CN105823659A - Manufacturing technology of test block for comparison of micro cracks in thermal barrier coating of engine blade - Google Patents

Manufacturing technology of test block for comparison of micro cracks in thermal barrier coating of engine blade Download PDF

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Publication number
CN105823659A
CN105823659A CN201610144506.9A CN201610144506A CN105823659A CN 105823659 A CN105823659 A CN 105823659A CN 201610144506 A CN201610144506 A CN 201610144506A CN 105823659 A CN105823659 A CN 105823659A
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CN
China
Prior art keywords
thermal barrier
barrier coating
crack
micro
test block
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Pending
Application number
CN201610144506.9A
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Chinese (zh)
Inventor
邬冠华
李泽
吴伟
王婵
周笔文
何喜
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Nanchang Hangkong University
Xian Aviation Power Co Ltd
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Nanchang Hangkong University
Xian Aviation Power Co Ltd
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Priority to CN201610144506.9A priority Critical patent/CN105823659A/en
Publication of CN105823659A publication Critical patent/CN105823659A/en
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N1/00—Sampling; Preparing specimens for investigation
    • G01N1/28—Preparing specimens for investigation including physical details of (bio-)chemical methods covered elsewhere, e.g. G01N33/50, C12Q
    • G01N1/286—Preparing specimens for investigation including physical details of (bio-)chemical methods covered elsewhere, e.g. G01N33/50, C12Q involving mechanical work, e.g. chopping, disintegrating, compacting, homogenising
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N1/00—Sampling; Preparing specimens for investigation
    • G01N1/28—Preparing specimens for investigation including physical details of (bio-)chemical methods covered elsewhere, e.g. G01N33/50, C12Q
    • G01N2001/2893—Preparing calibration standards

Abstract

The invention discloses a manufacturing technology of a test block for the comparison of micro cracks in the thermal barrier coating of an engine blade. According to the technology, a pressure is applied on a thermal barrier coating on the basis of a Vicker's hardness meter; the stress of the diamond quadrangular pressure head of the Vicker's hardness meter is converged so as to form micro cracks around the edge of the pressure head; the technology is used to produce comparison test blocks for nondestructive test calibration, a Vicker's hardness meter is used, multiple flat test sheets, whose surface is larger than 10*10 mm, are used; different loads are loaded, finally electron microscopy detection is performed, scanning electron microscope observation and measurement are carried out, and drawing instruction is performed. The technology has the advantages that micro cracks can be formed in thermal barrier coating with a thickness of 22-120 [mu]m; compared with other crack manufacturing method, the provided technology is simple and reliable, and moreover, the brittleness of thermal barrier coating can also be evaluated.

