Calibration method for dynamic rotor blade temperature

Abstract

The invention belongs to the technical field of rotor blade temperature monitoring, and particularly relates to a dynamic rotor blade temperature calibration method comprising the following steps: a high temperature furnace simulates a high temperature environment, and the temperature is raised to a preset temperature; the motor moving platform pushes the rotor blade coated with the fluorescent coating into a high-temperature furnace, and the rotation operation of the rotor blade is simulated; a photoelectric counter is used for externally triggering a laser to realize dynamic synchronization with a rotor blade; fluorescence signals are detected through the photoelectric detector and imported into the upper computer to be processed, obtained fluorescence signal data and the set temperature of the high-temperature furnace are fitted, a fluorescence characteristic-temperature relation curve is obtained, and dynamic rotor blade temperature calibration is achieved. The device is high in integration degree, can calibrate the temperature of the dynamic rotor blade, and can provide conditions and support for the measurement of the surface temperature of the rotating blade of an aero-engine.

Description

Technical Field

[0001] The invention belongs to the technical field of rotor blade temperature monitoring, and in particular relates to a calibration method for dynamic rotor blade temperature. Background Art

[0002] Compared with traditional measurement conditions, the rotating blades of aircraft engines have the characteristics of high temperature, high load, and high speed. Such a harsh test environment puts higher requirements on traditional temperature monitoring technology. When measuring the temperature of high-speed moving parts, traditional thermocouple temperature measurement technology usually adopts buried installation. Due to the temperature gradient in the thickness direction of the blade, the temperature of the measuring point is difficult to keep consistent with the surface, so the surface temperature of the blade cannot be accurately measured. In addition, it will cause damage to the surface of the test piece. The use of metal skin welding fixation will cause gaps around the sensing part of the thermocouple, resulting in a large contact thermal resistance. Therefore, it is not suitable for temperature measurement on the surface of blades that are expensive and require strict installation accuracy. Although the infrared thermal imaging temperature measurement technology, which has developed rapidly in recent years, has been used for internal temperature measurement of gas turbines due to its non-contact characteristics, there are many influencing factors in the actual temperature measurement process, mainly emissivity, background noise, absorption and scattering on the optical path, and the stability of the infrared thermal imager. The degree of influence of the above factors varies with different measurement conditions, and it is difficult to ensure the reliability of the measurement. Therefore, in order to effectively monitor the real-time temperature status of high-temperature components and dynamic rotor blades inside aircraft engines, it is urgent to develop a new type of high-precision, high-resolution, non-contact, less disturbed by environmental factors, and transient response temperature detection technology. Fluorescence temperature measurement is a method of measuring temperature using the emission spectrum characteristics of fluorescent molecules. Fluorescence temperature measurement has the advantages of non-contact, high sensitivity, wide temperature measurement range, high precision, online real-time monitoring, and single-point and array temperature detection. Compared with contact thermocouple temperature measurement, fluorescence temperature measurement overcomes the shortcomings of interfering with the flow field and damaging the measured object. Compared with infrared temperature measurement, fluorescence temperature measurement uses the intrinsic characteristics of fluorescent materials for temperature detection, is not affected by emissivity, and has high temperature measurement accuracy. In summary, fluorescence temperature measurement is a very potential temperature measurement technology with broad application prospects. Through the calibration method and device construction of dynamic rotor blade temperature, the feasibility of fluorescence temperature synchronous measurement technology under high-speed rotation conditions can be verified, providing a basis for subsequent research and application of dynamic rotor blade surface temperature measurement. Summary of the invention

[0003] 1. Technical issues to be resolved

[0004] The technical problem to be solved by the present invention is that the design and manufacture of simulated high-speed rotor blades is a complex and precise project, which requires in-depth consideration of factors in multiple academic fields to restore the actual operating conditions of aircraft engine blades to the greatest extent possible and ensure that the blades have excellent performance and reliability under high-speed rotation conditions. To measure the temperature of simulated high-speed rotor blades based on fluorescence temperature measurement technology, it is necessary to solve the problem of synchronous triggering between systems and calculate the response time and repetition frequency of the detection system for different speeds. The construction of a calibration method and device for dynamic rotor blade temperature should specifically consider the following points:

[0005] (1) Design of rotor blade simulation module: The key components of the model are designed based on the high-speed rotation linear speed of the rotor blades, including the number and size of blades and the size of the rotor disk; based on the principle of dynamic balance, the number, position and size of the bonded fluorescent temperature-sensitive sensing coating are designed in combination with the number of blades.

