CN105403582A - Damage evaluation method of service tissue of gas turbine blade - Google Patents
Damage evaluation method of service tissue of gas turbine blade Download PDFInfo
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Abstract
The present invention discloses a damage evaluation method of a service organization of a gas turbine blade, and belongs to the technical field of high-temperature alloys. The method is as below: first, simulating rules of tissue damage and performance degradation service and the corresponding relation between tissue damage and performance degradation in the service process according to a high-temperature alloy material for hot end component; establishing a tissue damage characteristic spectrum and a corresponding performance degradation database of the high-temperature alloy material for hot end component; then conducting comparison analysis by using the actual service damage state and the tissue damage characteristic spectrum and the performance degradation database of the high-temperature alloy material for hot end component; combined with the design requirements of the hot end component, establishing a high-temperature alloy hot end component service damage detection and evaluation standard database; and finally comparing the actual service tissue and performance data of high-temperature alloy hot end component material and tissue and performance data in the database, and presenting the results of service blade damage evaluation.
Description
Technical field
The present invention relates to technical field of high temperature alloy, particularly a kind of combustion engine blade military service tissue damage evaluation method.
Background technology
Nickel base superalloy has excellent elevated temperature strength, oxidation and creep resistance, is thus widely used in the high-temperature component making key position in gas turbine and aeromotor.In-service, these parts not only cause fatigue damage because repeatedly starting a transient state load cycle of stopping, and owing to working under certain steady temperature for a long time, and also can the time of origin creep impairment of being correlated with.Ru Bian ?the reciprocation of fatigue often become its main failure mode.A large amount of research work shows: the experiment parameters such as the low-cycle fatigue life of high-temperature alloy blades and temperature, cycle frequency, loading wave mode and retention time are closely related.Evaluate high-temperature alloy blades military service degree of impairment and have many methods, as linear progressive damage method, strain range partitioning method, strain energy differentiating approach, frequency separation method, damage function method etc.Although these methods demonstrate preferably fatigue life prediction ability in some materials, but Ru Bian ?Pi Lao ?carry out life prediction under the interactive condition of environment three time, then show certain limitation, still can not meet the actual demand of combustion engine blade service life prediction.Therefore, be necessary to invent a kind of new blade service life Forecasting Methodology.
Summary of the invention
The object of the present invention is to provide a kind of combustion engine blade military service tissue damage evaluation method, the method is a kind of new blade service life Forecasting Methodology, can meet combustion engine blade service life prediction actual demand.
For achieving the above object, the technical solution adopted in the present invention is as follows:
A kind of combustion engine blade military service tissue damage evaluation method, this evaluation method comprises the steps:
(1) according to hot-end component high-temperature alloy material tissue damage and performance degradation rule and the corresponding relation between damaged tissue and degraded performance in Simulated Service process, hot-end component high-temperature alloy material tissue damage characteristic spectrum and corresponding Performance Degradation Data storehouse in Simulated Service process is set up;
(2) according to hot-end component alloy tissue damage and performance degradation rule and the corresponding relation between damaged tissue and degraded performance in actual military service process, hot-end component alloy tissue damage characteristic spectrum and corresponding Performance Degradation Data storehouse in actual military service process is set up;
(3) tissue damage characteristic spectrum and performance data in the actual military service process of hot-end component alloy in tissue damage characteristic spectrum in hot-end component high-temperature alloy material Simulated Service process in step (1) database and performance data and step (2) database are compared, and in conjunction with the designing requirement of hot-end component, set up high temperature alloy hot-end component military service tissue damage evaluation criterion database;
(4) the combustion engine blade material that reality is on active service is sampled, fabric analysis and performance test are carried out to blade material sample and and damage characteristic collection of illustrative plates in step (3) standard database of advising and performance data contrast, provide the combustion engine blade military service lesion assessment result of this actual military service.
