CN112525907B - Method for evaluating residual creep life of high-temperature static component material of gas turbine in service - Google Patents
Method for evaluating residual creep life of high-temperature static component material of gas turbine in service Download PDFInfo
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Abstract
The invention discloses a method for evaluating the residual creep life of a high-temperature static part material of a service gas turbine, which mainly comprises metallographic structure observation, endurance test and life calculation analysis, and solves the problems of large error, time consumption and the like of the traditional residual creep life evaluation method adopting a dual-logarithmic-coordinate endurance life curve. The method combines metallographic examination and endurance test methods, considers the actual material aging and damage states of the parts under different service time, samples from the actual service parts, determines the accelerated endurance test conditions, and quantitatively calculates and obtains the residual creep life of the high-temperature static part material of the gas turbine according to test data. The method is simple to operate, reliable, accurate in result, high in applicability and universality, capable of meeting the requirement of residual life evaluation of the high-temperature components of the gas turbine and guiding reasonable formulation of maintenance plans.
Description
Technical Field
The invention belongs to the technical field of metallurgy, and particularly relates to a method for evaluating residual creep life of a high-temperature static component material of a gas turbine in service.
Background
High-temperature components such as a gas turbine flame tube, a transition section, a turbine blade, a protective ring, a wheel disc, a shaft and the like are used as core components of the gas turbine, and are the components with the worst working environment, the most complex structure, the most faults and the highest replacement cost. The high-temperature component is in service under the conditions of long-time high temperature and high stress, creep damage of different degrees is inevitably generated on the high-temperature component, the service life of the high-temperature component is seriously influenced, and the high-temperature performance and the service life of the high-temperature component are seriously influenced. In order to reasonably utilize the service life of components and make a reasonable overhaul period and repair scheme so as to ensure the safe, economic and continuous operation of the power generation equipment of the gas turbine, the creep life analysis method of the high-temperature components of the gas turbine is concerned by researchers at home and abroad.
At present, the research on the creep life method of high-temperature parts at home and abroad mainly focuses on three aspects: ultrasonic measurement based on the change of structural performance parameters of the detection material; a long-time creep test data is obtained by extrapolation of a short-time long-time endurance life test; microstructure analysis method based on the microstructure change mechanism of high-temperature creep of material. The ultrasonic detection method for evaluating the creep damage state and the service life of the high-temperature part material is still in a laboratory test stage, the method has large error and small practical application significance. The development of the current widely used extrapolation of the endurance life test has generally gone through three stages: the method needs a large number of long-time endurance performance tests, does not consider the self material aging and the structural performance change of the service parts, has poor timeliness, conserves the predicted service life result and has low extrapolation accuracy. The microstructure metallographic analysis method is to evaluate the creep state and further predict the high-temperature creep life by observing the change of the grain boundary morphology and the microscopic change of the size of carbide particles from the microscopic angle of material creep damage, and is generally suitable for high-temperature part materials in the first and second stages of creep. Quantitative analysis by metallographic analysis is very difficult due to uneven distribution of the microstructure of the material at each stage of creep life.
From the current research situation at home and abroad, the existing high-temperature part creep life evaluation method has defects, and the development of the method for evaluating the residual creep life of the high-temperature part of the gas turbine, which has strong applicability, relatively simple operation and high accuracy, has important practical significance.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a method for evaluating the residual creep life of a high-temperature static component material of a gas turbine in service, which is simple to operate, reliable, accurate in result, high in applicability and universality, and capable of meeting the requirement on evaluating the residual life of the high-temperature component of the gas turbine and guiding the reasonable formulation of a maintenance plan.
