CN117949277B - Defect prefabrication structure and method for circumferential high-stress part of wheel disc - Google Patents
Defect prefabrication structure and method for circumferential high-stress part of wheel disc Download PDFInfo
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- CN117949277B CN117949277B CN202410338720.2A CN202410338720A CN117949277B CN 117949277 B CN117949277 B CN 117949277B CN 202410338720 A CN202410338720 A CN 202410338720A CN 117949277 B CN117949277 B CN 117949277B
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- 230000007547 defect Effects 0.000 title claims abstract description 52
- 238000000034 method Methods 0.000 title claims abstract description 28
- 238000009417 prefabrication Methods 0.000 title claims abstract description 21
- 239000011248 coating agent Substances 0.000 claims description 51
- 238000000576 coating method Methods 0.000 claims description 51
- 238000005520 cutting process Methods 0.000 claims description 11
- 230000000977 initiatory effect Effects 0.000 claims description 6
- 238000005507 spraying Methods 0.000 claims description 6
- 238000007750 plasma spraying Methods 0.000 claims description 4
- 239000000758 substrate Substances 0.000 description 7
- 238000012360 testing method Methods 0.000 description 6
- 238000013461 design Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 239000002344 surface layer Substances 0.000 description 4
- 238000010892 electric spark Methods 0.000 description 3
- 239000010410 layer Substances 0.000 description 3
- 238000004088 simulation Methods 0.000 description 3
- 238000003754 machining Methods 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- NPXOKRUENSOPAO-UHFFFAOYSA-N Raney nickel Chemical compound [Al].[Ni] NPXOKRUENSOPAO-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009661 fatigue test Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- CNRZQDQNVUKEJG-UHFFFAOYSA-N oxo-bis(oxoalumanyloxy)titanium Chemical compound O=[Al]O[Ti](=O)O[Al]=O CNRZQDQNVUKEJG-UHFFFAOYSA-N 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000005480 shot peening Methods 0.000 description 1
- 238000001228 spectrum Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- OGIDPMRJRNCKJF-UHFFFAOYSA-N titanium oxide Inorganic materials [Ti]=O OGIDPMRJRNCKJF-UHFFFAOYSA-N 0.000 description 1
Abstract
The invention relates to the technical field of aeroengines, and discloses a defect prefabrication structure and a defect prefabrication method for a circumferential high-stress part of a wheel disc.
Description
Technical Field
The invention relates to the technical field of aeroengines, and discloses a defect prefabrication structure and method for a circumferential high-stress part of a wheel disc.
Background
Aircraft engine wheels are critical components on the engine that, once broken, can have catastrophic consequences. The life design concept of advanced aeroengine wheels has been changed from a safe life design to a damage tolerant design, i.e. considering that the wheel has sufficient life from the occurrence of a crack when it has some initial defect to the crack propagation to the failure of the wheel, should be at least greater than two engine service cycles.
The development of crack growth tests is an important support for the improvement of damage tolerance design capability. The purpose of the crack propagation test is to understand the service life of a typical part of the wheel disc (such as a disc center, a bolt hole edge, a drum barrel, a radial plate and the like) after a detectable crack is generated until the wheel disc completely loses the bearing capacity until the whole process of the crack is broken. In order to accurately control crack initiation positions and save test resource consumption, defects are usually needed to be prefabricated at the concerned positions, so that the wheel disc naturally initiates cracks under the action of local stress concentration effect.
The existing method for prefabricating defects is to process grooves on the surface or edges of a wheel disc by using electric sparks, the length and depth of the grooves are determined to be matched with the crack detection capability, the narrower the width of the grooves is, the more easily cracks still occur, and when the width of the grooves tends to zero, the prefabricating defects can be considered to be no difference from natural cracks. However, under the current technical conditions, when the electric spark prefabricates the defect to regenerate cracks, the method is limited by the size of an electric spark machining electrode, the width of an actually machined groove is more than 0.1mm, and the width of the larger prefabricate defect is smaller than that of the actual crack, so that the stress intensity factor of the front edge of the defect is lower than that of the actual crack, the process from the crack initiation to the initial stage of the expansion is difficult to regenerate, and the defect exists in the initial stage of the experimental actually measured crack expansion life curve.
