CN113865751B - Test system and method for turbine blade integrated film temperature sensor - Google Patents
Test system and method for turbine blade integrated film temperature sensor Download PDFInfo
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- CN113865751B CN113865751B CN202111153517.0A CN202111153517A CN113865751B CN 113865751 B CN113865751 B CN 113865751B CN 202111153517 A CN202111153517 A CN 202111153517A CN 113865751 B CN113865751 B CN 113865751B
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- 238000012360 testing method Methods 0.000 title claims abstract description 31
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
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Abstract
The invention provides a test system and a test method for a turbine blade integrated film temperature sensor, which solve the problem that the existing turbine blade integrated film temperature sensor cannot adopt an industrial thermocouple temperature measurement calibration mode. The system comprises a heating box, an instantaneous heating unit, an imaging unit, a standard thermocouple, a tester and a control unit; the instantaneous heating unit comprises a laser, a light condensing unit and a turntable; the condensing unit is positioned on the outer side of the observation port of the side wall of the heating box and on the outgoing light path of the laser; the light condensing unit is arranged on the turntable; the imaging unit is arranged outside the observation port of the heating box; the number of the standard thermocouples is equal to that of the film temperature sensors on the turbine blade to be tested, and the positions of the standard thermocouples are in one-to-one correspondence; the film temperature sensor and the standard thermocouple are respectively connected with the tester; the control unit controls the emergent energy of the laser and is connected with the turntable; the control unit compares the temperatures obtained by the film temperature sensor and the standard thermocouple and judges whether the performance of the film temperature sensor is qualified.
Description
Technical Field
The invention relates to the field of sensor testing, in particular to a testing system and method for a turbine blade integrated film temperature sensor.
Background
Aeroengines are complex machines that operate in harsh environments with high temperature, high pressure and high speed rotation, and have extremely high requirements on materials and manufacturing processes. According to research, the thrust of the aero-engine can be increased by 20% and the thermal efficiency can be increased by 8% when the turbine inlet temperature of the aero-engine is increased by 100 ℃. In pursuit of higher performance and more economical energy consumption, modern aero-engines have been studied mainly for further increasing the pre-turbine temperature. As a main component for converting thermal energy into mechanical energy, the reliability design of turbine blades is a key to new engine designs. In order to improve the reliability of the turbine blade, the temperature field distribution of the surface of the turbine blade needs to be measured and analyzed so as to take effective measures in the aspects of materials, cooling, structure, process and the like.
The film thermocouple is a transient temperature sensor directly prepared on the surface of the turbine blade, does not interfere with heat exchange inside the turbine blade and gas flow, is an ideal measurement technology for solving the problem of measurement of the surface temperature of the turbine blade, and has been studied and partially applied at present.
As a measuring sensor, the thermocouple needs to be tested and calibrated before being put into use. The film thermocouple is directly prepared on the turbine blade, is designed integrally with the turbine blade, and cannot be independently tested and calibrated like common industrial thermocouples such as thermocouple wires and sheathed thermocouples. Currently, the detection of an industrial thermocouple generally adopts a comparison method, and the thermocouple to be detected and a standard thermocouple are placed in a high-temperature detection furnace and heated to a constant temperature at the same time to realize the measurement of the thermocouple. However, because the high-temperature verification furnace has longer heating and heat-preserving time, the measured piece is in a high-temperature environment for a long time, and the service lives of the film thermocouple and the turbine blade are adversely affected. For the film thermocouple, the service life of the film thermocouple at the highest temperature is only about 10 hours under the limit of the thickness of the protective layer, and even if the process is continuously optimized, the service life can only reach tens of hours under the consideration of the use environment and the engine test requirement. In addition, for the turbine blade, the metal surface temperature can be 200-300 ℃ lower than the surface gas temperature and the internal temperature is lower through the application of various technologies such as thermal barrier coating, air film cooling and the like in operation. However, in the static environment of the high-temperature verification furnace, air cooling measures cannot be used, and after the long-time temperature is constant, the heat insulation effect of the thermal barrier coating is obviously reduced, so that the metal temperature of the turbine blade can exceed the reasonable working temperature of the turbine blade, and irreversible damage is caused.
