CN112730021A - Vibration thermal shock coupling service working condition loading system and method - Google Patents
Vibration thermal shock coupling service working condition loading system and method Download PDFInfo
- Publication number
- CN112730021A CN112730021A CN202011378613.0A CN202011378613A CN112730021A CN 112730021 A CN112730021 A CN 112730021A CN 202011378613 A CN202011378613 A CN 202011378613A CN 112730021 A CN112730021 A CN 112730021A
- Authority
- CN
- China
- Prior art keywords
- thermal shock
- vibration
- loading device
- turbine blade
- clamp
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- 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
-
- 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
- G01N3/60—Investigating resistance of materials, e.g. refractory materials, to rapid heat changes
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A vibration thermal shock coupling service condition loading system comprises: the fixture (1) is provided with a clamping groove and is used for fixing the turbine blade (100); the clamping grooves are arranged in a plurality of numbers so that the turbine blade (100) and the clamp (1) are arranged at a preset angle; the vibration loading device is fixedly connected with the clamp (1) and is used for driving the turbine blade (100) on the clamp (1) to vibrate; the spray gun is used for spraying high-temperature gas so as to load thermal shock working conditions on the turbine blade (100); and a lance moving device (3) for moving the lance so that the direction of the high-temperature gas injected from the lance is perpendicular to the blade body of the turbine blade (100). The loading system for the service working condition can accurately simulate the failure mechanism of the turbine blade in different service environments.
Description
Technical Field
The invention belongs to the field of aircraft engines, and particularly relates to a vibration thermal shock coupling service condition loading system and method.
Background
The aircraft engine is known as the 'heart' of the aircraft and plays a decisive role in the development of the aerospace industry. The key parameter of the engine is its thrust-weight ratio, which has been developed from less than 2 to more than 10, for example, with the first generation fighter F86 and the fourth generation fighter F22, and obviously, increasing the thrust-weight ratio of an aircraft engine is a necessary measure and a necessary trend to improve the performance and efficiency of the engine. Along with the increase of the thrust-weight ratio, the temperature of the fuel gas inlet of the engine is continuously increased, and the temperature of the fuel gas inlet of the aircraft engine reaches about 1700 ℃ by the fourth-generation fighter. The large increase in gas inlet temperature undoubtedly places higher demands on the hot end components of the engine, i.e. the turbine blade material. In order to meet the use requirements of turbine blades, a series of super high-temperature alloy materials for the turbine blades are developed in sequence in various countries, the use limit temperature of the prior nickel-based high-temperature single crystal is 1150 ℃, and obviously, the technology of singly using the high-temperature metal alloy materials cannot meet the urgent requirements of rapid development of the prior aero-engine. The NASA center in the united states as early as 1953 proposed the concept of thermal barrier coating, i.e., high temperature resistant, highly insulating ceramic material coated on the surface of a base alloy to lower the operating temperature of the alloy surface and thereby increase the thermal efficiency of the engine. After the concept is put forward, the high attention of national defense departments, colleges and research institutions of all countries in the world is immediately aroused, and the thermal barrier coating technology is classified as one of the key technologies of high-performance aircraft engines in the aviation engine propulsion plans of the United states, Europe and China. Moreover, the thermal barrier coating technology is considered to be the most feasible method for greatly improving the working temperature of the aero-engine at present.
Thermal Barrier Coatings (TBCs) are ceramic coatings that are deposited on the surface of high temperature resistant metals or superalloys. The thermal barrier coating acts as a thermal barrier for the substrate material, which can degrade the substrate
The bottom temperature enables a device (such as an engine turbine blade) made of the alloy to run at high temperature, and has the characteristics of high melting point, low thermal conductivity, corrosion resistance and thermal shock resistance. In the high-temperature service process, the thermal barrier coating can protect a high-temperature substrate and improve the temperature and the thermal efficiency of a heat engine, so that the thermal barrier coating is widely applied to the fields of aviation, chemical engineering, metallurgy and energy.
However, in the practical application process, due to the influence of mismatch of material parameters and thermal residual stress, high-temperature sintering effect of ceramic materials, high-temperature interface oxidation and the like, cracks are prone to occur inside the coating, and the turbine blade thermal barrier coating inevitably generates low-frequency or high-frequency vibration in service due to factors such as rotor imbalance, meshing instability and aerodynamic load, and cracks inside the coating rapidly expand and peel off under the high-frequency vibration. Once the coating peels off, the base metal part is exposed to high temperature conditions, and the consequences are very severe.
Therefore, the research on the mechanism of failure of the thermal barrier coating caused by blade vibration in a high-temperature environment is very important, and the method not only can be used for analyzing the spallation failure process and reason of the thermal barrier coating, but also can be used for designing the coating, prolonging the service time of the coating after microcracks are generated, and promoting the development of the thermal barrier coating of the aeroengine in China.
Disclosure of Invention
Objects of the invention
The invention aims to provide a service working condition loading system and method capable of accurately simulating failure mechanisms of turbine blades in different service environments.