Disclosure of Invention
The invention aims to provide a defect prefabrication structure and a defect prefabrication method for a circumferential high-stress part of a wheel disc, which can naturally initiate cracks on the surface of a tested piece, do not need to process defects on the wheel disc, have smaller crack size and shape which is closer to a real crack, and have better effect on experimental simulation of the initial stage of crack growth of the wheel disc.
In order to achieve the technical effects, the technical scheme adopted by the invention is as follows:
A defect prefabrication method for a circumferential high stress portion of a wheel disc, comprising:
Spraying a whole circle of coating on the position of the crack to be obtained on the wheel disc according to the damage tolerance requirement of the wheel disc;
preparing a notch on the whole circle of coating corresponding to the position of the crack to obtain a defect prefabricated structure;
Assembling the defect prefabricated structure with the notch coating onto a wheel disc tester, and loading the defect prefabricated structure with the notch coating for rotating speed circulation to enable fatigue cracks to be initiated at the wheel disc corresponding to the notch;
after initiation of the crack, the coating is removed.
Further, the plasma spraying process is adopted to obtain crack positions on the wheel disc, and the crack positions are sprayed for multiple times, so that a whole circle of coating is obtained.
Further, the total thickness of the coating is 1.5-2 mm.
Further, the cutting depth of the notch is 0.15-0.2 mm away from the wheel disc substrate, and the cutting width is smaller than 0.5mm.
In order to achieve the technical effects, the invention also provides a defect prefabrication structure for the circumferential high-stress part of the wheel disc, which comprises the wheel disc, wherein an annular coating is sprayed on the wheel disc; the coating is provided with a notch at a position where a crack needs to be obtained.
Further, the total thickness of the coating is 1.5-2 mm.
Further, the cutting depth of the notch is 0.15-0.2 mm away from the wheel disc substrate, and the cutting width is smaller than 0.5mm.
Compared with the prior art, the invention has the following beneficial effects: according to the invention, the hard coating is sprayed on the region to be prefabricated along the circumferential direction of the wheel disc, then the coating is locally notched on the region to be prefabricated, and then the wheel disc is put into a wheel disc tester for low-cycle fatigue loading, so that cracks are initiated at the notch of the coating and are expanded to the wheel disc substrate, the cracks can be naturally initiated on the surface of a tested piece, the defects are not required to be processed on the wheel disc, the shape of the crack is smaller, the crack is more similar to the shape of a real crack, and the test simulation in the initial stage of crack expansion of the wheel disc is better.
Drawings
FIG. 1 is a flow chart of a defect prefabrication method for a high stress circumferential portion of a wheel disc in example 1 or 2;
FIG. 2 is a schematic illustration of the positions of the coating and wheel disc of examples 1 or 2;
FIG. 3 is a schematic illustration of the location of a crack in a wheel disc in examples 1 or 2;
FIG. 4 is a partial schematic view of a notched coated wheel disc of example 1 or 2;
1, a wheel disc; 2. cracking; 3. a coating; 4. and (5) a notch.
Detailed Description
The present invention will be described in further detail with reference to the following examples and drawings. It should not be construed that the scope of the above subject matter of the present invention is limited to the following embodiments, and all techniques realized based on the present invention are within the scope of the present invention.
Example 1
Referring to fig. 1-4, a defect prefabrication method for a circumferential high stress portion of a wheel disc includes:
according to the damage tolerance requirement of the wheel disc 1, spraying a whole circle of coating 3 on the position of the wheel disc 1, where the crack 2 needs to be obtained;
Preparing a notch 4 on the whole circle of coating 3 corresponding to the position of the crack 2 to obtain a defect prefabricated structure;
assembling the defect prefabricated structure with the notch 4 coating 3 on a wheel disc 1 tester, and loading and rotating the defect prefabricated structure with the notch 4 coating 3 at a rotating speed for circulation to enable fatigue cracks 2 to be initiated at the wheel disc 1 corresponding to the notch 4;
after initiation of the crack 2, the coating 3 is removed.
In this embodiment, when the crack 2 needs to be prefabricated on the area of the wheel disc 1 having the stress of Xiang Gao, firstly, the hard coating 3 is sprayed on the area to be prefabricated along the whole circle of the wheel disc 1, then the coating 3 is partially notched 4 in the area to be prefabricated, and then the wheel disc 1 is loaded into the wheel disc 1 tester to perform low cycle fatigue loading, so that the crack 2 can be initiated at the notch 4 of the coating 3 and expanded to the wheel disc 1 substrate, the crack 2 can be naturally initiated on the surface of the tested piece, the machining defect on the wheel disc 1 is not needed, the crack 2 has smaller size and shape closer to the real crack 2, and the test simulation at the initial stage of the crack 2 expansion of the wheel disc 1 has better effect.
