle fatigue characteristic test of the non-permeable layer rotor blade standard test piece and the low cycle fatigue characteristic test of the non-permeable layer stator blade standard test piece are carried out;
the low cycle fatigue characteristic test of the standard test piece with the seeping layer comprises the following steps: the low cycle fatigue characteristic test of the standard test piece of the rotor blade with the permeable layer and the low cycle fatigue characteristic test of the standard test piece of the stator blade with the permeable layer are carried out;
testing the high cycle fatigue property of the air film hole structure characteristic part of the blade body of the non-permeable layer rotor;
testing the high cycle fatigue property of the air film hole structure characteristic part of the blade body of the rotor with the permeable layer;
testing the low cycle fatigue characteristic of the corner structure feature of the blade root of the non-seeping layer rotor;
testing the low cycle fatigue characteristic of the corner structure feature of the blade root of the rotor with the infiltrated layer;
testing the low-cycle fatigue property of the air film pore structure characteristic part of the non-permeable stator blade body;
and (3) testing the low-cycle fatigue property of the air film pore structure characteristic part of the blade body of the stator with the permeable layer.
Optionally, the minimum number of samples per test item is not less than 3.
Optionally, in the second step, after the test data is obtained, the method further includes removing abnormal data in the test data, and screening the abnormal data in the following manner:
observing the fracture of the test piece to be determined under a microscope, and if determining that the failure damage of the test piece is related to the material tissue defect and the processing quality of the test piece, considering the test piece as abnormal data;
carrying out statistical judgment on the test data through the Xiaoweinai criterion, and if the test data do not accord with the statistical rule, determining the test data as abnormal data;
if the failure of the test piece occurs on the non-working section, the test piece is considered to be abnormal data;
and (4) the test data influenced by operation errors or equipment faults are regarded as abnormal data.
Optionally, in step three, performing quantitative evaluation of individual performance based on the test data comprises:
obtaining the yield strength of a non-permeable layer standard test piece and a permeable layer standard test piece, and calculating the influence degree of the permeable layer on the yield strength of the standard test piece as follows:
PR＝R0.2′/R0.2
wherein, PRIs the yield strength influence index, R, of a standard test piece0.2Yield strength, R, for a standard test piece without a strike-through layer0.2' is the yield strength of the standard test piece with the infiltrated layer;
the elongation of the standard test piece without the permeable layer and the standard test piece with the permeable layer are obtained, and the influence degree of the permeable layer on the elongation of the standard test piece is calculated as follows:
PA＝A′/A
wherein, PAThe elongation coefficient influence index of the standard test piece is shown, A is the elongation coefficient of the standard test piece without the permeable layer, and A' is the elongation coefficient of the standard test piece with the permeable layer;
the method comprises the following steps of obtaining the endurance life of a non-permeable layer standard test piece and a permeable layer standard test piece, and calculating the influence degree of the permeable layer on the endurance life of the standard test piece as follows:
Pt＝lgt′/lgt
wherein, PtThe index is the endurance life influence index of the standard test piece, t is the endurance life of the standard test piece without the permeable layer, and t' is the endurance life of the standard test piece with the permeable layer;
the method comprises the following steps of obtaining the high cycle fatigue life of a non-permeable layer standard test piece and a permeable layer standard test piece, and calculating the influence degree of the permeable layer on the high cycle fatigue life of the standard test piece:
PhS＝lgNhS′/lgNhS
wherein, PhSIs a high cycle fatigue life influence index, N, of a standard test piecehSHigh cycle fatigue life for standard test pieces without a diffusion layer, NhS' is the high cycle fatigue life of the standard test piece with the infiltration layer;
the method comprises the following steps of obtaining the low-cycle fatigue life of a non-permeable layer standard test piece and a permeable layer standard test piece, and calculating the influence degree of the permeable layer on the low-cycle fatigue life of the standard test piece as follows:
PLS＝lgNLS′/lgNLS
wherein,PLSis a low cycle fatigue life influence index, NLSLow cycle fatigue life for standard test piece without strike-through, NLS' is the low cycle fatigue life of the standard test piece with the infiltrated layer;
obtain the high all fatigue life who does not have permeable layer rotor blade body air film hole structural feature spare and take permeable layer rotor blade body air film hole structural feature spare, calculate the influence degree of permeable layer to the high all fatigue life of rotor blade body air film hole structural feature spare and be:
PhA＝lgNhA′/lgNhA
