CN115952699B - Method for determining material performance parameters of engine coating - Google Patents
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Abstract
The invention discloses a method for determining material performance parameters of an engine coating, relates to the technical field of surface coating material performance parameter testing, and provides a technical scheme capable of testing the material performance parameters of the engine coating at different temperatures. A method for determining material performance parameters for engine coatings, comprising the steps of: sequentially placing a plurality of coating samples at different preset temperatures, and measuring the length of a neutral plane of each coating sample after bending at different preset temperatures; establishing a first relation of material performance parameters of the characterization coating sample based on a Stoney formula; establishing a second relation for representing material performance parameters of the coating sample based on the equilibrium relation of the surface force after the coating sample is bent and deformed and the lengths of neutral surfaces of the sample at different preset temperatures; the material performance parameters of the engine coating are determined based on the length of the neutral plane of each sample at different preset temperatures, and the first and second relationships.
Description
Technical Field
The invention relates to the technical field of surface coating material performance parameter testing, in particular to a method for determining material performance parameters of an engine coating.
Background
The hot end component of the pump post-swing liquid oxygen kerosene rocket engine is usually in service under high-temperature, oxygen-enriched and other environments, and the conventional structural materials (such as high-temperature alloy) at present are difficult to adapt to the extreme environments. In order to improve the service life and service durability of the hot-end component and ensure the safe service of the high-temperature component in an oxygen-enriched environment, a coating, such as an enamel coating, is often coated on the surface of the hot-end component to thermally protect the hot-end component.
The coating thermally expands under heat at high temperature and its modulus of elasticity changes with increasing temperature. In order to evaluate the strength and service life of the coating, the elastic modulus and the thermal expansion coefficient of the coating at different temperatures need to be measured to analyze the thermal stress and the damage evolution rule in the use process.
The ejector rod method is a common method for measuring the thermal expansion coefficients of bulk materials at different temperatures. However, engine coatings are typically prepared on metal substrate surfaces by thermal spraying, slurry sintering, etc., and are very thin, not individual coated blocks, and thus, the push rod method cannot be directly applied to thermal expansion coefficient testing of hot end coatings.
High temperature nanoindentation is a method for measuring the modulus of elasticity of a material at different temperatures, and has been more applied in recent years to measuring the local modulus of elasticity of a homogeneous bulk material. However, the accuracy of the measurement results is still to be questionable when high temperature nanoindentation is applied to hot end coating. In addition, the thermal expansion coefficient test piece and the high temperature nano-indentation test piece have completely different geometric configurations, so that the test piece for performing the thermal expansion coefficient test and the test piece for performing the nano-indentation test are necessarily different, and different test pieces may generate test deviations due to different production batches, test environments, test methods and the like, and such deviations are unavoidable.
Disclosure of Invention
The invention aims to provide a method for determining material performance parameters of an engine coating, and provides a technical scheme capable of testing the material performance parameters of the engine coating at different temperatures.
The invention provides a method for determining material performance parameters of an engine coating, which comprises the following steps:
sequentially placing a plurality of coating samples at different preset temperatures, and measuring the length of a neutral plane of each coating sample after bending at the different preset temperatures;
establishing a first relationship characterizing a material performance parameter of the coating sample based on a ston formula;
establishing a second relation representing material performance parameters of the coating sample based on the equilibrium relation of the surface force after the coating sample is bent and deformed and the lengths of the neutral surfaces of the sample at different preset temperatures;
determining a material performance parameter of the engine coating based on the length of the neutral plane of each sample at different preset temperatures and the first and second relationships.
Compared with the prior art, the method for determining the material performance parameters of the engine coating provided by the invention comprises the steps of firstly determining the lengths of the midplanes of a plurality of coating samples after being bent at different preset temperatures, then establishing a first relation for representing the material performance parameters of the coating samples based on a Stoney formula, and establishing a second relation for representing the material performance parameters of the coating samples based on the equilibrium relation of the surface forces after the coating samples are bent and deformed and the lengths of the neutral surfaces of the samples at different preset temperatures; and combining the first relation and the second relation, and determining the material performance parameters of the engine coating based on the lengths of the neutral surfaces of each sample at different preset temperatures. The method for determining the material performance parameters of the engine coating overcomes the limitation that the traditional ejector rod method cannot be used for the coating, also overcomes the limitation that the high-temperature nano indentation method cannot obtain the macroscopic elastic modulus of the coating, and can perform a test on a coating sample and simultaneously measure the elastic modulus and the thermal expansion coefficient of the coating at different temperatures.