Further, the plasma spraying process is adopted to spray the positions, where the cracks 2 are required to be obtained, on the wheel disc 1 in multiple times, so as to obtain the whole circle of coating 3.
Based on the same inventive concept, the embodiment also provides a defect prefabrication structure for the circumferential high-stress part of the wheel disc, which comprises a wheel disc 1, wherein an annular coating 3 is sprayed on the wheel disc 1; the coating 3 is provided with a notch 4 at the location where the crack 2 is to be obtained.
Example 2
Referring to fig. 1 to fig. 4, in this embodiment, defect prefabrication at a high stress position in a circumferential direction of a wheel disc of a certain type of aeroengine is taken as an example, and the defect prefabrication method of the present invention is described in detail, and a specific operation flow is as follows:
step 1, spraying a whole circle of coating 3 on a position where a crack 2 needs to be obtained on a wheel disc 1 according to the damage tolerance requirement of the wheel disc 1;
In this embodiment, stress analysis is performed on the aeroengine wheel disc 1, and according to the result of the stress analysis, a position on the disc body with a low cycle fatigue life is selected to be determined as a crack 2 initiation dangerous position, and then a position with an axisymmetric structure and a dominant circumferential stress is selected therefrom to be used as a defect prefabrication position in the method. Taking a disc center prefabricated defect as an example, the crack 2 is shown in fig. 3, the prefabricated defect is a semicircular crack 2 in the depth direction along the radial direction of the engine and the length direction along the axial direction of the engine, and the prefabricated defect size r=0.38 mm.
The preparation of the coating 3 is carried out by adopting a plasma spraying process in the embodiment, the width of the coating 3 should completely cover the length of the crack 2 to be prefabricated, and the width of the coating 3 is 1.0mm in the embodiment. The method is characterized in that the position of the center of the wheel disc 1, where the crack 2 is required to be obtained, is sprayed twice to obtain a whole circle of coating 3, wherein the bottom layer close to the wheel disc 1 of the base body is made of nickel-aluminum powder, the bottom layer spraying function is to ensure the combination of the surface layer and the base body, and the spraying thickness is determined to be 0.08-0.13 mm. The aluminum oxide-titanium oxide powder for the surface layer is adopted in the embodiment, and Al 2O3 -13% TiO is adopted, so that the surface layer coating 3 has enough bearing capacity and stress concentration degree after the notch 4 is artificially manufactured, and the total thickness of the coating 3 is controlled to be 1.8-2.0 mm.
Step 2, preparing a notch 4 on the whole circle of coating 3 corresponding to the position of the crack 2 to be obtained, so as to obtain a defect prefabricated structure;
In this embodiment, at the same circumferential position of the defect to be prefabricated on the whole circle of the sprayed coating 3, cutting the coating 3 in a direction perpendicular to the circumferential direction of the engine, wherein the cutting depth is 0.15-0.2 mm based on the substrate, the substrate cannot be damaged, and the cutting width is less than 0.5mm, thereby obtaining the defect prefabricated structure for the high-stress circumferential position of the wheel disc 1.
And 3, assembling the defect prefabricated structure with the notch 4 coating 3 on a wheel disc 1 tester, and loading and rotating the defect prefabricated structure with the notch 4 coating 3 at a rotating speed for circulation to enable the wheel disc 1 corresponding to the notch 4 to initiate fatigue cracks 2.
In this example, a defect preform structure with a notch 4 coating 3 was assembled to a wheel disc 1 tester and a simulated low cycle fatigue test was performed at a uniform temperature of 500 ℃. The test load spectrum is: the peak value is determined according to the maximum steady-state rotating speed of the engine corresponding to the part, the valley value is determined according to the capacity of the tester, the circulation of the valley value, the peak value and the valley value is repeatedly carried out, at the moment, the disc body generates circumferential stress circulation, and the circumferential stress amplitude is obviously higher than the rest circumferential positions of the part due to stress concentration in a local area of a notch 4 with a coating 3 on the disc body, so that low-cycle fatigue cracks 2 can be rapidly initiated.