The invention is realized by the following technical scheme:
a method for evaluating the residual creep life of a high-temperature static component material of a gas turbine in service comprises the following steps:
1) Obtaining a metallographic specimen and a lasting sample of a typical damaged part of the damaged part, and obtaining a lasting sample of a corresponding part of the damaged part in an original state;
2) Acquiring creep damage tissue characteristics of a damaged part of a metallographic sample;
3) Obtaining the durable life data t of the durable sample of the damaged part under the test condition t And obtaining the durable life data T of the durable sample of the original state part under the same test condition t ；
4) According to the persistent lifetime data t t And persistent lifetime data T t Determining residual creep life T of service component S 。
Preferably, in the step 2, the metallographic specimen is ground, polished and corroded and then detected to obtain the metallographic structure morphology characteristics.
Preferably, the creep damage texture characteristics in step 2 include γ', TCP phase, grain boundary morphology, composition, morphology, size and volume fraction of carbides.
Preferably, the test conditions include stress and temperature, and the test temperature is higher than the service temperature.
Preferably, the temperature is 900 ℃ to 1100 ℃.
Preferably, in the step 3, a high-temperature lasting tensile testing machine is used for carrying out lasting tests under stress and different heating conditions, the test times are 2-4, and lasting life data are obtained.
Preferably, the residual creep life T of the service part in the step 4 S The calculation method of (2) is as follows:
t s /(t s +T S )+t t /T t ＝1
wherein, t s For the time of service of the component, T S The creep life of the component remains.
Preferably, when a plurality of persistent lifetime data t are acquired in step 3 t Then, respectively calculating the corresponding residual creep life T S And then averaging the values to obtain the residual creep life value of the service part.
Preferably, the damaged component is a nickel-based or cobalt-based superalloy material.
Preferably, the material of the damage part is IN738, IN939, hastelloy X, FSX414, GTD-222, MGA1400, MAR-M200Hf, MAR-M002 or DS GTD 111.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention provides a method for evaluating the residual creep life of a high-temperature static component material of a service gas turbine, which combines alloy phase inspection and a lasting life experiment. The method for evaluating the residual creep life of the high-temperature static part material of the gas turbine in service is provided aiming at the problem of evaluation of the residual life of the high-temperature parts of the gas turbine in service, such as E-class, F-class and even H-class, is generally suitable for evaluating the residual life of the high-temperature static part material of the main gas turbine in service, such as a flame tube, a transition section, a turbine blade, a retaining ring, a wheel disc and a shaft, and has extremely high universality.
Furthermore, the method combining metallographic examination and endurance life experiment not only considers the actual damage structure state of the service part, but also considers the problems of the traditional residual creep life evaluation method based on the log-log coordinate endurance life curve, and finally obtains the residual creep life of the high-temperature part material through a small amount of endurance life tests and quantitative calculation, thereby having extremely strong applicability and accuracy.
Furthermore, the residual creep life evaluation method provided by the invention can predict the residual creep life of the component material, and the creep life is a main parameter for determining the aging degree of the component material and whether to repair and prolong the life, so that the method is not only used for establishing a basis of a maintenance period, but also can be used for establishing a basis of whether to repair and prolong the life, and has wide application prospect.
Furthermore, the residual creep life evaluation method can accurately obtain the residual creep life value of the component material. According to the evaluation result, a maintenance cycle can be established, and the available state of the component can be determined, so that whether the component can be continuously used, repaired and scrapped can be determined. For the component which can be repaired and has a prolonged service life, the component can be continuously used for the next overhaul period after being repaired and prolonged, so that the rejection rate of the component is reduced and great economic benefit is brought.
Furthermore, as the main procedures of the residual creep life evaluation method comprise sample interception, metallographic observation, endurance test, life calculation analysis and the like, the main evaluation processes of different high-temperature component materials are basically the same, and the test testing workload is less and the timeliness is high. Therefore, the recovery method of the invention has the advantages of low cost, simple operation, high timeliness and convenient flow operation.
In conclusion, the method is simple to operate, reliable, accurate in result, high in timeliness, applicability and universality, capable of meeting the residual life evaluation requirement of the high-temperature components of the gas turbine and guiding the reasonable formulation of the maintenance plan and the determination of the repair life-prolonging scheme.