(II) technical scheme
In order to solve the above problems, a first aspect of the present invention provides a service condition loading system for vibration thermal shock coupling, including: the clamp is provided with a clamping groove and used for fixing the turbine blade; a plurality of clamping grooves are formed, so that the turbine blade and the clamp are arranged at a preset angle; the vibration loading device is fixedly connected with the clamp and is used for driving the turbine blade on the clamp to vibrate; the thermal shock loading device is used for jetting high-temperature gas so as to load thermal shock working conditions on the turbine blade; and the moving device is used for moving the thermal shock loading device so that the direction of the high-temperature gas sprayed by the thermal shock loading device faces to the front edge of the turbine blade.
Optionally, the service condition loading system of the vibration thermal shock coupling further includes: the control device is in communication connection with the vibration loading device, the thermal shock loading device and the mobile device and is used for controlling the vibration parameters of the vibration loading device, the thermal shock parameters of the thermal shock loading device and the moving position of the mobile device; the thermal shock parameters comprise flame temperature, flame excitation frequency and heating time.
Optionally, the following relationship is satisfied among the flame excitation frequency of the thermal shock loading device, the vibration frequency of the vibration loading device, and the temperature rise time of the thermal shock loading device:
in the formula, P is the flame excitation frequency;
the rated frequency of the flame; Δ P is the amplitude; omega is the vibration frequency; t is the temperature rise time.
Optionally, the vibration frequency and the temperature of the turbine blade satisfy the following relation so as to simulate thermal shock vibration conditions of the aircraft engine during takeoff, cruising and landing:
f1＝k1T1(t)
f2＝k2T2
f3＝k3T3(t)
in the formula (f)1，f2，f3The vibration frequencies of the turbine blades during take-off, cruising and landing are respectively; t is1，T2，T3The surface temperatures of the turbine blades during take-off, cruise and landing respectively; k is a radical of1，k2，k3Is a constant; t is time.
Optionally, the thermal shock loading device is a spray gun.
Optionally, the mobile device comprises: a first track; a second rail slidably coupled to the first rail such that the second rail slides on the first rail; a third rail slidably coupled to the second rail such that the third rail slides on the second rail; a slider slidably coupled to the third rail such that the slider slides on the third rail; the sliding block is fixedly connected with the thermal shock loading device.
Optionally, the vibration loading device comprises: the vibration generation module is used for generating vibration; and one end of the supporting shaft is connected with the vibration generation module, and the other end of the supporting shaft is connected with the clamp and used for transmitting the vibration generated by the vibration generation module to the clamp.
Optionally, the supporting shaft is provided as a hollow shaft, one end of the supporting shaft is communicated with an air compressor, and the other end of the supporting shaft is communicated to the clamp; a communication channel is arranged in the clamp; the communicating channel extends to the clamping groove from the connecting position of the clamp and the supporting shaft.
Optionally, the service condition loading system of the vibration thermal shock coupling further includes: and the liquid cooling component is used for carrying out liquid cooling on the thermal shock loading device.
Optionally, the service condition loading system of the vibration thermal shock coupling further includes: further comprising: and the display module is used for displaying the vibration parameters of the vibration loading device, the flame excitation frequency and the temperature rise time of the spray gun and the moving position of the spray gun moving device.
The second aspect of the present invention provides a method for loading service conditions of a vibration thermal shock coupling, wherein the loading is performed by using the service condition loading device of a vibration thermal shock coupling provided by the first aspect of the present invention, and the method includes: fixing the turbine blade on a clamping groove of a clamp; starting a moving device to move a thermal shock loading device, so that the direction of high-temperature gas sprayed by the thermal shock loading device faces to the front edge of the turbine blade; and starting the vibration loading device and the thermal shock loading device.
(III) advantageous effects
The technical scheme of the invention has the following beneficial technical effects:
by arranging the clamp, the vibration loading device, the thermal shock loading device and the moving device, the vibration thermal shock coupling service environment of the turbine blade or the thermal barrier coating of the turbine blade of the aero-engine can be accurately simulated, and the change rule can be autonomously controlled, so that the vibration thermal shock coupling service environment of the thermal barrier coating of the turbine blade of the aero-engine at different stages of take-off, cruise and landing is simulated, and an important experimental platform and a reference basis are provided for correctly understanding the high-temperature vibration damage mechanism of the thermal barrier coating of the turbine blade and optimizing the design of the thermal barrier coating of the turbine blade.
Drawings
FIG. 1 is a schematic structural diagram of a loading system for the service condition of the vibration thermal shock coupling according to a first embodiment of the present invention;
FIG. 2 is a schematic structural view of one form of a specimen according to a first embodiment of the present invention set on a jig;
FIG. 3 is a schematic structural view of another form of the specimen according to the first embodiment of the present invention set on a jig;
fig. 4 is a schematic structural diagram of a mobile device according to a first embodiment of the present invention;
fig. 5 is a schematic view of air cooling according to the first embodiment of the present invention.
Reference numerals:
1: a clamp; 2: a thermal shock loading device; 21: a kerosene tank; 22: an oxygen tank; 23: a nitrogen tank; 3: a mobile device; 31: a first track; 32: a second track; 33: a third track; 34: a slider; 35: a servo motor; 41: a vibration generating module; 42: a support shaft; 51: an air compressor; 52: a water chiller; 6: and a control device.
100: a turbine blade;
200: and (4) a test testing table.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings in conjunction with the following detailed description. It should be understood that the description is intended to be exemplary only, and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
First embodiment
Fig. 1 is a schematic structural diagram of a service condition loading system of a vibration thermal shock coupling according to a first embodiment of the present invention.