wherein, PhAIs a high cycle fatigue life impact index, N, of a rotor blade airfoil film hole structure featurehAHigh cycle fatigue life for a non-laminated rotor blade airfoil film pore structure feature, NhA' is the high cycle fatigue life of the air film pore structure feature of the blade body of the rotor with the infiltrated layer;
the low-cycle fatigue life of the non-permeable layer rotor blade root corner structural feature and the permeable layer rotor blade root corner structural feature is obtained, and the influence degree of the permeable layer on the low-cycle fatigue life of the rotor blade root corner structural feature is calculated as follows:
PLB＝lgNLB′/lgNLB
wherein, PLBIs a low cycle fatigue life impact index, N, of rotor blade root corner structural featuresLBLow cycle fatigue life for non-infiltrated rotor blade root corner feature, NLB' Low cycle fatigue life of rotor blade root corner structural features with infiltrated layers;
the low cycle fatigue life who obtains no permeable layer stator blade body air film pore structure characteristic and take permeable layer stator blade body air film pore structure characteristic is calculated the influence degree of permeable layer to the low cycle fatigue life of stator blade body air film pore structure characteristic and is:
PLC＝lgNLC′/lgNLC
wherein, PLCIs the low cycle fatigue life impact index, N, of the stator blade airfoil pore structure featureLCLow cycle fatigue life for a non-exudative stator blade airfoil pore structure feature, NLC' is the low cycle fatigue life of the permeable stator blade airfoil pore structure feature.
Optionally, in step three, the performing of quantitative evaluation of the comprehensive performance based on the test data includes:
acquiring the weight of each single performance analysis index;
according to the influence indexes of the single performance analysis indexes and the corresponding weight distribution, the evaluation index of the permeable layer process to the comprehensive performance is calculated:
PQ＝∑P·S
wherein, PQFor the comprehensive performance evaluation index, P is the influence index of the single performance analysis index, and S is the weight of the corresponding single performance analysis index.
Alternatively,
the evaluation indexes of the comprehensive performance of the rotor blade by the layer infiltration process are as follows:
Pq turn＝∑P·S＝(PR0.2·SR0.2+PA·SA)×(Pt·St)×(PhS·ShS+PhA·ShA)×(PLS·SLS+PLB·SLB)
The evaluation indexes of the comprehensive performance of the stator blade by the seeping layer process are as follows:
Pqjing＝∑P·S＝(PR0.2·SR0.2+PA·SA)×(PhS·ShS)×(PLC·SLC)
Wherein, PQ turnIs an evaluation index of the comprehensive performance of the rotor blade, PQjingThe method is an evaluation index of the comprehensive performance of the rotor blade.
The invention has at least the following beneficial technical effects:
the turbine blade penetration mechanical property test evaluation method can comprehensively reflect the quantitative evaluation of the penetration mechanical property of the actual use requirement of the turbine blade, can be used for screening and optimizing a blade corrosion protection scheme in the design and development and improvement optimization processes of an engine and a gas turbine, and can also be used for evaluating the influence of factors such as penetration component proportion, diffusion depth and the like on the performance, and guiding a production department to adjust and optimize the preparation process of an aluminide corrosion-resistant penetration.
Drawings
FIG. 1 is a flow chart of a turbine blade mechanical property test evaluation method for a turbine blade penetration layer according to an embodiment of the present disclosure.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1.
The application provides a mechanical property test evaluation method for a turbine blade seeping layer, which comprises the following steps:
the method comprises the following steps of firstly, demand analysis, including:
determining the concerned part of the turbine blade according to the service working condition;
determining performance analysis indexes of the turbine blade;
step two, experimental design, including:
designing a test piece according to the concerned part of the turbine blade, wherein the test piece comprises a standard test piece and a structural feature piece;
determining test items and loading conditions of each standard test piece and each structural feature piece according to performance analysis indexes of the turbine blade;
respectively testing each standard test piece and each structural characteristic piece, and acquiring test data;
and thirdly, carrying out quantitative evaluation on the single performance and the comprehensive performance based on the test data.
According to the turbine blade seepage mechanical property test evaluation method, firstly, demand analysis is carried out, and the concerned part of the turbine blade is determined according to the service working condition. In the present embodiment, the main focus points of the aircraft engine and the turbine rotor blade and stator blade of the gas turbine are as follows: the concerned part of the rotor blade comprises a blade body and a blade root, wherein the blade body represents a high-temperature low-stress service state, and the blade root represents a medium-temperature high-stress service state; the concerned part of the stator blade comprises a blade body which represents a high-temperature high-stress service state.
