CN108710747B - Method for determining 1Cr12Ni2WMoVNb martensitic stainless steel gas turbine blade shot peening optimal parameters - Google Patents
Method for determining 1Cr12Ni2WMoVNb martensitic stainless steel gas turbine blade shot peening optimal parameters Download PDFInfo
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D7/00—Modifying the physical properties of iron or steel by deformation
- C21D7/02—Modifying the physical properties of iron or steel by deformation by cold working
- C21D7/04—Modifying the physical properties of iron or steel by deformation by cold working of the surface
- C21D7/06—Modifying the physical properties of iron or steel by deformation by cold working of the surface by shot-peening or the like
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
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- G06F30/17—Mechanical parametric or variational design
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- G—PHYSICS
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- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2111/00—Details relating to CAD techniques
- G06F2111/06—Multi-objective optimisation, e.g. Pareto optimisation using simulated annealing [SA], ant colony algorithms or genetic algorithms [GA]
Abstract
The invention relates to an evaluation method, in particular to a method for determining the optimal parameters of shot peening strengthening of 1Cr12Ni2WMoVNb martensitic stainless steel gas turbine blades, which comprises the following steps: designing a test piece structure; shot blasting process of the test piece; testing fatigue of the test piece; analyzing the fatigue life; analyzing a residual stress field; and (4) analyzing roughness. The shot peening strengthening can effectively improve the high cycle fatigue life of parts, the effectiveness of improving the vibration fatigue life of the stainless steel material through shot peening strengthening under different shot peening parameters is verified through standard test piece design and test aiming at 1Cr12Ni2WMoVNb martensitic stainless steel turbine blades, the stainless steel test piece vibration fatigue test is designed, and the shot peening parameters with the best strengthening effect are determined. And (3) synthesizing the surface state and the vibration fatigue life of the strengthened test piece to obtain the optimal parameters suitable for shot peening strengthening of the 1Cr12Ni2WMoVNb stainless steel gas turbine blade product.
Description
The technical field is as follows:
the invention belongs to the technical field of energy power, and particularly relates to a method for determining optimal parameters of shot peening strengthening of 1Cr12Ni2WMoVNb martensitic stainless steel gas turbine blades.
Background art:
the shot peening strengthening can effectively prolong the fatigue life of the parts. For the gas turbine compressor blade, the obvious improvement of the fatigue life is one of important ways for improving the reliability of the engine, and the work has great significance. The 1Cr12Ni2WMoVNb is an excellent martensitic stainless steel and is widely adopted in the selection of design materials of gas turbine compressor blades at present. However, for the blade made of the 1Cr12Ni2WMoVNb stainless steel material, no relevant standard or literature research is carried out, and the optimal parameter of the shot blasting corresponding to the material is not given at present. The standard or research results only give empirical parameter ranges for stainless steel materials, and in practice there should be corresponding optimum parameters for different types of stainless steel.
The invention content is as follows:
the invention aims to provide the optimal shot peening strengthening parameters for the blades designed by adopting the 1Cr12Ni2WMoVNb stainless steel material, and improve the high cycle fatigue life of the blades to the maximum extent so as to improve the running reliability of a combustion engine and ensure the unit performance.