As shown in fig. 1, the present embodiment provides a service condition loading system of vibration thermal shock coupling, including: the fixture 1 is provided with a clamping groove and used for fixing the turbine blade 100; a plurality of clamping grooves are arranged, so that the turbine blade 100 and the clamp 1 are arranged at a preset angle; the vibration loading device is fixedly connected with the clamp 1 and is used for driving the turbine blade 100 on the clamp 1 to vibrate; the thermal shock loading device 2 is used for jetting high-temperature gas so as to load thermal shock working conditions on the turbine blade 100; and the moving device 3 is used for moving the thermal shock loading device 2 so that the direction of the high-temperature gas sprayed by the thermal shock loading device 2 faces the front edge of the turbine blade 100. By arranging the clamp 1, the vibration loading device, the thermal shock loading device 2 and the moving device 3, the vibration thermal shock coupling service environment of the turbine blade 100 of the aero-engine or the thermal barrier coating of the turbine blade 100 can be accurately simulated, and the change rule can be autonomously controlled, so that the vibration thermal shock coupling service environment of the thermal barrier coating of the turbine blade 100 of the aero-engine at different stages of takeoff, cruise and landing is simulated, and an important experimental platform and a reference basis are provided for correctly understanding the high-temperature vibration damage mechanism of the thermal barrier coating of the turbine blade 100 and optimizing the design of the high-temperature vibration damage mechanism.
When the device is used for testing, the device is placed on a test bench for testing.
FIG. 2 is a schematic structural view of one form of a sample of the first embodiment of the present invention set on a jig 1; fig. 3 is a schematic structural view of another form of the sample according to the first embodiment of the present invention, which is set on the jig 1.
In some embodiments, the clamping grooves on the fixture 1 are provided with a plurality of sample grooves, which can be flat-plate-shaped, cylindrical or actual turbine blade 100 tenon-shaped, and can be used for loading various turbine blades 100, thermal barrier coating samples or blades with different shapes and sizes; by adjusting the sample clamping manner, the angle between the sample and the supporting shaft 42 connected with the vibration generating module 41 can be changed from 0 degrees to 180 degrees, and generally, the angle is adjusted to be horizontal as shown in fig. 3 or vertical as shown in fig. 2.
In some embodiments, the service condition loading system of the vibration thermal shock coupling further includes: the control device 6 is in communication connection with the vibration loading device, the thermal shock loading device 2 and the moving device 3 and is used for controlling the vibration parameters of the vibration loading device, the thermal shock parameters of the thermal shock loading device 2 and the moving position of the moving device 3; the thermal shock parameters include flame temperature, flame excitation frequency and heating time. The flame excitation frequency of the thermal shock loading device 2, the vibration frequency of the vibration loading device and the heating time of the thermal shock loading device 2 satisfy the following relations:
in the formula, P is the flame excitation frequency;
the rated frequency of the flame; Δ P is the amplitude; omega is the vibration frequency; t is the temperature rise time. In addition, the vibration frequency and the temperature of the turbine blade 100 satisfy the following relationship so as to simulate the thermal shock vibration working conditions of the aircraft engine during takeoff, cruising and landing:
f1＝k1T1(t)
f2＝k2T2
f3＝k3T3(t)
in the formula (f)1，f2，f3The vibration frequencies of the turbine blade 100 during take-off, cruise and landing, respectively; t is1，T2，T3The surface temperatures of the turbine blades 100 at take-off, cruise, and landing, respectively; k is a radical of1，k2，k3Is a constant; t is time. k is a radical of1，k2，k3Is constant and is set in the system according to the test condition, for example, the test target is to heat up to 1200 ℃ in 20S, keep the temperature for 20S, cool down to 40S, and finally the vibration frequency is 3000Hz, k is the moment1Is 150, k2Is 2.5, k3It is 75. Generally, turbine blades heat up during takeoff, keep warm during cruise, and cool down during landing of an aircraft.
Wherein, the flame excitation frequency: refers to the number of times of excitation of the blade by the flame in unit time. It is similar to the flame pulse frequency, and the flicker phenomenon appears when the frequency is low, and the higher the frequency is, the more stable and continuous the flame is.
The control device 6 includes a control panel (see fig. 1).
The control module can control all mechanical transmission, experimental parameter acquisition, regulation and storage on the experimental test platform, detect the test surface temperature of a sample through the infrared thermometer, and simultaneously realize that the vibration frequency of the vibration exciter changes along with the change of the temperature value through the control of a corresponding computer program according to the feedback temperature value, and can realize the autonomous control change rule, thereby simulating the vibration environment of the thermal barrier coating of the turbine blade 100 of the aeroengine at different stages of takeoff, cruising and landing; the display module displays all experimental parameters, experimental process data and real-time video on the experimental test platform.