The demand analysis also includes determining turbine blade performance analysis indicators including bleed performance, tensile performance, durability performance, low cycle fatigue performance, and high cycle fatigue performance. In this example, the influence of the penetrated layer on the tensile properties, the durability, the low cycle fatigue properties, and the high cycle fatigue properties was mainly studied. The characteristic recognition of the penetration layer is that the commonly used aluminide diffusion corrosion-resistant penetration layer has a specific ductile-brittle transition temperature (DBTT), the penetration layer shows toughness when the DBTT is higher than the DBTT, the penetration layer shows brittleness when the DBTT is lower than the DBTT, and the possibility of easy micro-crack initiation exists under a larger static or dynamic load. Advantageously, in this embodiment, the high temperature performance is tested while some medium to low temperature performance is addressed with the necessary attention. In the performance indexes, the strength, plasticity, endurance life, high cycle fatigue life and low cycle fatigue life of the rotor blade are mainly concerned; for stator blades, the strength, plasticity, low cycle fatigue life are of major concern. The problem of stress concentration of the air film hole and the corner part of the blade root is also concerned based on the structural characteristics of the blade.
The turbine blade mechanical property test evaluation method of the turbine blade seepage layer, secondly, carry out the experimental design, carry out the test piece design according to the focus on position of turbine blade, in this embodiment, the test piece includes standard test piece and structural feature, and the standard test piece includes rotor blade standard test piece and stator blade standard test piece, and structural feature includes rotor blade body air film hole structural feature, rotor blade root corner structural feature and stator blade body air film hole structural feature.
In a preferred embodiment of the present application, see table 1 for test piece design.
TABLE 1
The method specifically comprises the following steps:
the structural design of the test piece is as follows:
(a) standard smooth test bars: a tensile test bar, a durable test bar, a low cycle fatigue test bar and a high cycle fatigue test bar;
(b) structural feature simulation piece: and designing a structural feature part according to the stress distribution of the blade dead weight part to simulate the characteristics of a blade body air film hole part and a blade root corner part.
Heat treatment state of test piece substrate:
the heat treatment conditions of the test piece matrix alloys should be consistent with the latest requirements of the blade under study.
Surface state of the test piece:
in order to research the influence degree of the permeable layer on the performance, a test piece comprises two states of a permeable layer and a non-permeable layer, the coating area needs to be strictly limited for the coating requirement of the permeable layer, only the working part of the test piece is coated, and proper protection measures need to be taken for the clamping part.
According to the turbine blade mechanical property test evaluation method for the turbine blade seeping layer, test items and corresponding loading conditions of each standard test piece and each structural characteristic piece are determined according to performance analysis indexes of the turbine blade. In this embodiment, a typical failure mode of a blade critical weight portion is analyzed, and it is determined by combining the investigation result that the test items are characteristic tests of tensile, endurance, low cycle fatigue and high cycle fatigue under the condition of presence or absence of a seeping layer, and the total of the test items of the structural feature part is 7. On the basis of analyzing the service working condition characteristics (temperature, stress mode, characteristic structure, surface state and the like) of the blade critical weight part, various test parameters are formulated according to the actual performance requirement characteristics of different parts of the blade. The test temperature and load setting principles, using turbine rotor blades as an example, are shown in table 2. In the embodiment, only recommended test items, test parameters and selection principles are provided, and necessary test items and corresponding test parameters are selected and formulated according to special analysis requirements of specific models and actual application scenes of test objects in actual application.