The technical scheme adopted by the invention is as follows: a method for determining optimal parameters of 1Cr12Ni2WMoVNb martensitic stainless steel gas turbine blade shot peening comprises the following steps:
step one, test piece structure design: designing a test piece structure according to HB/Z5277, wherein the test piece structure can represent the stress state of the blade most effectively, the thickness of the test piece is (3 +/-0.2) mm, the test piece is required to be consistent with the raw material standard of the prepared blade and is in the same furnace batch with the blade, and thus, the heat treatment state can be ensured to be consistent with the blade to the maximum extent; the processing process comprises forging piece-linear cutting-grinding-polishing;
step two, shot blasting process of the test piece: performing shot blasting treatment on the upper surface and the lower surface of the test piece according to HB/Z26 to cover the whole surface, and performing shot blasting strengthening of 0.08A (0.264N), 0.12A, 0.16A, 0.20A and 0.26A according to the shot blasting intensity level in the standard;
step three, specimen fatigue test: carrying out high-cycle fatigue tests on 5 groups of shot blasting test pieces and 1 group of non-shot blasting test pieces, taking the non-shot blasting test pieces as a search object of initial stress (amplitude), wherein the fatigue life of the non-shot blasting test pieces is 105 grades, finally determining the test amplitude (peak-peak value) to be 7.5mm through 10 initial tests, and finally determining the maximum vibration stress (near a fillet) of the whole test piece to be about 626MPa, and examining the shot blasting test pieces at the same or slightly higher stress level to finally find out the shot blasting strength value which can improve the fatigue life amplitude to the maximum;
step four, fatigue life analysis: counting and summarizing the fatigue life of each component under different shot blasting specifications, and carrying out data statistics and analysis according to HB/Z112;
step five, analyzing a residual stress field: in order to comprehensively examine the surface state changes of the test piece before and after shot blasting, the residual stress field and the roughness of the test piece are respectively measured, three points are selected at the part with larger stress of each test piece, and the longitudinal sigma is measured r2 And a transverse direction σ r1 2 pieces of the residual stress in each state (shot blasting and non-shot blasting) are selected for testing, and 1 piece of the residual stress in each state is subjected to a delamination test to examine a stress field in the depth direction;
step six, roughness analysis: and (3) detecting the roughness of the blade part under the determined shot blasting parameters, and measuring and analyzing the roughness Ra of at least 3 blades.
Further, the optimal parameters for shot peening strengthening of the gas turbine compressor blade designed and manufactured by 1Cr12Ni2WMoVNb martensitic stainless steel or similar martensitic stainless steel materials are determined; clearly, the shot blasting medium is S110 shot (or shot with equivalent size and material); the shot strength value is determined to be 0.08A (0.264N) (30% of floating, namely 0.264N-0.33N, can be achieved during actual strengthening); clearly, the depth of the residual stress field after shot blasting is more than or equal to 0.10mm, and the surface compressive stress is more than or equal to 590Mpa.
The invention has the beneficial effects that: the method provides optimal shot peening parameters for the blades designed by adopting the 1Cr12Ni2WMoVNb stainless steel material, and improves the high cycle fatigue life of the blades to the maximum extent so as to improve the running reliability of a combustion engine and ensure the performance of a unit. For the gas turbine compressor blade designed and manufactured by 1Cr12Ni2WMoVNb martensitic stainless steel, S110 pellets (or pellets with equivalent size and equivalent material) can be used for surface shot peening strengthening according to the shot peening strength of 0.08A (0.264N) (30% can float upwards in actual strengthening, namely 0.264N-0.33N), the coverage rate is more than or equal to 100%, the depth of a residual stress field is more than or equal to 0.10mm, and the surface pressure stress is more than or equal to 590MPa, so that the fatigue life of the blade can be optimally prolonged. The similar martensitic stainless steel material can be strengthened by adopting the same shot blasting parameters.
The shot peening strengthening can effectively improve the high cycle fatigue life of the parts. Aiming at a 1Cr12Ni2WMoVNb martensitic stainless steel gas turbine blade, the effectiveness of improving the vibration fatigue life of the stainless steel material by shot peening under different shot blasting parameters is verified through standard test piece design and test, the stainless steel test piece vibration fatigue test is designed, the shot blasting parameters with the best strengthening effect are determined, and the result shows that the high cycle fatigue strength of the strengthened blade is obviously improved, and the vibration median fatigue life of the test piece is improved by at least 8.5 times under the 685MPa vibration stress level. The surface state (roughness, residual stress and the like) and the vibration fatigue life of the strengthened test piece are integrated, and the optimal parameters suitable for shot peening strengthening of the 1Cr12Ni2WMoVNb stainless steel gas turbine blade product are obtained.
The specific implementation mode is as follows:
through a large number of experimental researches, the optimum parameters suitable for shot peening strengthening of 1Cr12Ni2WMoVNb stainless steel gas turbine blade products, including the contents of shot peening strength, surface roughness, formed residual stress fields and the like, are found out from the aspects of the surface state (roughness, residual stress and the like) and the vibration fatigue life after the test piece strengthening. Shot blasting is carried out according to HB/Z26 by adopting S110, and fatigue test is designed according to HB/Z5277, and the structural design, production and fatigue test process of the test piece are included.