In some embodiments, the thermal shock loading apparatus 2 is a spray gun. The spray gun is internally provided with a gas channel and a water-cooling channel, the gas channel is connected with a liquid and gas storage device, wherein the liquid storage device can be a kerosene tank, and for the test accuracy, 3 # aviation kerosene can be adopted as fuel, so that the test is closer to the real service environment of an aeroengine, the heating and cooling rates of the test are faster, and the test can reach the working temperature of high-temperature materials in the aeroengine. Then the distance from the spray gun to the sample is controlled by a mechanical transmission device, the heating area and the heating temperature can be conveniently adjusted, and the high-temperature gas spray gun loading system is characterized in that: the heating temperature range is wide, and the heating from room temperature to 1700 ℃ can be realized; the operation is simple, the test equipment is easy to realize, the test cost is low, and the device can be used together with other devices such as nondestructive testing and the like. The gas storage device can be an oxygen tank and a nitrogen tank, and the control device 6 can control the thermal shock of the sample by controlling the kerosene flow, the proportion of oxygen and nitrogen, the flow of oxygen and nitrogen, the water cooling parameter and the distance from the nozzle to the sample. Wherein, the water-cooling channel is arranged for water-cooling the spray gun, and the water-cooling channel is connected with the water chiller. The water in the cooling water tank in the water cooler flows through the cooling channel to enter the cooling channel to surround the gas spray gun for cooling for a circle through the control of the electronic flow valve through the inlet of the cooling channel, and flows out from the outlet of the cooling channel after the spray gun is cooled, so that the water flows between the spray gun and the cooling water tank in a circulating manner.
Fig. 4 is a schematic structural diagram of the mobile device 3 according to the first embodiment of the present invention.
As shown in fig. 4, in some embodiments, the mobile device 3 includes: a first rail 31; a second rail 32 slidably coupled to the first rail 31 such that the second rail 32 slides on the first rail 31; a third rail 33 slidably coupled to the second rail 32 such that the third rail 33 slides on the second rail 32; a slider 34 slidably coupled to the third rail 33 such that the slider 34 slides on the third rail 33; the slide block 34 is fixedly connected with the thermal shock loading device 2. Optionally, the moving means 3, is also used to move the nozzle of the lance to a preset distance from the leading edge of the turbine blade 100, wherein the setting of the preset distance is set by the degree of thermal shock required for the required test. Further alternatively, the moving means 3 comprise a servo motor 35, the movement of the lance being directly controlled by the servo motor 35.
In some embodiments, the vibration loading device comprises: a vibration generation module 41 for generating vibration; the support shaft 42 has one end connected to the vibration generating module 41 and the other end connected to the jig 1, and is configured to transmit the vibration generated by the vibration generating module 41 to the jig 1. Wherein the vibration generating module 41 may be an exciter. Optionally, the vibration loading module consists of a vibration exciter and a fixed shaft, the vibration direction is vertical, but the vibration of the sample in different directions can be realized according to different sample clamping modes; a vibration loading device is connected below the fixed shaft, the vibration frequency is 0-5000Hz, and the maximum thrust is 6000N; in operation, vibration is generated by the vibration exciter and transmitted to the sample through the supporting shaft 42 and the sample clamp 1.
Fig. 5 is a schematic view of air cooling according to the first embodiment of the present invention.
Referring to fig. 5, in some embodiments, the support shaft 42 is provided as a hollow shaft, one end of which is communicated with an air compressor and the other end of which is communicated to the clamp 1; a communication channel is arranged in the clamp 1; the communication passage extends from the junction with the clamp 1 and the support shaft 42 to the catching groove. The cold air enters from the bottom inlet of the cooling channel in the sample, passes through the channel in the sample and is discharged from the outlet of the cooling gas at the top, and the sample is cooled; the bottom inlet of the sample corresponds to the position of the cold air outlet of the clamping groove, so that cold air enters the sample.
In some embodiments, the service condition loading system of the vibration thermal shock coupling further includes: and the liquid cooling component is used for carrying out liquid cooling on the thermal shock loading device 2.
Optionally, the service condition loading system of the vibration thermal shock coupling further includes: further comprising: and the display module is used for displaying the vibration parameters of the vibration loading device, the flame excitation frequency and the temperature rise time of the spray gun and the moving position of the spray gun moving device 3.
The second aspect of the present invention provides a method for loading service conditions of a vibration thermal shock coupling, wherein the loading is performed by using the service condition loading device of a vibration thermal shock coupling provided in the first aspect of the present invention, and the method includes: fixing the turbine blade 100 on the clamping groove of the clamp 1; starting the moving device 3 to move the thermal shock loading device 2, so that the direction of the high-temperature gas sprayed by the thermal shock loading device 2 faces the front edge of the turbine blade 100; and starting the vibration loading device and the thermal shock loading device 2.
Second embodiment
In some embodiments, the method for loading service condition of vibration thermal shock coupling by using the service condition loading device of vibration thermal shock coupling according to the first embodiment of the present invention includes: fixing the turbine blade 100 on the clamping groove of the clamp 1; starting the moving device 3 to move the thermal shock loading device 2, so that the direction of the high-temperature gas sprayed by the thermal shock loading device 2 faces the front edge of the turbine blade 100; and starting the vibration loading device and the thermal shock loading device 2.
In a specific embodiment, the service condition loading method of the vibration thermal shock coupling comprises the following steps:
first, a sample is prepared: and (3) spraying thermal barrier coating thermal insulation material on the surface of the hollow turbine blade 100 with the measuring model by adopting an electron beam physical vapor deposition spraying process (EB-PVD). The system comprises the following components: the ceramic layer material is stabilized zirconia containing 7% yttria, the ceramic layer has a thickness of about 300 μm, and the transition layer material is an NiCrAIY alloy having a thickness of about 100 μm.
