CN114136594A - Turbine blade thermal shock test device - Google Patents
Turbine blade thermal shock test device Download PDFInfo
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- CN114136594A CN114136594A CN202111222035.6A CN202111222035A CN114136594A CN 114136594 A CN114136594 A CN 114136594A CN 202111222035 A CN202111222035 A CN 202111222035A CN 114136594 A CN114136594 A CN 114136594A
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- 238000012360 testing method Methods 0.000 title claims abstract description 94
- 230000035939 shock Effects 0.000 title claims abstract description 34
- 238000001816 cooling Methods 0.000 claims abstract description 40
- 238000010438 heat treatment Methods 0.000 claims abstract description 35
- 238000012545 processing Methods 0.000 claims abstract description 24
- 238000001514 detection method Methods 0.000 claims abstract description 16
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 9
- 230000006698 induction Effects 0.000 claims description 5
- 229920000742 Cotton Polymers 0.000 claims description 4
- 238000009529 body temperature measurement Methods 0.000 claims description 4
- 230000007246 mechanism Effects 0.000 claims description 3
- 238000012544 monitoring process Methods 0.000 claims description 3
- RVTZCBVAJQQJTK-UHFFFAOYSA-N oxygen(2-);zirconium(4+) Chemical compound [O-2].[O-2].[Zr+4] RVTZCBVAJQQJTK-UHFFFAOYSA-N 0.000 claims description 3
- 229910001928 zirconium oxide Inorganic materials 0.000 claims description 3
- 239000012720 thermal barrier coating Substances 0.000 abstract description 6
- 239000002131 composite material Substances 0.000 abstract description 4
- 238000004088 simulation Methods 0.000 abstract description 3
- 230000009471 action Effects 0.000 abstract description 2
- 239000000956 alloy Substances 0.000 abstract description 2
- 229910045601 alloy Inorganic materials 0.000 abstract description 2
- 238000002485 combustion reaction Methods 0.000 abstract description 2
- 238000003912 environmental pollution Methods 0.000 abstract description 2
- 238000009413 insulation Methods 0.000 description 10
- 238000010586 diagram Methods 0.000 description 3
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000012267 brine Substances 0.000 description 1
- 238000005524 ceramic coating Methods 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000010365 information processing Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- HPALAKNZSZLMCH-UHFFFAOYSA-M sodium;chloride;hydrate Chemical compound O.[Na+].[Cl-] HPALAKNZSZLMCH-UHFFFAOYSA-M 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0073—Fatigue
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Combustion & Propulsion (AREA)
- Health & Medical Sciences (AREA)
- Engineering & Computer Science (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
Abstract
The invention provides a turbine blade thermal shock test device, which comprises: a heating system; a cooling system; a detection system; a sample transfer system and a processing system. The turbine blade thermal shock test device provided by the invention can be used for performing thermal shock fatigue performance and service life assessment tests of thermal barrier coatings and fatigue life tests of turbine guide blades, working blades, combustion parts and simulation samples made of high-temperature alloys and composite materials under the action of temperature cycle. The test device has the advantages of simple structure, convenient operation, high heating speed, low use cost, little environmental pollution and high test efficiency.
Description
Technical Field
The invention belongs to the technical field of aero-engine part tests, and particularly relates to a thermal shock test device for turbine blades.
Background
With the continuous improvement of the turbine front temperature, thrust-weight ratio and gas pressure of the aero-engine, higher requirements are made on the high-temperature resistance of hot-end components, particularly composite materials and ceramic coatings. Among various methods for performing thermal fatigue simulation assessment on a hot-end component, the thermal shock test method can realize the support of the strength performance assessment and the design optimization of the thermal barrier coating and the high-temperature composite material. The thermal shock tester for the thermal barrier coating is special test equipment for evaluating the strength and the service life of the thermal barrier coating in a high-temperature environment.
Disclosure of Invention
In order to solve the above problems, a special apparatus is provided to examine the strength and life of the thermal barrier coating in a high temperature environment.