And obtaining the optimal shot blasting parameters and the corresponding surface state through the test data meeting the sample statistical standard. The specific process is as follows:
1. test piece structure design
And designing a test piece structure according to HB/Z5277, wherein the test piece structure can represent the stress state of the blade most effectively, and the thickness of the test piece is (3 +/-0.2) mm. The test piece is required to be consistent with the raw material standard of the manufactured blade and is in the same furnace batch with the blade, so that the heat treatment state can be kept consistent with the blade to the maximum extent. The machining process comprises forging piece, linear cutting, grinding and polishing, so that the test piece can meet the design drawing requirements in all aspects.
2. Test piece shot blasting process
The shot peening of the upper and lower surfaces of the test piece was performed in accordance with HB/Z26 to cover the entire surface, particularly the round corner portions. Shot peening was performed at 0.08A (0.264N), 0.12A, 0.16A, 0.20A and 0.26A in accordance with the shot peening intensity levels suggested in the standards.
3. Specimen fatigue test
The high cycle fatigue test was performed on 5 groups of shot-blasted test pieces and 1 group of non-shot-blasted test pieces, and the fatigue life of the non-shot-blasted test pieces was preferably 105 levels, with the non-shot-blasted test pieces being the subject of the initial stress (amplitude) investigation. After 10 initial tests, the test amplitude (peak-to-peak) was finally determined to be 7.5mm, and the maximum vibration stress (near the fillet) of the entire test piece was about 626MPa. And (4) examining the stress level of the shot blasting test piece which is the same or slightly higher, and finally finding out the shot blasting strength value which can improve the fatigue life amplitude to the maximum.
4. Fatigue life analysis
The fatigue life of each component under different shot specifications is shown in table 1.
TABLE 1 summary of fatigue life of 6 test pieces under different shot blasting specifications
Data statistics and statistics were performed according to HB/Z112, with the final results summarized in Table 2.
TABLE 2 fatigue test results of samples subjected to different shot blasting treatments
| Test specification | Is not sprayed | 0.08A(0.264N) | Spraying 0.12A | Spraying 0.16A | Spraying 0.20A | Spray 0.26A |
| Fatigue life/10 5 Next time | 1.879 * | 17.847 * | 16.249 * | 6.394 * | 4.837 *1 | 8.57 *1 |
Note: the confidence of 95% is satisfied, and the maximum error is 5%.
The confidence 90% is satisfied, and the maximum error is 5%.
From the results, it is understood that the life of the test piece is improved by at least 8.5 times at the 0.08A (0.264N) shot strength. However, since the depth of field of the residual stress is related to the shot strength, the smaller the shot strength is, the shallower the effective depth of field of the compressive stress is, and in order to secure a certain depth of field of the residual compressive stress, no test item of shot strength < 0.08A (0.264N) was conducted. When the shot strength is 0.08A (0.264N), the fatigue life of the test piece is the highest.
5. Residual stress field analysis
In order to comprehensively examine the change of the surface state of the test piece before and after shot blasting, the measurement of the residual stress field of the test piece and the measurement of the roughness were respectively carried out. Selecting three points at the position with larger stress of each test piece, and measuring the longitudinal sigma r2 And a transverse direction σ r1 The residual stress of (a). 2 pieces were selected for each condition (shot, no shot) and tested. And a delamination test was performed on 1 of them, and the stress field in the depth direction was examined.
The residual stress on the test piece surface before and after shot blasting is shown in Table 3.
TABLE 3 surface residual stress before and after shot blasting of the test pieces
From the results, it is understood that the longitudinal stress before the shot blasting of the test piece is tensile stress, and the transverse stress is small compressive stress. After shot blasting, the stress is compressive in both directions and is relatively uniform. In order to further study the characteristics of the residual compressive stress field, a delamination test was performed on one of the shot-peening test pieces, and the results are shown in table 4.