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FIG. 1 is a flow of evaluating the residual creep life of a high-temperature static component material of a gas turbine in service according to the present invention;
FIG. 2 is a schematic diagram of evaluation of residual creep life of a high-temperature static component material of a gas turbine in service;
FIG. 3 shows the creep damage structure morphology of the service part material. Wherein, fig. 3 (a) and fig. 3 (b) are metallographic structures after creep damage of Nimonic263 deformed superalloy material for the transition section and FSX414 cast cobalt-based superalloy material for the turbine vane, respectively;
FIG. 4 shows the results of the material endurance tests of the original state and the in-service state components;
FIG. 5 is the calculation result of the residual creep life of the high-temperature component material in service state.
Detailed Description
The present invention will now be described more fully hereinafter with reference to the accompanying drawings, in which the invention is shown by way of illustration and not by way of limitation.
As shown in FIG. 1 and FIG. 2, the invention relates to a method for evaluating residual creep life of a high-temperature static component material of a gas turbine in service, which comprises the following steps:
1) And (3) metallographic detection: and (3) cutting and inlaying a metallographic specimen from the service state part, grinding, polishing and corroding, detecting and analyzing creep damage structure characteristics of the damaged part, including gamma', carbide, TCP phase, grain boundary morphology and the like, and determining a lasting test heating condition (1-3 data points are selected at will when the temperature is higher than the actual service temperature).
2) And (3) endurance test: processing a sheet-like durable sample. Testing the durable life data of the part material in service state under heating or stress, and recording the data as t t . Meanwhile, the endurance life data of the original state part material heated or stressed is obtained through testing and is recorded as T t 。
3) And (3) calculating and analyzing the service life: the service time of the part is recorded as t s And its residual creep life is denoted as T S . At known t s 、t t 、T t Under the condition of (1), according to t s /(t s +T S )+t t /T t The formula of =1 can be directly calculated to obtain the residual creep life T of the high-temperature component of the gas turbine in service S . If there are a plurality of t t The test values are calculated according to the residual creep life T S And then averaging to serve as serviceResidual creep life values for high temperature components of gas turbines.
Example 2
Cutting out a metallographic sample from an FSX414 cast high-temperature alloy material used by the creep damage turbine stationary blade, inlaying the metallographic sample, grinding, polishing and corroding the metallographic sample, detecting and analyzing the morphological characteristics of the metallographic structure, and determining the accelerated conditions of the endurance test temperature as 870 ℃, 900 ℃ and 950 ℃; 3 sheet-shaped durable samples are cut from the original state turbine stator blade material and the service state turbine stator blade component material and processed. Testing the durable service life data of the turbine stator blade material in service state under the conditions of service stress and heating (870 ℃, 900 ℃ and 950 ℃), and respectively recording the data as t t1 、t t2 And t t3 . Meanwhile, the test obtains the durable service life data of the original state turbine stator blade material heated or stressed, and the data is recorded as T t1 、T t2 And T t3 . Service time of the turbine stator blade is recorded as t s And its residual creep life is denoted as T S . At known t s 、t t 、T t Under the condition of (1), according to t s /(t s +T S )+t t /T t =1 formula can directly calculate residual creep life T of service transition section material S1 、T S2 And T S3 And then, averaging to obtain the residual creep life value of the high-temperature part of the gas turbine in service.
FIG. 3 shows the microstructure of the creep-damaged transition section material (Nimonic 263) and the turbine vane material (FSX 414). The transition section is made of Nimonic263 nickel-based wrought superalloy, has a polycrystalline structure, and has a strengthening effect by dispersing and distributing carbide in a crystal boundary. The material used for the turbine stator blade is FSX414 cast cobalt-based high-temperature alloy, and the material has a polycrystalline structure and dendritic crystal inside grains. The carbide is dispersed and distributed in the crystal boundary to play a role in strengthening. Under the action of high-temperature and high-stress creep, creep pores and grain boundary microcracks are found in the two material structures, and carbides are precipitated along the grain boundaries and distributed in a membranization manner.