Disclosure of Invention
The invention provides a test system and a test method for a turbine blade integrated film temperature sensor, which are used for solving the technical problem that the existing turbine blade integrated film temperature sensor cannot adopt an industrial thermocouple temperature measurement calibration mode, and the service lives of the turbine blade and the film temperature sensor can be adversely affected by continuous high temperature.
In order to achieve the above purpose, the technical scheme provided by the invention is as follows:
a test system for a turbine blade integrated film temperature sensor is characterized in that: the system comprises a heating box, an instantaneous heating unit, an imaging unit, a standard thermocouple, a tester and a control unit;
The heating box is internally used for placing turbine blades to be tested, and the side wall of the heating box is provided with an observation port;
The instantaneous heating unit is positioned outside the heating box and comprises a laser, a light condensing unit and a turntable; the condensing unit is positioned at the outer side of the observation port of the side wall of the heating box and on the emergent light path of the laser; the focusing unit is arranged on the turntable, and the turntable is used for adjusting the position of the focusing unit, so that laser beams emitted by the laser are converged and reflected by the focusing unit and then irradiated to a temperature measuring area of the turbine blade to be measured through the observation port;
the imaging unit is arranged at the outer side of the observation port of the heating box and is used for shooting the turbine blade to be detected and inputting shot video signals to the control unit;
The number of the standard thermocouples is equal to that of the film temperature sensors on the turbine blade to be tested, and the mounting positions correspond to the positions of the temperature measuring areas of the turbine blade where the film temperature sensors are located one by one;
The film temperature sensor and the standard thermocouple are respectively connected with the tester, the tester collects the temperatures of the film temperature sensor and the standard thermocouple, and the collected temperature data is input to the control unit;
the control unit is connected with the laser and used for controlling the emergent energy of the laser, and is connected with the turntable and used for controlling the turntable to drive the light condensing unit to rotate according to the video signal;
And the control unit compares the temperatures obtained by the film temperature sensor and the standard thermocouple and judges whether the performance of the film temperature sensor is qualified or not.
Further, the light condensing unit is a concave reflector;
or the light condensing unit comprises a converging mirror and a reflecting mirror which are sequentially arranged along the emergent light path of the laser.
Further, a platform for placing turbine blades to be tested is arranged in the heating box.
Further, the heating box is welded by a stainless steel plate, the inner wall of the heating box is filled with a ceramic heat-insulating material, a ceramic heater is arranged in the heating box, and a temperature sensor is arranged on the heating box;
And a proximity sensor is arranged on the periphery of the laser.
Further, the laser is a high-power CO 2 laser;
the turntable is a biaxial servo turntable;
the standard thermocouple, the film temperature sensor and the tester are connected through compensation wires.
Meanwhile, the invention also provides a test method for the turbine blade integrated film temperature sensor, which is characterized by comprising the following steps:
1) Placing a turbine blade to be tested, which is integrated with a film temperature sensor, in a heating box, installing a standard thermocouple in a temperature measuring area of the turbine blade, and respectively connecting the film temperature sensor to be tested and the standard thermocouple to a tester outside the heating box;
The number of the standard thermocouples is equal to that of the film temperature sensors on the turbine blades, and the positions of the standard thermocouples are in one-to-one correspondence;
2) Starting an imaging unit, shooting an image of the turbine blade, and calibrating a laser heating point on the image;
the number of the laser heating points is equal to that of the temperature measuring areas of the turbine blades, and the positions are in one-to-one correspondence;
3) Raising the temperature of the inner cavity of the heating box to the preheating temperature;
4) The turntable drives the condensing unit to rotate, so that the outgoing beam of the condensing unit aims at one of the laser heating points in the step 2), then the laser is started, the laser beam emitted by the laser is reflected and converged by the condensing unit and then irradiates a temperature measuring area corresponding to the laser heating point on the turbine blade through an observation port to carry out instantaneous heating, and the process is repeated to complete the heating of all the temperature measuring areas of the turbine blade;
5) The tester collects the temperature obtained by the standard thermocouple at each laser heating point and inputs the temperature into the control unit;
6) The control unit controls the laser to irradiate the energy of the corresponding laser heating point in real time according to the temperature data obtained by each standard thermocouple, so that the temperature measuring area where each standard thermocouple is positioned is heated according to a preset temperature curve, and the temperature obtained by the standard thermocouple at each laser heating point is collected in real time by the inspection instrument and is input to the control unit;
Meanwhile, when the temperature data obtained by each standard thermocouple reach a set temperature point, the temperature obtained by the film temperature sensor is collected in real time by the inspection instrument and is input into the control unit;
7) The control unit compares the temperature obtained by the standard thermocouple corresponding to each laser heating point at each set temperature point with the temperature obtained by the film temperature sensor, and if the difference value of the temperature obtained by the standard thermocouple and the temperature obtained by the film temperature sensor is within the tolerance range, the performance of the film temperature sensor corresponding to the laser heating point is normal; if not, the performance of the film temperature sensor does not reach the standard.
