CN216246911U - Testing system for turbine blade integrated thin film temperature sensor - Google Patents
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- CN216246911U CN216246911U CN202122390096.5U CN202122390096U CN216246911U CN 216246911 U CN216246911 U CN 216246911U CN 202122390096 U CN202122390096 U CN 202122390096U CN 216246911 U CN216246911 U CN 216246911U
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Abstract
The utility model provides a testing system for a turbine blade integrated film temperature sensor, which solves 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 rotary table; the light condensing unit is positioned outside the observation port on the side wall of the heating box and on an emergent light path of the laser; the light condensing unit is arranged on the rotary table; 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 measured, and the standard thermocouples correspond to the film temperature sensors in position one to one; 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 rotary table; 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 utility model relates to the field of sensor testing, in particular to a testing system for a turbine blade integrated film temperature sensor.
Background
An aircraft engine is a complex machine that operates in a harsh environment of high temperature, high pressure, and high speed rotation, and has extremely high requirements for 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% for every 100 ℃ increase of the turbine inlet temperature of the aero-engine. In the pursuit of higher performance and more economical energy consumption, the research work on modern aircraft engines has been directed primarily to further increase the temperature in front of the turbine. Turbine blades are the primary components that convert thermal energy to mechanical energy, and their reliability design becomes the key to new engine designs. In order to improve the reliability of the turbine blade, the temperature field distribution on the surface of the turbine blade needs to be measured and analyzed so as to take effective measures in the aspects of materials, cooling, structures, processes and the like.
The film thermocouple is a transient temperature sensor directly prepared on the surface of the turbine blade, does not interfere the internal heat exchange of the turbine blade, does not influence the gas flow, is an ideal measurement technology for solving the problem of measuring the surface temperature of the turbine blade, and has already been researched and partially tried and applied at present.
As a sensor for measurement, 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 separately tested and calibrated like common industrial thermocouples such as thermocouple wires and sheathed thermocouples. At present, the verification of industrial thermocouples generally adopts a comparison method, and the measurement of the thermocouple is realized by putting the tested thermocouple and a standard thermocouple into a high-temperature verification furnace and heating to a constant temperature simultaneously. However, since the high-temperature verification furnace has long temperature rise and holding time, the tested piece is in a high-temperature environment for a long time, and the service life of the film thermocouple and the turbine blade is adversely affected. The thin-film thermocouple is limited by the thickness of a protective layer, the service life of the thin-film thermocouple at the highest temperature is only about 10 hours at the present stage, and even if the process is continuously optimized, the design life can only reach dozens of hours in consideration of the use environment and the engine test requirements. In addition, for the turbine blade, the surface temperature of the metal is 200 ℃ and 300 ℃ lower than the surface fuel gas temperature and the internal temperature is lower through the application of various technologies such as thermal barrier coating and air film cooling in operation. However, in the static environment of the high-temperature verification furnace, air cooling measures cannot be used, and after the temperature is constant for a long time, the heat insulation effect of the thermal barrier coating is also obviously reduced, so that the metal temperature of the turbine blade may exceed the reasonable working temperature, and irreversible damage is caused.
SUMMERY OF THE UTILITY MODEL
The utility model provides a testing system for a turbine blade integrated film temperature sensor, which aims to solve the technical problems that the existing turbine blade integrated film temperature sensor cannot adopt an industrial thermocouple temperature measurement calibration mode, and the continuous high temperature can generate adverse effects on the service lives of a turbine blade and the film temperature sensor.
In order to achieve the purpose, the technical scheme provided by the utility model is as follows:
a test system for turbine blade integrated thin film temperature sensors is characterized in that: the device comprises a heating box, an instantaneous heating unit, an imaging unit, a standard thermocouple, a tester and a control unit;
the heating box is used for placing turbine blades to be detected, 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 rotary table; the light condensing unit is positioned on the outer side of the observation port on the side wall of the heating box and on an emergent light path of the laser; the rotary table is used for adjusting the position of the light condensing unit, so that laser beams emitted by the laser are converged and reflected by the light condensing unit and then irradiate the temperature measuring area of the turbine blade to be measured through the observation port;
the imaging unit is arranged on the outer side of the observation port of the heating box and used for shooting the turbine blade to be detected and inputting a shot video signal 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 measured, and the installation positions correspond to the turbine blade temperature measurement areas where the film temperature sensors are located one by one;
the film temperature sensor and the standard thermocouple are respectively connected with the tester, and the tester collects the temperatures of the film temperature sensor and the standard thermocouple and inputs the collected temperature data 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.
Further, the light gathering 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 the turbine blade to be tested is arranged in the heating box.