FIG. 4 is a graph illustrating the results of a durability test of the turbine vane and transition section materials in the as-received and creep-damaged states. As the endurance test temperature increases, the stress rupture life of the original state and creep damage state transition section and turbine vane material decreases.
FIG. 5 is the calculation result of the residual creep life of the high-temperature component material in service state. The error between the residual creep life estimation value obtained by the residual creep life estimation method and the life test average value is less than 10 percent.
Referring to fig. 2, the basic principle of the present invention is: the creep damage accumulation of the high-temperature component material is regarded as a linear process, namely the service course of the component is converted into the creep service life consumption rate, the creep service life consumption rate and the service life are approximately in direct proportion under constant temperature and stress, and when the creep service life accumulation consumption rate reaches a critical value of 1, the service component material is regarded as being damaged. For the high-temperature static component of the gas turbine in service, the creep damage is mainly influenced by temperature due to higher temperature load and smaller mechanical stress, and the main forms are represented by coarse structures and material aging. And analyzing the metallographic structure morphology characteristics of the typical dangerous part material by metallographic detection, wherein the metallographic structure morphology characteristics comprise creep damage structure characteristics such as gamma', carbide, TCP phase, crystal boundary morphology and the like, judging the creep damage degree of the service part according to the metallographic structure, and determining the temperature condition of a endurance test. As the performance state of the component material after creep damage changes, the permanent test samples are required to be respectively cut from the original component material and the service component and subjected to accelerated test (the accelerated durable service life test value is respectively recorded as T) t And t t ) Obtaining creep life consumption rate t of the service component material under the accelerated condition t /T t (to improve accuracy, it may take more than t if sampling conditions allow t Test value). Assuming the service time of the service state component as t s With a residual creep life of T S The creep life consumption rate of the in-service part under the in-service condition is t s /(t s +T S ). And when the sum of the creep life consumption rate of the original state component material and the creep life consumption rate of the service state component material tends to a critical value, the service component material is damaged. At known t s 、t t 、T t Under the condition of (1), the residual creep life T of the high-temperature part of the gas turbine in service can be calculated and obtained S . Is calculated by the formulat s /(t s +T S )+t t /T t =1. Taking the Nimonic263 deformation high-temperature alloy material used for the service transition section and the FSX414 casting high-temperature alloy material used for the turbine stationary blade as examples, the residual creep life evaluation values of the Nimonic263 deformation high-temperature alloy material used for the transition section obtained by applying the residual creep life evaluation method are 432h, 420h and 467h respectively, and the average value of the residual creep life evaluation values is about 439.7h; the residual creep life estimates for the FSX414 cast cobalt-based superalloy materials used for the stationary turbine vanes were 510h, 506h, 526h, respectively, with an average of about 510.4h.
The embodiment result shows that the method for evaluating the residual creep life of the high-temperature static component material of the service gas turbine is combined with actual creep damage and endurance life tests, not only takes the actual damage organization state of the service component into consideration, but also takes the problems of large error, time consumption and the like of the traditional method for evaluating the residual creep life by using the traditional double-logarithmic coordinate endurance life curve into consideration, and finally obtains the residual creep life of the high-temperature component material through quantitative calculation of a small amount of endurance life test data. The method is simple to operate, reliable, accurate in result, high in applicability and universality, capable of meeting the requirement of residual life evaluation of the high-temperature components of the gas turbine and guiding reasonable formulation of maintenance plans.