Further, in step 6), different emission energies of the lasers are achieved by changing the emission power and the integration time of the lasers.
Further, the method further comprises the following steps:
And 8) recording the heating start time of the laser and the step response output time of the film temperature sensor by the control unit, obtaining the thermal response time of the film temperature sensor by the difference value of the laser and the step response output time, comparing the thermal response time of the film temperature sensor with the tolerance range, if the thermal response time of the film temperature sensor is within the tolerance range, the response time of the film temperature sensor is normal, and if the response time of the film temperature sensor is not up to the standard, the response time of the film temperature sensor is not up to the standard.
Compared with the prior art, the invention has the advantages that:
1. according to the test system and the test method, the turbine blade is preheated to a high-temperature zone safe to materials through the heating box, and the laser beam is controlled to locally and transiently heat the temperature measuring zone under the condition that the service lives of the turbine blade and the film temperature sensor are not influenced, so that the damage to the film temperature sensor and the turbine blade caused by long-time high temperature is avoided.
2. The test system controls the laser beam to locally and transiently heat the temperature measuring area through the control unit, so that the temperature change of the film temperature sensor can be controlled in extremely short time, and the influence of the continuous high-temperature environment on the service lives of the film temperature sensor and the turbine blade is avoided; meanwhile, the control unit is used for controlling the emission power and the accumulated irradiation time of the laser, so that a temperature change curve can be flexibly adjusted, and the simulation of the internal temperature change of the engine is realized; and more accurate temperature control can be realized, and more comprehensive test is carried out on the film temperature sensor.
3. The test system provided by the invention is based on laser transient heating control of visual detection technology (the imaging unit shoots the laser spot position), can simulate a complex temperature curve, reduces the influence on the service life of a tested product, and is suitable for rapid test calibration of a temperature sensor.
4. According to the testing system, the imaging unit is used for detecting the laser spot position, and the two-axis servo turntable is used for adjusting the spot position, so that a plurality of turbine blades can be heated, and the testing of a plurality of film temperature sensors on the plurality of turbine blades is realized.
Drawings
FIG. 1 is a schematic diagram of a test system for a turbine blade integrated film temperature sensor according to the present invention;
wherein, the reference numerals are as follows:
the device comprises a 1-heating box, a 11-observation port, a 2-instantaneous heating unit, a 21-laser, a 22-light condensing unit, a 23-turntable, a 3-imaging unit, a 4-standard thermocouple, a 5-inspection instrument, a 6-control unit, a 7-turbine blade and a 71-film temperature sensor.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
As shown in fig. 1, a test system for a turbine blade integrated film temperature sensor of the present invention includes a heating box 1, a momentary heating unit 2, an imaging unit 3, a standard thermocouple 4, a tester 5, and a control unit 6.
The heating box 1 is internally used for placing the turbine blade 7 to be tested, and in order to facilitate the placement of the turbine blade 7, a platform for placing the turbine blade 7 to be tested is arranged in the heating box 1. The heating box 1 is welded by stainless steel plates, and the inner wall is filled with ceramic heat-insulating materials; the heating box 1 is also internally provided with a ceramic heater which is used for heating the inner cavity of the heating box 1 and controlling the whole heating inside the heating box 1 by using a temperature controller; the heating box 1 is provided with a temperature sensor for measuring the temperature of the inner cavity of the heating box 1; the side wall of the heating box 1 is provided with an observation port 11.
The instantaneous heating unit 2 is located outside the heating cabinet 1 and comprises a laser 21, a condensing unit 22 and a turntable 23; the laser 21 is arranged outside the heating box 1, and the proximity sensor is arranged on the periphery of the laser 21, so that injury caused by personnel approaching in the using process can be avoided. The condensing unit 22 is positioned outside the observation port 11 on the side wall of the heating box 1 and on the emergent light path of the laser 21, and after the laser beams emitted by the laser 21 are reflected and converged by the condensing unit 22, the laser beams are irradiated onto the turbine blade 7 to be detected through the observation port 11 on the side wall of the heating box 1 for rapid instantaneous heating; the condensing unit 22 in this embodiment is a concave reflector, which is used for converging and reflecting laser beams, and the laser beams are condensed and then irradiated to the temperature measuring area of the turbine blade 7 through the observation port 11; in other embodiments, the condensing unit 22 may be composed of a converging mirror and a reflecting mirror sequentially disposed along the outgoing light path of the laser 21.
The laser 21 is connected with the control unit 6, the control unit 6 is a computer, the laser 21 is a high-power CO 2 laser, a high-power CO 2 laser control signal is given by the computer, the emission energy of the laser 21 can be controlled, and the embodiment realizes the change of the emission energy of the laser 21 by changing the emission power and the accumulation time of the laser.
The turntable 23 is a servo turntable, the concave reflector is arranged on the servo turntable, the servo turntable is controlled by a computer, the servo turntable is driven to rotate by the computer, the concave reflector on the servo turntable is further driven to move, the heating position of the concave reflector emitting laser to the turbine blade 7 is adjusted, and the laser focused by the concave reflector is aimed at a temperature measuring area of the turbine blade 7.
The imaging unit 3 adopts a high-definition industrial camera, uses gigabit Ethernet to connect with a computer, the imaging unit 3 is arranged outside the observation port 11 of the heating box 1 and is used for shooting the turbine blade 7 to be detected, and shooting video signals are input into the computer, and the computer adjusts the position of the condensing unit 22 through the turntable 23 in real time according to the shot temperature measuring area of the turbine blade 7 and the laser irradiated spot position, so that the laser spot position and the position of the temperature measuring area of the turbine blade 7 are accurately aligned.
Each temperature measuring area on the turbine blade 7 to be measured is provided with a film temperature sensor 71, the number of the standard thermocouples 4 is equal to that of the film temperature sensors 71, and the installation positions are in one-to-one correspondence with the positions of the temperature measuring areas of the turbine blade 7 where the film temperature sensors 71 are positioned; in this embodiment, taking the case of installing 2 film temperature sensors 71 on the turbine blade 7 as an example, the number of standard thermocouples 4 is 2, and the positions of the standard thermocouples are in one-to-one correspondence with the 2 film temperature sensors 71, and are respectively located in 2 temperature measuring areas of the turbine blade 7, the standard thermocouples 4 adopt thin thermocouple wires, and the measuring ends are adhered to the positions of the temperature measuring areas where the film temperature sensors 71 are located through high temperature resistant glue.
The film temperature sensor 71 and the standard thermocouple 4 are connected to the tester 5 outside the heating box 1 through compensation wires, the tester 5 collects the temperatures of the film temperature sensor 71 and the standard thermocouple 4 and inputs the collected temperature data to a computer, the computer compares the temperatures obtained by the film temperature sensor 71 and the standard thermocouple 4, and whether the performance of the film temperature sensor 71 is qualified is judged according to the difference value of the two temperatures.