Further, before the plurality of coating samples are sequentially placed at different preset temperatures, the method for determining the material performance parameters of the engine coating further includes:
a plurality of coating coupons were prepared on the substrate.
Further, the preparing a plurality of coating samples on the substrate comprises:
and preparing a coating on the substrate according to a preset size to obtain a plurality of coating samples.
Further, before the plurality of coating samples are sequentially placed at different preset temperatures, the method for determining the material performance parameters of the engine coating further includes:
and determining a plurality of preset temperatures according to the working temperature of the engine.
Further, the sequentially placing the plurality of coating samples at different preset temperatures, and determining the length of the neutral plane of each of the coating samples after bending at the different preset temperatures includes:
sequentially placing a plurality of coating samples at different preset temperatures, wherein each coating sample can generate different integral bending deformation at the different preset temperatures;
and respectively measuring the neutral plane length of each coating sample after the whole bending deformation at different temperatures.
Further, the material performance parameters include a coefficient of thermal expansion and an elastic modulus;
the first relationship characterizing the material performance parameters of the coating sample based on the Stoney formula is:
in the method, in the process of the invention,
is the temperature T i The coefficient of thermal expansion of the coating sample, < >>
Is the temperature T i Thermal expansion coefficient of the substrate->
,/>
Is the coating sampleAnd the substrate is at T i Elastic modulus and poisson ratio at temperature, +.>
，/>
Is the substrate at T i Modulus of elasticity and poisson's ratio at temperature,t f andt s the thickness of the coating sample and the substrate, respectively.
Further, the material performance parameters include a coefficient of thermal expansion and an elastic modulus;
the equilibrium relation based on bending deformation force obtains a second relation of material performance parameters of the coating sample, wherein the second relation is as follows:
T 0 is the curing temperature at which the coating coupon is prepared,l 0 the neutral plane length of the coating sample,
is the coating sample at T i Length of neutral plane after bending at temperature.
Further, the determining the material performance parameters of the engine coating based on the length of the neutral plane of each of the coating samples at different preset temperatures, and the first and second relationships includes:
and combining the first relation and the second relation to obtain an equation set of an elastic modulus table and a thermal expansion coefficient of the coating sample:
and obtaining the elastic modulus and the thermal expansion coefficient of the coating sample at the corresponding preset temperatures based on the lengths of the neutral surfaces of the coating samples at different preset temperatures and the equation set of the elastic modulus and the thermal expansion coefficient of the coating samples.
Further, the coating samples include enamel coating samples, ceramic coating samples, or metal coating samples.
Further, a high temperature deformation sensor is used to determine the length of the neutral plane of each coating sample after bending at the different preset temperatures.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and do not constitute a limitation on the invention. In the drawings:
FIG. 1 shows a flow chart of steps of a method for determining performance parameters of an engine enamel coating provided by an embodiment of the invention;
FIG. 2 is a schematic diagram showing the change of the thermal expansion coefficient with temperature of an enamel coating prepared by sintering slurry according to the embodiment of the invention;
FIG. 3 is a schematic view showing the change of the elastic modulus with temperature of an enamel coating prepared by sintering slurry according to an embodiment of the present invention;
FIG. 4 is a schematic diagram showing the variation of the thermal expansion coefficient with temperature of another enamel coating prepared by thermal spraying in accordance with an embodiment of the present invention;
fig. 5 shows a schematic diagram of the change of the elastic modulus with temperature of another enamel coating prepared by thermal spraying in an embodiment of the invention.
Description of the embodiments
Hereinafter, embodiments of the present disclosure will be described with reference to the accompanying drawings. It should be understood that the description is only exemplary and is not intended to limit the scope of the present disclosure. In addition, in the following description, descriptions of well-known structures and techniques are omitted so as not to unnecessarily obscure the concepts of the present disclosure.