In a second step, the service state of the turbine blade 100 is simulated: fixing the turbine blade 100 sample with the thermal barrier coating on a fixture 1, fixing the fixture 1 on a fixed shaft connected with a vibration exciter, and adjusting the holding angle of the sample.
And thirdly, starting the cold machine, and opening cooling water switches of the spray gun and the fixed shaft. And starting an air compressor, opening a cooling gas control switch of the internal channel of the turbine blade 100, enabling cooling gas to enter the blade from the cooling channel of the turbine blade 100 and be discharged from the outlet of the cooling channel, and enabling the surface of the ceramic layer to form a large temperature gradient to the inner surface of the metal substrate.
And fourthly, starting the vibration loading device, turning on a power button of the vibration exciter, and rotating the knob to the five-o-clock direction after LINE, COOLING and OPER on the display panel turn green. And opening an operation panel of the experiment platform, entering a vibration parameter setting interface, and respectively setting control parameters, limiting parameters, a target spectrum, an experiment schedule, a vibration mode and miscellaneous items required by the experiment.
And fifthly, starting the kerosene rapid heating device, opening an operation panel of the experiment platform, and entering a temperature parameter setting interface, such as temperature rise time, heat preservation time, temperature reduction time, program section and the like. And regulating the gas flow, and stabilizing the temperature of the gas at 1200 ℃ after 15S after ignition. By controlling a mechanical transmission switch, the spray gun moves to a vibration station to rapidly heat the surface of the turbine blade 100, and the temperature rise rate is 100 ℃/s, so that the surface temperature of the sample is stabilized at a required temperature, such as about 1200 ℃; meanwhile, according to the temperature value fed back by the infrared thermometer, the system can adjust the vibration value of the vibration exciter according to the preset rule, and if the vibration value is increased along with the temperature rise, the vibration value is correspondingly increased.
In the experiment, the method can change the experiment parameters such as vibration frequency, random vibration of vibration mode, sinusoidal vibration and the like, residence of loading mode, frequency sweep and the like, analyze the correlation between the high-temperature vibration thermal shock failure mechanism and failure degree of the thermal barrier coating and the experiment parameters, and find out the key parameters influencing the vibration thermal shock coupling failure.
The high-temperature gas spray gun loading system of the test device takes No. 3 aviation kerosene as fuel, is closer to the real service environment of an aero-engine, has higher heating and cooling rates, and can reach the working temperature of high-temperature materials in the aero-engine. Then the distance from the spray gun to the sample is controlled by a mechanical transmission device, the heating area and the heating temperature can be conveniently adjusted, and the high-temperature gas spray gun loading system is characterized in that: the heating temperature range is wide, and the heating from room temperature to 1700 ℃ can be realized; the operation is simple, the test equipment is easy to realize, the test cost is low, and the device can be used together with other devices such as nondestructive testing and the like.
The sample clamping device of the test device comprises a fixed shaft, a sample clamp 1 and a turbine blade 100 or a flat-plate-shaped clamp 1 groove which is directly fixed on the sample clamp 1. When an experiment for simulating the thermal barrier coating of the turbine blade 100 of the aero-engine is carried out, a sample groove which is flat, cylindrical and in the shape of the tenon of the actual turbine blade 100 is carved on the sample clamp 1, so that thermal barrier coating samples or blades in different shapes and sizes can be loaded; by adjusting the sample clamping mode, the angle between the thermal barrier coating sample and the fixed shaft connected with the vibration exciter can be realized, and the angle can be horizontal or vertical.
The test device provided by the invention has two different types of cooling devices, one is a cooling system for fixing the connecting shaft, and the cooling is carried out in a cooling water mode; another is to cool the turbine blade 100 sample with cooling channels by means of cooling air. For example, taking a hollow turbine blade 100 sample with a thermal barrier coating as an example, cooling air enters the interior of the turbine blade 100 through the cooling channel for cooling, so as to ensure that the temperature inside the blade is kept at a set temperature, and further, a temperature gradient is formed from the surface of the coating to the interior of the blade. The cooling air flow is controlled and measured by an electronic flow valve.
The test control system of the test device comprises a test control module and a display module; the control module can control all mechanical transmission and experimental parameter acquisition, regulation and storage on the test platform, regulate the test temperature of the sample through the infrared thermometer, and simultaneously realize that the vibration frequency of the vibration exciter changes along with the change of the temperature value through the control of a corresponding computer program according to the feedback temperature value, and can realize the autonomous control change rule, thereby simulating the vibration environments of the thermal barrier coating of the turbine blade 100 of the aero-engine at different stages of takeoff, cruising and landing; the display module displays all experimental parameters and experimental processes on the experimental test platform.
It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explaining the principles of the invention and are not to be construed as limiting the invention. Therefore, any modification, equivalent replacement, improvement and the like made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. Further, it is intended that the appended claims cover all such variations and modifications as fall within the scope and boundaries of the appended claims or the equivalents of such scope and boundaries.
Claims (10)
1. A vibration thermal shock coupling service working condition loading system is characterized by comprising:
the fixture (1) is provided with a clamping groove and is used for fixing the turbine blade (100); the clamping grooves are arranged in a plurality of numbers so that the turbine blade (100) and the clamp (1) are arranged at a preset angle;
the vibration loading device is fixedly connected with the clamp (1) and is used for driving the turbine blade (100) on the clamp (1) to vibrate;
the thermal shock loading device (2) is used for injecting high-temperature gas so as to load thermal shock working conditions on the turbine blade (100);
a moving device (3) for moving the thermal shock loading device (2) so that the thermal shock loading device (2) jets the direction of the high temperature gas towards the leading edge of the turbine blade (100).