And stopping loading when the online monitoring system of the crack 2 on the tester of the wheel disc 1 gives an early warning, and stopping for checking the crack 2. The eddy current test method is used to determine whether the substrate initiates a crack 2.
After the crack 2 of the matrix is initiated, the surface layer and the bottom layer of the coating 3 are thoroughly removed by a turning method. And then shot peening strengthening is carried out on the surface of the sprayed area according to the requirements of the design drawing of the wheel disc 1, so that the technical state of the wheel disc 1 is ensured to be consistent with the requirements of original paper.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (7)
1. A defect prefabrication method for a circumferential high stress portion of a wheel disc, comprising:
spraying a whole circle of coating (3) on the position where the crack (2) needs to be obtained on the wheel disc (1) according to the damage tolerance requirement of the wheel disc (1);
Preparing a notch (4) on the whole circle of coating (3) corresponding to the position of the crack (2) to obtain a defect prefabricated structure;
assembling the defect prefabricated structure with the notch (4) coating (3) onto a wheel disc (1) tester, and loading the defect prefabricated structure with the notch (4) coating (3) with a rotating speed for circulation to enable fatigue cracks (2) to be initiated at the wheel disc (1) corresponding to the notch (4);
After initiation of the crack (2), the coating (3) is removed.
2. The defect prefabrication method for the high-stress parts in the circumferential direction of the wheel disc according to claim 1, wherein the positions of the cracks (2) required to be obtained on the wheel disc (1) are sprayed for a plurality of times by adopting a plasma spraying process, so that the whole circle of coating (3) is obtained.
3. The defect prefabrication method for a wheel disc circumferential high stress portion according to claim 1, wherein the total thickness of the coating (3) is 1.5-2 mm.
4. The defect prefabrication method for the circumferential high-stress parts of the wheel disc according to claim 3, wherein the cutting depth of the notch (4) is 0.15-0.2 mm from the base body of the wheel disc (1), and the cutting width is smaller than 0.5mm.
5. A defect prefabrication structure for a wheel disc circumferential high stress portion for implementing the defect prefabrication method for a wheel disc (1) circumferential high stress portion according to any of claims 1-4, characterized in that the structure comprises a wheel disc (1), wherein an annular coating (3) is sprayed on the wheel disc (1); the coating (3) is provided with a notch (4) at a position where a crack (2) needs to be obtained.
6. The defect pre-fabricated structure for a wheel disc circumferential high stress portion according to claim 5, wherein the total thickness of the coating (3) is 1.5-2 mm.
7. The defect prefabricated structure for a wheel disc circumferential high-stress part according to claim 6, wherein the cutting depth of the notch (4) is 0.15-0.2 mm from the base body of the wheel disc (1), and the cutting width is smaller than 0.5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410338720.2A CN117949277B (en) | 2024-03-25 | Defect prefabrication structure and method for circumferential high-stress part of wheel disc |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410338720.2A CN117949277B (en) | 2024-03-25 | Defect prefabrication structure and method for circumferential high-stress part of wheel disc |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117949277A CN117949277A (en) | 2024-04-30 |
| CN117949277B true CN117949277B (en) | 2024-06-04 |
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Citations (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5734439A (en) * | 1980-08-08 | 1982-02-24 | Kawasaki Heavy Ind Ltd | Production of artificial defect test piece |