TABLE 4 depth variation law of residual stress field
| Depth/mum | Longitudinal stress value/MPa | Transverse stress value/MPa |
| 0 | -715.52 | -656.19 |
| 20 | -798.90 | -721.63 |
| 40 | -763.99 | -775.65 |
| 60 | -520.68 | -527.78 |
| 80 | -90.19 | -71.77 |
| 110 | -14.55 | -23.66 |
| 130 | -41.35 | 8.67 |
| 160 | -42.35 | 7.59 |
| 200 | -15.21 | -4.44 |
| 240 | -25.87 | 15.82 |
The longitudinal stress is 0-0.255 mm in the whole testing depth, and the effective range of the transverse compressive stress is about 0-0.12 mm. The depth of the compressive stress layer can be more than or equal to 0.10mm, and the surface compressive stress range is about-590 to-768 MPa.
6. Roughness analysis
And (4) carrying out roughness detection on the blade part under the determined shot blasting parameters, and measuring the roughness Ra of 3 blades.
The result shows that the average roughness value before shot blasting is 0.12 mu m, the average roughness value after shot blasting is 0.3 mu m, and the general design requirements of the blade can be well met.
For the gas turbine compressor blade designed and manufactured by 1Cr12Ni2WMoVNb martensitic stainless steel, S110 pellets (or pellets with equivalent size and equivalent material) can be adopted to carry out surface shot peening strengthening according to the shot peening strength of 0.08A (0.264N) (30% floating up according to HB/Z26 standard in actual strengthening, namely 0.264N-0.33N), the coverage rate is more than or equal to 100%, the depth of a residual stress field is more than or equal to 0.10mm, and the surface pressure stress is more than or equal to 590MPa, so that the fatigue life of parts can be optimally improved.
Claims (1)
1. A method for determining the optimal parameters of shot peening strengthening of 1Cr12Ni2WMoVNb martensitic stainless steel gas turbine blades is characterized by comprising the following steps: the method comprises the following steps:
step one, test piece structure design: designing the thickness of a test piece structure according to HB/Z5277 to be (3 +/-0.2) mm, wherein the requirement of the test piece is consistent with the raw material standard of the prepared blade, and the test piece and the blade are in the same furnace batch; the processing process comprises forging piece-linear cutting-grinding-polishing;
step two, test piece shot blasting process: performing shot blasting treatment on the upper surface and the lower surface of the test piece according to HB/Z26 to cover the whole surface, and performing shot blasting strengthening of 0.08A, 0.12A, 0.16A, 0.20A and 0.26A according to the shot blasting intensity level in the standard;
step three, specimen fatigue test: carrying out high cycle fatigue tests on 5 groups of shot blasting test pieces and 1 group of non-shot blasting test pieces, taking the non-shot blasting test pieces as a groping object of initial stress, setting the fatigue life of the non-shot blasting test pieces to be 105 grades, finally determining the test amplitude to be 7.5mm and the maximum vibration stress of the whole test piece to be 626MPa through 10 initial tests, checking the shot blasting test pieces at the same stress level, and finally finding out the shot blasting strength value which can improve the fatigue life amplitude to the maximum extent;
step four, fatigue life analysis: counting and summarizing the fatigue life of each component under different shot blasting specifications, and carrying out data statistics and analysis according to HB/Z112;
step five, analyzing a residual stress field: in order to comprehensively examine the surface state changes of the test piece before and after shot blasting, the residual stress field and the roughness of the test piece are respectively measured, three points are selected at the part with larger stress of each test piece, and the longitudinal sigma is measured r2 And a transverse direction σ r1 2 pieces of the residual stress in each state are selected for testing, and 1 piece of the residual stress is subjected to a stripping test to examine a stress field in the depth direction;
step six, roughness analysis: and (3) detecting the roughness of the blade part under the determined shot blasting parameters, and measuring and analyzing the roughness Ra of at least 3 blades.
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| CN112025561B (en) * | 2020-08-28 | 2022-11-18 | 中国航发贵阳发动机设计研究所 | Method for determining surface integrity requirement of aeroengine turbine disc |
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