2. The in-service condition loading system for the coupling of the vibratory thermal shock according to claim 1, further comprising:
the control device (6) is in communication connection with the vibration loading device, the thermal shock loading device (2) and the moving device (3) and is used for controlling the vibration parameters of the vibration loading device, the thermal shock parameters of the thermal shock loading device (2) and the moving position of the moving device (3);
the thermal shock parameters comprise flame temperature, flame excitation frequency and heating time.
3. The service condition loading system of the vibration thermal shock coupling according to claim 2, wherein the flame excitation frequency of the thermal shock loading device (2), the vibration frequency of the vibration loading device and the temperature rise time of the thermal shock loading device (2) satisfy the following relationship:
in the formula, P is the flame excitation frequency;
the rated frequency of the flame; Δ P is the amplitude; omega is the vibration frequency; t is the temperature rise time.
4. The in-service condition loading system for the coupling of the vibratory thermal shock according to claim 2,
the vibration frequency and the temperature of the turbine blade (100) meet the following relation so as to simulate thermal shock vibration working conditions of the aircraft engine during takeoff, cruising and landing:
f1＝k1T1(t)
f2＝k2T2
f3＝k3T3(t)
in the formula (f)1，f2，f3The vibration frequencies of the turbine blade (100) during take-off, cruise and landing respectively; t is1，T2，T3The surface temperatures of the turbine blades (100) during take-off, cruise and landing respectively; k is a radical of1，k2，k3Is a constant; t is time.
5. The in-service condition loading system for the coupling of the vibratory thermal shock according to claim 1,
the thermal shock loading device (2) is a spray gun.
6. The service condition loading system for the coupling of the vibratory thermal shock according to claim 1, wherein the moving device (3) comprises:
a first rail (31);
a second rail (32) slidably connected to the first rail (31) such that the second rail (32) slides on the first rail (31);
a third rail (33) slidably connected to the second rail (32) such that the third rail (33) slides on the second rail (32);
a slider (34) slidably connected to the third track (33) such that the slider (34) slides on the third track (33); the sliding block (34) is fixedly connected with the thermal shock loading device (2).
7. The in-service condition loading system for the coupling of the vibratory thermal shock according to claim 1, wherein the vibratory loading device comprises:
a vibration generation module (41) for generating vibrations;
and the supporting shaft (42) is connected with the vibration generation module (41) at one end and connected with the clamp (1) at the other end, and is used for transmitting the vibration generated by the vibration generation module (41) to the clamp (1).
8. The in-service condition loading system for the coupling of the vibratory thermal shock according to claim 1,
the supporting shaft (42) is a hollow shaft, one end of the supporting shaft is communicated with an air compressor, and the other end of the supporting shaft is communicated to the clamp (1);
a communication channel is arranged in the clamp (1);
the communication channel extends from the joint of the clamp (1) and the supporting shaft (42) to the clamping groove.
9. The in-service condition loading system for the coupling of the vibratory thermal shock according to claim 1, further comprising:
and the liquid cooling component is used for carrying out liquid cooling on the thermal shock loading device (2).
10. A method for loading service conditions of a vibration thermal shock coupling, which is characterized in that the service condition loading device of the vibration thermal shock coupling according to any one of claims 1 to 9 is used for loading, and comprises the following steps:
fixing the turbine blade (100) on a clamping groove of the clamp (1);
starting a moving device (3) to move a thermal shock loading device (2), so that the direction of the high-temperature gas sprayed by the thermal shock loading device (2) faces to the front edge of the turbine blade (100);
and starting the vibration loading device and the thermal shock loading device (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011378613.0A CN112730021B (en) | 2020-11-30 | 2020-11-30 | Vibration thermal shock coupling service working condition loading system and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011378613.0A CN112730021B (en) | 2020-11-30 | 2020-11-30 | Vibration thermal shock coupling service working condition loading system and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112730021A true CN112730021A (en) | 2021-04-30 |
| CN112730021B CN112730021B (en) | 2023-04-07 |
Family
ID=75598001
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011378613.0A Active CN112730021B (en) | 2020-11-30 | 2020-11-30 | Vibration thermal shock coupling service working condition loading system and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112730021B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114136761A (en) * | 2021-11-19 | 2022-03-04 | 中国航发北京航空材料研究院 | Ceramic matrix composite guide vane thermal shock test device and assessment method |