| CA2351590A1 (en) * | 1998-11-16 | 2000-05-25 | Helsinki University Of Technology | A method for producing defects and tensile residual stresses |
| CN1793835A (en) * | 2005-12-19 | 2006-06-28 | 大连海事大学 | Inner hole defect prestress-sound reflection integrated detection equipment and method |
| CN101118212A (en) * | 2007-08-10 | 2008-02-06 | 燕山大学 | Experiment method for accelerating superhard coatings part rolling contact fatigue failure |
| CN101398351A (en) * | 2008-10-31 | 2009-04-01 | 湘潭大学 | Method for preparing thermal curtain coating sample for researching flection damage of flat-plate structure thermal curtain coating interface |
| EP2199775A2 (en) * | 2008-12-17 | 2010-06-23 | Hamilton Sundstrand Corporation | Method and apparatus for evaluation of coated parts |
| CN203758810U (en) * | 2014-02-11 | 2014-08-06 | 中国水利水电科学研究院 | Test piece for evaluating low-temperature cracking resistance of material and measuring equipment |
| CN104316372A (en) * | 2014-10-22 | 2015-01-28 | 上海大学 | Preparation method of breaking tenacity sample made of ceramic material |
| CN204666488U (en) * | 2015-06-01 | 2015-09-23 | 中国人民解放军装甲兵工程学院 | A kind of pendant equipment that falls measuring anchoring strength of coating |
| CN105823666A (en) * | 2016-05-16 | 2016-08-03 | 中国航空工业集团公司西安飞机设计研究所 | Method for prefabricating composite laminate special-shaped layering defects |
| CN106191752A (en) * | 2015-03-10 | 2016-12-07 | 中国农业机械化科学研究院 | A kind of thermal barrier coating melt surface deposit protective coating and preparation method thereof |
| CN107345898A (en) * | 2017-07-18 | 2017-11-14 | 江苏大学 | A kind of measuring method of thermal barrier coating interface bond strength |
| CN107631935A (en) * | 2017-07-27 | 2018-01-26 | 中国航发北京航空材料研究院 | Using the crack growth threshold method of testing of pressure pressure cyclic loading precrack |
| CN110926972A (en) * | 2018-09-18 | 2020-03-27 | 中国航发商用航空发动机有限责任公司 | Fretting fatigue surface crack detection method and system |
| CN111678780A (en) * | 2020-05-14 | 2020-09-18 | 江苏禹治流域管理技术研究院有限公司 | Tensile-pulling test device and method for prefabricated crack test piece with microfiber embedded in cement matrix |
| CN112199848A (en) * | 2020-10-16 | 2021-01-08 | 中国航发四川燃气涡轮研究院 | Fatigue life evaluation method for low-pressure turbine shaft |
| CN112345380A (en) * | 2020-10-16 | 2021-02-09 | 中国建材检验认证集团股份有限公司 | Method for testing fracture toughness of ceramic coating |
| CN112525644A (en) * | 2020-12-22 | 2021-03-19 | 中国科学院西安光学精密机械研究所 | Prefabricated crack copper alloy polyurethane bonding structure tensile pull-off test piece and manufacturing method thereof |
| CN113514291A (en) * | 2020-04-09 | 2021-10-19 | 中国航发商用航空发动机有限责任公司 | Method for preparing test sample with surface cracks |
| CN113688546A (en) * | 2021-08-16 | 2021-11-23 | 台山核电合营有限公司 | Method for making metal weld seam service-induced defect receiving table |
| CN114074167A (en) * | 2021-11-11 | 2022-02-22 | 上海工程技术大学 | Difficult-deformation aluminum alloy plate cake component and composite forming method thereof |
| EP4036070A1 (en) * | 2021-01-29 | 2022-08-03 | Chongqing Aureavia Hi-tech Glass Co., Ltd | Coated microcrystalline glass with improved water-repellent and oil-repellent property, preparation method and application thereof |
| CN115290429A (en) * | 2022-07-27 | 2022-11-04 | 昆明理工大学 | Novel detection device and detection method for mechanical property of coating |
| CN115979806A (en) * | 2022-12-09 | 2023-04-18 | 魏桥轻量化(苏州)科技有限公司 | Method for quantitatively evaluating corrosion resistance of cast aluminum alloy/aluminum alloy casting |
| CN117195391A (en) * | 2023-08-10 | 2023-12-08 | 中国航发四川燃气涡轮研究院 | Design method for axial distance between bearing box support plate and mounting side |
Patent Citations (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5734439A (en) * | 1980-08-08 | 1982-02-24 | Kawasaki Heavy Ind Ltd | Production of artificial defect test piece |
| CA2351590A1 (en) * | 1998-11-16 | 2000-05-25 | Helsinki University Of Technology | A method for producing defects and tensile residual stresses |