[0006] (2) Design of optical signal transmitting and receiving modules: Taking the simulated rotor blade as the measurement target, it is necessary to consider the response frequency under different rotation speed conditions. Through systematic frequency analysis and adjustment, the synchronization of the response frequency of the measurement equipment and the rotation speed of the blade bonded with the temperature-sensitive sensing coating can be ensured.

[0007] (II) Technical solution

[0008] In order to solve the above technical problems, the present invention provides a calibration method for dynamic rotor blade temperature, wherein the calibration method is implemented based on a calibration device, wherein the calibration device comprises: a high temperature furnace (1), a motor moving platform (20), a blade with a fluorescent coating (9), a photoelectric counter (25), a laser (14), a photoelectric detector (17), and a host computer (26);

[0009] The calibration method comprises:

[0010] Step 1: A high temperature furnace (1) simulates a high temperature environment and heats up to a preset temperature;

[0011] Step 2: The motor moving platform (20) pushes the blade (9) with the fluorescent coating into a high temperature furnace to simulate the rotation of the blade of an aircraft engine;

[0012] Step 3: Using a photoelectric counter (25) to externally trigger the laser (14) to achieve dynamic synchronization with the rotor blades;

[0013] Step 4: Detect the fluorescence signal through the photoelectric detector (17) and import it into the host computer (26) for processing, fit the acquired fluorescence signal data with the set temperature of the high-temperature furnace (1), obtain the fluorescence characteristic-temperature relationship curve, and realize the calibration of the dynamic rotor blade temperature.

[0014] Wherein, in the step 2, when the temperature reaches a preset temperature, the motor moving platform (20) is started, the blade (9) with the fluorescent coating is pushed into the high-temperature furnace cavity (2) through the coupling (19), the blade motor (18) is started to select the measurement speed, and the blade (9) starts to rotate.

[0015] Wherein, in step 3, when the blade motor (18) is started and adjusted to a predetermined speed, the photoelectric counter (25) counts the number of rotor blades, and when the count reaches a certain number, the photoelectric counter (25) sends a signal to the laser (14) for external triggering to emit laser.

[0016] In the step 4, the laser (14) is triggered to irradiate the blade (9) with the fluorescent coating. When the temperature and the rotation speed are known, the fluorescent coating emits a fluorescent signal which is subjected to spectroscopic processing by a spectroscope (15). The collimator (16) transmits the fluorescent signal back to the photodetector (17) through the optical fiber (24). The fluorescent signal is then introduced into the host computer (18) through the photodetector (17) for fluorescent signal processing, and a fluorescence characteristic-temperature relationship curve is obtained by fitting.

[0017] The high-temperature furnace (1) is used to simulate a real temperature measurement environment, and is provided with a high-temperature furnace cavity (2) of a cube structure inside, a flange (3) is installed at the front center part, a blade insertion port (4) is installed at the rear center part, a small quartz observation window (5) is installed at the top center part, an air charging port (6) is installed on one side of the quartz observation window (5), and an air outlet (7) is installed on the other side of the quartz observation window (5); the air charging port (6) and the air outlet (7) are located on both sides of the top of the high-temperature furnace (1), and are used to make the furnace in a vacuum or protective gas environment, and simulate the influence of the temperature of the rotor blades in different gas environments;

[0018] The blade (9) is arranged at the center of the high-temperature furnace cavity (2) and is used to simulate the rotation of an aircraft engine blade.

[0019] The high-temperature furnace (1) has a circular hole at the center of the front face on which the flange (3) is installed; the flange (3) has a hole at the center on which a quartz window (11) is installed; a water inlet (12) and a water outlet (13) are installed on both sides of the flange (3), which are the two ends of a water cooling device and are used to reduce the temperature outside the high-temperature furnace (1) and reduce the influence of the internal temperature of the high-temperature furnace (1) on the flange (3), thereby avoiding the influence of high temperature on other external supporting devices.

[0020] Wherein, the laser (14) is used to generate excitation light to irradiate the blade (9) with the fluorescent coating;

[0021] The spectroscope (15) is used to perform spectroscopic processing on the returned excitation light and the fluorescent signal of the fluorescent coating, so as to facilitate detection by the photoelectric detector (17);

[0022] The collimator (16) sends the fluorescence signal to the photodetector (17) via the optical fiber (24); the photodetector (17) receives the fluorescence signal transmitted back by the optical fiber (24); the photodetector (17) is connected to a host computer (26) to analyze and process the fluorescence signal data to obtain a fluorescence characteristic-temperature relationship curve;

[0023] The fluorescence characteristic-temperature relationship curve inverts the actual test temperature information by measuring the fluorescence signal data.

[0024] The photoelectric counter (25) records the number of blades that have rotated, externally triggers the laser (14) and is used to ensure the response frequency at different rotation speeds, thereby ensuring that the laser (14) generates excitation light and can illuminate the blades (9) with a fluorescent coating, thereby ensuring the synchronization of the rotation speed.