The invention aims to provide a thermal shock test device for turbine blades, which comprises: the heating system is used for heating the sample; the cooling system is used for cooling the sample; the detection system is used for detecting the sample; a sample transport system for transport of samples among the heating system, the cooling system, and the detection system; and the processing system is used for receiving and processing the working data of the heating system, the cooling system, the detection system and the conveying system and generating working commands of the test conveying system so as to control the working of the sample conveying system.
The turbine blade thermal shock test device provided by the invention is also characterized in that the heating system comprises a test chamber for placing a sample and heating equipment for heating the sample, the outer layer of the test chamber is provided with a heat insulation layer, the test chamber is provided with an induction device, the induction device is used for controlling the opening and closing of a door of the test chamber when the sample enters and moves out of the test chamber, and the heat insulation layer sequentially comprises heat insulation cotton, a vacuum heat insulation layer and a zirconium oxide reflective film from inside to outside.
The thermal shock test device for the turbine blade is also characterized in that heating sources in the heating equipment are respectively arranged in an array mode at different heights, the heating sources at different heights are used for realizing an axial gradient temperature field in a test cabin, and the array arrangement is used for realizing a circumferential gradient temperature field in the test cabin.
The turbine blade thermal shock test device provided by the invention is also characterized in that the test cabin is provided with an observation window and an infrared temperature measuring hole, and the infrared temperature measuring hole is used for monitoring the temperature of a sample in the heating process through a thermal infrared imager.
The thermal shock test device for the turbine blade is also characterized in that the cooling system comprises air cooling equipment and water cooling equipment; one end of an air inlet of the air cooling system is of a circular structure, the other end of the air inlet of the air cooling system is of a flat structure, a plurality of air outlet holes distributed in an array mode are formed in the flat structure, and the direction of the air outlet holes is adjustable.
The turbine blade thermal shock test device provided by the invention is also characterized in that the detection system comprises an image processing device, and the image processing device is used for acquiring surface information of a test.
The turbine blade thermal shock test device provided by the invention also has the characteristics that the surface information processing process acquired by the image processing equipment comprises the following steps: s1: comparing the first image information and the second image information which are respectively collected by the image processing equipment, if the first image information is the same as the second image information, continuing the test, and if the first image information is different from the second image information, performing the next step; s2: and comparing the second image information with a database in the processing system, if the database comprises the test crack image information which is the same as the second image information, judging that the sample has the crack, sending a stop command by the processing system, and recording a test result, wherein the test result comprises the length of the crack, the number of cycles for the crack to appear and the appearance of the crack.
The turbine blade thermal shock test device provided by the invention is also characterized in that the sample conveying system comprises a clamp for fixing a sample, a lifting mechanism for changing the height of the sample and a slide rail for moving in the device, a cooling channel is arranged in the clamp, and the slide rail is arranged above the heating system, the cooling system and the detection system.
The turbine blade thermal shock test device provided by the invention is also characterized in that the sample conveying system further comprises a mass sensor for detecting the mass of the sample and a temperature sensor for detecting the temperature of the clamp.
The turbine blade thermal shock test device provided by the invention is also characterized in that the test sample is provided with a spring piece which is tightly pressed with the measuring end of the temperature sensor, and the spring piece is fixed on the test sample through bolts arranged at two ends of the test sample.
Compared with the prior art, the invention has the following beneficial effects
The turbine blade thermal shock test device provided by the invention can be used for performing thermal shock fatigue performance and service life assessment tests of thermal barrier coatings and fatigue life tests of turbine guide blades, working blades, combustion parts and simulation samples made of high-temperature alloys and composite materials under the action of temperature cycle. The test device has the advantages of simple structure, convenient operation, high heating speed, low use cost, little environmental pollution and high test efficiency.
Description of the drawings:
in order to more clearly illustrate the technical solution of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a turbine blade thermal shock test apparatus according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a test temperature measuring part in the thermal shock testing device for the turbine blade according to the embodiment of the invention;
fig. 3 is a schematic structural diagram of a test fixture in the thermal shock test device for the turbine blade according to the embodiment of the invention.
Detailed Description
In order to make the technical means, the creation features, the achievement purposes and the effects of the invention easy to understand, the following embodiments are specifically described with reference to the attached drawings.
In the description of the embodiments of the present invention, it should be understood that the terms "central", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only used for convenience in describing and simplifying the description of the present invention, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified. The terms "mounted," "connected," and "coupled" are to be construed broadly and may, for example, be fixedly coupled, detachably coupled, or integrally coupled; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.
The embodiment of the invention provides a thermal shock test device for turbine blades, which comprises: a heating system for heating the sample 3; a cooling system for cooling the sample 3; a detection system for detecting the sample 3; a sample transport system 7 for transport of the sample 3 among the heating system, the cooling system and the detection system; and the processing system is used for receiving and processing the working data of the heating system, the cooling system, the detection system and the conveying system and generating working commands of the test conveying system so as to control the working of the sample conveying system.
In some embodiments, the heating system comprises a test chamber for placing a sample and a heating device 1 for heating the sample 3, the outer layer of the test chamber is provided with a heat insulation layer, the test chamber is provided with an induction device, the induction device is used for controlling the opening and closing of a door of the test chamber when the sample 3 enters and moves out of the test chamber, and the heat insulation layer sequentially comprises heat insulation cotton, a vacuum heat insulation layer and a zirconium oxide reflective film from inside to outside. Wherein, the vacuum heat insulation layer blocks heat conduction, and the heat insulation cotton and the zirconia reflective film are used for blocking heat radiation.
In some embodiments, the heat sources in the heating device 1 are respectively arranged in an array at different heights, the heat sources at different heights are used for realizing an axial gradient temperature field in the test chamber, and the array is used for realizing a circumferential gradient temperature field in the test chamber.
In some embodiments, the test chamber is provided with an observation window 2 and an infrared temperature measurement hole, and the infrared temperature measurement hole is used for monitoring the temperature of the sample in the heating process through an infrared thermal imager.
In some embodiments, the cooling system includes an air cooling device 8 and a water cooling device 10; one end of an air inlet of the air cooling system 8 is of a circular structure, the other end of the air inlet is of a flat structure, a plurality of air outlet holes distributed in an array mode are formed in the flat structure, and the direction of the air outlet holes is adjustable. The direction of the air outlet is adjusted according to the actual requirement of the cooling effect, overtemperature and water shortage warning equipment is arranged in the water cooling equipment 10, and when the water temperature exceeds a threshold value or the water level is lower than the threshold value, the water cooling equipment 10 gives an alarm. The cooling medium in the water cooling equipment can also be other media such as brine and the like.
In some embodiments, the detection system comprises an image processing device 9, and the image processing device 9 is configured to acquire surface information of the test.
In some embodiments, the surface information collected by the image processing device 9 is processed by the following steps:
s1: comparing the first image information and the second image information which are respectively collected by the image processing equipment, if the first image information is the same as the second image information, continuing the test, and if the first image information is different from the second image information, performing the next step;
s2: and comparing the second image information with a database in the processing system, if the database comprises the test crack image information which is the same as the second image information, judging that the sample has the crack, sending a stop command by the processing system, and recording a test result, wherein the test result comprises the length of the crack, the number of cycles for the crack to appear and the appearance of the crack.
In some embodiments, the sample transport system 7 comprises a fixture 4 for holding the sample 3, a lifting mechanism for changing the height of the sample 3, and a slide rail for moving within the apparatus, wherein a gas cooling channel 41 is provided in the fixture 4, and the slide rail is disposed above the heating system, the cooling system, and the detection system. As shown in fig. 3, cold air enters from an air inlet 42 on one side of the jig 4, passes through a gas cooling channel 41, and is discharged from an air outlet 43 arranged on the other side of the jig 4, one end of the jig 4 is provided with a test connection flange 44 for connecting the test sample 3, the air inlet 42 and the air outlet 43 are arranged on the other end of the jig 4, and the gas cooling channel 41 is used for cooling the jig 4 to prevent the jig 4 from overheating.
In some embodiments, the sample transport system 7 further comprises a mass sensor 5 for detecting the mass of the sample 3 and a temperature sensor for detecting the temperature of the clamp.