TABLE 2
Specifically, in the preferred embodiment of the present application, the test items of each standard test piece and the structural feature piece include:
the tensile property test of the standard test piece without the permeation layer comprises the following steps: the tensile property test of the standard test piece of the non-permeable layer rotor blade and the tensile property test of the standard test piece of the non-permeable layer stator blade are carried out;
the tensile property test of the standard test piece with the permeable layer comprises the following steps: the tensile property test of the standard test piece of the rotor blade with the permeable layer and the tensile property test of the standard test piece of the stator blade with the permeable layer are carried out;
the endurance test of the standard test piece without the permeation layer comprises the following steps: the endurance characteristic test of the standard test piece of the non-permeable layer rotor blade and the endurance characteristic test of the standard test piece of the non-permeable layer stator blade;
the test of the endurance quality of the standard test piece with the permeable layer comprises the following steps: the endurance characteristic test of the standard test piece of the rotor blade with the permeable layer and the endurance characteristic test of the standard test piece of the stator blade with the permeable layer are carried out;
the high cycle fatigue characteristic test of the standard test piece without the seeping layer comprises the following steps: testing the high cycle fatigue property of the standard test piece of the non-permeable layer rotor blade;
the high cycle fatigue characteristic test of the standard test piece with the seeping layer comprises the following steps: testing the high cycle fatigue property of a standard test piece of the rotor blade with the infiltrated layer;
the low cycle fatigue characteristic test of the standard test piece without the seeping layer comprises the following steps: the low cycle fatigue characteristic test of the non-permeable layer rotor blade standard test piece and the low cycle fatigue characteristic test of the non-permeable layer stator blade standard test piece are carried out;
the low cycle fatigue characteristic test of the standard test piece with the seeping layer comprises the following steps: the low cycle fatigue characteristic test of the standard test piece of the rotor blade with the permeable layer and the low cycle fatigue characteristic test of the standard test piece of the stator blade with the permeable layer are carried out;
testing the high cycle fatigue property of the air film hole structure characteristic part of the blade body of the non-permeable layer rotor;
testing the high cycle fatigue property of the air film hole structure characteristic part of the blade body of the rotor with the permeable layer;
testing the low cycle fatigue characteristic of the corner structure feature of the blade root of the non-seeping layer rotor;
testing the low cycle fatigue characteristic of the corner structure feature of the blade root of the rotor with the infiltrated layer;
testing the low-cycle fatigue property of the air film pore structure characteristic part of the non-permeable stator blade body;
and (3) testing the low-cycle fatigue property of the air film pore structure characteristic part of the blade body of the stator with the permeable layer.
According to the turbine blade seepage mechanical property test evaluation method, execution of each test refers to corresponding aviation standards, in order to simplify the test process and save the test cost, a single-parameter small subsample test method is adopted in the tests, the subsample number of each test item needs to meet the requirement that the minimum sample number is not less than 3, and the confidence coefficient is higher than 90%. As the penetrated layer has higher brittleness, the size of all test pieces with the penetrated layer for stress calculation is measured by adopting the measurement result before the penetrated layer is coated.
The small subsample test has high requirement on data reliability, and if the results of several subsamples in certain group of data have large difference, abnormal data is judged and accepted. In a preferred embodiment of the present application, after the test data is acquired, the abnormal data in the test data is removed, wherein the abnormal data is screened in the following manner:
and (3) microscopic analysis: observing the fracture of the test piece to be determined under a microscope, and if determining that the failure damage of the test piece is related to the material tissue defect and the processing quality of the test piece, considering the test piece as abnormal data;
statistical analysis method: carrying out statistical judgment on the test data through the Xiaoweinai criterion, and if the test data do not accord with the statistical rule, determining the test data as abnormal data;
if the failure of the test piece occurs on the non-working section, the test piece is considered to be abnormal data;
and (4) the test data influenced by operation errors or equipment faults are regarded as abnormal data.
If the data meets the above arbitrary judgment criteria, the data can be considered as abnormal data, and the abnormal data should be eliminated during statistics.
The turbine blade seepage layer mechanical property test evaluation method can be used for grouping and counting data according to the requirements of a test piece with a seepage layer and a test piece without the seepage layer according to the requirements of a table 3, and calculating the statistical mean value of each performance test result respectively, wherein the logarithmic mean value is calculated by relating to the fatigue life.
TABLE 3
According to the turbine blade mechanical property test evaluation method for the turbine blade seeping layer, after test data are counted, qualitative evaluation of a single performance index is firstly carried out. The method specifically comprises the following steps: and aiming at a certain performance index shown in the table 1, drawing a data chart according to the test result mean value, error distribution and other information obtained by the test and statistical method. During drawing, linear coordinates are adopted for performance indexes conforming to the linear change rule such as strength and plasticity, and exponential coordinates are adopted for performance indexes conforming to the exponential change rule such as endurance life and fatigue life. And comparing the influence degrees of different infiltration layer processes on the performance qualitatively through visual comparison.
Advantageously, in this embodiment, the method further includes performing quantitative evaluation on the single performance index, and calculating a permeability influence index according to the test results of the non-permeability test piece and the permeability test piece to characterize the influence degree of the permeability process on the mechanical performance of the blade.