[0025] The collimator (16) has a circular hole at the center of the bottom for installing a first filter (21) to reduce the passage of light with a wavelength of more than 600 nm, thereby reducing the influence of high-temperature background radiation; a second filter (22) is installed at the center below the first filter (21) to prevent the passage of light with a wavelength of 355 nm, thereby reducing the interference of the excitation light on the collected fluorescence signal;

[0026] An optical fiber interface (23) is fixed below the collimator (16), and the optical fiber interface (23) is connected to the optical fiber (24). The light inlet port of the optical fiber (24) is arranged at the focus of the lens of the collimator (16), so as to ensure that more fluorescent signals are detected;

[0027] The photoelectric detector (17) selects different detection modes according to the different blade shapes, the different temperature environments in which the blades are located, and the different temperature parameter information to be obtained for the blades. For measuring the temperature of a single point on the blade, an avalanche photodiode and a photomultiplier tube are selected; for measuring the temperature of the blade surface, an array CCD camera and a multi-channel high-speed camera are selected; and different temperature measurement methods are performed according to different selected forms.

[0028] The blade motor (18), the coupling (19), and the motor moving platform (20) are located outside the high-temperature furnace cavity (2) behind the blade extension port (4);

[0029] The blade (9) with the fluorescent coating includes different coating forms according to different ambient temperatures and blade rotation speeds, and the different coating forms include: chemical bonding method and plasma spraying method; the number and form of the selected coatings are different according to the different temperature measurement modes or methods used;

[0030] The coupling (19) is made of heat-insulating materials with different thermal conductivity according to different ambient temperatures, so as to protect the blade motor (18) outside the furnace; when different blade (9) rotation speeds are selected, a material with strong torque resistance is selected according to the adjusted rotation speed to prevent damage caused by shaft breakage during operation.

[0031] (III) Beneficial effects

[0032] Compared with the prior art, the present invention provides a calibration method for dynamic rotor blade temperature, adopts fluorescence testing technology to measure temperature, adopts a high-temperature furnace as the test environment for the calibration experiment, and can more realistically restore the gas environment of the measured temperature field through the gas system, so as to design rotor blades that are closer to the real environment, and make the calibration data more suitable for complex temperature measurement environments; it realizes integration and precision, and the equipment operation process is simple, which can provide conditions and support for the measurement of the surface temperature of rotating blades of aircraft engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is the overall structural diagram of the temperature measurement system of the present invention.

[0034] Figure 2 The dynamic rotor blade coating design of the present invention. DETAILED DESCRIPTION

[0035] In order to make the purpose, content, and advantages of the present invention more clear, the specific implementation methods of the present invention are further described in detail below in conjunction with the accompanying drawings and examples.

[0036] In order to solve the above technical problems, the present invention provides a calibration method for dynamic rotor blade temperature, wherein the calibration method is implemented based on a calibration device, wherein the calibration device comprises: a high temperature furnace (1), a motor moving platform (20), a blade with a fluorescent coating (9), a photoelectric counter (25), a laser (14), a photoelectric detector (17), and a host computer (26);

[0037] The calibration method comprises:

[0038] Step 1: A high temperature furnace (1) simulates a high temperature environment and heats up to a preset temperature;

[0039] Step 2: The motor moving platform (20) pushes the blade (9) with the fluorescent coating into a high temperature furnace to simulate the rotation of the blade of an aircraft engine;

[0040] Step 3: Using a photoelectric counter (25) to externally trigger the laser (14) to achieve dynamic synchronization with the rotor blades;

[0041] Step 4: Detect the fluorescence signal through the photoelectric detector (17) and import it into the host computer (26) for processing, fit the acquired fluorescence signal data with the set temperature of the high-temperature furnace (1), obtain the fluorescence characteristic-temperature relationship curve, and realize the calibration of the dynamic rotor blade temperature.

[0042] Wherein, in the step 2, when the temperature reaches a preset temperature, the motor moving platform (20) is started, the blade (9) with the fluorescent coating is pushed into the high-temperature furnace cavity (2) through the coupling (19), the blade motor (18) is started to select the measurement speed, and the blade (9) starts to rotate.

[0043] Wherein, in step 3, when the blade motor (18) is started and adjusted to a predetermined speed, the photoelectric counter (25) counts the number of rotor blades, and when the count reaches a certain number, the photoelectric counter (25) sends a signal to the laser (14) for external triggering to emit laser.