Various structural schematic diagrams according to embodiments of the present disclosure are shown in the drawings. The figures are not drawn to scale, wherein certain details are exaggerated for clarity of presentation and may have been omitted. The shapes of the various regions, layers and relative sizes, positional relationships between them shown in the drawings are merely exemplary, may in practice deviate due to manufacturing tolerances or technical limitations, and one skilled in the art may additionally design regions/layers having different shapes, sizes, relative positions as actually required.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise. The meaning of "a number" is one or more than one unless specifically defined otherwise.
The hot end component of the pump post-swing liquid oxygen kerosene rocket engine is usually in service under high-temperature, oxygen-enriched and other environments, and the conventional structural materials (such as high-temperature alloy) at present are difficult to adapt to the extreme environments. In order to improve the service life and service durability of the hot end component and ensure the safe service of the high-temperature component in an oxygen-enriched environment, enamel coatings are often coated on the surface of the hot end component to thermally protect the hot end component.
The enamel coating is a compact coating which is finally obtained by performing physical-chemical reaction on a metal matrix and inorganic glass frit (enamel glaze) at high temperature when one or more layers of enamel glaze coated on the metal surface is enamel-burned at high temperature, and separating out crystals at an interface and forming chemical bonds. The enamel coating thermally expands under heat at high temperature, and the elastic modulus of the enamel coating also changes along with the temperature rise. In order to evaluate the strength and service life of the enamel coating, the elastic modulus and the thermal expansion coefficient of the enamel coating at different temperatures need to be measured to analyze the thermal stress and the damage evolution rule in the use process.
The ejector rod method is a common method for measuring the thermal expansion coefficients of bulk materials at different temperatures. However, enamel coatings are generally prepared on the surface of a metal substrate by thermal spraying, slurry sintering and the like, and have very thin thickness, and are not individual coating blocks, so that the ejector rod method cannot be directly applied to the thermal expansion coefficient test of the enamel coating.
High temperature nanoindentation is a method for measuring the modulus of elasticity of a material at different temperatures, and has been more applied in recent years to measuring the local modulus of elasticity of a homogeneous bulk material. However, the accuracy of the measurement results is still to be questionable when the high temperature nanoindentation is applied to enamel coating. In addition, the thermal expansion coefficient test piece and the high temperature nano-indentation test piece have completely different geometric configurations, so that the test piece for performing the thermal expansion coefficient test and the test piece for performing the nano-indentation test are necessarily different, and different test pieces may generate test deviations due to different production batches, test environments, test methods and the like, and such deviations are unavoidable.
Thus, there is currently no macroscopic elastic modulus test method for enamel coatings at high temperatures.
Based on the above, the embodiment of the invention discloses a method for determining a material performance parameter of an engine coating, which comprises the following steps:
and S100, sequentially placing a plurality of coating samples at different preset temperatures, and measuring the length of a neutral plane of each coating sample after bending at the different preset temperatures.
In the embodiment of the present invention, the preset temperature may be determined according to an operating temperature of the engine. The number of preset temperatures may be specifically set according to the requirement, but at least two temperature points are included. For example, when the operating temperature of the engine ranges from 100 ℃ to 550 ℃, the different preset temperatures may include: 100 ℃, 150 ℃, 200 ℃, 250 ℃, 300 ℃, 350 ℃, 400 ℃, 450 ℃, 500 ℃ and 550 ℃.
Specifically, before the plurality of coating samples are sequentially placed at different preset temperatures, the method for determining the material performance parameters of the engine coating further includes: a plurality of coating samples were prepared on a substrate according to a preset size. The coating sample can be an enamel coating sample, a ceramic coating sample or a metal coating sample.
In practice, most of the methods currently available can be used to prepare a coating coupon on a substrate. For example, a slurry method and a thermal spraying method can be used for preparing a coating sample, and an electron beam physical vapor deposition method and a laser cladding method can be used. It should be appreciated that in preparing the coated coupon, the choice may be made according to the practical range of application, economics, and the need for thermal shock resistance of the coated coupon.
When the coating sample is an enamel coating sample, in a specific example, the preparation process of the enamel coating sample may include coating enamel slurry on one surface of a flat substrate by a slurry sintering method, wherein the enamel coating is formed to have a thickness of 70 μm, and the flat substrate is made of a superalloy, and has a length of 100mm, a width of 30mm, and a thickness of 500 μm.