In some embodiments, as shown in fig. 2, the test sample 3 is provided with a spring plate 15 which is pressed against a measuring end 16 of the temperature sensor, the spring plate 15 is fixed on the test sample by bolts 13 arranged at two ends of the test sample 3, and the bolts are tightened by matched nuts.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are also included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. A turbine blade thermal shock test device, characterized in that, the device includes:
the heating system is used for heating the sample;
the cooling system is used for cooling the sample;
the detection system is used for detecting the sample;
a sample transport system for transport of samples among the heating system, the cooling system, and the detection system;
and the processing system is used for receiving and processing the working data of the heating system, the cooling system, the detection system and the conveying system and generating working commands of the test conveying system so as to control the working of the sample conveying system.
2. The turbine blade thermal shock test device according to claim 1, wherein the heating system comprises a test chamber for placing a sample and heating equipment for heating the sample, an insulating layer is arranged on the outer layer of the test chamber, an induction device is arranged on the test chamber and used for controlling the opening and closing of a door of the test chamber when the sample enters and leaves the test chamber, and the insulating layer sequentially comprises insulating cotton, a vacuum insulating layer and a zirconium oxide reflective film from inside to outside.
3. The turbine blade thermal shock test device according to claim 2, wherein the heat sources in the heating equipment are respectively arranged in an array form at different heights, the heat sources at different heights are used for realizing an axial gradient temperature field in the test chamber, and the array form is used for realizing a circumferential gradient temperature field in the test chamber.
4. The turbine blade thermal shock test device of claim 2, wherein an observation window and an infrared temperature measurement hole are arranged on the test chamber, and the infrared temperature measurement hole is used for monitoring the temperature of a sample in a heating process through a thermal infrared imager.
5. The turbine blade thermal shock test device according to claim 1, wherein the cooling system comprises an air cooling device and a water cooling device; one end of an air inlet of the air cooling system is of a circular structure, the other end of the air inlet of the air cooling system is of a flat structure, a plurality of air outlet holes distributed in an array mode are formed in the flat structure, and the direction of the air outlet holes is adjustable.
6. The turbine blade thermal shock test apparatus of claim 1, wherein the detection system comprises an image processing device for collecting experimental surface information.
7. The turbine blade thermal shock test device according to claim 6, wherein the surface information collected by the image processing equipment is processed by the following steps:
s1: comparing the first image information and the second image information which are respectively collected by the image processing equipment, if the first image information is the same as the second image information, continuing the test, and if the first image information is different from the second image information, performing the next step;
s2: and comparing the second image information with a database in the processing system, if the database comprises the test crack image information which is the same as the second image information, judging that the sample has the crack, sending a stop command by the processing system, and recording a test result, wherein the test result comprises the length of the crack, the number of cycles for the crack to appear and the appearance of the crack.
8. The turbine blade thermal shock test device of claim 1, wherein the sample transport system comprises a fixture for holding a sample, a lifting mechanism for changing the height of the sample, and a slide for moving within the device, wherein a cooling channel is provided in the fixture, and the slide is disposed above the heating system, the cooling system, and the detection system.
9. The turbine blade thermal shock test apparatus of claim 8, wherein the specimen transport system further comprises a mass sensor for detecting specimen mass and a temperature sensor for detecting the clamp temperature.
10. The turbine blade thermal shock test device according to claim 9, wherein the test sample is provided with a spring piece which is pressed against the measuring end of the temperature sensor, and the spring piece is fixed on the test sample through bolts arranged at two ends of the test sample.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111222035.6A CN114136594A (en) | 2021-10-20 | 2021-10-20 | Turbine blade thermal shock test device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111222035.6A CN114136594A (en) | 2021-10-20 | 2021-10-20 | Turbine blade thermal shock test device |
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| CN114136594A true CN114136594A (en) | 2022-03-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111222035.6A Pending CN114136594A (en) | 2021-10-20 | 2021-10-20 | Turbine blade thermal shock test device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118310758A (en) * | 2024-06-11 | 2024-07-09 | 西安航天动力研究所 | Part test method and part test device |
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Application publication date: 20220304 |