Description

Micro-crack reference block processing technology on engine blade thermal barrier coating
Technical field
The invention belongs to mechanical manufacturing field, relate to Non-Destructive Testing and ultrasound detection, be specially a kind of engine blade heat Micro-crack reference block processing technology on barrier coating.
Background technology
Engine thermal barrier coating is the key ensureing aero-engine service life, and the micro-crack how detecting thermal barrier coating is to protect The important technology that barrier engine health is run, preparing micro-crack reference block becomes detection technique for nondestructive detecting instrument calibration Crucial.Conventional micro-crack manufacture method has: bending method, the method for heat expansion and cold contraction, indentation method, friction etc., and wherein impression is sent out the simplest, Easily realize.
Summary of the invention
It is an object of the invention to provide micro-crack reference block processing technology on a kind of engine blade thermal barrier coating, should Technique can preferably detect the micro-crack of thermal barrier coating, ensures that engine health is run.
The technical solution used in the present invention is as follows: on a kind of engine blade thermal barrier coating, micro-crack reference block makes work Skill, it is characterised in that step method is as follows: this technique applies pressure based on Vickers on thermal barrier coating surface, utilizes Vickers The stress at scleroscopic diamond four rib pressure head edge is concentrated, and forms micro-crack at pressure head edge, is used for making Non-Destructive Testing school Mutatis mutandis reference block, its equipment uses Vickers, uses some areas more than 10 × 10mm plane test piece, loads different Load, finally carries out Electronic Speculum detection, scanning electron microscopic observation and measurement, carries out explanation of drawing.
Further, this technique described produces micro-crack on the thermal barrier coating of thickness range 22-120 μm.
Further, described applying pressure loading is 50N, 100N, 200N, 500N.
Further, the composition of described coating includes Al203And SiO2 , Al203With SiO2Ratio 3:1 to 1:4 it Between.
Further, the thickness of described coating is between 22 μm to 122 μm.
Further, described reference block is planar structure, area be more than 10mm × 10mm, surface cleaning, pollution-free.
Further, the matrix of described reference block is nickel base superalloy, rustless steel.
Further, described reference block scanning electron microscopic observation and measurement, explanation of drawing.
The invention have the advantage that the technique of the present invention effectively produces micro-on the thermal barrier coating of thickness range 22-120 μm Crackle, compares other crackle manufacture methods, simple and reliable, and can evaluate the fragility of thermal barrier coating.
Accompanying drawing explanation
Fig. 1 is reference block.
Fig. 2 is 1# sample loading position crackle schematic diagram.
Fig. 3 is 1# sample loading position SEM figure.
Fig. 4 is 2# sample loading position crackle schematic diagram.
Fig. 5 is 2# sample loading position SEM figure.
Fig. 6 is 3# sample loading position crackle schematic diagram.
Fig. 7 is 3# sample loading position SEM figure.
Fig. 8 is 4# sample loading position crackle schematic diagram.
Fig. 9 is 5# sample loading position SEM figure.
Figure 10 is 5# sample loading position crackle schematic diagram.
Figure 11 is 5# sample loading position SEM figure.
In fig. 2, the crackle that 50KG position downwardly extends, length is about 200 μm.
In the diagram, the upwardly extending crackle in 50KG position, length is more than 50 μm.
In figure 6, the crackle that 50KG position downwardly extends, length is more than 100 μm.
In fig. 8, the crackle that 50KG position extends to the left, length is about 200 μm.
In Fig. 10, the crackle that 50KG position extends to the left, length is about 100 μm.
Wherein: the coating composition of 1# test block is Al203With SiO2Ratio be 3:1, average coating thickness is 122 μm, matrix For nickel base superalloy；The coating composition of 2# test block is Al203With SiO2Ratio be 1:2, average coating thickness is 50 μm, base Body is nickel base superalloy；The coating composition of 3# test block is Al203With SiO2Ratio be 1:3, average coating thickness is 42 μm, Matrix is nickel base superalloy；The coating composition of 4# test block is Al203With SiO2Ratio be 2:1, average coating thickness is 22 μ M, matrix is rustless steel；The coating composition of 5# test block is Al203With SiO2Ratio be 1:4, average coating thickness is 34 μm, base Body is nickel base superalloy.
Detailed description of the invention
The equipment of the present invention: Vickers, Vickers HV-50.
The test piece of the present invention: plane test piece, area be more than 10 × 10mm, surface cleaning, pollution-free.
Numbering Coating composition Average coating thickness (mm) Matrix
1 3Al203+SiO2 122 Nickel base superalloy
2 Al203+2SiO2 50 Nickel base superalloy
3 Al203+3SiO2 42 Nickel base superalloy
4 2 Al203+SiO2 22 Rustless steel
6 Al203+4SiO2 34 Nickel base superalloy
The loaded load of the present invention: 50N, 100N, 200N, 500N.
The Electronic Speculum detection of the present invention: scanning electron microscopic observation and measurement, explanation of drawing.
Result is as follows:
Embodiment one:
As it is shown in figure 1, the processing technology of micro-crack reference block on a kind of engine blade thermal barrier coating, it is characterised in that: should Technique applies pressure based on Vickers on thermal barrier coating surface, utilizes the diamond four rib pressure head edge of Vickers Stress is concentrated, and forms micro-crack at pressure head edge, is used for making calibration reference block 1#.Described applying pressure loading is 500N, the composition of described coating includes Al203And SiO2 , Al203With SiO2 Ratio at 3:1, the thickness of described coating is 122 μ M, described test block 1# are planar structure, and area is more than 10mm × 10mm, and surface cleaning, pollution-free, the matrix of described test block 1# is Nickel base superalloy, described test block 1# scanning electron microscopic observation and measurement, explanation result of drawing, as shown in Figure 2,3.
Embodiment two:
As it is shown in figure 1, the processing technology of micro-crack reference block on a kind of engine blade thermal barrier coating, it is characterised in that: should Technique applies pressure based on Vickers on thermal barrier coating surface, utilizes the diamond four rib pressure head edge of Vickers Stress is concentrated, and forms micro-crack at pressure head edge, is used for making calibration reference block 2#.Described applying pressure loading is 500N, the composition of described coating includes Al203And SiO2 , Al203With SiO2 Ratio at 1:2, the thickness of described coating is 50 μ M, described test block 2# are planar structure, and area is more than 10mm × 10mm, and surface cleaning, pollution-free, the matrix of described test block 2# is Nickel base superalloy, described test block 2# scanning electron microscopic observation and measurement, explanation result of drawing, as shown in Figure 4,5.
Embodiment three:
As it is shown in figure 1, the processing technology of micro-crack reference block on a kind of engine blade thermal barrier coating, it is characterised in that: should Technique applies pressure based on Vickers on thermal barrier coating surface, utilizes the diamond four rib pressure head edge of Vickers Stress is concentrated, and forms micro-crack at pressure head edge, is used for making calibration reference block 3#.Described applying pressure loading is 500N, the composition of described coating includes Al203And SiO2 , Al203With SiO2 Ratio at 1:3, the thickness of described coating is 42 μ M, described test block 3# are planar structure, and area is more than 10mm × 10mm, and surface cleaning, pollution-free, the matrix of described test block 3# is Nickel base superalloy, described test block 3# scanning electron microscopic observation and measurement, explanation result of drawing, as shown in Figure 6,7.
Embodiment four:
As it is shown in figure 1, the processing technology of micro-crack reference block on a kind of engine blade thermal barrier coating, it is characterised in that: should Technique applies pressure based on Vickers on thermal barrier coating surface, utilizes the diamond four rib pressure head edge of Vickers Stress is concentrated, and forms micro-crack at pressure head edge, is used for making calibration reference block 4#.Described applying pressure loading is 500N, the composition of described coating includes Al203And SiO2 , Al203With SiO2 Ratio at 2:1, the thickness of described coating is 22 μ M, described test block 4# are planar structure, and area is more than 10mm × 10mm, and surface cleaning, pollution-free, the matrix of described test block 4# is Rustless steel, described test block 4# scanning electron microscopic observation and measurement, explanation result of drawing, as shown in Figure 8,9.
Embodiment five:
As it is shown in figure 1, the processing technology of micro-crack reference block on a kind of engine blade thermal barrier coating, it is characterised in that: should Technique applies pressure based on Vickers on thermal barrier coating surface, utilizes the diamond four rib pressure head edge of Vickers Stress is concentrated, and forms micro-crack at pressure head edge, is used for making calibration reference block 5#.Described applying pressure loading is 500N, the composition of described coating includes Al203And SiO2 , Al203With SiO2 Ratio at 1:4, the thickness of described coating is 34 μ M, described test block 5# are planar structure, and area is more than 10mm × 10mm, and surface cleaning, pollution-free, the matrix of described test block 5# is Nickel base superalloy, described test block 5# scanning electron microscopic observation and measurement, explanation result of drawing, such as Figure 10, shown in 11.
Embodiment six:
The processing technology of micro-crack reference block on a kind of engine blade thermal barrier coating, it is characterised in that: this technique is based on dimension Family name's durometer applies pressure on thermal barrier coating surface, utilizes the stress at the diamond four rib pressure head edge of Vickers to concentrate, Form micro-crack at pressure head edge, be used for making calibration reference block.Described test block is planar structure, area more than 10mm × 10mm, surface cleaning, pollution-free, the composition of described coating includes Al203And SiO2 , Al203With SiO2 Ratio at 1:4, described The matrix of test block is nickel base superalloy, described test block scanning electron microscopic observation and measurement.Described applying pressure loading is 50N Time, do not find crackle；When described applying pressure loading is 100N, do not find crackle；Described applying pressure loading is 200N Time, do not find crackle；When described applying pressure loading is 300N, do not find crackle.
Embodiment seven:
The processing technology of micro-crack reference block on a kind of engine blade thermal barrier coating, it is characterised in that: this technique is based on dimension Family name's durometer applies pressure on thermal barrier coating surface, utilizes the stress at the diamond four rib pressure head edge of Vickers to concentrate, Form micro-crack at pressure head edge, be used for making calibration reference block.Described test block is planar structure, area more than 10mm × 10mm, surface cleaning, pollution-free, the composition of described coating includes Al203And SiO2 , Al203With SiO2 Ratio at 1:2, described The matrix of test block is nickel base superalloy, described test block scanning electron microscopic observation and measurement.Described applying pressure loading is 50N Time, do not find crackle；When described applying pressure loading is 100N, do not find crackle；Described applying pressure loading is 200N Time, find several small branching crackses to the left；When described applying pressure loading is 300N, find a upwards fine crack.
Embodiment eight:
The processing technology of micro-crack reference block on a kind of engine blade thermal barrier coating, it is characterised in that: this technique is based on dimension Family name's durometer applies pressure on thermal barrier coating surface, utilizes the stress at the diamond four rib pressure head edge of Vickers to concentrate, Form micro-crack at pressure head edge, be used for making calibration reference block.Described test block is planar structure, area more than 10mm × 10mm, surface cleaning, pollution-free, the composition of described coating includes Al203And SiO2 , Al203With SiO2 Ratio at 2:1, described The matrix of test block is nickel base superalloy, described test block scanning electron microscopic observation and measurement.Described applying pressure loading is 50N Time, do not find crackle；When described applying pressure loading is 100N, find upwards 100 microns of crackle；Described applying is pressed When power load is 200N, find to the left and more downward fine cracks；When described applying pressure loading is 300N, find the most very Many branching crackses, there is fine crack in other directions.
Embodiment nine:
The processing technology of micro-crack reference block on a kind of engine blade thermal barrier coating, it is characterised in that: this technique is based on dimension Family name's durometer applies pressure on thermal barrier coating surface, utilizes the stress at the diamond four rib pressure head edge of Vickers to concentrate, Form micro-crack at pressure head edge, be used for making calibration reference block.Described test block is planar structure, area more than 10mm × 10mm, surface cleaning, pollution-free, the composition of described coating includes Al203And SiO2 , Al203With SiO2 Ratio at 2:1, described The matrix of test block is rustless steel, described test block scanning electron microscopic observation and measurement.When described applying pressure loading is 50N, find Four direction has fine crack；When described applying pressure loading is 100N, there is no upwards 300 microns of crackle, its other party To there being fine crack；When described applying pressure loading is 200N, finding that four direction has a lot of branching cracks, total length is big In 50 microns；When described applying pressure loading is 300N, finding that four direction has a lot of branching cracks, total length is more than 100 Micron.
Embodiment ten:
The processing technology of micro-crack reference block on a kind of engine blade thermal barrier coating, it is characterised in that: this technique is based on dimension Family name's durometer applies pressure on thermal barrier coating surface, utilizes the stress at the diamond four rib pressure head edge of Vickers to concentrate, Form micro-crack at pressure head edge, be used for making calibration reference block.Described test block is planar structure, area more than 10mm × 10mm, surface cleaning, pollution-free, the composition of described coating includes Al203And SiO2 , Al203With SiO2 Ratio at 1:3, described The matrix of test block is nickel base superalloy, described test block scanning electron microscopic observation and measurement.Described applying pressure loading is 50N Time, do not find crackle；When described applying pressure loading is 100N, find 50 microns of crackle to the left；Described applying pressure When load is 200N, find there is fine crack to the left and downwards；When described applying pressure loading is 300N, find four direction all There is fine crack.

Claims (2)

1. micro-crack reference block processing technology on an engine blade thermal barrier coating, it is characterised in that step method is as follows: This technique applies pressure based on Vickers on thermal barrier coating surface, utilizes the diamond four rib pressure head edge of Vickers Stress concentrate, form micro-crack at pressure head edge, be used for making Non-Destructive Testing calibration reference block, its equipment uses Vickers Durometer, uses some areas more than 10 × 10mm plane test piece, loads different load, finally carry out Electronic Speculum detection, scanning Electron microscopic observation and measurement, carry out explanation of drawing.
Micro-crack reference block processing technology on a kind of engine blade thermal barrier coating the most according to claim 1, it is special Levy and be: this technique described produces micro-crack on the thermal barrier coating of thickness range 22-120 μm.
CN201610144506.9A 2016-03-15 2016-03-15 Manufacturing technology of test block for comparison of micro cracks in thermal barrier coating of engine blade Pending CN105823659A (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111122266A (en) * 2019-12-19 2020-05-08 西北工业大学 Device for generating specific local geometric initial defects on outer surface of pipeline
CN111323484A (en) * 2020-04-17 2020-06-23 中国飞机强度研究所 Method for manufacturing kiss-joint defect reference test block and method for detecting by using test block

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CN105043832A (en) * 2015-07-10 2015-11-11 国网天津市电力公司 Making method of copper-aluminum transition hardware fitting penetration testing block
EP2962677A2 (en) * 2014-07-03 2016-01-06 Shofu Inc. Dental curable composition including chain transfer agent
CN105353028A (en) * 2015-10-22 2016-02-24 合肥工业大学 Manufacturing method of test block having surface artificial crack defect used for magnetic particle testing

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Publication number Priority date Publication date Assignee Title
CN102393341A (en) * 2011-08-03 2012-03-28 湘潭大学 Device for testing hardness, fracture toughness and residual stress of brittle material with indentation method
CN103017955A (en) * 2012-11-29 2013-04-03 北京理工大学 Manufacturing process and protection method for constant value residual stress welding test piece
CN104422628A (en) * 2013-09-03 2015-03-18 北京时代之峰科技有限公司 Indentation image identification method and system based on Vickers hardness
CN103808566A (en) * 2013-12-19 2014-05-21 余姚市电波机械有限公司 Compressive strength testing method of shaft
EP2962677A2 (en) * 2014-07-03 2016-01-06 Shofu Inc. Dental curable composition including chain transfer agent
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CN105353028A (en) * 2015-10-22 2016-02-24 合肥工业大学 Manufacturing method of test block having surface artificial crack defect used for magnetic particle testing

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111122266A (en) * 2019-12-19 2020-05-08 西北工业大学 Device for generating specific local geometric initial defects on outer surface of pipeline
CN111122266B (en) * 2019-12-19 2021-06-25 西北工业大学 Device for generating specific local geometric initial defects on outer surface of pipeline
CN111323484A (en) * 2020-04-17 2020-06-23 中国飞机强度研究所 Method for manufacturing kiss-joint defect reference test block and method for detecting by using test block
CN111323484B (en) * 2020-04-17 2022-11-01 中国飞机强度研究所 Method for manufacturing kiss-joint defect reference test block and method for detecting by using test block

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