[0044] In the step 4, the laser (14) is triggered to irradiate the blade (9) with the fluorescent coating. When the temperature and the rotation speed are known, the fluorescent coating emits a fluorescent signal which is subjected to spectroscopic processing by a spectroscope (15). The collimator (16) transmits the fluorescent signal back to the photodetector (17) through the optical fiber (24). The fluorescent signal is then introduced into the host computer (18) through the photodetector (17) for fluorescent signal processing, and a fluorescence characteristic-temperature relationship curve is obtained by fitting.

[0045] The high-temperature furnace (1) is used to simulate a real temperature measurement environment, and is provided with a high-temperature furnace cavity (2) of a cube structure inside, a flange (3) is installed at the front center part, a blade insertion port (4) is installed at the rear center part, a small quartz observation window (5) is installed at the top center part, an air charging port (6) is installed on one side of the quartz observation window (5), and an air outlet (7) is installed on the other side of the quartz observation window (5); the air charging port (6) and the air outlet (7) are located on both sides of the top of the high-temperature furnace (1), and are used to make the furnace in a vacuum or protective gas environment, and simulate the influence of the temperature of the rotor blades in different gas environments;

[0046] The blade (9) is arranged at the center of the high-temperature furnace cavity (2) and is used to simulate the rotation of an aircraft engine blade.

[0047] The high-temperature furnace (1) has a circular hole at the center of the front face on which the flange (3) is installed; the flange (3) has a hole at the center on which a quartz window (11) is installed; a water inlet (12) and a water outlet (13) are installed on both sides of the flange (3), which are the two ends of a water cooling device and are used to reduce the temperature outside the high-temperature furnace (1) and reduce the influence of the internal temperature of the high-temperature furnace (1) on the flange (3), thereby avoiding the influence of high temperature on other external supporting devices.

[0048] Wherein, the laser (14) is used to generate excitation light to irradiate the blade (9) with the fluorescent coating;

[0049] The spectroscope (15) is used to perform spectroscopic processing on the returned excitation light and the fluorescent signal of the fluorescent coating, so as to facilitate detection by the photoelectric detector (17);

[0050] The collimator (16) sends the fluorescence signal to the photodetector (17) via the optical fiber (24); the photodetector (17) receives the fluorescence signal transmitted back by the optical fiber (24); the photodetector (17) is connected to a host computer (26) to analyze and process the fluorescence signal data to obtain a fluorescence characteristic-temperature relationship curve;

[0051] The fluorescence characteristic-temperature relationship curve inverts the actual test temperature information by measuring the fluorescence signal data.

[0052] The photoelectric counter (25) records the number of blades that have rotated, externally triggers the laser (14) and is used to ensure the response frequency at different rotation speeds, thereby ensuring that the laser (14) generates excitation light and can illuminate the blades (9) with a fluorescent coating, thereby ensuring the synchronization of the rotation speed.

[0053] The collimator (16) has a circular hole at the center of the bottom for installing a first filter (21) to reduce the passage of light with a wavelength of more than 600 nm, thereby reducing the influence of high-temperature background radiation; a second filter (22) is installed at the center below the first filter (21) to prevent the passage of light with a wavelength of 355 nm, thereby reducing the interference of the excitation light on the collected fluorescence signal;

[0054] An optical fiber interface (23) is fixed below the collimator (16), and the optical fiber interface (23) is connected to the optical fiber (24). The light inlet port of the optical fiber (24) is arranged at the focus of the lens of the collimator (16), so as to ensure that more fluorescent signals are detected;

[0055] The photoelectric detector (17) selects different detection modes according to the different blade shapes, the different temperature environments in which the blades are located, and the different temperature parameter information to be obtained for the blades. For measuring the temperature of a single point on the blade, an avalanche photodiode and a photomultiplier tube are selected; for measuring the temperature of the blade surface, an array CCD camera and a multi-channel high-speed camera are selected; and different temperature measurement methods are performed according to different selected forms.

[0056] The blade motor (18), the coupling (19), and the motor moving platform (20) are located outside the high-temperature furnace cavity (2) behind the blade extension port (4);

[0057] The blade (9) with the fluorescent coating includes different coating forms according to different ambient temperatures and blade rotation speeds, and the different coating forms include: chemical bonding method and plasma spraying method; the number and form of the selected coatings are different according to the different temperature measurement modes or methods used;

[0058] The coupling (19) is made of heat-insulating materials with different thermal conductivity according to different ambient temperatures, so as to protect the blade motor (18) outside the furnace; when different blade (9) rotation speeds are selected, a material with strong torque resistance is selected according to the adjusted rotation speed to prevent damage caused by shaft breakage during operation.

[0059] In addition, the present invention also provides a calibration device for dynamic rotor blade temperature, the calibration device comprising: a high temperature furnace (1) with a temperature control system, a rotor blade simulation module (8), and an optical signal transmitting and receiving module (10);

[0060] The high-temperature furnace (1) is used to simulate a real temperature measurement environment, and is provided with a high-temperature furnace cavity (2) of a cube structure inside, a flange (3) is installed at the front center part, a blade insertion port (4) is installed at the rear center part, a small quartz observation window (5) is installed at the top center part, an air charging port (6) is installed on one side of the quartz observation window (5), and an air outlet (7) is installed on the other side of the quartz observation window (5); the air charging port (6) and the air outlet (7) are located on both sides of the top of the high-temperature furnace (1), and are used to make the furnace in a vacuum or protective gas environment, and simulate the influence of the temperature of the rotor blades in different gas environments;

[0061] The simulated rotor blade module (8) comprises a blade (9) with a fluorescent coating; the blade (9) is arranged at the center of the high-temperature furnace cavity (2) and is used to simulate the rotation of an aircraft engine blade;

[0062] The optical signal transmitting and receiving module (10) is used to generate an excitation optical signal, receive a fluorescent signal transmitted back by the optical fiber, analyze and process the fluorescent signal data, and obtain a fluorescence characteristic-temperature relationship curve.

[0063] The high-temperature furnace (1) has a circular hole at the center of the front face on which the flange (3) is installed; the flange (3) has a hole at the center on which a quartz window (11) is installed; a water inlet (12) and a water outlet (13) are installed on both sides of the flange (3), which are the two ends of a water cooling device and are used to reduce the temperature outside the high-temperature furnace (1) and reduce the influence of the internal temperature of the high-temperature furnace (1) on the flange (3), thereby avoiding the influence of high temperature on other external supporting devices.

[0064] The optical signal transmitting and receiving module (10) comprises: a laser (14), a beam splitter (15), a collimator (16), a photodetector (17), a host computer (26), and a photoelectric counter (25);

[0065] The laser (14) is used to generate excitation light to irradiate the blade (9) with the fluorescent coating;

[0066] The spectroscope (15) is used to perform spectroscopic processing on the returned excitation light and the fluorescent signal of the fluorescent coating, so as to facilitate detection by the photoelectric detector (17);

[0067] The collimator (16) sends the fluorescence signal to the photodetector (17) via the optical fiber (24). The photodetector (17) receives the fluorescence signal transmitted back by the optical fiber (24). The photodetector (17) is connected to a host computer (26) to analyze and process the fluorescence signal data to obtain a fluorescence characteristic-temperature relationship curve.

[0068] The photoelectric counter (25) records the number of blades that have rotated, externally triggers the laser (14) and is used to ensure the response frequency at different rotation speeds, thereby ensuring that the laser (14) generates excitation light and can illuminate the blades (9) with a fluorescent coating, thereby ensuring the synchronization of the rotation speed.

[0069] The collimator (16) has a circular hole at the center of the bottom for installing a first filter (21) to reduce the passage of light with a wavelength of more than 600 nm, thereby reducing the influence of high-temperature background radiation; a second filter (22) is installed at the center below the first filter (21) to prevent the passage of light with a wavelength of 355 nm, thereby reducing the interference of the excitation light on the collected fluorescence signal;

[0070] An optical fiber interface (23) is fixed below the collimator (16), and the optical fiber interface (23) is connected to the optical fiber (24). The light inlet port of the optical fiber (24) is arranged at the focus of the lens of the collimator (16), so as to ensure that more fluorescent signals are detected.

[0071] The photoelectric detector (17) selects different detection modes according to the different blade shapes, the different temperature environments in which the blades are located, and the different temperature parameter information to be obtained for the blades. For measuring the temperature of a single point on the blade, an avalanche photodiode and a photomultiplier tube are selected; for measuring the temperature of the blade surface, an array CCD camera and a multi-channel high-speed camera are selected; and different temperature measurement methods are performed according to different selection forms.

[0072] The simulated rotor blade module (8) comprises a blade (9) with a fluorescent coating, a blade motor (18), a coupling (19), and a motor moving platform (20); the remaining parts except the blade (9) are located outside the high-temperature furnace cavity (2) behind the blade extension port (4);

[0073] The blade (9) with the fluorescent coating includes different coating forms according to different ambient temperatures and blade rotation speeds. The different coating forms include: chemical bonding and plasma spraying. The number and form of the selected coatings are different according to the different temperature measurement methods or methods used. When a single-point temperature measurement method is used, the number and form of the selected coatings are different. Figure 2 The first blade (27) or the second blade (28) shown is prepared. If a surface array temperature measurement method is used, the temperature can be measured using Figure 2 The third blade (29) form shown is prepared.

