CN109883938A - A kind of detection method of thermal barrier coating CMAS high temperature corrosion - Google Patents
A kind of detection method of thermal barrier coating CMAS high temperature corrosion Download PDFInfo
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- CN109883938A CN109883938A CN201910218665.2A CN201910218665A CN109883938A CN 109883938 A CN109883938 A CN 109883938A CN 201910218665 A CN201910218665 A CN 201910218665A CN 109883938 A CN109883938 A CN 109883938A
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Abstract
The invention discloses a kind of detection method of thermal barrier coating CMAS high temperature corrosion, include the following steps: corrosive medium being coated in the sample surfaces with thermal barrier coating；The sample for being coated with corrosive medium heats preset time under the first preset temperature, and corrosive medium is made to be sintered in sample surfaces；The sample coated with corrosive medium after heating is fixed on predeterminated position；High temperature gas flow is sprayed to sample surfaces, sample surface temperature is made to reach the second preset temperature, acquires the temperature of sample and the coating state of thermal barrier coating in real time.The present invention is by spraying high temperature gas flow to the thermal barrier coating for being coated with corrosive medium, the CMAS high temperature corrosion suffered in true use environment of accurate simulation blade of aviation engine thermal barrier coating influences, design and selection to heat barrier coat material provide reliable foundation, the problem that brought adult is high when being tested in detection process using aero-engine is overcome, the detection efficiency that blade thermal barrier coating is influenced by CMAS high temperature corrosion is improved.
Description
Technical field
The present invention relates to aero-engine technology field, in particular to a kind of detection side of thermal barrier coating CMAS high temperature corrosion
Method.
Background technique
The development of aero-engine is to measure the important symbol of national a military capability of the country and scientific and technological level, improves aviation hair
Inlet temperature is to improve the important measures and inexorable trend of engine performance before the thrust ratio and turbine of motivation.Thermal barrier coating skill
Art, high temperature single crystal alloy, cooling air membrane technology are classified as three big core technologies of aero-engine high-temperature hot protection.However,
Substantially close to the fusing point of material and the processing technology limit, Thermal Barrier Coating Technologies are mesh for single crystal super alloy and cooling air membrane technology
The preceding most practicable method of raising aero-engine service temperature, and in the models aviation such as XX10, the XX20 in China
It is widely applied on engine, also there is good application prospect in the aero-engine of other models.Thermal barrier coating
Too early spalling failure significantly limits its development and security application, such case are particularly acute in China, becomes and restricts me
The important bottleneck of state's thermal barrier coating security application.
By the research of over half a century, people gradually extract thermal barrier coating high-temperature oxydation, CMAS burn into hard particles
Erosion is to cause three big key factors of disbonding.The extremely severe multi- scenarios method clothes being made of these three key factors
Labour environment leads to the thermal barrier coating rapid deterioration failure during being on active service, and exposes alloy substrates, and then lead to aero-engine
The serious consequences such as damage, aviation accident.This is because thermal barrier coating is in high temperature, erosion, corrosion and the changeable military service ring of Mach number
Under border, it may occur that the failure mode of the Various Complexes such as phase transformation, sintering, oxidation, erosion, corrosion, and eventually lead to coating cracking,
Spalling failure.In order to sufficiently study and be effectively predicted heating power failure and the integrity problem of heat barrier coat material, pass through correlation
Experiment loading unit to simulate the heat of thermal barrier coating, power, change multi- scenarios method environment to carry out analysis to its failure mechanism be thermal boundary
The research hotspot and development trend of coatings art.
Cause the critical environments factor of thermal barrier coating spalling failure first is that some dusts of flight course sucking, the grains of sand with
And remaining volcanic ash melts be bonded in coating surface at high temperature after volcano eruption, reacts with coating, and eventually lead to
Spalling failure, i.e. CMAS high temperature corrosion.For the failure mechanism for studying thermal barrier coating high temperature corrosion, improve coating service life, just
Thermal barrier coating high-temperature corrosion environment must be simulated, and traditional engine test method is costly, low efficiency, detection difficult.
Summary of the invention
The purpose of the embodiment of the present invention is that provide a kind of detection method of thermal barrier coating CMAS high temperature corrosion, by coating
There is the thermal barrier coating injection high temperature gas flow of corrosive medium, accurate simulation blade of aviation engine thermal barrier coating is really using ring
Suffered CMAS high temperature corrosion influences in border, and design and selection to heat barrier coat material provide reliable foundation, overcome
Brought adult high problem when being tested in detection process using aero-engine, improves blade thermal barrier coating
The detection efficiency influenced by CMAS high temperature corrosion.
In order to solve the above technical problems, the embodiment of the invention provides a kind of detection sides of thermal barrier coating CMAS high temperature corrosion
Method includes the following steps:
Corrosive medium is coated in the sample surfaces with thermal barrier coating by S200；
S300, the sample for being coated with the corrosive medium heat preset time under the first preset temperature, make institute
It states corrosive medium and is sintered in the sample surfaces；
The sample coated with the corrosive medium after heating is fixed on predeterminated position by S400；
S500, Xiang Suoshu sample surfaces spray high temperature gas flow, and the sample surface temperature is made to reach the second preset temperature, real
When acquire the temperature of the sample and the coating state of the thermal barrier coating.
Further, the detection method of thermal barrier coating CMAS high temperature corrosion further includes following steps:
S100 carries out polishing to the sample surfaces and removes flash removed, and carries out ultrasonic cleaning using alcohol.
Further, the temperature of the sample and the coating state of the thermal barrier coating are acquired described in step S500 in real time
Before, further include following steps: the sample being cooled down by cooling gas.
Further, the sample includes: test piece sample or leaf sample；The cooling gas is vertical by cooling duct
Blow to the side of the test piece sample far from the high temperature gas flow；Or, the cooling gas is vertically blown into the leaf sample tenon
In the cooling duct of head.
Further, the corrosive medium includes the oxide of calcium, magnesium, aluminium and/or silicon.
Further, the corrosive medium is evenly applied to the surface of the sample according to preset concentration.
Further, sample surface temperature is made to reach the second preset temperature described in step S500, comprising: adjustment is described super
Velocity of sound spray gun makes the sample surface temperature reach the second preset temperature at a distance from the sample；And/or adjust the combustion
The pressure and/or flow for expecting gas source, make the sample surface temperature reach the second preset temperature.
Further, the temperature of the sample and the painting stratiform of the thermal barrier coating are acquired described in step S500 in real time
State, comprising: the temperature of the sample is acquired by infrared radiation thermometer and/or thermocouple；And/or by CCD industrial camera and/
Or thermal infrared imager acquires the surface of the sample surfaces, the differentiation of interface topography figure and Fatigue crack initiation；And/or pass through
Acoustic radiating instrument acquires the thermal barrier coating underbead crack damage signal.
Further, the infrared radiation thermometer measures the sample close to the temperature of the side of the high temperature gas flow；With/
Or, the temperature of the internal temperature of sample described in the thermocouple measurement and/or the side far from the high temperature gas flow.
Further, one end of the Acoustic radiating instrument and waveguide rod connects；The other end of the waveguide rod and sintering are
The sample for stating corrosive medium is fixedly connected far from the side of the high temperature gas flow.
Further, the generation step of the high temperature gas flow are as follows: kerosene is pressurized to preset pressure, and is atomized, is obtained
To atomization kerosene；By the atomization kerosene and oxygen mix, fuel gas source is obtained；By the fuel gas source in supersonic spray gun
It lights, obtains the high temperature gas flow.
Further, the flow of the oxygen is 130-250L/min；With, it is described atomization kerosene flow be 3-6L/h；
With the pressure of the atomization kerosene is 0.6-1.2MPa, and the high 0.2MPa of pressure of kerosene is atomized described in the pressure ratio of the oxygen.