Furthermore, the heating box is welded by stainless steel plates, the inner wall of the heating box is filled with ceramic heat-insulating materials, 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 high-power CO2A laser;
the rotary table is a two-axis servo rotary table;
the standard thermocouple, the film temperature sensor and the tester are connected through compensating wires.
Meanwhile, the utility model also provides a testing method for the turbine blade integrated film temperature sensor, which is characterized by comprising the following steps:
1) placing the turbine blade to be detected integrated with the 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 detected 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 standard thermocouples correspond to the film temperature sensors in position one to one;
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 turbine blade temperature measuring areas, and the positions of the laser heating points correspond to those of the turbine blade temperature measuring areas one by one;
3) raising the temperature of the inner cavity of the heating box to a preheating temperature;
4) the turntable drives the condensing unit to rotate, so that an emergent light beam of the condensing unit is aimed at one of the laser heating points in the step 2), then the laser is started, a laser beam emitted by the laser is reflected and converged by the condensing unit, and then the laser beam 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 finish 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 energy of the laser device irradiating the corresponding laser heating points in real time according to the temperature data obtained by each standard thermocouple, so that the temperature measuring area where each standard thermocouple is located is heated according to a preset temperature curve, and the tester collects the temperature obtained by the standard thermocouple at each laser heating point in real time and inputs the temperature to the control unit;
meanwhile, when the temperature data obtained by each standard thermocouple reaches a set temperature point, the tester collects the temperature obtained by the film temperature sensor in real time and inputs the temperature to 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 two 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 realized by changing the emission power and the accumulation time of the lasers.
Further, still include:
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 through the difference value of the heating start time and the step response output time of the film temperature sensor, 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 not, the response time of the film temperature sensor does not reach the standard.
Compared with the prior art, the utility model has the advantages that:
1. according to the testing system and method, the turbine blade is preheated to a high-temperature region safe to materials through the heating box, and the film temperature sensor and the turbine blade are prevented from being damaged by long-time high temperature by controlling laser beams to heat the local transient state of the temperature measuring region under the condition that the service lives of the turbine blade and the film temperature sensor are not influenced.
2. The testing system controls the laser beam to heat the local transient state of the temperature measuring area through the control unit, can control the temperature change of the film temperature sensor in a very short time, and avoids the influence of continuous high-temperature environment on the service life of the film temperature sensor and the turbine blade; meanwhile, the control unit controls the transmitting power and the accumulated irradiation time of the laser, so that the temperature change curve can be flexibly adjusted, and the simulation of the temperature change in the engine is realized; and then can more accurate temperature control, realize carrying out more comprehensive test to film temperature sensor.
3. The testing system disclosed by the utility model is based on the laser transient heating control of a visual detection technology (the imaging unit shoots the position of a laser spot), can simulate a complex temperature curve, reduces the influence on the service life of a tested product, and is suitable for the rapid test calibration of the temperature sensor.
4. The testing system provided by the utility model can be used for detecting the laser spot position through the imaging unit and adjusting the spot position through the two-axis servo turntable, 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 thin film temperature sensor according to the present invention;
wherein the reference numbers are as follows:
1-heating box, 11-observation port, 2-instantaneous heating unit, 21-laser, 22-light gathering unit, 23-rotary table, 3-imaging unit, 4-standard thermocouple, 5-tester, 6-control unit, 7-turbine blade, 71-film temperature sensor.
Detailed Description
The utility model is described in further detail below with reference to the figures and specific embodiments.
As shown in FIG. 1, the testing system for the turbine blade integrated thin film temperature sensor of the utility model 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.
Be used for placing turbine blade 7 that awaits measuring in the heating cabinet 1, for the convenience of placing of turbine blade 7, be provided with the platform that is used for placing turbine blade 7 that awaits measuring in the heating cabinet 1. In the embodiment, the heating box 1 is welded by stainless steel plates, and the inner wall of the heating box 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 temperature controller to heat the whole inside of the heating box 1; 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 box 1, and comprises a laser 21, a light condensing unit 22 and a turntable 23; laser instrument 21 is installed in heating cabinet 1 outside, installs proximity sensor in laser instrument 21 periphery, can avoid the personnel to approach in the use and cause the injury. The light condensing unit 22 is positioned outside the observation port 11 on the side wall of the heating box 1 and on an emergent light path of the laser 21, and laser beams emitted by the laser 21 are reflected and converged by the light condensing unit 22 and then are irradiated onto the turbine blade 7 to be measured through the observation port 11 on the side wall of the heating box 1 for rapid instantaneous heating; the light gathering unit 22 in this embodiment is a concave reflective mirror, the concave reflective mirror is used for gathering and reflecting laser beams, and the laser beams are irradiated to the temperature measuring area of the turbine blade 7 through the observation port 11 after being gathered; in other embodiments, the light-gathering unit 22 may be composed of a converging mirror and a reflecting mirror sequentially arranged along the emergent light path of the laser 21.
The laser 21 is connected with the control unit 6, the control unit 6 is a computer, and the laser 21 is a high-power CO2Laser, high power CO2The laser control signal is given by a computer and can control the emitting energy of the laser 21, and the emitting energy of the laser 21 is changed by changing the emitting power and the accumulated time of the laser in the embodiment.
The rotary table 23 is a servo rotary table, the concave mirror is mounted on the servo rotary table, the servo rotary table is controlled by a computer, the servo rotary table is driven by the computer to rotate, the concave mirror on the servo rotary table is further driven to move, the heating position of the laser emitted by the concave mirror to the turbine blade 7 is adjusted, and the laser condensed by the concave mirror is aimed at the temperature measuring area of the turbine blade 7.
The imaging unit 3 adopts a high-definition industrial camera, a gigabit Ethernet is connected with a computer, the imaging unit 3 is installed outside an observation port 11 of the heating box 1 and used for shooting the turbine blade 7 to be detected, the shot video signal is input into the computer, and the computer adjusts the position of the light condensing unit 22 through the rotary table 23 in real time according to the shot temperature measuring area of the turbine blade 7 and the laser-irradiated light spot position, so that the laser light spot position is accurately aligned with the position of the temperature measuring area of the turbine blade 7.
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 correspond to the positions of the temperature measuring areas of the turbine blade 7 where the film temperature sensors 71 are located one by one; in this embodiment, for example, 2 film temperature sensors 71 are installed on the turbine blade 7, the number of the standard thermocouples 4 is also 2, the positions of the standard thermocouples correspond to the 2 film temperature sensors 71 one by one, and the standard thermocouples 4 are located in the 2 temperature measuring areas of the turbine blade 7 respectively, and the measuring ends of the standard thermocouples 4 are bonded to the positions of the temperature measuring areas where the film temperature sensors 71 are located by high temperature resistant glue.
The film temperature sensor 71 and the standard thermocouple 4 are both 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 the computer, and the computer 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 according to the difference value of the two temperatures.
In the embodiment, the test system carries out image calibration once during installation, and establishes the 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.
The testing process of the testing system of the embodiment for the film temperature sensor 71 on the turbine blade 7 comprises the following steps:
1) placing the turbine blade 7 to be measured integrated with the film temperature sensor 71 in the heating box 1, and enabling the temperature measuring area of the turbine blade 7 to be over against the observation port 11 of the heating box 1; respectively installing standard thermocouples 4 in 2 temperature measuring areas of the turbine blade 7, and respectively connecting 2 to-be-measured film temperature sensors 71 and 2 standard thermocouples 4 in the 2 temperature measuring areas to a tester 5 outside the heating box 1;
2) starting the 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 blades 7, and the positions of the laser heating points correspond to one another, so that the number of the laser heating points is 2;
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 safety range of the heating box 1, the turbine blade 7, the film temperature sensor 71 and the standard thermocouple 4;
4) the computer controls the rotation of the rotary table 23, the rotary table 23 drives the light condensing unit 22 to rotate, so that the emergent light beam condensed by the light condensing unit 22 aims at one laser heating point, then the laser 21 is started, and the laser beam emitted by the laser 21 is reflected and condensed by the light condensing unit 22 and then irradiates a temperature measuring area corresponding to the laser heating point on the turbine blade 7 through the observation port 11 to carry out instantaneous heating;
then, the computer controls the rotation of the rotating platform 23, the rotating platform 23 drives the light condensing unit 22 to rotate, so that the emergent light beam converged by the light condensing unit 22 aims at another laser heating point, then the laser 21 is started, and the laser beam emitted by the laser 21 is reflected and converged by the light condensing unit 22 and then irradiates a temperature measuring area corresponding to the laser heating point on the turbine blade 7 through the observation port 11 to carry out instantaneous heating; completing laser instantaneous heating of 2 temperature measuring areas of the turbine blade 7;
5) the tester 5 collects the temperatures obtained by the 2 standard thermocouples 4 and inputs the temperatures into 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 irradiating the corresponding laser heating point, wherein the change of the emission power and the accumulated time meets the following requirements: heating a temperature measuring area where each road sign quasi-thermocouple 4 is located according to a preset temperature curve; in the temperature rise process, the tester 5 collects the temperature obtained by the standard thermocouple 4 at each laser heating point under different emitting energies of the laser 21 in real time and inputs the temperature to the control unit 6;
meanwhile, when the temperature data obtained by each standard thermocouple 4 reaches a set temperature point, the tester 5 collects 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 between 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 meet the standard.
The test process of this embodiment further includes a step of testing the response time of the film temperature sensor 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 from the difference between the two, compares the thermal response time of the film temperature sensor 71 with the tolerance range, and 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 finished, the heating box 1 is cooled to the room temperature, and the turbine blade 7 is taken out.
The servo turntable can also be a biaxial servo turntable, a plurality of turbine blades 7 provided with the film temperature sensors 71 and the standard thermocouples 4 can be placed in the heating box 1, and the computer controls the rotation angle of the biaxial servo turntable to further control emergent laser spots of the light condensing unit 22 to move on a plane, so that the test of the film temperature sensors 71 on the plurality of turbine blades 7 in the heating box 1 is realized.
According to the embodiment, the laser beam is controlled to heat the local transient state of the temperature measuring area, so that the damage of the film temperature sensor and the turbine blade caused by long-time high temperature is avoided; laser spots irradiated on the temperature measuring area of the turbine blade 7 by laser are detected through a vision (imaging unit), the positions of the spots are adjusted through a servo turntable, and the film temperature sensors 71 of the turbine blades 7 can be heated at the same time for performance testing; the turbine blade 7 is preheated to a high-temperature interval safe to materials through the heating box, and under the condition that the service lives of the turbine blade 7 and the film temperature sensor 71 are not influenced, the laser emission power and time are reduced, and more accurate temperature control is realized; in the embodiment, the emitting power and the accumulated time of the laser 21 are controlled by the computer, so that the complicated temperature curve control based on computer simulation is realized, and the film temperature sensor 71 can be tested more comprehensively.
The above description is only for the preferred embodiment of the present invention and does not limit the technical solution of the present invention, and any modifications made by those skilled in the art based on the main technical idea of the present invention belong to the technical scope of the present invention.
Claims (5)
1. A test system for a turbine blade integrated thin film temperature sensor, comprising: 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 used for placing a turbine blade (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-gathering unit (22) and a rotary table (23); the light condensing unit (22) is positioned on the outer side of the observation port (11) on the side wall of the heating box (1) and on an emergent light path of the laser (21); the light condensing unit (22) is arranged on the rotary table (23), and the rotary table (23) is used for adjusting the position of the light condensing unit (22) so that laser beams emitted by the laser (21) are condensed and reflected by the light condensing unit (22) and then irradiate the temperature measuring area of the turbine blade (7) to be measured through the observation port (11);
the imaging unit (3) is arranged on the outer side of 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 measured, and the installation positions correspond to the temperature measuring areas of the turbine blades (7) where the film temperature sensors (71) are located one by one;
the film temperature sensor (71) and the standard thermocouple (4) are respectively connected with the tester (5), and the tester (5) acquires the temperatures of the film temperature sensor (71) and the standard thermocouple (4) and inputs the acquired temperature data 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 is connected with the rotary table (23) and used for controlling the rotary table (23) to drive the light condensing unit (22) to rotate according to the video signal;
and 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.
2. The test system for a turbine blade integrated thin film temperature sensor of claim 1, wherein: the light gathering unit (22) is a concave reflector;
or the light condensation unit (22) comprises a converging mirror and a reflecting mirror which are sequentially arranged along the emergent light path of the laser (21).
3. The test system for a turbine blade integrated thin film temperature sensor of claim 2, wherein: a platform used for placing the turbine blade (7) to be tested is arranged in the heating box (1).
4. The test system for a turbine blade integrated thin film temperature sensor according to any one of claims 1 to 3, wherein: the heating box (1) is welded by stainless steel plates, the inner wall of the heating box is filled with ceramic heat-insulating materials, a ceramic heater is arranged in the heating box (1), and a temperature sensor is arranged on the heating box (1);
and a proximity sensor is arranged on the periphery of the laser (21).
5. The test system for a turbine blade integrated thin film temperature sensor of claim 4, wherein: the laser (21) is high-power CO2A laser;
the rotary table (23) is a biaxial servo rotary table;
the standard thermocouple (4), the film temperature sensor (71) and the tester (5) are connected through compensating wires.
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| CN202122390096.5U CN216246911U (en) | 2021-09-29 | 2021-09-29 | Testing system for turbine blade integrated thin film temperature sensor |
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| CN202122390096.5U CN216246911U (en) | 2021-09-29 | 2021-09-29 | Testing system for turbine blade integrated thin film temperature sensor |
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