For the performance indexes of which the strength, the plasticity and the like accord with the linear change rule, the ratio of the mean values of the results of the states with the permeable layer and the non-permeable layer is adopted to represent that:
obtaining the yield strength of a non-permeable layer standard test piece and a permeable layer standard test piece, and calculating the influence degree of the permeable layer on the yield strength of the standard test piece as follows:
PR＝R0.2′/R0.2
wherein, PRIs the yield strength influence index, R, of a standard test piece0.2Yield strength, R, for a standard test piece without a strike-through layer0.2' is the yield strength of the standard test piece with the infiltrated layer;
the elongation of the standard test piece without the permeable layer and the standard test piece with the permeable layer are obtained, and the influence degree of the permeable layer on the elongation of the standard test piece is calculated as follows:
PA＝A′/A
wherein, PAThe elongation coefficient influence index of the standard test piece is shown, A is the elongation coefficient of the standard test piece without the permeable layer, and A' is the elongation coefficient of the standard test piece with the permeable layer;
for performance indexes such as endurance life and fatigue life which accord with the exponential change rule, the logarithmic mean value of the results of the states with the permeable layer and without the permeable layer is adopted for representing:
the method comprises the following steps of obtaining the endurance life of a non-permeable layer standard test piece and a permeable layer standard test piece, and calculating the influence degree of the permeable layer on the endurance life of the standard test piece as follows:
Pt＝lgt′/lgt
wherein, PtIs the long-term life influence index of the standard test pieceT is the endurance life of the standard test piece without the permeable layer, and t' is the endurance life of the standard test piece with the permeable layer;
the method comprises the following steps of obtaining the high cycle fatigue life of a non-permeable layer standard test piece and a permeable layer standard test piece, and calculating the influence degree of the permeable layer on the high cycle fatigue life of the standard test piece:
PhS＝lgNhS′/lgNhS
wherein, PhSIs a high cycle fatigue life influence index, N, of a standard test piecehSHigh cycle fatigue life for standard test pieces without a diffusion layer, NhS' is the high cycle fatigue life of the standard test piece with the infiltration layer;
the method comprises the following steps of obtaining the low-cycle fatigue life of a non-permeable layer standard test piece and a permeable layer standard test piece, and calculating the influence degree of the permeable layer on the low-cycle fatigue life of the standard test piece as follows:
PLS＝lgNLS′/lgNLS
wherein, PLSIs a low cycle fatigue life influence index, NLSLow cycle fatigue life for standard test piece without strike-through, NLS' is the low cycle fatigue life of the standard test piece with the infiltrated layer;
obtain the high all fatigue life who does not have permeable layer rotor blade body air film hole structural feature spare and take permeable layer rotor blade body air film hole structural feature spare, calculate the influence degree of permeable layer to the high all fatigue life of rotor blade body air film hole structural feature spare and be:
PhA＝lgNhA′/lgNhA
wherein, PhAIs a high cycle fatigue life impact index, N, of a rotor blade airfoil film hole structure featurehAHigh cycle fatigue life for a non-laminated rotor blade airfoil film pore structure feature, NhA' is the high cycle fatigue life of the air film pore structure feature of the blade body of the rotor with the infiltrated layer;
the low-cycle fatigue life of the non-permeable layer rotor blade root corner structural feature and the permeable layer rotor blade root corner structural feature is obtained, and the influence degree of the permeable layer on the low-cycle fatigue life of the rotor blade root corner structural feature is calculated as follows:
PLB＝lgNLB′/lgNLB
wherein, PLBIs a low cycle fatigue life impact index, N, of rotor blade root corner structural featuresLBLow cycle fatigue life for non-infiltrated rotor blade root corner feature, NLB' Low cycle fatigue life of rotor blade root corner structural features with infiltrated layers;
the low cycle fatigue life who obtains no permeable layer stator blade body air film pore structure characteristic and take permeable layer stator blade body air film pore structure characteristic is calculated the influence degree of permeable layer to the low cycle fatigue life of stator blade body air film pore structure characteristic and is:
PLC＝lgNLC′/lgNLC
wherein, PLCIs the low cycle fatigue life impact index, N, of the stator blade airfoil pore structure featureLCLow cycle fatigue life for a non-exudative stator blade airfoil pore structure feature, NLC' is the low cycle fatigue life of the permeable stator blade airfoil pore structure feature.