In step (4), the process sampled the combustion engine blade of reality military service is as follows: three xsects A1, A2 and A3 are cut in blade position, lay respectively at 1/3 of blade height, 2/3 and blade root place, three xsects are respectively chosen four test points, the process of choosing is: on each xsect, mark leading edge (leading edge), exhaust limit (trailing edge), leaf basin, blade back four test points respectively, be denoted as Q, H, P, B, wherein Q, H point lays respectively in leading edge and trailing edge radius, and P, B point lays respectively at leaf basin and the blade back at 1/3 chord length place; Other requirements are undertaken by GB/T13298.
In step (4), the process of blade material sample being carried out to fabric analysis is: the structure observation carrying out blade material sample under a scanning electron microscope, sample microstructural characterisation parameter is that dendrite does γ ' mutually and interdendritic carbides and crystal boundary, respectively the relative area mark of the appearance and size of detection interdendritic district γ ' phase, interdendritic and crystal boundary area carbonide; Standard diagram relative method or sizing technique is adopted to characterize microstructure and evaluate.The process characterizing sample microstructure and evaluate is as follows:
A the visual field of collection and dendrite are done γ ' and are on active service mutually and damage rating scale collection of illustrative plates and compare by (), be γ ' damage rank mutually with the damage rank corresponding to the immediate normal pictures of detected image.Fig. 2 is that dendrite is done γ ' and to be on active service mutually damage rating scale figure, does γ ' phase degree of degeneration and is divided into I to III level from light to heavy: I level by dendrite---normal, and II level---slight damage, III level---major injury.
B are on active service and damage rating scale collection of illustrative plates and compare in the visual field of collection and interdendritic carbides by (), be carbonide damage rank with the damage rank corresponding to the immediate normal pictures of detected image.Fig. 3 is interdendritic carbides military service damage rating scale figure, is divided into I to III level from light to heavy: I level by interdendritic carbides degree of degeneration---normal, and II level---slight damage, III level---major injury.
Principle and the beneficial effect of evaluation method of the present invention are as follows:
According to hot-end component high-temperature alloy material tissue damage and performance degradation rule and corresponding relation of damaging between injured tissue ?degraded performance thereof in Simulated Service process, set up hot-end component high-temperature alloy material tissue damage characteristic spectrum and corresponding Performance Degradation Data storehouse.Compared by the actual military service faulted condition of hot-end component and parts high-temperature alloy material military service damage characteristic collection of illustrative plates and performance database, and in conjunction with the designing requirement of hot-end component, set up high temperature alloy hot-end component military service damage check evaluation criterion database.Utilize the structure and properties data in the high temperature alloy hot-end component material military service structure and properties data of actual measurement and database to contrast, finally provide blade military service Damage Evaluation result.
Accompanying drawing explanation
Fig. 1 is combustion engine blade sample position of the present invention schematic diagram; Wherein: (a) blade blade sampling cross section; (b) blade profile sampling and testing position.
Fig. 2 is that brilliant dry γ ' is on active service mutually and damages judge picture; Wherein: (a) I grade; (b) II grade; (c) III grade.
Fig. 3 is interdendritic carbides military service damage judge picture; Wherein: (a) I grade; (b) II grade; (c) III grade.
Fig. 4 is the typical enduring quality of different tissues damage.
Fig. 5 is γ ' the tissue contrast of military service blade and standard analog military service blade; Wherein: (a) military service blade, 25000h; (b) standard analog military service blade, 24000h.
Fig. 6 is the grain boundary carbide tissue contrast of military service blade and standard analog military service blade; Wherein: (a) military service blade, 25000h; (b) standard analog military service blade, 24000h.
Embodiment
Below in conjunction with accompanying drawing in detail the present invention is described in detail.
