CN105403502A - Experiment assessment method of service temperature of high temperature alloy turbine blade - Google Patents
Experiment assessment method of service temperature of high temperature alloy turbine blade Download PDFInfo
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Abstract
The invention provides an experiment assessment method of the service temperature of a high temperature alloy turbine blade, and relates to experiment assessment of the service temperature of a DZ125 directional solidification high temperature alloy turbine blade. A corresponding relationship among the temperature, the time and the volume fraction of a primary gamma' phase in dendrite arm is determined through blade material laboratory heat exposure experiments according to a thermodynamic phase equilibrium principle. The substrate temperature of the service blade is assessed by using the relationship and the volume fraction of the primary gamma' phase of the blade after practical service for a period of time. The method eliminates complex influences of blade coating and gas film cooling on the service temperature of the blade, is reliable in assessment of the service temperature of the blade substrate, is suitable for being applied in engineering, and has strong engineering application values and wide prospect in the service temperature assessment of the DZ125 blade.
Description
Technical field
The invention belongs to Ni-based directionally solidified superalloy, DS superalloy blade technology field, be specifically related to a kind of experimental evaluation method of directional solidification turbo blade service temperature.
Background technology
Aeromotor is high complexity and accurate thermal machine, and the turbo blade as one of aeromotor most critical parts is the important hot-end component that the enthalpy of combustion gas and kinetic energy convert mechanical energy to.Along with improving constantly of aeromotor thrust-weight ratio, blade exterior fuel gas temperature improves constantly, the usually fusing point of far super blade material, therefore need to utilize the mode such as coating, surperficial gaseous film control, internal cooling hole to reduce blade base temperature, but add difficulty also to the substrate temperature measurement and calculation of blade.Meanwhile, because from firing chamber, combustion gas out exists thermograde, the complicacy of turbo blade self structure in addition, the thermograde during different parts work of turbo blade is usually comparatively large, and service temperature field is very uneven.But leaf temperature distribution is the important foundation of turbo blade leaf and cooling structure design, determines the important evidence examining point simultaneously when being also blade maintenance conditions, there is remarkable industrial application value.
At present, the numerical simulation method be based upon on boundary condition is the method predicting that leaf temperature field is the most general.But, due to turbine blade coating structure and cooling system complicacy and they are on the impact of result of calculation, the method for numerical evaluation is often difficult to the substrate temperature of Accurate Prediction blade.
Turbo blade is under arms in process, under being in creep effect that high-temperature high-pressure fuel gas and complex stress cause for a long time, inevitably can there is lesion regression in internal metallurgical tissue, as the decline of the alligatoring of γ ' phase, raft shape and volume fraction, the decomposition of carbonide and transformation, the formation of crystal boundary γ ' phase film, the precipitation of the brittlement phase such as TCP and creep hole and crackle etc.The different parts of blade is due to the difference of operating mode, after being on active service, the degree of degeneration of tissue there are differences, characterize by quantifying blade be on active service after the degree of degeneration of microstructure can the Service Environment of indirect anti-leaf-pushing plate, make to utilize the microstructure assessment blade service temperature field of degenerating to become possibility, but there is no at present and degenerate tissue carried out quantizing and utilizes it to the relevant report of carrying out quantitative evaluation of the actual service temperature of blade.
Therefore, urgently invent a kind of service temperature experimental evaluation method of the directional solidification DZ125 high-temperature alloy turbine blade based on degenerate tissue, qualitative assessment is carried out to the substrate temperature of blade.
Summary of the invention
The object of this invention is to provide a kind of experimental evaluation method of the directional solidification DZ125 alloy turbine blade service temperature based on degenerate tissue.The method can be assessed the service temperature at each position of DZ125 alloy turbine blade blade, and Evaluation accuracy is ± 50 DEG C, and assessment result is more reliable, is applicable to engineer applied.
A kind of high-temperature alloy turbine blade service temperature experimental evaluation method, its core technology main points are: directional solidification DZ125 alloy turbine blade is that its phase composition is by the process of metastable state to equilibrium state transition in actual military service process, temperature is the determinative of the volume fraction of DZ125 alloy equilibrium state γ ' phase, also be the main influence factor of the volume fraction of DZ125 alloy metastable state γ ' phase simultaneously, the corresponding relation between temperature and time and the volume fraction of the γ ' phase in dendrite dry middle part can be set up thus, based on organizing quantized data, thus the actual service temperature of blade is assessed.Concrete assessment comprises the following steps:
1) because the design serviceability temperature of DZ125 alloy turbine blade blade is less than 1050 DEG C, consider that actual use Leaf exists the phenomenon of overtemperature simultaneously, the beat exposure experiment of different duration under different temperatures is carried out to turbo blade material DZ125 alloy, γ ' the phase volume fraction of alloy under the different duration of each temperature after beat exposure carries out quantitative statistics, the corresponding relation under obtaining different time between each temperature and a γ ' phase volume fraction subsequently.
2) a γ ' phase volume fraction of the DZ125 alloy vane a part after actual military service m hour is added up, obtain a γ ' phase volume fraction of military service m hour blade.
3) be averaged service temperature and the assessment of the highest service temperature, after m hour that a γ ' phase volume fraction of the DZ125 alloy vane of military service m hour of statistics gained and laboratory beat exposure is obtained, the corresponding relation of a γ ' phase volume fraction and temperature contrasts, and obtains the average service temperature of blade; After m*15%-35% hour that a γ ' phase volume fraction of the DZ125 alloy vane of military service m hour of statistics gained and laboratory beat exposure is obtained, the corresponding relation of a γ ' phase volume fraction and temperature contrasts, and obtains the highest service temperature of blade.
Described actual active time m≤blade serviceable life.
Under described DZ125 alloy carries out different temperatures different duration beat exposure experiment temperature be 900 DEG C, 950 DEG C, 1000 DEG C, 1050 DEG C and 1100 DEG C, beat exposure duration is no more than the serviceable life of blade, and within the scope of this duration with blade actual active time m isometric or isometric with actual active time m*15% ~ 35% of blade.
The described beat exposure isometric with the actual active time m of blade is tested and is used for assessing average service temperature, and the beat exposure isometric with actual active time m*15% ~ 35% of blade is tested and be used for assessing the highest service temperature.
The invention has the advantages that, the corresponding relation established between temperature and time and the volume fraction of a γ ' phase is tested by beat exposure, utilize the volume fraction of a γ ' phase of the military service certain hour rear blade matrix of this relation and actual measurement, achieve the quantitative evaluation to military service blade base temperature.Compared with numerical simulation method, the process eliminate blade coatings and gaseous film control to the complex effects of blade service temperature, the precision in assessment blade base service temperature is ± 50 DEG C.Assessment result is more reliable, is applicable to engineer applied, in the service temperature assessment of DZ125 blade, have stronger engineer applied meaning and bright prospects.
Accompanying drawing explanation
Fig. 1 is DZ125 alloy vane tenon position xsect dendrite dry place microstructure after military service 900h.
Fig. 2 is DZ125 alloy xsect dendrite dry place microstructure after standard heat treatment.
Fig. 3 is the corresponding relation of DZ125 alloy γ ' phase volume fraction and service temperature and duration.
Fig. 4 is military service 900 hours DZ125 alloy vane a part xsect dendrite dry place microstructures.
Embodiment
Following example will be further described the present invention, so that those skilled in the art understand advantages and features of the invention better.
First, verify that whether the original structure of DZ125 military service blade and sheet material DZ125 alloy is approximate or consistent.Observe the microstructure of DZ125 alloy vane tenon position and the blade material DZ125 alloy after standard heat treatment, the pattern of the two γ ' phase, size and cube degree are very close, respectively as shown in Figures 1 and 2.With reference to the volume fraction of the grid number point standard measure statistics γ ' phase in GB/T15749.Set 216 grid intersection points, count 1 mutually when intersection point is arranged in γ ', count 0.5 when intersection point is positioned at γ ' with basal body interface, count 0 when intersection point is arranged in matrix, the ratio of above-mentioned statistics and intersection point sum is γ ' phase volume fraction.In each observation place, at least the nonoverlapping visual field of random selecting 5 calculates γ ' phase volume fraction, averages as measurement result (following Statistical Volume mark all uses the method).γ ' phase volume fraction through statistics DZ125 alloy and blade tenon is about 67%, and under empirical tests virgin state, the γ ' phase volume fraction of the two is also consistent substantially.
This type blade phase of overhauling is 300h, and the actual active time of the blade therefore obtained mostly is 300h, 600h and 900h, and current MaLS is 900h.Therefore blade material DZ125 alloy is carried out to the simulated experiment of beat exposure 100h, 300h, 600h and 900h respectively at 900 DEG C, 950 DEG C, 1000 DEG C, 1050 DEG C, 1100 DEG C.Quantitative statistics is carried out to the volume fraction of γ ' phase after beat exposure, obtains the volume fraction of the γ ' phase after the different duration beat exposure of each temperature, thus establish service temperature and the corresponding relation between time and the volume fraction of γ ' phase, as shown in Figure 3.
The definition average service temperature of blade and the highest service temperature: in the whole military service process of blade, assuming that the service temperature of blade is constant; In known active time, blade equivalent or the temperature corresponding to approximate damaged tissue are average service temperature.But, the service temperature of blade in whole military service process is not constant, aircraft take off and active time shared by the larger running status such as ramp-up period accounts for the 15%-35% of total active time, but the tissue caused and life damage account for more than 80% of total damage.Therefore, assuming that the larger running status of blade accounts for the 15%-35% of total active time, due to higher temperature and the stronger damaging action of larger running status, within the 15%-35% time period of known active time, blade equivalent or the service temperature corresponding to approximate damaged tissue are the highest service temperature of blade.
Carry out quantitative statistics to the volume fraction of DZ125 alloy vane blade a part γ ' phase after military service 900h actual in Fig. 4, the volume fraction obtaining its γ ' phase is 59.8%.
Contrasted by corresponding relation under the volume fraction at this position and 900h in Fig. 3 between service temperature and the volume fraction of γ ' phase, obtaining its average service temperature is 950 ~ 1000 DEG C.The volume fraction at this position and 300h(are accounted for 33% of total military service duration) under corresponding relation between service temperature and the volume fraction of γ ' phase contrast, obtaining its highest service temperature is 1000 ~ 1050 DEG C.
Obtain the average service temperature of DZ125 alloy vane and the highest service temperature by assessment, due in the actual military service process of blade, its service state is more close with the hypothesis of the highest service temperature, and namely blade service temperature is constantly change.And because the temperature difference of high temperature and low temperature is comparatively large, result in the overwhelming majority that damage that the high-temperature service stage shorter when accounting for causes but accounts for total damage.Therefore, the assessment result of the highest service temperature is closer to the actual service condition of blade, and this assessment result has stronger engineer applied meaning in the design and maintenance of blade.
Claims (3)
1. an experimental evaluation method for high-temperature alloy turbine blade service temperature, is characterized in that, specifically comprise the following steps:
1) the beat exposure experiment of different duration under different temperatures being carried out to turbo blade material DZ125 alloy, γ ' the phase volume fraction of alloy under the different duration of each temperature after beat exposure carries out quantitative statistics, the corresponding relation under obtaining different time between each temperature and a γ ' phase volume fraction subsequently;
2) a γ ' phase volume fraction of the DZ125 alloy vane a part after actual military service m hour is added up, obtain a γ ' phase volume fraction of military service m hour blade;
3) be averaged service temperature and the assessment of the highest service temperature, after m hour that a γ ' phase volume fraction of the DZ125 alloy vane of military service m hour of statistics gained and laboratory beat exposure is obtained, the corresponding relation of a γ ' phase volume fraction and temperature contrasts, and obtains the average service temperature of blade; In m*15% ~ 35% hours window obtain a γ ' phase volume fraction of the DZ125 alloy vane of military service m hour of statistics gained and laboratory beat exposure, the corresponding relation of a γ ' phase volume fraction and temperature contrasts, and obtains the highest service temperature of blade.
2. the experimental evaluation method of high-temperature alloy turbine blade service temperature as claimed in claim 1, is characterized in that, described actual active time m≤blade serviceable life.
3. the experimental evaluation method of high-temperature alloy turbine blade service temperature as claimed in claim 1, it is characterized in that, under described DZ125 alloy carries out different temperatures different duration beat exposure experiment temperature be 900 DEG C, 950 DEG C, 1000 DEG C, 1050 DEG C and 1100 DEG C, beat exposure duration is no more than the serviceable life of blade, and within the scope of this duration with blade actual active time m isometric or isometric with actual active time m*15% ~ 35% of blade.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN112214875A (en) * | 2020-09-11 | 2021-01-12 | 东方电气集团东方汽轮机有限公司 | Method for evaluating real service temperature of workpiece through precipitated particle phase size |
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| CN102788811A (en) * | 2012-06-06 | 2012-11-21 | 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 temperature range of high-temperature alloy coating of segment of blading of gas turbine |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| 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 |
| CN112214875A (en) * | 2020-09-11 | 2021-01-12 | 东方电气集团东方汽轮机有限公司 | Method for evaluating real service temperature of workpiece through precipitated particle phase size |
| CN112214875B (en) * | 2020-09-11 | 2022-03-22 | 东方电气集团东方汽轮机有限公司 | Method for evaluating real service temperature of workpiece through precipitated particle phase size |
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