In the preferred embodiment of the present application, when P >0.95, it is believed that this strike-through process has no significant impact on this property of the material; certain effects are considered to exist when 0.8< P < 0.95; when P is less than 0.8, the infiltration layer process is considered to have a great influence on the performance of the material.
The turbine blade mechanical property test evaluation method for the turbine blade seeping layer can also carry out quantitative evaluation on comprehensive properties based on test data.
Acquiring the weight of each single performance analysis index;
according to the influence indexes of the single performance analysis indexes and the corresponding weight distribution, the evaluation index of the permeable layer process to the comprehensive performance is calculated:
PQ＝∑P·S
wherein, PQFor the comprehensive performance evaluation index, P is the influence index of the single performance analysis index, and S is the weight of the corresponding single performance analysis index.
According to the design requirements of the strength of the turbine blade and the statistical analysis of the past related failure cases, the weight proportion of each mechanical property in quantitative evaluation is set on the basis of representing the actual performance requirements of service, the four properties of short-time mechanical property, durability, high-cycle fatigue and low-cycle fatigue are mainly concerned, and the weight S of each performance index is determined according to the importance degree, and the weight S is shown in a table 4.
TABLE 4
In one embodiment of the present application, the evaluation index of the lamination process on the comprehensive performance of the rotor blade is as follows:
Pq turn＝∑P·S＝(PR0.2·SR0.2+PA·SA)×(Pt·St)×(PhS·ShS+PhA·ShA)×(PLS·SLS+PLB·SLB)
The evaluation indexes of the comprehensive performance of the stator blade by the seeping layer process are as follows:
Pqjing＝∑P·S＝(PR0.2·SR0.2+PA·SA)×(PhS·ShS)×(PLC·SLC)
Wherein, PQ turnIs an evaluation index of the comprehensive performance of the rotor blade, PQjingThe method is an evaluation index of the comprehensive performance of the rotor blade.
A larger P-value indicates a greater effect of the infiltration process on the turbine blade, and the P-values may be compared for different infiltration processes.
The turbine blade penetration mechanical property test evaluation method can quantitatively represent the influence of the penetration process on the service mechanical property of a part, and can be used for screening and optimizing blade corrosion protection schemes in the design, development, improvement and optimization processes of engines and gas turbines by combining the evaluation result of the corrosion protection performance of the part. The method can also be used for evaluating the influence of factors such as the composition proportion of the infiltration layer, the diffusion depth and the like on the performance, and guiding the production department to adjust and optimize the preparation process of the aluminide corrosion-resistant infiltration layer.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A mechanical property test evaluation method for turbine blade seeping layers is characterized by comprising the following steps:
the method comprises the following steps of firstly, demand analysis, including:
determining the concerned part of the turbine blade according to the service working condition;
determining a performance analysis indicator for the turbine blade;
step two, experimental design, including:
performing test piece design according to the concerned part of the turbine blade, wherein the test piece comprises a standard test piece and a structural feature piece;
determining test items and loading conditions of each standard test piece and each structural feature piece according to the performance analysis indexes of the turbine blade;
respectively testing each standard test piece and each structural characteristic piece, and acquiring test data;
and thirdly, carrying out quantitative evaluation on the single performance and the comprehensive performance based on the test data.
2. The method for evaluating the mechanical property test of the turbine blade penetration layer according to claim 1, wherein in the first step, the turbine blade comprises a rotor blade and a stator blade, the part of interest of the rotor blade comprises a blade body and a blade root, and the part of interest of the stator blade comprises the blade body.
3. The turbine blade carburized layer mechanical property test evaluation method according to claim 2, characterized in that in step one, the turbine blade performance analysis indicators include carburized layer performance, tensile property, durability, low cycle fatigue performance, and high cycle fatigue performance.
4. The turbine blade delamination mechanical property test evaluation method as claimed in claim 3, wherein in the second step, the standard test pieces comprise a rotor blade standard test piece and a stator blade standard test piece, and the structural features comprise a rotor blade airfoil pore structural feature, a rotor blade root corner structural feature and a stator blade airfoil pore structural feature.
5. The turbine blade mechanical property test evaluation method for turbine blade delamination as set forth in claim 4, wherein the test items of each of the standard test pieces and the structural feature pieces include:
the tensile property test of the standard test piece without the permeation layer comprises the following steps: the tensile property test of the standard test piece of the non-permeable layer rotor blade and the tensile property test of the standard test piece of the non-permeable layer stator blade are carried out;
the tensile property test of the standard test piece with the permeable layer comprises the following steps: the tensile property test of the standard test piece of the rotor blade with the permeable layer and the tensile property test of the standard test piece of the stator blade with the permeable layer are carried out;
the endurance test of the standard test piece without the permeation layer comprises the following steps: the endurance characteristic test of the standard test piece of the non-permeable layer rotor blade and the endurance characteristic test of the standard test piece of the non-permeable layer stator blade;
the test of the endurance quality of the standard test piece with the permeable layer comprises the following steps: the endurance characteristic test of the standard test piece of the rotor blade with the permeable layer and the endurance characteristic test of the standard test piece of the stator blade with the permeable layer are carried out;
the high cycle fatigue characteristic test of the standard test piece without the seeping layer comprises the following steps: testing the high cycle fatigue property of the standard test piece of the non-permeable layer rotor blade;
the high cycle fatigue characteristic test of the standard test piece with the seeping layer comprises the following steps: testing the high cycle fatigue property of a standard test piece of the rotor blade with the infiltrated layer;
the low cycle fatigue characteristic test of the standard test piece without the seeping layer comprises the following steps: the low cycle fatigue characteristic test of the non-permeable layer rotor blade standard test piece and the low cycle fatigue characteristic test of the non-permeable layer stator blade standard test piece are carried out;
the low cycle fatigue characteristic test of the standard test piece with the seeping layer comprises the following steps: the low cycle fatigue characteristic test of the standard test piece of the rotor blade with the permeable layer and the low cycle fatigue characteristic test of the standard test piece of the stator blade with the permeable layer are carried out;
testing the high cycle fatigue property of the air film hole structure characteristic part of the blade body of the non-permeable layer rotor;
testing the high cycle fatigue property of the air film hole structure characteristic part of the blade body of the rotor with the permeable layer;
testing the low cycle fatigue characteristic of the corner structure feature of the blade root of the non-seeping layer rotor;
testing the low cycle fatigue characteristic of the corner structure feature of the blade root of the rotor with the infiltrated layer;
testing the low-cycle fatigue property of the air film pore structure characteristic part of the non-permeable stator blade body;
and (3) testing the low-cycle fatigue property of the air film pore structure characteristic part of the blade body of the stator with the permeable layer.
6. The turbine blade carburized mechanical property test evaluation method of claim 5, characterized in that the minimum number of samples per test item is not less than 3.
7. The turbine blade mechanical property test evaluation method for the turbine blade carburized layer as claimed in claim 6, wherein in the second step, after the test data are obtained, the method further comprises the step of eliminating abnormal data in the test data, and the abnormal data are screened in the following mode:
observing the fracture of the test piece to be determined under a microscope, and if determining that the failure damage of the test piece is related to the material tissue defect and the processing quality of the test piece, considering the test piece as abnormal data;
carrying out statistical judgment on the test data through the Xiaoweinai criterion, and if the test data do not accord with the statistical rule, determining the test data as abnormal data;
if the failure of the test piece occurs on the non-working section, the test piece is considered to be abnormal data;
and (4) the test data influenced by operation errors or equipment faults are regarded as abnormal data.