The invention discloses a method for evaluating the residual creep life of a high-temperature static part material of a service gas turbine, which mainly comprises metallographic structure observation, endurance test and life calculation analysis, and solves the problems of large error, time consumption and the like of the traditional residual creep life evaluation method adopting a dual-logarithmic-coordinate endurance life curve. The method combines metallographic examination and endurance test methods, considers the actual material aging and damage states of the parts under different service time, samples from the actual service parts, determines the accelerated endurance test conditions, and quantitatively calculates and obtains the residual creep life of the high-temperature static part material of the gas turbine according to test data.
The method combining metallographic examination and endurance life experiment not only considers the actual damage structure state of the service part, but also considers the problems of the traditional residual creep life evaluation method based on the log-log coordinate endurance life curve, finally obtains the residual creep life of the high-temperature part material through a small amount of endurance life tests and quantitative calculation, and has extremely strong applicability and accuracy.
The method for evaluating the residual creep life can predict the residual creep life of the component material, and the creep life is a main parameter for determining the aging degree of the component material and whether to repair and prolong the life, so that the method is not only used for establishing a basis of an overhaul period, but also can be used for establishing a basis of whether to repair and prolong the life, and has wide application prospect.
By adopting the residual creep life evaluation method, the residual creep life value of the component material can be accurately obtained. Based on the evaluation, a repair cycle may be established, while the health of the component may be determined, and a determination may be made as to whether the component may continue to be placed in service, repaired, and scrapped. For the components which can be repaired and have prolonged service life, the components can be continuously used for the next overhaul period after being repaired and prolonged service life, so that the rejection rate of the components is reduced, and great economic benefit is brought.
The method for evaluating the residual creep life mainly comprises the steps of sample interception, metallographic observation, endurance test, life calculation analysis and the like, the main evaluation processes of different high-temperature component materials are basically the same, the test testing workload is less, and the timeliness is high. Therefore, the recovery method provided by the invention has the advantages of low cost, simplicity in operation, high timeliness, convenience for flow operation, strong applicability and universality, and can meet the requirement of residual life evaluation of the high-temperature components of the gas turbine, and guide the reasonable formulation of the maintenance plan and the determination of the repair life-prolonging scheme.
The above-mentioned contents are only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited thereby, and any modification made on the basis of the technical idea of the present invention falls within the protection scope of the claims of the present invention.
Claims (9)
1. A method for evaluating the residual creep life of a high-temperature static component material of a gas turbine in service is characterized by comprising the following steps of:
1) Obtaining a metallographic specimen and a lasting sample of a typical damaged part of the damaged part, and obtaining a lasting sample of a corresponding part of the damaged part in an original state;
2) Acquiring creep damage structure characteristics of a damaged part of a metallographic sample;
3) Obtaining the durable life data t of the durable sample of the damaged part under the test condition t And obtaining the durable life data T of the durable sample of the original state part under the same test condition t ；
4) According to the persistent lifetime data t t And persistent lifetime data T t Determining the residual creep life T of a service part S ；
The residual creep life T of the service part S The calculation method of (2) is as follows:
t s /(t s +T S )+t t /T t ＝1
wherein, t s For the service time of the component, T S The remaining creep life of the component.
2. The method for evaluating the residual creep life of the material of the high-temperature static component of the gas turbine in service according to claim 1, wherein the metallographic specimen is detected after being ground, polished and corroded in the step 2 to obtain the morphological characteristics of the metallographic structure.
3. The method for evaluating the residual creep life of the material of the high-temperature static component of the gas turbine in service according to claim 1, wherein the creep damage organization characteristics in the step 2 comprise gamma', TCP phases, grain boundary morphology, composition, morphology, size and volume fraction of carbides.
4. The method for residual creep life evaluation of a high temperature static component material of a gas turbine in service of claim 1, wherein the test conditions include stress and temperature, and the test temperature is higher than the service temperature.
5. The method for evaluating the residual creep life of the material of the high-temperature static component of the gas turbine in service according to claim 4, wherein the temperature is 900-1100 ℃.