| CN1793835A (en) * | 2005-12-19 | 2006-06-28 | 大连海事大学 | Inner hole defect prestress-sound reflection integrated detection equipment and method |
| CN101118212A (en) * | 2007-08-10 | 2008-02-06 | 燕山大学 | Experiment method for accelerating superhard coatings part rolling contact fatigue failure |
| CN101398351A (en) * | 2008-10-31 | 2009-04-01 | 湘潭大学 | Method for preparing thermal curtain coating sample for researching flection damage of flat-plate structure thermal curtain coating interface |
| EP2199775A2 (en) * | 2008-12-17 | 2010-06-23 | Hamilton Sundstrand Corporation | Method and apparatus for evaluation of coated parts |
| CN203758810U (en) * | 2014-02-11 | 2014-08-06 | 中国水利水电科学研究院 | Test piece for evaluating low-temperature cracking resistance of material and measuring equipment |
| CN104316372A (en) * | 2014-10-22 | 2015-01-28 | 上海大学 | Preparation method of breaking tenacity sample made of ceramic material |
| CN106191752A (en) * | 2015-03-10 | 2016-12-07 | 中国农业机械化科学研究院 | A kind of thermal barrier coating melt surface deposit protective coating and preparation method thereof |
| CN204666488U (en) * | 2015-06-01 | 2015-09-23 | 中国人民解放军装甲兵工程学院 | A kind of pendant equipment that falls measuring anchoring strength of coating |
| CN105823666A (en) * | 2016-05-16 | 2016-08-03 | 中国航空工业集团公司西安飞机设计研究所 | Method for prefabricating composite laminate special-shaped layering defects |
| CN107345898A (en) * | 2017-07-18 | 2017-11-14 | 江苏大学 | A kind of measuring method of thermal barrier coating interface bond strength |
| CN107631935A (en) * | 2017-07-27 | 2018-01-26 | 中国航发北京航空材料研究院 | Using the crack growth threshold method of testing of pressure pressure cyclic loading precrack |
| CN110926972A (en) * | 2018-09-18 | 2020-03-27 | 中国航发商用航空发动机有限责任公司 | Fretting fatigue surface crack detection method and system |
| CN113514291A (en) * | 2020-04-09 | 2021-10-19 | 中国航发商用航空发动机有限责任公司 | Method for preparing test sample with surface cracks |
| CN111678780A (en) * | 2020-05-14 | 2020-09-18 | 江苏禹治流域管理技术研究院有限公司 | Tensile-pulling test device and method for prefabricated crack test piece with microfiber embedded in cement matrix |
| CN112199848A (en) * | 2020-10-16 | 2021-01-08 | 中国航发四川燃气涡轮研究院 | Fatigue life evaluation method for low-pressure turbine shaft |
| CN112345380A (en) * | 2020-10-16 | 2021-02-09 | 中国建材检验认证集团股份有限公司 | Method for testing fracture toughness of ceramic coating |
| CN112525644A (en) * | 2020-12-22 | 2021-03-19 | 中国科学院西安光学精密机械研究所 | Prefabricated crack copper alloy polyurethane bonding structure tensile pull-off test piece and manufacturing method thereof |
| EP4036070A1 (en) * | 2021-01-29 | 2022-08-03 | Chongqing Aureavia Hi-tech Glass Co., Ltd | Coated microcrystalline glass with improved water-repellent and oil-repellent property, preparation method and application thereof |
| CN113688546A (en) * | 2021-08-16 | 2021-11-23 | 台山核电合营有限公司 | Method for making metal weld seam service-induced defect receiving table |
| CN114074167A (en) * | 2021-11-11 | 2022-02-22 | 上海工程技术大学 | Difficult-deformation aluminum alloy plate cake component and composite forming method thereof |
| CN115290429A (en) * | 2022-07-27 | 2022-11-04 | 昆明理工大学 | Novel detection device and detection method for mechanical property of coating |
| CN115979806A (en) * | 2022-12-09 | 2023-04-18 | 魏桥轻量化(苏州)科技有限公司 | Method for quantitatively evaluating corrosion resistance of cast aluminum alloy/aluminum alloy casting |
| CN117195391A (en) * | 2023-08-10 | 2023-12-08 | 中国航发四川燃气涡轮研究院 | Design method for axial distance between bearing box support plate and mounting side |
Non-Patent Citations (4)
| Title |
|---|
| Study on Properties of High-Vanadium Full-Locked Cable with Alloy Coating with Defects;Zhou Fang 等;《processes》;20220304;第10卷(第513期);第1-16页 * |
| TiAl涂层中孔洞对微裂纹影响的分子动力学研究;常筠袖 等;《中国有色金属学报》;20230930;第33卷(第9期);第2936-2947页 * |
| 再制造件涂覆层内部裂纹扩展行为研究;温飞娟;董丽虹;王海斗;吕振林;;表面技术;20170920(第09期);第189-194页 * |
| 考虑应力比及温度影响的粉末高温合金短裂纹扩展模型研究;徐宇飞 等;《推进技术》;20230531;第44卷(第5期);第2207063-1-8页 * |
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