8. The turbine blade mechanical property test evaluation method of the turbine blade seeping layer according to the claim 7, characterized in that in the third step, the quantitative evaluation of the single performance based on the test data comprises:
obtaining the yield strength of a non-permeable layer standard test piece and a permeable layer standard test piece, and calculating the influence degree of the permeable layer on the yield strength of the standard test piece as follows:
PR＝R0.2′/R0.2
wherein, PRIs the yield strength influence index, R, of a standard test piece0.2Yield strength, R, for a standard test piece without a strike-through layer0.2' is the yield strength of the standard test piece with the infiltrated layer;
the elongation of the standard test piece without the permeable layer and the standard test piece with the permeable layer are obtained, and the influence degree of the permeable layer on the elongation of the standard test piece is calculated as follows:
PA＝A′/A
wherein, PAThe elongation coefficient influence index of the standard test piece is shown, A is the elongation coefficient of the standard test piece without the permeable layer, and A' is the elongation coefficient of the standard test piece with the permeable layer;
the method comprises the following steps of obtaining the endurance life of a non-permeable layer standard test piece and a permeable layer standard test piece, and calculating the influence degree of the permeable layer on the endurance life of the standard test piece as follows:
Pt＝lgt′/lgt
wherein, PtThe index is the endurance life influence index of the standard test piece, t is the endurance life of the standard test piece without the permeable layer, and t' is the endurance life of the standard test piece with the permeable layer;
the method comprises the following steps of obtaining the high cycle fatigue life of a non-permeable layer standard test piece and a permeable layer standard test piece, and calculating the influence degree of the permeable layer on the high cycle fatigue life of the standard test piece:
PhS＝lgNhS′/lgNhS
wherein，PhSIs a high cycle fatigue life influence index, N, of a standard test piecehSHigh cycle fatigue life for standard test pieces without a diffusion layer, NhS' is the high cycle fatigue life of the standard test piece with the infiltration layer;
the method comprises the following steps of obtaining the low-cycle fatigue life of a non-permeable layer standard test piece and a permeable layer standard test piece, and calculating the influence degree of the permeable layer on the low-cycle fatigue life of the standard test piece as follows:
PLS＝lgNLS′/lgNLS
wherein, PLSIs a low cycle fatigue life influence index, NLSLow cycle fatigue life for standard test piece without strike-through, NLS' is the low cycle fatigue life of the standard test piece with the infiltrated layer;
obtain the high all fatigue life who does not have permeable layer rotor blade body air film hole structural feature spare and take permeable layer rotor blade body air film hole structural feature spare, calculate the influence degree of permeable layer to the high all fatigue life of rotor blade body air film hole structural feature spare and be:
PhA＝lgNhA′/lgNhA
wherein, PhAIs a high cycle fatigue life impact index, N, of a rotor blade airfoil film hole structure featurehAHigh cycle fatigue life for a non-laminated rotor blade airfoil film pore structure feature, NhA' is the high cycle fatigue life of the air film pore structure feature of the blade body of the rotor with the infiltrated layer;
the low-cycle fatigue life of the non-permeable layer rotor blade root corner structural feature and the permeable layer rotor blade root corner structural feature is obtained, and the influence degree of the permeable layer on the low-cycle fatigue life of the rotor blade root corner structural feature is calculated as follows:
PLB＝lgNLB′/lgNLB
wherein, PLBIs a low cycle fatigue life impact index, N, of rotor blade root corner structural featuresLBLow cycle fatigue life for non-infiltrated rotor blade root corner feature, NLB' Low cycle fatigue life of rotor blade root corner structural features with infiltrated layers;
the low cycle fatigue life who obtains no permeable layer stator blade body air film pore structure characteristic and take permeable layer stator blade body air film pore structure characteristic is calculated the influence degree of permeable layer to the low cycle fatigue life of stator blade body air film pore structure characteristic and is:
PLC＝lgNLC′/lgNLC
wherein, PLCIs the low cycle fatigue life impact index, N, of the stator blade airfoil pore structure featureLCLow cycle fatigue life for a non-exudative stator blade airfoil pore structure feature, NLC' is the low cycle fatigue life of the permeable stator blade airfoil pore structure feature.
9. The turbine blade mechanical property test evaluation method for the turbine blade penetration layer as claimed in claim 8, wherein in the third step, the quantitative evaluation of the comprehensive properties based on the test data comprises:
acquiring the weight of each single performance analysis index;
according to the influence indexes of the single performance analysis indexes and the corresponding weight distribution, the evaluation index of the permeable layer process to the comprehensive performance is calculated:
PQ＝∑P·S
wherein, PQFor the comprehensive performance evaluation index, P is the influence index of the single performance analysis index, and S is the weight of the corresponding single performance analysis index.
10. The turbine blade mechanical property test evaluation method of the turbine blade penetration layer according to claim 9,
the evaluation indexes of the comprehensive performance of the rotor blade by the layer infiltration process are as follows:
Pq turn＝∑P·S＝(PR0.2·SR0.2+PA·SA)×(Pt·St)×(PhS·ShS+PhA·ShA)×(PLS·SLS+PLB·SLB)
The evaluation indexes of the comprehensive performance of the stator blade by the seeping layer process are as follows:
Pqjing＝∑P·S＝(PR0.2·SR0.2+PA·SA)×(PhS·ShS)×(PLC·SLC)
Wherein, PQ turnIs an evaluation index of the comprehensive performance of the rotor blade, PQjingThe method is an evaluation index of the comprehensive performance of the rotor blade.
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