The test system of the embodiment performs one-time image calibration during installation, and establishes a spatial corresponding relation among the test position in the high-temperature box, the image of the imaging unit and the position of the servo turntable.
Test procedure of the test system of the present embodiment for the film temperature sensor 71 on the turbine blade 7:
1) Placing the turbine blade 7 to be tested, which is integrated with the film temperature sensor 71, in the heating box 1, so that the temperature measuring area of the turbine blade 7 is opposite to the observation port 11 of the heating box 1; standard thermocouples 4 are respectively arranged in 2 temperature measuring areas of the turbine blade 7, and 2 film temperature sensors 71 to be measured in the 2 temperature measuring areas and 2 standard thermocouples 4 are respectively connected to the tester 5 outside the heating box 1;
2) Starting an imaging unit 3, shooting an image of the turbine blade 7, and calibrating a laser heating point on the image;
the number of the laser heating points is equal to that of the temperature measuring areas of the turbine blade 7, and the positions are in one-to-one correspondence, so that the number of the laser heating points is 2 in the embodiment;
3) The computer controls the ceramic heater to work, and the temperature of the inner cavity of the heating box 1 is heated to a preheating temperature which is within the safe range of the heating box 1, the turbine blades 7, the film temperature sensor 71 and the standard thermocouple 4;
4) The computer controls the turntable 23 to rotate, the turntable 23 drives the light condensing unit 22 to rotate, so that the emergent light beams converged by the light condensing unit 22 aim at one of the laser heating points, then the laser 21 is started, and after the laser beams emitted by the laser 21 are reflected and converged by the light condensing unit 22, the laser beams are irradiated to a temperature measuring area corresponding to the laser heating point on the turbine blade 7 through the observation port 11 for instantaneous heating;
Then, the computer controls the turntable 23 to rotate, the turntable 23 drives the light condensing unit 22 to rotate, so that the emergent light beams converged by the light condensing unit 22 aim at another laser heating point, then the laser 21 is started, and after being reflected and converged by the light condensing unit 22, the laser beams emitted by the laser 21 are irradiated to a temperature measuring area corresponding to the laser heating point on the turbine blade 7 through the observation port 11 for instantaneous heating; completing laser instant heating of 2 temperature measuring areas of the turbine blade 7;
5) The temperature obtained by the 2 standard thermocouples 4 is collected by the tester 5 and is input to the control unit 6;
6) The control unit 6 controls the emission power and the accumulated time of the laser 21 in real time according to the temperature data obtained by each standard thermocouple 4, so as to change the energy of the laser 21 for irradiating the corresponding laser heating point, wherein the change of the emission power and the accumulated time should satisfy the following conditions: heating the temperature measuring area where each standard thermocouple 4 is positioned according to a preset temperature curve; in the heating process, the tester 5 collects the temperature obtained by the standard thermocouple 4 at each laser heating point under different emission energy of the laser 21 in real time and inputs the temperature into the control unit 6;
meanwhile, when the temperature data obtained by each standard thermocouple 4 reaches a set temperature point, the tester 5 acquires the temperature obtained by the film temperature sensor 71 in real time and inputs the temperature to the control unit 6;
7) The control unit 6 compares the temperature obtained by the standard thermocouple 4 corresponding to each laser heating point at each set temperature point with the temperature obtained by the film temperature sensor 71, and if the difference value of the two is within the tolerance range, the performance of the film temperature sensor 71 corresponding to the laser heating point is normal; if not, the performance of the film temperature sensor 71 does not reach the standard.
The test process of the embodiment further includes a response time test step of the film temperature sensors 71, and the test methods of the 2 film temperature sensors 71 are the same, specifically:
the control unit 6 records the heating start time of the laser 21 and the step response output time of the film temperature sensor 71, obtains the thermal response time of the film temperature sensor 71 by the difference value of the two, compares the thermal response time of the film temperature sensor 71 with the tolerance range, if the thermal response time of the film temperature sensor 71 is within the tolerance range, the response time of the film temperature sensor 71 is normal, and if not, the response time of the film temperature sensor 71 does not reach the standard.