| CN114563262A (en) * | 2022-02-22 | 2022-05-31 | 纳诺科技有限公司 | Impact-resistant detection device for material |
Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4793716A (en) * | 1987-11-18 | 1988-12-27 | Gte Laboratories Incorporated | Thermal shock test apparatus and the method of testing |
| DE10349700B3 (en) * | 2003-10-24 | 2005-05-04 | Daimlerchrysler Ag | Thermoshock testing method for automobile engine exhaust manifold using simulated cylinder head for supplying exhaust manifold with heated pressurized air |
| US20100045273A1 (en) * | 2008-06-09 | 2010-02-25 | Instytut Techniczny Wojsk Lotniczych | Measuring vibrations of a turbo-machine rotor blade with the help of an induction sensor in high temperature |
| CN103063563A (en) * | 2013-01-10 | 2013-04-24 | 湘潭大学 | Testing device for simulation and real-time detection of high-temperature deposition corrosion of thermal barrier coatings |
| CN103063534A (en) * | 2013-01-10 | 2013-04-24 | 湘潭大学 | Testing device for simulation and real-time detection of erosion of thermal barrier coatings of turbine blades |
| CN103091189A (en) * | 2013-01-10 | 2013-05-08 | 湘潭大学 | Tester for simulating service environment of thermal barrier coating and detecting failure of thermal barrier coating in real time |
| US20130344204A1 (en) * | 2012-06-22 | 2013-12-26 | Mark E. Goodson | Beverage Mixing System and Method |
| CN103674753A (en) * | 2013-12-09 | 2014-03-26 | 昆明理工大学 | Test platform for thermal shock and thermal fatigue |
| FR2997499A1 (en) * | 2012-10-31 | 2014-05-02 | Snecma | Method for testing ingestion of projectile i.e. bird, by e.g. turbojet, of aircraft, involves actuating temporary connection to obtain dissociation of projectile from support such that projectile is sucked by fluid flow during operation |
| JP2014139586A (en) * | 2014-04-23 | 2014-07-31 | Risoh Kesoku Kk Ltd | Thermal shock test device |
| CN204788866U (en) * | 2015-08-07 | 2015-11-18 | 山东厚丰汽车散热器有限公司 | A cold and hot impact and device of nai vibration test for auto radiator |
| CN106525444A (en) * | 2016-09-27 | 2017-03-22 | 南京航空航天大学 | Jet-engine-gas-based apparatus and method for thermal shock and thermal fatigue testing |
| CN108663198A (en) * | 2017-03-27 | 2018-10-16 | 清华大学 | The test system of turbo blade |
| CN109580410A (en) * | 2018-12-10 | 2019-04-05 | 湘潭大学 | A kind of equivalent loading device and method of working-blade thermal barrier coating service load |
| CN109682702A (en) * | 2018-12-10 | 2019-04-26 | 湘潭大学 | A kind of thermal barrier coating of turbine blade Work condition analogue experiment test system |
| CN109827735A (en) * | 2019-04-02 | 2019-05-31 | 湘潭大学 | A kind of high-temperature vibrating analog machine |
| CN110369668A (en) * | 2019-08-08 | 2019-10-25 | 无锡航亚科技股份有限公司 | A kind of forging technology of the aero-compressor blade based on nickel base superalloy |
| CN110470446A (en) * | 2019-08-21 | 2019-11-19 | 东北大学 | Shock and vibration, the lower material blade service reliability experimental provision again of high temperature excitation |
| US20200300111A1 (en) * | 2019-03-18 | 2020-09-24 | Rolls-Royce Plc | Condition determination of a gas turbine engine |
-
2020
- 2020-11-30 CN CN202011378613.0A patent/CN112730021B/en active Active
Patent Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4793716A (en) * | 1987-11-18 | 1988-12-27 | Gte Laboratories Incorporated | Thermal shock test apparatus and the method of testing |
| DE10349700B3 (en) * | 2003-10-24 | 2005-05-04 | Daimlerchrysler Ag | Thermoshock testing method for automobile engine exhaust manifold using simulated cylinder head for supplying exhaust manifold with heated pressurized air |
| US20100045273A1 (en) * | 2008-06-09 | 2010-02-25 | Instytut Techniczny Wojsk Lotniczych | Measuring vibrations of a turbo-machine rotor blade with the help of an induction sensor in high temperature |
| US20130344204A1 (en) * | 2012-06-22 | 2013-12-26 | Mark E. Goodson | Beverage Mixing System and Method |
| FR2997499A1 (en) * | 2012-10-31 | 2014-05-02 | Snecma | Method for testing ingestion of projectile i.e. bird, by e.g. turbojet, of aircraft, involves actuating temporary connection to obtain dissociation of projectile from support such that projectile is sucked by fluid flow during operation |
| US20150355074A1 (en) * | 2013-01-10 | 2015-12-10 | Xiangtan University | Type of testing equipment for detecting the failure process of thermal barrier coating in a simulted working environment |
| CN103063563A (en) * | 2013-01-10 | 2013-04-24 | 湘潭大学 | Testing device for simulation and real-time detection of high-temperature deposition corrosion of thermal barrier coatings |
| CN103063534A (en) * | 2013-01-10 | 2013-04-24 | 湘潭大学 | Testing device for simulation and real-time detection of erosion of thermal barrier coatings of turbine blades |
| CN103091189A (en) * | 2013-01-10 | 2013-05-08 | 湘潭大学 | Tester for simulating service environment of thermal barrier coating and detecting failure of thermal barrier coating in real time |
| CN103674753A (en) * | 2013-12-09 | 2014-03-26 | 昆明理工大学 | Test platform for thermal shock and thermal fatigue |