The above-mentioned technical proposal of the embodiment of the present invention has following beneficial technical effect:
By spraying high temperature gas flow, accurate simulation blade of aviation engine heat to the thermal barrier coating for being coated with corrosive medium
Barrier coating CMAS high temperature corrosion suffered in true use environment influences, and the design and selection to heat barrier coat material provide
Reliable foundation, overcomes the problem that brought adult is high when being tested in detection process using aero-engine,
Improve the detection efficiency that blade thermal barrier coating is influenced by CMAS high temperature corrosion.
Detailed description of the invention
Fig. 1 is the detection method flow chart of thermal barrier coating CMAS high temperature corrosion provided in an embodiment of the present invention.
Specific embodiment
In order to make the objectives, technical solutions and advantages of the present invention clearer, With reference to embodiment and join
According to attached drawing, the present invention is described in more detail.It should be understood that these descriptions are merely illustrative, and it is not intended to limit this hair
Bright range.In addition, in the following description, descriptions of well-known structures and technologies are omitted, to avoid this is unnecessarily obscured
The concept of invention.
Fig. 1 is the detection method flow chart of thermal barrier coating CMAS high temperature corrosion provided in an embodiment of the present invention.
Fig. 1 is please referred to, the embodiment of the present invention provides a kind of detection method of thermal barrier coating CMAS high temperature corrosion, comprising:
S100 carries out polishing to sample surfaces and removes flash removed；And/or ultrasonic cleaning is carried out to the sample.By sample
After the sanding burr on surface, the flatness of sample surfaces can be improved, the precision of detection can be improved when carrying out Corrosion monitoring,
Reduce error.It is similar, ultrasonic cleaning is carried out to sample, removes the various dirts that sample surfaces are infected with, improves sample table
The cleannes in face, and then the precision of Corrosion monitoring is improved, reduce error.
Optionally, the burr of sample surfaces is lightly beaten using the emery paper of 410 mesh.
Optionally, ultrasonic cleaning is carried out to sample using alcohol.
Corrosive medium is coated in the sample surfaces with thermal barrier coating by S200.
Optionally, corrosive medium includes the oxide of calcium, magnesium, aluminium and/or silicon.
Corrosive medium is evenly applied to the surface of sample according to preset concentration.Optionally, preset concentration 13mg/cm2.It can
To ensure in the detection process, the corrosive medium of preset concentration may insure to carry out high temperature corrosion to thermal barrier coating always.
S300, the sample for being coated with corrosive medium heat preset time under the first preset temperature, burn corrosive medium
It ties in sample surfaces.
Optionally, the sample for being coated with corrosive medium is put into high temperature resistance furnace to be heated 0.5 hour at 900 DEG C, is made
Corrosive medium is sintered in the surface of sample.
Correspondingly, the first preset temperature is 900 DEG C, preset time is 0.5 hour.
The sample coated with corrosive medium after heating is fixed on predeterminated position by S400.
In an embodiment of the embodiment of the present invention, sample is fixed on predeterminated position using special fixture, is used for
The surface of the spout of the supersonic spray gun of high temperature gas flow vertically one side of sample.
S500 sprays high temperature gas flow to sample surfaces, so that sample surface temperature is reached the second preset temperature, acquire sample in real time
The temperature of product and the coating state of thermal barrier coating.
The generation step of high temperature gas flow are as follows: kerosene is pressurized by nitrogen, and is pressurized to 0.6MPa-1.2MPa；Make
Pressurized kerosene is atomized with device for atomizing liquid, atomized kerosene；It will be atomized kerosene and oxygen mix, fired
Expect gas source；Fuel gas source is lighted in supersonic spray gun, obtains high temperature gas flow.
Optionally, the range of kerosene oil flow is 3L/h-6L/h；The flow of oxygen is 130L/min-250L/min, and pressure is
0.8-2.4MPa；Kerosene is aviation kerosine.