After the whole testing process is completed, the heating box 1 is cooled to room temperature, and the turbine blades 7 are taken out.
The servo turntable of the embodiment can also be a biaxial servo turntable, a plurality of turbine blades 7 provided with the film temperature sensor 71 and the standard thermocouple 4 can be placed in the heating box 1, and the computer can further control the emergent laser spots of the light condensing unit 22 to move in the plane by controlling the rotation angle of the biaxial servo turntable, so that the test of the film temperature sensor 71 on the plurality of turbine blades 7 in the heating box 1 is realized.
In the embodiment, the laser beam is controlled to locally and transiently heat the temperature measuring region, so that the damage to the film temperature sensor and the turbine blade caused by long-time high temperature is avoided; the laser spots irradiated on the temperature measuring areas of the turbine blades 7 are detected through vision (imaging units), and the positions of the laser spots are adjusted through a servo turntable, so that a plurality of thin film temperature sensors 71 of a plurality of turbine blades 7 can be heated at the same time, and performance tests can be carried out; the turbine blade 7 is preheated to a high-temperature zone which is safe for materials by the heating box, so that the laser emission power and time are reduced under the condition that the service lives of the turbine blade 7 and the film temperature sensor 71 are not influenced, and more accurate temperature control is realized; the present embodiment realizes the control based on the computer simulation of the complex temperature curve by controlling the emission power and the accumulated time of the laser 21 by the computer, and can perform the more comprehensive test of the film temperature sensor 71.
The above description is only of the preferred embodiments of the present invention, and the technical solution of the present invention is not limited thereto, and any modifications made by those skilled in the art based on the main technical concept of the present invention are included in the technical scope of the present invention.
Claims (8)
1. A test system for a turbine blade integrated film temperature sensor, characterized by: comprises a heating box (1), an instantaneous heating unit (2), an imaging unit (3), a standard thermocouple (4), a tester (5) and a control unit (6);
the heating box (1) is internally used for placing turbine blades (7) to be tested, and the side wall of the heating box is provided with an observation port (11);
The instantaneous heating unit (2) is positioned outside the heating box (1) and comprises a laser (21), a light condensing unit (22) and a turntable (23); the condensing unit (22) is positioned on the outer side of the side wall observation port (11) of the heating box (1) and on an emergent light path of the laser (21); the focusing unit (22) is arranged on the rotary table (23), and the rotary table (23) is used for adjusting the position of the focusing unit (22) so that the laser beam emitted by the laser (21) is converged and reflected by the focusing unit (22) and then irradiates to a temperature measuring area of the turbine blade (7) to be measured through the observation port (11);
the imaging unit (3) is arranged outside an observation port (11) of the heating box (1) and is used for shooting the turbine blade (7) to be detected and inputting a shot video signal to the control unit (6);
The number of the standard thermocouples (4) is equal to that of the film temperature sensors (71) on the turbine blades (7) to be tested, and the mounting positions are in one-to-one correspondence with the positions of the temperature measuring areas of the turbine blades (7) where the film temperature sensors (71) are located;
The film temperature sensor (71) and the standard thermocouple (4) are respectively connected with the tester (5), the tester (5) collects the temperatures of the film temperature sensor (71) and the standard thermocouple (4), and the collected temperature data are input to the control unit (6);
the control unit (6) is connected with the laser (21) and used for controlling the emergent energy of the laser (21) and connected with the turntable (23) and used for controlling the turntable (23) to drive the light condensing unit (22) to rotate according to a video signal;
the control unit (6) compares the temperatures obtained by the film temperature sensor (71) and the standard thermocouple (4) and judges whether the performance of the film temperature sensor (71) is qualified or not.
2. The test system for a turbine blade integrated film temperature sensor of claim 1, wherein: the light gathering unit (22) is a concave reflector;
or the light condensing unit (22) comprises a converging mirror and a reflecting mirror which are sequentially arranged along an emergent light path of the laser (21).
3. The test system for a turbine blade integrated film temperature sensor of claim 2, wherein: a platform for placing turbine blades (7) to be tested is arranged in the heating box (1).
4. A test system for a turbine blade integrated film temperature sensor according to any one of claims 1 to 3, wherein: the heating box (1) is welded by adopting a stainless steel plate, the inner wall of the heating box (1) is filled with a ceramic heat-insulating material, a ceramic heater is arranged in the heating box (1), and a temperature sensor is arranged on the heating box (1);
A proximity sensor is mounted on the periphery of the laser (21).
5. The test system for a turbine blade integrated film temperature sensor of claim 4, wherein: the laser (21) is a high-power CO 2 laser;
the turntable (23) is a biaxial servo turntable;
The standard thermocouple (4) and the film temperature sensor (71) are connected with the tester (5) through compensation wires.
6. A test method for a turbine blade integrated film temperature sensor based on the test system for a turbine blade integrated film temperature sensor according to any one of claims 1-5, characterized by comprising the steps of:
1) Placing a turbine blade (7) to be tested, which is integrated with a film temperature sensor (71), in a heating box (1), installing a standard thermocouple (4) in a temperature measuring area of the turbine blade (7), and respectively connecting the film temperature sensor (71) to be tested and the standard thermocouple (4) to a tester (5) outside the heating box (1);
the number of the standard thermocouples (4) is equal to that of the film temperature sensors (71) on the turbine blades (7), and the positions of the standard thermocouples are in one-to-one correspondence;
2) Starting an imaging unit (3), shooting an image of a turbine blade (7), and calibrating a laser heating point on the image;
The number of the laser heating points is equal to that of the temperature measuring areas of the turbine blade (7), and the positions are in one-to-one correspondence;
3) Raising the temperature of the inner cavity of the heating box (1) to the preheating temperature;
4) The turntable (23) drives the light condensing unit (22) to rotate, so that the emergent light beam of the light condensing unit (22) aims at one of the laser heating points in the step 2), then the laser (21) is started, the laser beam emitted by the laser (21) is reflected and converged by the light condensing unit (22), and then is irradiated to a temperature measuring area corresponding to the laser heating point on the turbine blade (7) through the observation port (11) to be heated instantaneously, and the process is repeated to complete the heating of all the temperature measuring areas of the turbine blade (7);
5) The tester (5) collects the temperature obtained by the standard thermocouple (4) at each laser heating point and inputs the temperature into the control unit (6);
6) The control unit (6) controls the energy of the laser (21) for irradiating the corresponding laser heating point in real time according to the temperature data obtained by each standard thermocouple (4), so that the temperature measuring area where each standard thermocouple (4) is positioned is heated according to a preset temperature curve, and the temperature obtained by the standard thermocouple (4) at each laser heating point is collected in real time by the tester (5) and input to the control unit (6);
Meanwhile, when the temperature data obtained by each standard thermocouple (4) reach a set temperature point, the tester (5) collects the temperature obtained by the film temperature sensor (71) in real time and inputs the temperature into the control unit (6);
7) The control unit (6) compares the temperature obtained by the standard thermocouple (4) corresponding to each laser heating point at each set temperature point with the temperature obtained by the film temperature sensor (71), and if the difference value of the two is within the tolerance range, the performance of the film temperature sensor (71) corresponding to the laser heating point is normal; if not, the performance of the film temperature sensor (71) does not reach the standard.
7. The test method for a turbine blade integrated film temperature sensor of claim 6, wherein: in step 6), the energy of the laser (21) is controlled by varying the power emitted by the laser (21) and the integration time.
8. The test method for a turbine blade integrated film temperature sensor according to claim 6 or 7, further comprising:
Step 8) the control unit (6) records the heating start time of the laser (21) and the step response output time of the film temperature sensor (71), obtains the thermal response time of the film temperature sensor (71) through the difference value of the heating start time and the step response output time, compares the thermal response time of the film temperature sensor (71) with the tolerance range, if the thermal response time of the film temperature sensor (71) is within the tolerance range, the response time of the film temperature sensor (71) is normal, and if the thermal response time of the film temperature sensor (71) is not up to the standard.
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