In another specific example, the preparation process of the enamel coating sample may include preparing an enamel slurry on one surface of a flat substrate using a thermal spray method, wherein the enamel coating has a thickness of 300 μm; the flat substrate is made of high-temperature alloy, and has the length of 150mm, the width of 30mm and the thickness of 1mm.
The dimensions of the coating coupon are set according to the test requirements, and it is noted that the thickness of the coating coupon needs to be much smaller than the thickness of the substrate to be able to coat or otherwise form a coating on the substrate. Illustratively, when the thickness of the coated coupon is 70 μm, the thickness of the substrate is 500 μm. When the thickness of the coated sample was 300. Mu.m, the thickness of the substrate was 1mm.
The sequentially placing the plurality of coating samples at different preset temperatures and determining the length of the neutral plane of each of the coating samples after being bent at the different preset temperatures may include: and sequentially placing a plurality of coating samples at different preset temperatures, wherein each coating sample is subjected to different overall bending deformation. It should be appreciated that each coated coupon would experience a different degree of global bending deformation due to the different temperatures. Thereafter, the neutral plane length after the whole bending deformation of each of the coating samples at different temperatures was measured, respectively. The method for specifically measuring the neutral plane length of the coating sample after the whole bending deformation can be any existing method, and the embodiment of the invention is not particularly limited.
S200, establishing a first relation for representing the material performance parameters of the coating sample based on a Stoney formula.
In particular, the material performance parameters may include a coefficient of thermal expansion and an elastic modulus. Based on the Stoney formula, a first relationship characterizing the material performance parameters of the coating sample is obtained as follows:
in the method, in the process of the invention,
is the temperature T i The coefficient of thermal expansion of the coating sample, < >>
Is the temperature T i Thermal expansion coefficient of the substrate->
，/>
Is the coating sample and the substrate at T i Elastic modulus and poisson ratio at temperature, +.>
，/>
Is the substrate at T i Modulus of elasticity and poisson's ratio at temperature,t f andt s the thickness of the coating sample and the substrate, respectively.
S300, establishing a second relation of material performance parameters representing the coating sample based on the equilibrium relation of the surface forces after the coating sample is bent and deformed and the lengths of the neutral surfaces of the sample at different preset temperatures.
In particular, the material performance parameters include coefficient of thermal expansion and modulus of elasticity.
Based on the equilibrium relation of the surface forces after the coating sample is bent and deformed and the lengths of the neutral surfaces of the sample at different preset temperatures, a second relation for representing the material performance parameters of the coating sample is established, wherein the second relation comprises the following steps:
（2）；
T 0 is the curing temperature at which the coating coupon is prepared,l 0 the neutral plane length of the coating sample,
is the coating sample at T i Length of neutral plane after bending at temperature.
S400, determining the material performance parameters of the engine coating based on the lengths of the neutral planes of the samples at different preset temperatures and the first relation and the second relation.
In a specific implementation process, the first relation and the second relation are combined to obtain an equation set of the elastic modulus and the thermal expansion coefficient of the coating sample:
obtaining the coating samples at different preset temperatures based on the lengths of neutral planes of the coating samples at different preset temperatures and the equation sets of the elastic modulus and the thermal expansion coefficient of the coating samplesModulus of elasticity and coefficient of thermal expansion. Further, each of the coating samples measured at the preset temperature was subjected to T i Length of neutral plane after bending at temperature
Substituting into the formula (3) to obtain the elastic modulus +.>
Then ∈>
And substituting the thermal expansion coefficient into the formula (3) to obtain the thermal expansion coefficient of the coating sample at the corresponding temperature>
。
In a specific implementation manner, the method for determining the material performance parameters of the engine coating provided by the embodiment of the invention comprises the following steps:
step 1: sample preparation.
Coating an enamel coating on one surface of a flat substrate by adopting a slurry sintering method, wherein the thickness of the enamel coating is as follows
The method comprises the steps of carrying out a first treatment on the surface of the The plate substrate is made of high-temperature alloy, and has the length of 100mm, the width of 30mm and the thickness +.>
。
Step 2: and determining the temperature range to be measured.