[0074] The coupling (19) is made of heat-insulating materials with different thermal conductivity according to different ambient temperatures, so as to protect the blade motor (18) outside the furnace; when different blade (9) rotation speeds are selected, a material with strong torque resistance is selected according to the adjusted rotation speed to prevent damage caused by shaft breakage during operation.

[0075] The calibration process of the calibration device is as follows: the high temperature furnace (1) is turned on, and when the temperature reaches the set temperature, the motor moving platform (20) is started, and the blade (9) with the fluorescent coating is pushed into the inner cavity (2) of the high temperature furnace through the coupling (19), and the blade motor (18) is started to select the measurement speed, and the blade (9) starts to rotate;

[0076] When the blade motor (18) is started and adjusted to a predetermined speed, the photoelectric counter (25) counts the number of rotor blades. When the count reaches a certain number, the photoelectric counter (25) sends a signal to the laser (14) for external triggering to emit laser light.

[0077] The trigger laser (14) is used to irradiate the blade (9) with the fluorescent coating. When the temperature and the rotation speed are known, the fluorescent coating emits a fluorescent signal which is then split by a spectroscope (15). The collimator (16) transmits the fluorescent signal back to the photodetector (17) through an optical fiber (24). The fluorescent signal is then imported into a host computer (18) through the photodetector (17) for fluorescent signal processing, and a fluorescence characteristic-temperature relationship curve is obtained by fitting.

[0078] The fluorescence characteristic-temperature relationship curve is used to invert the actual test temperature information by measuring the fluorescence signal data.

[0079] Example 1

[0080] The overall structure of this embodiment is shown in FIG. Figure 1 As shown, first refer to Figure 1 Provide specific instructions for setting up the temperature measurement system.

[0081] For the convenience of description, the system is divided into the following four parts: the first part includes a high temperature furnace (1), a high temperature furnace cavity (2), a blade extension port (4), an air filling port (6), an air outlet (7), a quartz window (11) on a flange (3) and water inlets and outlets (13) on both sides; the second part includes a blade motor (18), a rotor blade with a fluorescent coating (9), and a motor moving platform (20); the third part includes a spectroscope (15), a collimator (16), a photoelectric detector (17), a host computer (26), a laser (14), and a photoelectric counter (25).

[0082] The first part is used to provide a dynamically calibrated high temperature environment and the gas environment space. The high temperature furnace (1) has its own temperature control system, which is heated by ten silicon molybdenum rods, and the gas environment is controlled by an external operating system; the inner cavity (2) of the high temperature furnace is a rectangular parallelepiped with a bottom length of 200 mm, a width of 200 mm, and a height of 100 mm; the quartz window (11) is a circular window with a radius of 75 mm.

[0083] The second part uses a blade motor (18) to control the rotation speed of the rotor blade (9), and when the high-temperature furnace (1) is heated to the temperature to be measured, the motor moving platform (20) is used to extend the rotor blade (9) into the inner cavity (2) of the high-temperature furnace, located in the center surrounded by ten silicon molybdenum rods, to ensure that the blade is heated evenly and quickly reaches the measured temperature value when extended, and the blade motor (18) is started and adjusted to the rotation speed to be measured, and the fluorescence characteristic-temperature measurement is performed.

[0084] The third part is a structure for information output, reception and processing. When the blade motor (18) is started and adjusted to a predetermined speed, the photoelectric counter (25) counts the number of rotor blades. When the count reaches a certain number, the photoelectric counter (25) sends a signal to the laser (14) for external triggering of laser emission. At this time, the rotor blade (9) containing the fluorescent coating should be irradiated. The fluorescent coating emits a fluorescent signal which is split by a spectroscope (15). The collimator (16) transmits the fluorescent signal back to the photoelectric detector (17) through the optical fiber (24), and then transmits it back to the host computer (26) through the data line for information processing. Through repeated operations, a dynamic rotor blade temperature curve is finally formulated.

[0085] Example 2

[0086] This embodiment provides a method and device for calibrating the temperature of a dynamic rotor blade. The calibration device includes: a simulated environment based on a high-temperature furnace, a simulated rotor blade device, a signal generation and processing system, and a rotor blade with a fluorescent coating; the high-temperature furnace contains a temperature control system and an externally controlled gas environment system, as well as a flange water cooling protection system on the front of the high-temperature furnace; the rotor blade device includes a motor, a horizontal propulsion device, and a rotor blade; the information module includes a detector, a spectroscope, a laser, a photoelectric counter, a spectrometer, and a host computer. The rotor blade with a fluorescent coating has a variety of coating methods and can be used for a variety of dynamic measurement methods and methods, which can be used for fluorescence intensity method, fluorescence lifetime method, single-point temperature measurement method, and array temperature measurement method.

[0087] In order to realize dynamic rotor blade temperature measurement, the rotor blade with fluorescent coating uses YAG:Dy as the fluorescent powder used in the experiment, which has a wide range of applications and can also use other types of fluorescent powders. The coating preparation method of the present invention is chemical bonding method.

[0088] When preparing the blades in the first way, the photoelectric counter can be adjusted to count multiple blades at a time. The specific number of blades is adjusted according to the rotation speed to ensure the synchronization of the response frequency of the laser and the rotation speed of the fluorescent coating blades. When preparing the blades in the second way, the photoelectric counter can be adjusted to count multiple cycles at a time. The specific number of cycles is adjusted according to the rotation speed to ensure the synchronization of the response frequency of the laser and the rotation speed of the fluorescent coating blades. At the same time, it is also necessary to ensure that the single pulse power of the laser is large enough. The specific power requirement varies according to the choice of phosphor. When using the fluorescence lifetime method, the detector must be connected to a power amplifier and an oscilloscope to measure the fluorescence lifetime. These two preparation methods are used for the calibration of the fluorescence characteristic-temperature relationship curve using a single-point temperature measurement method.

[0089] When the third blade preparation method is used, the photoelectric counter can be adjusted to count once per cycle. According to the specific blade size and quantity, the laser is expanded to ensure that the spot after laser expansion covers the entire fluorescent coating rotor blade, so that the detector can receive the signal. For the array temperature measurement method, the detector can be a multi-channel high-speed camera or an array CCD camera, and the camera receives the signal for information processing. This setting method can be used for array temperature measurement calibration.

[0090] It should be noted that, in this application, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0091] In summary, the present invention belongs to the technical field of rotor blade temperature monitoring, and specifically relates to a method for calibrating the temperature of a dynamic rotor blade, including: a high-temperature furnace simulates a high-temperature environment and heats up to a preset temperature; a motor moving platform pushes the rotor blade coated with a fluorescent coating into the high-temperature furnace to simulate the rotation of the rotor blade; a photoelectric counter is used to externally trigger the laser to achieve dynamic synchronization with the rotor blade; a photoelectric detector is used to detect the fluorescent signal and import it into the host computer for processing, and the acquired fluorescent signal data is fitted with the set temperature of the high-temperature furnace to obtain a fluorescence characteristic-temperature relationship curve to achieve the calibration of the dynamic rotor blade temperature. The present invention has a high degree of integration, can perform dynamic rotor blade temperature calibration, and can provide conditions and support for the measurement of the surface temperature of the rotating blades of an aircraft engine.

[0092] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the technical principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A method for calibrating dynamic rotor blade temperature, characterized in that: The calibration method is implemented based on a calibration device, which comprises: a high temperature furnace (1), a motor moving platform (20), a blade with a fluorescent coating (9), a photoelectric counter (25), a laser (14), a photoelectric detector (17), and a host computer (26); The calibration method comprises: Step 1: The high temperature furnace (1) simulates a high temperature environment and heats up to a preset temperature; Step 2: The motor moving platform (20) pushes the blade (9) with the fluorescent coating into a high temperature furnace to simulate the rotation of the blade of an aircraft engine; Step 3: Using a photoelectric counter (25) to externally trigger the laser (14) to achieve dynamic synchronization with the rotor blades; Step 4: Detect the fluorescence signal through the photoelectric detector (17) and import it into the host computer (26) for processing, fit the acquired fluorescence signal data with the set temperature of the high-temperature furnace (1), obtain the fluorescence characteristic-temperature relationship curve, and realize the calibration of the dynamic rotor blade temperature.

2. The method for calibrating dynamic rotor blade temperature according to claim 1, characterized in that: In step 2, when the temperature reaches a preset temperature, the motor moving platform (20) is started, the blade (9) with the fluorescent coating is pushed into the high-temperature furnace cavity (2) through the coupling (19), the blade motor (18) is started to select the measurement speed, and the blade (9) starts to rotate.

3. The method for calibrating dynamic rotor blade temperature according to claim 2, characterized in that: In step 3, when the blade motor (18) is started and adjusted to a predetermined speed, the photoelectric counter (25) counts the number of rotor blades. When the count reaches a certain number, the photoelectric counter (25) sends a signal to the laser (14) for external triggering to emit laser light.

4. The method for calibrating dynamic rotor blade temperature according to claim 3, characterized in that: In step 4, the laser (14) is triggered to irradiate the blade (9) with the fluorescent coating. When the temperature and the rotation speed are known, the fluorescent coating emits a fluorescent signal which is subjected to spectroscopic processing by a spectroscope (15). The collimator (16) transmits the fluorescent signal back to the photodetector (17) through the optical fiber (24). The fluorescent signal is then introduced into the host computer (18) through the photodetector (17) for fluorescent signal processing, and a fluorescence characteristic-temperature relationship curve is obtained by fitting.

5. The method for calibrating dynamic rotor blade temperature according to claim 4, characterized in that: The high-temperature furnace (1) is used to simulate a real temperature measurement environment, and is provided with a high-temperature furnace cavity (2) of a cube structure inside, a flange (3) is installed at the front center part, a blade insertion port (4) is installed at the rear center part, a small quartz observation window (5) is installed at the top center part, an air charging port (6) is installed on one side of the quartz observation window (5), and an air outlet (7) is installed on the other side of the quartz observation window (5); the air charging port (6) and the air outlet (7) are located on both sides of the top of the high-temperature furnace (1), and are used to make the furnace in a vacuum or protective gas environment, and simulate the influence of the temperature of the rotor blades in different gas environments; The blade (9) is arranged at the center of the high-temperature furnace cavity (2) and is used to simulate the rotation of an aircraft engine blade.

6. The method for calibrating dynamic rotor blade temperature according to claim 5, characterized in that: A circular hole is opened at the center of the front of the high-temperature furnace (1) to install the flange (3); a hole is opened at the center of the flange (3) to install a quartz window (11); a water inlet (12) and a water outlet (13) are installed on both sides of the flange (3), which are the two ends of the water cooling device and are used to reduce the temperature outside the high-temperature furnace (1) and reduce the influence of the internal temperature of the high-temperature furnace (1) on the flange (3), thereby avoiding the influence of high temperature on other external supporting devices.

7. The method for calibrating dynamic rotor blade temperature according to claim 4, characterized in that: The laser (14) is used to generate excitation light to irradiate the blade (9) with the fluorescent coating; The spectroscope (15) is used to perform spectroscopic processing on the returned excitation light and the fluorescent signal of the fluorescent coating, so as to facilitate detection by the photoelectric detector (17); The collimator (16) sends the fluorescence signal to the photodetector (17) via the optical fiber (24); the photodetector (17) receives the fluorescence signal transmitted back by the optical fiber (24); the photodetector (17) is connected to a host computer (26) to analyze and process the fluorescence signal data to obtain a fluorescence characteristic-temperature relationship curve; The fluorescence characteristic-temperature relationship curve inverts the actual test temperature information by measuring the fluorescence signal data.

8. The method for calibrating dynamic rotor blade temperature according to claim 7, characterized in that: The photoelectric counter (25) records the number of blades that have rotated, externally triggers the laser (14) and is used to ensure the response frequency at different rotation speeds, thereby ensuring that the laser (14) generates excitation light and can illuminate the blades (9) with the fluorescent coating, thereby ensuring the synchronization of the rotation speed.

9. The method for calibrating dynamic rotor blade temperature according to claim 7, characterized in that: The collimator (16) has a circular hole at the center of the bottom for installing a first filter (21) to reduce the passage of light with a wavelength of more than 600 nm, thereby reducing the influence of high-temperature background radiation; a second filter (22) is installed at the center below the first filter (21) to prevent the passage of light with a wavelength of 355 nm, thereby reducing the interference of the excitation light on the collected fluorescence signal; An optical fiber interface (23) is fixed below the collimator (16), and the optical fiber interface (23) is connected to the optical fiber (24). The light inlet port of the optical fiber (24) is arranged at the focus of the lens of the collimator (16), so as to ensure that more fluorescent signals are detected; The photoelectric detector (17) selects different detection modes according to the different blade shapes, the different temperature environments in which the blades are located, and the different temperature parameter information to be obtained for the blades. The avalanche photodiode and the photomultiplier tube are selected for measuring the temperature of a single point on the blade. To measure the blade surface temperature, select an array CCD camera or a multi-channel high-speed camera; different temperature measurement methods are used according to different selection forms.

10. The method for calibrating dynamic rotor blade temperature according to claim 5, characterized in that: The blade motor (18), the coupling (19), and the motor moving platform (20) are located outside the high-temperature furnace cavity (2) behind the blade extension port (4); The blade (9) with the fluorescent coating includes different coating forms according to different ambient temperatures and different blade rotation speeds, and the different coating forms include: chemical bonding method and plasma spraying method; Depending on the temperature measurement method or method used, the number and form of coatings selected will also be different; The coupling (19) is made of heat-insulating materials with different thermal conductivity according to different ambient temperatures, so as to protect the blade motor (18) outside the furnace; when different blade (9) rotation speeds are selected, a material with strong torque resistance is selected according to the adjusted rotation speed to prevent damage caused by shaft breakage during operation.

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