The present invention is combustion engine blade military service tissue damage evaluation method, and this evaluation method comprises the steps:
1, according to hot-end component high-temperature alloy material tissue damage and performance degradation rule and the corresponding relation between damaged tissue and degraded performance in Simulated Service process, hot-end component high-temperature alloy material tissue damage characteristic spectrum and corresponding Performance Degradation Data storehouse in Simulated Service process is set up;
2, according to hot-end component alloy tissue damage and performance degradation rule and the corresponding relation between damaged tissue and degraded performance in actual military service process, hot-end component alloy tissue damage characteristic spectrum and corresponding Performance Degradation Data storehouse in actual military service process is set up;
3, tissue damage characteristic spectrum and performance data in the actual military service process of hot-end component alloy in tissue damage characteristic spectrum in hot-end component high-temperature alloy material Simulated Service process in step (1) database and performance data and step (2) database are compared, and in conjunction with the designing requirement of hot-end component, set up high temperature alloy hot-end component military service tissue damage evaluation criterion database;
4, the combustion engine blade material that reality is on active service is sampled, fabric analysis and performance test are carried out to blade material sample and and damage characteristic collection of illustrative plates in step (3) standard database of advising and performance data contrast, provide the combustion engine blade military service lesion assessment result of this actual military service.
The process that the combustion engine blade of 5, being on active service to reality samples is as follows: as shown in Figure 1, three xsects A1, A2 and A3 are cut in blade position, lay respectively at 1/3 of blade height, 2/3 and blade root place, three xsects are respectively chosen four test points, the process of choosing is: on each xsect, mark leading edge (leading edge), exhaust limit (trailing edge), leaf basin, blade back four test points respectively, be denoted as Q, H, P, B, wherein Q, H point lays respectively in leading edge and trailing edge radius, and P, B point lays respectively at leaf basin and the blade back at 1/3 chord length place; Other requirements are undertaken by GB/T13298.
6, to the process that blade material sample carries out fabric analysis be: the structure observation carrying out blade material sample under a scanning electron microscope, sample microstructural characterisation parameter is that dendrite does γ ' mutually and interdendritic carbides and crystal boundary, respectively the relative area mark of the appearance and size of detection interdendritic district γ ' phase, interdendritic and crystal boundary area carbonide; Standard diagram relative method or sizing technique is adopted to characterize microstructure and evaluate.
7, the process characterizing and evaluate sample microstructure is as follows:
A the visual field of collection and dendrite are done γ ' and are on active service mutually and damage rating scale collection of illustrative plates and compare by (), be γ ' damage rank mutually with the damage rank corresponding to the immediate normal pictures of detected image.Fig. 2 is that dendrite is done γ ' and to be on active service mutually damage rating scale figure, does γ ' phase degree of degeneration and is divided into I to III level from light to heavy: I level by dendrite---normal, and II level---slight damage, III level---major injury.
B are on active service and damage rating scale collection of illustrative plates and compare in the visual field of collection and interdendritic carbides by (), be carbonide damage rank with the damage rank corresponding to the immediate normal pictures of detected image.Fig. 3 is interdendritic carbides military service damage rating scale figure, is divided into I to III level from light to heavy: I level by interdendritic carbides degree of degeneration---normal, and II level---slight damage, III level---major injury.
8, carry out performance evaluation to the sample gathered, and contrast with standard performance result, standard performance is shown in Fig. 4.
9, comprehensive above test result in conjunction with the designing requirement of hot-end component, provide final appraisal results.
Embodiment 1
According to the corresponding relation of hot-end component high-temperature alloy material in Simulated Service process between tissue damage and performance degradation rule and damaged tissue-degraded performance thereof, set up hot-end component high-temperature alloy material tissue damage characteristic spectrum and corresponding Performance Degradation Data storehouse.According to the corresponding relation of hot-end component alloy in actual military service process between tissue damage and performance degradation rule and damaged tissue-degraded performance thereof, set up hot-end component alloy structure damage characteristic collection of illustrative plates and corresponding Performance Degradation Data storehouse.Compared by damage characteristic collection of illustrative plates in parts high-temperature alloy material Simulated Service process and performance data and hot-end component alloy actual military service damage characteristic collection of illustrative plates and performance data, and in conjunction with the designing requirement of hot-end component, provide evaluation criterion.Sample the DZ411 blade material that reality is on active service, sample position is by Fig. 1 requirement, and sample corrosion is undertaken by GB/T13298.γ ' shows recommendation mutually and adopts electrolytic corrosion method, and metallographic sample is at 10mlHNO
3+ 30mlHCl+40mlC
3h
8o
3electrolytic corrosion in solution, electrolytic parameter is 7 ~ 10V/10s.Carbide Phases display is recommended to adopt chemical etching method, at 17mlHNO
3+ 100mlHCl+7.5gCuCl
2+ 7.5gFeCl
3deep etch 10 ~ 15min in solution.Structure observation carries out under a scanning electron microscope.Microstructural characterisation parameter is that dendrite does γ ' mutually and interdendritic carbides and crystal boundary, respectively the relative area mark of the appearance and size of detection interdendritic district γ ' phase, interdendritic and crystal boundary area carbonide.Standard diagram relative method or sizing technique is adopted to characterize microstructure and evaluate.The visual field of collection and dendrite are done γ ' to be on active service mutually and to damage rating scale collection of illustrative plates and compare, be γ ' with the damage rank corresponding to the immediate normal pictures of detected image and damage rank mutually.Fig. 5 be dendrite do γ ' be on active service mutually damage judge picture, doing γ ' phase degree of degeneration by dendrite is III level---major injury.Are on active service in the visual field of collection and interdendritic carbides and damage rating scale collection of illustrative plates and compare, be carbonide with the damage rank corresponding to the immediate normal pictures of detected image and damage rank.Fig. 6 is interdendritic carbides military service damage judge picture, is III level---major injury by interdendritic carbides degree of degeneration.Performance test is carried out to the sample gathered, close with standard performance result.Comprehensive above test result, blade injury degree is major injury.Prediction blade active time 24000 hours, actual active time 25000 hours.
Embodiment 2
Sample the DZ411 blade material that reality is on active service, do γ ' phase, interdendritic carbides and alloy sample enduring quality data by dendrite, the active time of prediction blade is 5200 hours, and actual DZ411 alloy vane is on active service 5100 hours.
Embodiment 3
Sample the DZ411 blade material that reality is on active service, do γ ' phase, interdendritic carbides and alloy sample enduring quality data by dendrite, the active time of prediction blade is 10800 hours, and actual DZ411 alloy vane is on active service 11500 hours.
Embodiment 4
Sample the DZ411 blade material that reality is on active service, do γ ' phase, interdendritic carbides and alloy sample enduring quality data by dendrite, the active time of prediction blade is 14000 hours, and actual DZ411 alloy vane is on active service 14800 hours.
Claims (5)
1. a combustion engine blade military service tissue damage evaluation method, is characterized in that: this evaluation method comprises the steps:
(1) according to hot-end component high-temperature alloy material tissue damage and performance degradation rule and the corresponding relation between damaged tissue and degraded performance in Simulated Service process, hot-end component high-temperature alloy material tissue damage characteristic spectrum and corresponding Performance Degradation Data storehouse in Simulated Service process is set up;
(2) according to hot-end component alloy tissue damage and performance degradation rule and the corresponding relation between damaged tissue and degraded performance in actual military service process, hot-end component alloy tissue damage characteristic spectrum and corresponding Performance Degradation Data storehouse in actual military service process is set up;
(3) tissue damage characteristic spectrum and performance data in the actual military service process of hot-end component alloy in tissue damage characteristic spectrum in hot-end component high-temperature alloy material Simulated Service process in step (1) database and performance data and step (2) database are compared, and in conjunction with the designing requirement of hot-end component, set up high temperature alloy hot-end component military service tissue damage evaluation criterion database;
(4) the combustion engine blade material that reality is on active service is sampled, fabric analysis and performance test are carried out to blade material sample and and damage characteristic collection of illustrative plates in step (3) standard database of advising and performance data contrast, provide the combustion engine blade military service lesion assessment result of this actual military service.
2. combustion engine blade military service tissue damage evaluation method according to claim 1, it is characterized in that: in step (4), the process sampled the combustion engine blade of reality military service is as follows: three xsects A1, A2 and A3 are cut in blade position, lay respectively at 1/3 of blade height, 2/3 and blade root place, three xsects choose some test points.