6. The method for evaluating the residual creep life of the material of the high-temperature static component of the gas turbine in service according to claim 1, wherein in the step 3, a high-temperature endurance tensile testing machine is used for endurance tests under stress and different heating conditions, the number of the tests is 2-4, and endurance life data are obtained.
7. The method of claim 1, wherein the step 3 of obtaining a plurality of endurance life data t is performed by using a plurality of creep life evaluation methods t Then, the corresponding residual creep life T is calculated S And then averaging the values to obtain the residual creep life value of the service part.
8. The method for evaluating the residual creep life of a high temperature static component material of a gas turbine in service according to claim 1, wherein the damaged component is a nickel-based or cobalt-based superalloy material.
9. The method for the evaluation of the residual creep life of a material of a high temperature static component of a gas turbine IN service as recited IN claim 8, wherein the material of the damaged component is IN738, IN939, hastelloy X, FSX414, GTD-222, MGA1400, MAR-M200Hf, MAR-M002 or DS GTD 111.
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| CN113704915B (en) * | 2021-08-26 | 2023-09-19 | 华能国际电力股份有限公司 | Thermal barrier coating thermal fatigue life prediction method for turbine blade of heavy-duty gas turbine |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08262009A (en) * | 1995-03-23 | 1996-10-11 | Hitachi Ltd | Evaluation method of remaining life of high-temperature member |
| CN1945269A (en) * | 2006-10-09 | 2007-04-11 | 大连理工大学 | Method for predicting life and life consumption of high temperature member material |
| CN104502446A (en) * | 2014-11-27 | 2015-04-08 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Method for predicting service conditions of high-temperature alloy coating based on nondestructive testing technology |
| CN105158080A (en) * | 2015-05-12 | 2015-12-16 | 上海发电设备成套设计研究院 | Accelerated testing method for prediction of high temperature material creep life |
| JP2017083324A (en) * | 2015-10-29 | 2017-05-18 | 新日鐵住金株式会社 | Method for predicting remaining life of metal material |
| CN110411851A (en) * | 2019-07-22 | 2019-11-05 | 北京科技大学 | A kind of high-temperature alloy turbine blade military service Damage Evaluation and creep life prediction technique |
| CN110907475A (en) * | 2019-10-17 | 2020-03-24 | 上海发电设备成套设计研究院有限责任公司 | Method for evaluating residual life of martensite heat-resistant steel |
-
2020
- 2020-11-23 CN CN202011333042.9A patent/CN112525907B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08262009A (en) * | 1995-03-23 | 1996-10-11 | Hitachi Ltd | Evaluation method of remaining life of high-temperature member |
| CN1945269A (en) * | 2006-10-09 | 2007-04-11 | 大连理工大学 | Method for predicting life and life consumption of high temperature member material |
| CN104502446A (en) * | 2014-11-27 | 2015-04-08 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Method for predicting service conditions of high-temperature alloy coating based on nondestructive testing technology |
| CN105158080A (en) * | 2015-05-12 | 2015-12-16 | 上海发电设备成套设计研究院 | Accelerated testing method for prediction of high temperature material creep life |
| JP2017083324A (en) * | 2015-10-29 | 2017-05-18 | 新日鐵住金株式会社 | Method for predicting remaining life of metal material |
| CN110411851A (en) * | 2019-07-22 | 2019-11-05 | 北京科技大学 | A kind of high-temperature alloy turbine blade military service Damage Evaluation and creep life prediction technique |
| CN110907475A (en) * | 2019-10-17 | 2020-03-24 | 上海发电设备成套设计研究院有限责任公司 | Method for evaluating residual life of martensite heat-resistant steel |
Non-Patent Citations (2)
| Title |
|---|
| 基于Ω方法的T/P91耐热钢蠕变持久寿命预测;王峥等;《动力工程学报》;20190515;第39卷(第05期);第425-432页 * |
| 烟气轮机涡轮盘高温合金剩余寿命预测;韦家虎等;《失效分析与预防》;20080815;第3卷(第03期);第65-68页 * |
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