In an embodiment of the embodiment of the present invention, high temperature gas flow is to light atomization kerosene and oxygen in supersonic spray gun
The mixture of gas obtains, and to make the flame of supersonic spray gun reach supersonic speed, needs to configure corresponding Laval-cavity nozzle, it is also necessary to
The pressure and flow of atomization kerosene and oxygen reach respective preset value.
The flow of oxygen is 130-250L/min；And/or being atomized the flow of kerosene is 3-6L/h；And/or atomization kerosene
Pressure be 0.6-1.2MPa, oxygen pressure ratio atomization kerosene the high 0.2MPa of pressure.When oxygen flow is 130L/min, mist
When the flow for changing kerosene is 3L/h, the pressure for being atomized kerosene is 0.6-1.2MPa, meets experimental provision starting and requires, works as oxygen stream
Amount is 250L/min, and when the flow for being atomized kerosene is 6L/h, the pressure for being atomized kerosene is 0.6-1.2MPa, can make high temperature gas flow
It is heated to 1250 DEG C -1300 DEG C.
Optionally, so that sample surface temperature is reached the second preset temperature in step S500, comprising: adjustment supersonic spray gun with
The distance of sample makes sample surface temperature reach the second preset temperature；And/or the pressure and/or flow of fuel gas source are adjusted,
Sample surface temperature is set to reach the second preset temperature.
Optionally, the range of the second preset temperature is 1250 DEG C -1300 DEG C, ensure that corrosive medium can melt and go deep into
In the thermal barrier coating of sample surfaces.
Before acquiring the temperature of the sample and the coating state of the thermal barrier coating described in step S500 in real time, also wrap
Include following steps:
The sample is cooled down by cooling gas.
Optionally, the pressure of cooling gas is 0.1MPa-1MPa, flow 0L/min-100L/min.Firstly, cooling air
When the pressure and flow of body are in above-mentioned numberical range, it can make sample in high temperature gas flow impact with certain temperature ladder
Degree, Service Environment at this time are more nearly true working environment；Secondly, the pressure and flow of cooling gas are in above-mentioned numerical value
When range, the thermal barrier coating of sample surfaces can be down to room temperature rapidly after high temperature gas flow stops 2 minutes in the detection process,
It realizes and is quickly cooled down.
Optionally, sample includes: test piece sample or leaf sample.
When sample is test piece sample, cooling gas vertically blows to test piece sample far from high temperature gas flow by cooling duct
Side cools down test piece sample, simulates the real operating environments of blade of aviation engine.
When sample is leaf sample, cooling gas is vertically blown into the cooling duct of leaf sample tenon, to test piece sample
Product are cooled down, and the real operating environments of blade of aviation engine are simulated.
Optionally, when sample is test piece sample, test piece sample is disc-shaped, a diameter of 30mm, with a thickness of 5mm.
Optionally, the through-current capacity of cooling gas is 100L/h.
When the temperature of sample surfaces reaches the second preset temperature, the temperature of sample and the coating of thermal barrier coating are acquired in real time
State, comprising: the temperature of sample is acquired by infrared radiation thermometer and/or thermocouple；And/or by CCD industrial camera and/or
Thermal infrared imager acquires the surface of sample surfaces, the differentiation of interface topography figure and Fatigue crack initiation；And/or pass through sound emission
Instrument acquires thermal barrier coating underbead crack damage signal.
Infrared radiation thermometer measures sample close to the temperature of the side of high temperature gas flow；The inside of thermocouple measurement sample and/or
Temperature and/or the temperature of the side far from high temperature gas flow.
To prevent normal signal transmission line by high temperature or Oxidative demage, the embodiment of the present invention uses high temperature waveguide rod.It is high
One end of warm waveguide rod is fixedly connected with sample far from the side of high temperature gas flow, and the other end is connect with Acoustic radiating instrument.
In the specific embodiment of the present invention, the step of to the detection process of thermal barrier coating CMAS high temperature corrosion such as
Under:
S100: the sample surfaces comprising thermal barrier coating are subjected to polishing and remove flash removed, and is clear using alcohol progress ultrasonic wave
It washes；Wherein, the size of sample is
S110: preparing corrosive medium, and corrosive medium is 33CaO -9MgO -13AlO1.5–45SiO2(mol%).
S200: by corrosive medium according to concentration 13mg/cm2It is coated uniformly on sample surfaces.
S300: the sample for being coated with corrosive medium is put into high temperature circuit, is heated 0.5 hour at 900 DEG C, is made to corrode
Medium is sintered in sample surfaces.
S310: welding the waveguide rod that a diameter is 1.4mm far from the side of high temperature gas flow in the sample sintered, to
Connecting acoustic emission acquisition system.
S320: being pressurized to 0.64MPa to aviation kerosine by nitrogen, using device for atomizing liquid to pressurization aviation kerosine into
Row atomization, and merge with oxygen and generate fuel gas source；Wherein, the flow of aviation kerosine is 5.7L/h, and the pressure of oxygen is
1.3MPa, the flow of oxygen is 230L/min, and the pressure ratio of oxygen is atomized at least big 0.2MPa of pressure of aviation kerosine.
S330: being pressurized air, obtains cooling gas；Wherein, the pressure of cooling gas is 0.5MPa, cooling gas
Flow be 50L/min.
S400: the sample coated with the corrosive medium after heating is fixed on predeterminated position.
S510: being lighted fuel gas source by electric spark in supersonic spray gun, generates high temperature gas flow.
S520: adjustment supersonic spray gun adjusts the pressure and flow of fuel gas source at a distance from sample, keeps sample close
The surface temperature of high temperature gas flow side reaches 1250 DEG C.
S530: cooling gas is led into a side surface of the sample far from high temperature gas flow by cooling duct.
S540: by infrared radiation thermometer and thermocouple acquisition sample close to the surface temperature of high temperature gas flow side, far from high
The surface temperature and sample interior temperature of warm air side；By industrial CCD camera and infrared thermal imager obtain sample surfaces,
Interface topography figure develops and Fatigue crack initiation；It is obtained by PCI-2 sound emission acquisition system and is split inside sample thermal barrier coating
Line damage signal.
The embodiment of the present invention is intended to protect a kind of detection method of thermal barrier coating CMAS high temperature corrosion, includes the following steps:
Corrosive medium is coated in the sample surfaces with thermal barrier coating；The sample of corrosive medium is coated under the first preset temperature
Preset time is heated, corrosive medium is made to be sintered in sample surfaces；The sample coated with corrosive medium after heating is fixed on pre-
If position；High temperature gas flow is sprayed to sample surfaces, sample surface temperature is made to reach the second preset temperature, acquires the temperature of sample in real time
The coating state of degree and thermal barrier coating.Above scheme has following beneficial technical effect:
By spraying high temperature gas flow, accurate simulation blade of aviation engine heat to the thermal barrier coating for being coated with corrosive medium
Barrier coating CMAS high temperature corrosion suffered in true use environment influences, and the design and selection to heat barrier coat material provide
Reliable foundation, overcomes the problem that brought adult is high when being tested in detection process using aero-engine,
Improve the detection efficiency that blade thermal barrier coating is influenced by CMAS high temperature corrosion.
It should be understood that above-mentioned specific embodiment of the invention is used only for exemplary illustration or explains of the invention
Principle, but not to limit the present invention.Therefore, that is done without departing from the spirit and scope of the present invention is any
Modification, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.In addition, appended claims purport of the present invention
Covering the whole variations fallen into attached claim scope and boundary or this range and the equivalent form on boundary and is repairing
Change example.
Claims (12)
1. a kind of detection method of thermal barrier coating CMAS high temperature corrosion, which comprises the steps of:
Corrosive medium is coated in the sample surfaces with thermal barrier coating by S200；
S300, the sample for being coated with the corrosive medium heat preset time under the first preset temperature, make the corruption
Erosion medium is sintered in the sample surfaces；
The sample coated with the corrosive medium after heating is fixed on predeterminated position by S400；
S500, Xiang Suoshu sample surfaces spray high temperature gas flow, so that the sample surface temperature is reached the second preset temperature, adopt in real time
Collect the temperature of the sample and the coating state of the thermal barrier coating.