Selecting a temperature interval to be measured to be 100-550 ℃, wherein the total temperature to be measured is 10, and T1-T10 are respectively as follows: 100 ℃, 150 ℃, 200 ℃, 250 ℃, 300 ℃, 350 ℃, 400 ℃, 450 ℃, 500 ℃ and 550 ℃.
Step 3: and measuring the length of the neutral surface of the enamel coating test piece at different temperatures.
The high-temperature deformation sensor is adopted to measure the length of the neutral surface of the test piece after bending at different temperatures Ti
The test results are shown in table 1.
TABLE 1
Step 4: and calculating the elastic modulus and the thermal expansion coefficient of the enamel coating.
Obtaining the elastic modulus of the enamel coating at different temperatures Ti according to the formula (4)
Then according to the formula (3), the thermal expansion coefficient of the enamel coating at different temperatures Ti is obtained>
. In the calculation process, the Poisson ratio of the enamel coating is not changed along with the temperature, and the thermal expansion coefficient and the elastic modulus of the substrate are not changed along with the temperature, namely +.>
，/>
，
. The results obtained by calculation according to the above steps are shown in table 1, fig. 2 and fig. 3. Fig. 2 is a schematic diagram showing a change of a thermal expansion coefficient with temperature of an enamel coating prepared by sintering slurry according to an embodiment of the invention, and fig. 3 is a schematic diagram showing a change of an elastic modulus with temperature of an enamel coating prepared by sintering slurry according to an embodiment of the invention.
In another specific embodiment, step 1: sample preparation.
Preparing enamel coating on one surface of the flat substrate by adopting a thermal spraying method, wherein the thickness of the enamel coating is as follows
The method comprises the steps of carrying out a first treatment on the surface of the The material of the flat substrate is high-temperature combinationGold, 150mm in length, 30mm in width, and +.>
。
Step 2: and determining the temperature range to be measured.
Selecting a temperature interval to be measured to be 25-1150 ℃ and 12 temperatures to be measured, wherein T1-T12 are respectively as follows: 25 ℃, 150 ℃, 250 ℃, 350 ℃, 450 ℃, 550 ℃, 650 ℃, 750 ℃, 850 ℃, 950 ℃, 1050 ℃ and 1150 ℃.
Step 3: and measuring the length of the neutral surface of the enamel coating test piece at different temperatures.
The high-temperature deformation sensor is adopted to measure the length of the neutral surface of the test piece after bending at different temperatures Ti
The test results are shown in table 2.
TABLE 2
Step 4: and calculating the elastic modulus and the thermal expansion coefficient of the enamel coating.
Obtaining the elastic modulus of the enamel coating at different temperatures Ti according to the formula (4)
Then according to the formula (3), the thermal expansion coefficient of the enamel coating at different temperatures Ti is obtained>
. In the calculation process, the Poisson's ratio of the enamel coating is considered to be unchanged with temperature,/>
The method comprises the steps of carrying out a first treatment on the surface of the The thermal expansion coefficient of the substrate varies with temperature, +.>
. The results obtained by calculation according to the above steps are shown in table 2, fig. 4 and fig. 5. FIG. 4 shows the use of thermal spraying in an embodiment of the inventionFig. 5 is a schematic diagram showing the change of the thermal expansion coefficient with temperature of an enamel coating prepared by thermal spraying, and fig. 5 is a schematic diagram showing the change of the elastic modulus with temperature of an enamel coating prepared by thermal spraying in the embodiment of the invention.
From the results of fig. 5, it can be seen that the thermal expansion coefficient of the enamel coating measured by the present invention increases with the increase of temperature, which is consistent with the trend of the test results of other enamel coatings measured by the conventional ejector pin method.
Although the invention is described herein in connection with various embodiments, other variations to the disclosed embodiments can be understood and effected by those skilled in the art in practicing the claimed invention, from a study of the drawings, the disclosure, and the appended claims. In the claims, the word "comprising" does not exclude other elements or steps, and the "a" or "an" does not exclude a plurality. A single processor or other unit may fulfill the functions of several items recited in the claims. The mere fact that certain measures are recited in mutually different dependent claims does not indicate that a combination of these measures cannot be used to advantage.
Although the invention has been described in connection with specific features and embodiments thereof, it will be apparent that various modifications and combinations can be made without departing from the spirit and scope of the invention. Accordingly, the specification and drawings are merely exemplary illustrations of the present invention as defined in the appended claims and are considered to cover any and all modifications, variations, combinations, or equivalents that fall within the scope of the invention. It will be apparent to those skilled in the art that various modifications and variations can be made to the present invention without departing from the spirit or scope of the invention. Thus, it is intended that the present invention also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.
Claims (7)
1. A method for determining a material property parameter for an engine coating, the method comprising the steps of:
sequentially placing a plurality of coating samples at different preset temperatures, and measuring the length of a neutral plane of each coating sample after bending at the different preset temperatures;
establishing a first relationship characterizing a material performance parameter of the coating sample based on a ston formula;
establishing a second relation representing material performance parameters of the coating sample based on the equilibrium relation of the surface force after the coating sample is bent and deformed and the lengths of the neutral surfaces of the sample at different preset temperatures;
determining a material performance parameter of the engine coating based on the length of the neutral plane of each sample at different preset temperatures, and the first and second relationships;
the material performance parameters include thermal expansion coefficient and elastic modulus;
the first relation for establishing the material performance parameters of the coating sample based on the Stoney formula is as follows:
in the method, in the process of the invention,
is the temperature T i The coefficient of thermal expansion of the coating sample, < >>
Is the temperature T i The coefficient of thermal expansion of the substrate at the time,
，/>
is the coating sample and the substrate at T i Elastic modulus and poisson ratio at temperature, +.>
，/>
Is the substrate at T i Modulus of elasticity and poisson's ratio at temperature,t f andt s the thickness of the coating sample and the substrate, respectively;
based on the equilibrium relation of the surface forces after the coating sample is bent and deformed and the lengths of the neutral surfaces of the sample at different preset temperatures, a second relation for representing the material performance parameters of the coating sample is established, wherein the second relation comprises the following steps:
T 0 is the curing temperature at which the coating coupon is prepared,l 0 the neutral plane length of the coating sample,
is that the coating sample is at T i The length of the neutral plane after bending at temperature;
determining the material performance parameters of the engine coating based on the length of the neutral plane of each of the samples at different preset temperatures, and the first and second relationships, comprises:
and combining the first relation and the second relation to obtain an equation set of the elastic modulus and the thermal expansion coefficient of the coating sample:
and obtaining the elastic modulus and the thermal expansion coefficient of the coating sample at the corresponding preset temperatures based on the lengths of the neutral surfaces of the coating samples at different preset temperatures and the equation set of the elastic modulus and the thermal expansion coefficient of the coating samples.
2. The method for determining a material property parameter for an engine coating according to claim 1, wherein the method for determining a material property parameter for an engine coating further comprises, before the sequentially exposing the plurality of coating samples to different preset temperatures:
a plurality of coating coupons were prepared on the substrate.
3. The method of determining material performance parameters for an engine coating of claim 2, wherein preparing a plurality of coating samples on a substrate comprises:
and preparing a coating on the substrate according to a preset size to obtain a plurality of coating samples.
4. The method for determining a material property parameter for an engine coating according to claim 1, wherein the method for determining a material property parameter for an engine coating further comprises, before the sequentially exposing the plurality of coating samples to different preset temperatures:
and determining a plurality of preset temperatures according to the working temperature of the engine.
5. The method of determining material performance parameters for engine coating according to claim 1, wherein sequentially exposing a plurality of coating samples to different preset temperatures and determining the length of the neutral plane of each of the coating samples after bending at the different preset temperatures comprises:
sequentially placing a plurality of coating samples at different preset temperatures, wherein each coating sample can generate different integral bending deformation at the different preset temperatures;
and respectively measuring the neutral plane length of each coating sample after the whole bending deformation at different temperatures.
6. The method for determining material performance parameters for engine coatings according to any one of claims 1-5, wherein the coating samples comprise enamel coating samples, ceramic coating samples, or metal coating samples.
7. The method for determining material performance parameters for engine coating according to any one of claims 1-5, wherein the length of the neutral plane of each of the coated samples after bending at the different preset temperatures is determined using a high temperature deformation sensor.
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