3. combustion engine blade military service tissue damage evaluation method according to claim 2, it is characterized in that: on three xsects, respectively choose four test points, the process of choosing is: on each xsect, mark leading edge, trailing edge, leaf basin, blade back four test points respectively, be denoted as Q, H, P, B, wherein Q, H point lays respectively in leading edge and trailing edge radius, and P, B point lays respectively at leaf basin and the blade back at 1/3 chord length place; Other requirements are undertaken by GB/T13298.
4. combustion engine blade military service tissue damage evaluation method according to claim 1, it is characterized in that: in step (4), the process of blade material sample being carried out to fabric analysis is: the structure observation carrying out blade material sample under a scanning electron microscope, sample microstructural characterisation parameter is that dendrite does γ ' mutually and interdendritic carbides and crystal boundary, respectively the relative area mark of the appearance and size of detection interdendritic district γ ' phase, interdendritic and crystal boundary area carbonide; Standard diagram relative method or sizing technique is adopted to characterize microstructure and evaluate.
5. combustion engine blade military service tissue damage evaluation method according to claim 4, is characterized in that: the process characterizing sample microstructure and evaluate is as follows:
A the visual field of collection and dendrite are done γ ' and are on active service mutually and damage rating scale collection of illustrative plates and compare by (), be γ ' damage rank mutually with the damage rank corresponding to the immediate normal pictures of detected image.
B are on active service and damage rating scale collection of illustrative plates and compare in the visual field of collection and interdendritic carbides by (), be carbonide damage rank with the damage rank corresponding to the immediate normal pictures of detected image.
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| CN109187543A (en) * | 2018-09-26 | 2019-01-11 | 中国特种设备检测研究院 | A kind of in-service ethylene cracking tube embrittlement classification lifetime estimation method |
| 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 |
| CN110411850A (en) * | 2019-07-22 | 2019-11-05 | 北京科技大学 | A kind of appraisal procedure of high-temperature alloy turbine blade service condition |
| CN111366450A (en) * | 2020-04-21 | 2020-07-03 | 中国航发沈阳发动机研究所 | Method for evaluating service structure damage of nickel-based superalloy turbine blade |
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| CN105606288B (en) * | 2016-03-21 | 2019-03-29 | 北京科技大学 | A kind of experimental evaluation method of high-temperature alloy turbine blade military service stress |
| CN105606288A (en) * | 2016-03-21 | 2016-05-25 | 北京科技大学 | Experimental assessment method for high temperature alloy turbine blade service stress |
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| CN111465837B (en) * | 2017-12-21 | 2023-08-08 | 三菱重工业株式会社 | Life evaluation device and life evaluation method |
| CN109002628A (en) * | 2018-07-31 | 2018-12-14 | 天津大学 | A kind of elevated temperature strength prediction technique for the martensite steel degenerated based on microstructure |
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| CN109187543A (en) * | 2018-09-26 | 2019-01-11 | 中国特种设备检测研究院 | A kind of in-service ethylene cracking tube embrittlement classification lifetime estimation method |
| CN110411851B (en) * | 2019-07-22 | 2020-06-26 | 北京科技大学 | High-temperature alloy turbine blade service damage evaluation and creep life prediction method |
| CN110411850A (en) * | 2019-07-22 | 2019-11-05 | 北京科技大学 | A kind of appraisal procedure of high-temperature alloy turbine blade service condition |
| 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 |
| CN111366450A (en) * | 2020-04-21 | 2020-07-03 | 中国航发沈阳发动机研究所 | Method for evaluating service structure damage of nickel-based superalloy turbine blade |
| CN111639145A (en) * | 2020-06-19 | 2020-09-08 | 国电锅炉压力容器检验有限公司 | Method for evaluating service life of moving blade at hot end of gas turbine |
| CN114778684A (en) * | 2022-06-21 | 2022-07-22 | 张家港沙龙精密管业有限公司 | Steel pipe performance evaluation method and system based on service scene |
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