2. the detection method of thermal barrier coating CMAS corrosion according to claim 1, which is characterized in that further include walking as follows
It is rapid:
S100 carries out polishing to the sample surfaces and removes flash removed, and carries out ultrasonic cleaning using alcohol.
3. the detection method of thermal barrier coating CMAS high temperature corrosion according to claim 1, which is characterized in that in step S500
Further include following steps before the coating state of the temperature for acquiring the sample in real time and the thermal barrier coating:
The sample is cooled down by cooling gas.
4. the detection method of thermal barrier coating CMAS high temperature corrosion according to claim 3, which is characterized in that
The sample includes: test piece sample or leaf sample；
The cooling gas vertically blows to the side of the test piece sample far from the high temperature gas flow by cooling duct；Or
The cooling gas is vertically blown into the cooling duct of the leaf sample tenon.
5. the detection method of thermal barrier coating CMAS high temperature corrosion according to claim 1, which is characterized in that
The corrosive medium includes the oxide of calcium, magnesium, aluminium and/or silicon.
6. the detection method of thermal barrier coating CMAS high temperature corrosion according to claim 5, which is characterized in that
The corrosive medium is evenly applied to the surface of the sample according to preset concentration.
7. the detection method of thermal barrier coating CMAS high temperature corrosion according to claim 1, which is characterized in that in step S500
It is described that sample surface temperature is made to reach the second preset temperature, comprising:
The supersonic spray gun is adjusted at a distance from the sample, the sample surface temperature is made to reach the second preset temperature；With/
Or
The pressure and/or flow for adjusting the fuel gas source, make the sample surface temperature reach the second preset temperature.
8. the detection method of thermal barrier coating CMAS high temperature corrosion according to claim 1, which is characterized in that in step S500
The coating state of the temperature for acquiring the sample in real time and the thermal barrier coating, comprising:
The temperature of the sample is acquired by infrared radiation thermometer and/or thermocouple；And/or
The sample thermal barrier coating surface topography is acquired by industrial CCD camera；And/or
The sample thermal barrier coating surface and interface Morphology and Fatigue crack initiation are acquired by infrared thermal imager；And/or
The sample thermal barrier coating underbead crack damage signal is acquired by Acoustic radiating instrument.
9. the detection method of thermal barrier coating CMAS high temperature corrosion according to claim 8, which is characterized in that
The infrared radiation thermometer measures the sample close to the temperature of the side of the high temperature gas flow；And/or
The temperature of the internal temperature of sample described in the thermocouple measurement and/or the side far from the high temperature gas flow.
10. the detection method of thermal barrier coating CMAS high temperature corrosion according to claim 8, which is characterized in that
The connection of one end of the Acoustic radiating instrument and waveguide rod；
The other end of the waveguide rod and sintering have the sample of the corrosive medium solid far from the side of the high temperature gas flow
Fixed connection.
11. the detection method of thermal barrier coating CMAS high temperature corrosion according to claim 1, which is characterized in that the high temperature
The generation step of air-flow are as follows:
Kerosene is pressurized to preset pressure, and is atomized, atomized kerosene；
By the atomization kerosene and oxygen mix, fuel gas source is obtained；
The fuel gas source is lighted in supersonic spray gun, obtains the high temperature gas flow.
12. the detection method of thermal barrier coating CMAS high temperature corrosion according to claim 11, which is characterized in that
The flow of the oxygen is 130-250L/min；And/or
The flow of the atomization kerosene is 3-6L/h；And/or
The pressure of the atomization kerosene is 0.6-1.2MPa, and the pressure of atomization kerosene described in the pressure ratio of the oxygen is high
0.2MPa。
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Application publication date: 20190614 |