| JP2014139586A (en) * | 2014-04-23 | 2014-07-31 | Risoh Kesoku Kk Ltd | Thermal shock test device |
| CN204788866U (en) * | 2015-08-07 | 2015-11-18 | 山东厚丰汽车散热器有限公司 | A cold and hot impact and device of nai vibration test for auto radiator |
| CN106525444A (en) * | 2016-09-27 | 2017-03-22 | 南京航空航天大学 | Jet-engine-gas-based apparatus and method for thermal shock and thermal fatigue testing |
| CN108663198A (en) * | 2017-03-27 | 2018-10-16 | 清华大学 | The test system of turbo blade |
| CN109580410A (en) * | 2018-12-10 | 2019-04-05 | 湘潭大学 | A kind of equivalent loading device and method of working-blade thermal barrier coating service load |
| CN109682702A (en) * | 2018-12-10 | 2019-04-26 | 湘潭大学 | A kind of thermal barrier coating of turbine blade Work condition analogue experiment test system |
| US20200300111A1 (en) * | 2019-03-18 | 2020-09-24 | Rolls-Royce Plc | Condition determination of a gas turbine engine |
| CN109827735A (en) * | 2019-04-02 | 2019-05-31 | 湘潭大学 | A kind of high-temperature vibrating analog machine |
| CN110369668A (en) * | 2019-08-08 | 2019-10-25 | 无锡航亚科技股份有限公司 | A kind of forging technology of the aero-compressor blade based on nickel base superalloy |
| CN110470446A (en) * | 2019-08-21 | 2019-11-19 | 东北大学 | Shock and vibration, the lower material blade service reliability experimental provision again of high temperature excitation |
Non-Patent Citations (6)
| Title |
|---|
| 尹峰等: "核电厂汽轮机低压转子叶片常见缺陷及其检测", 《无损检测》 * |
| 杨丽等: "航空发动机涡轮叶片热障涂层冲蚀试验装置的研制", 《装备环境工程》 * |
| 段力等: "涡轮导叶片表面MEMS高温测量技术", 《航空制造技术》 * |
| 温金鹏等: "高温真空阻尼测试系统的设计与性能测试", 《西北工业大学学报》 * |
| 翁史烈: "《燃气轮机设计基础》", 31 December 2015, 上海交通大学出版社 * |
| 苏棣: "N135-13.24/535型汽轮机ILB690叶片致裂分析", 《广东科技》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114136761A (en) * | 2021-11-19 | 2022-03-04 | 中国航发北京航空材料研究院 | Ceramic matrix composite guide vane thermal shock test device and assessment method |
| CN114136761B (en) * | 2021-11-19 | 2024-05-24 | 中国航发北京航空材料研究院 | Thermal shock test device and assessment method for ceramic matrix composite guide blade |
| CN114563262A (en) * | 2022-02-22 | 2022-05-31 | 纳诺科技有限公司 | Impact-resistant detection device for material |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112730021B (en) | 2023-04-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112730021B (en) | Vibration thermal shock coupling service working condition loading system and method | |
| CN109682702B (en) | Turbine blade thermal barrier coating working condition simulation experiment test system | |
| US9939364B2 (en) | Type of testing equipment for detecting the failure process of thermal barrier coating in a simulted working environment | |
| Li et al. | The correlation of the TBC lifetimes in burner cycling test with thermal gradient and furnace isothermal cycling test by TGO effects | |
| Vaßen et al. | Recent activities in the field of thermal barrier coatings including burner rig testing in the European Union | |
| EP1651790B1 (en) | Method of shielding effluents in spray devices | |
| CN111579410A (en) | Ceramic matrix composite gas environment fatigue test system | |
| Vardelle et al. | Plasma spray processes: diagnostics and control? | |
| Lima et al. | Insights on the high-temperature operational limits of ZrO 2-Y 2 O 3 TBCs manufactured via air plasma spray | |
| CN109357956B (en) | High-temperature gas corrosion fatigue test system | |
| Lepeshkin et al. | Investigations of thermal barrier coatings of turbine parts using gas flame heating | |
| CN105865961A (en) | Test apparatus for thermal shock life evaluation of thermal barrier coating | |
| CN112665864B (en) | Device and method for simulating random thermal shock load of aircraft engine | |
| Yan et al. | Real-time detection of damage evolution and failure of EB-PVD thermal barrier coatings using an environmental simulator with high-temperature and high-speed rotation | |
| Wang et al. | A review of multiphase flow and deposition effects in film-cooled gas turbines | |
| Lima et al. | Thermal gradient behavior of TBCS subjected to a laser gradient test rig: Simulating an air-to-air combat flight | |
| Bouchez et al. | Combustor Materials Research Studies for High Speed Aircraft in the European Program ATLLAS2 | |
| Katanoda et al. | Experimental study on shock wave structures in constant-area passage of cold spray nozzle | |
| CN211452847U (en) | High-temperature and high-speed flame flow generating device for simulating service environment of aircraft engine | |
| Chen et al. | Friction delamination mechanism of EB-PVD thermal barrier coatings in high-temperature and high-speed rotating service environment | |
| Conner et al. | Ranking protective coatings: Laboratory vs. field experience | |
| CN113049256A (en) | High-temperature and high-speed flame flow generating device for simulating service environment of aircraft engine | |
| Okajima et al. | Evolution of thermal barrier coatings for land based gas turbines at MHI | |
| Andreini et al. | Effusion cooling system optimization for modern lean burn combustor | |
| CN113176297A (en) | Thermal cycle device for simulating takeoff and landing and cruising service process of aircraft engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |