High-temperature-resistant telescopic turbine blade radiation temperature measurement probe

Abstract

The utility model provides a high-temperature-resistant telescopic turbine blade radiation temperature measurement probe, and belongs to the technical field of engine turbine blade radiation temperature measurement. The problems that an existing turbine blade temperature monitoring device is generally large in size, low in applicability, poor in flexibility and low in measurement precision are solved. The device comprises a corrugated pipe assembly, a probe assembly, a single-shaft assembly and a shell, a cover plate is arranged at the top of the shell, the corrugated pipe assembly and the single-shaft assembly are both arranged in the shell, the probe assembly comprises a probe body, an air pipe, an air inlet seat, a probe installation seat and a probe support, the corrugated pipe assembly comprises a telescopic corrugated pipe and a corrugated pipe installation seat, and the telescopic corrugated pipe is connected with the single-shaft assembly. One end of the corrugated pipe assembly is connected with the probe support. The device is mainly used for radiation temperature measurement of engine turbine blades.

Description

Technical Field

[0001] The utility model belongs to the technical field of radiation temperature measurement of engine turbine blades, in particular to a high-temperature resistant and retractable turbine blade radiation temperature measurement probe. Background Art

[0002] The engine is the "heart" of modern industrial technology. Its performance and safety are crucial and have high technical barriers. The engine is mainly composed of three major components: the compressor, the combustion chamber, and the turbine. Among them, the turbine blades are important components in the engine that withstand high temperature and high pressure airflow. The accurate measurement of their surface temperature is crucial for engine performance optimization, life management, and safe operation. The high temperature resistance of this component directly determines the maximum temperature of the engine when it is working. In addition, during the operation of the engine, the temperature of the turbine blades is easily increased, which will cause damage to the turbine blades, which will in turn cause a decrease in fuel efficiency and a significant increase in maintenance costs. It will seriously affect the safe operation of the engine, causing major safety hazards and huge economic losses. Therefore, real-time monitoring of the surface temperature of the engine turbine blades is of vital significance to the entire industry.

[0003] At present, the temperature measurement technology for engine turbine blades can be mainly divided into contact temperature measurement and non-contact temperature measurement. Contact temperature measurement is a method of measuring the temperature of an object by direct contact with a temperature sensor. Common contact temperature sensors include thermocouples, thermistors, etc. Contact temperature measurement equipment is simple and easy to implement, and is suitable for occasions with high temperature accuracy requirements, such as laboratory scientific research, precision machining and other fields. However, contact temperature measurement requires direct contact with the object to be measured, which may destroy the temperature field distribution on the surface of the object to be measured, and is not suitable for measurement needs in high temperature, high speed, and dangerous environments. Non-contact temperature measurement is a method of indirectly measuring the temperature of the object to be measured by measuring the infrared radiation energy of the object to be measured. It does not require contact with the object to be measured, does not affect the normal operation of the equipment, avoids interference with the object to be measured, has a short measurement time, and a wide temperature measurement range. It is suitable for long-distance measurement in high temperature, high speed, and dangerous environments. Non-contact temperature measurement methods are mainly divided into acoustic temperature measurement, radiation temperature measurement, thermal imaging temperature measurement, infrared temperature measurement, and laser temperature measurement. These methods are based on different physical principles and can achieve non-contact measurement of the surface temperature of an object.

[0004] Radiation temperature measurement is a non-contact temperature measurement method that uses the infrared radiation energy radiated by an object to be proportional to the surface temperature of the object, and indirectly measures the surface temperature of an object by measuring the amount of infrared radiation on the surface of the object. Due to the advantages of radiation temperature measurement such as fast response speed, wide application range, and no interference with the temperature field of turbine blades, it is widely used in online measurement of turbine blade surface temperature, with high flexibility and safety. In summary, radiation temperature measurement is particularly suitable for temperature measurement of devices such as turbine blades that work under the "three highs" extreme conditions of high temperature, high pressure and high speed for a long time. At present, there are still challenges in the measurement technology of engine blade surface temperature. The existing turbine blade temperature monitoring devices on the market generally have the problems of large size, low applicability, poor flexibility and low measurement accuracy. Some temperature measurement devices adopt a fixed design and cannot be flexibly adjusted according to different surface or environmental requirements, which reduces the applicability and flexibility of the measurement. Utility Model Content

[0005] In view of this, the utility model aims to propose a high-temperature resistant retractable turbine blade radiation temperature measuring probe to solve the problems of existing turbine blade temperature monitoring devices, such as large size, low applicability, poor flexibility, low measurement accuracy, and some temperature measuring devices adopt a fixed design, which cannot be flexibly adjusted according to different surface or environmental requirements, reducing the applicability and flexibility of the measurement.

[0006] To achieve the above-mentioned purpose, the utility model adopts the following technical scheme: a high-temperature resistant and retractable turbine blade radiation temperature measuring probe, which includes a bellows assembly, a probe assembly, a single-axis assembly and a shell, a cover plate is arranged on the top of the shell, the bellows assembly and the single-axis assembly are both arranged in the shell, the probe assembly is slidably arranged above the single-axis assembly, the probe assembly includes a probe body, an air pipe, an air intake seat, a probe mounting seat and a probe bracket, the probe bracket is slidably connected above the single-axis assembly, the air intake seat and the probe mounting seat are arranged at one end of the probe bracket in sequence, and the probe mounting seat is connected to one end of the shell The air intake seat is connected to the probe bracket, the probe body is a hollow structure, one end of the probe body is provided with an imaging lens, one end of the probe body passes through the probe mounting seat, the air intake seat and the probe bracket in sequence, and is fixedly connected to the probe bracket, one end of the air pipe is connected to the air intake seat, and is communicated with the inner cavity of the probe body through the air intake seat, the other end of the air pipe passes through the probe bracket and the bellows assembly in sequence, the bellows assembly includes a telescopic bellows and a bellows mounting seat, one end of the bellows assembly is connected to the probe bracket, and the other end is connected to the other end of the shell through the bellows mounting seat.

[0007] Furthermore, the single-axis assembly includes a base, a stepper motor, a ball screw and a workbench, the bottom of the probe bracket is connected to the workbench, the base is provided with a groove, a ball screw is rotatably arranged in the groove, the bottom of the workbench is cooperatively connected with the ball screw, the output end of the stepper motor is connected to one end of the ball screw and drives the workbench to move through the ball screw.

[0008] Furthermore, linear guide rails are provided on both sides of the groove, and the bottoms of both sides of the workbench are slidably matched with the linear guide rails.

[0009] Furthermore, a motor bracket is provided at one end of the base, and the stepper motor is connected to the base via the motor bracket.

[0010] Furthermore, the probe bracket includes a base, on which a first mounting head, a second mounting head and a third mounting head are arranged at intervals, a connecting plate is provided at one end of the probe body, one end of the probe body passes through the first mounting head and the second mounting head and is connected to the second mounting head through the connecting plate, the air inlet seat is connected to the first mounting head, and one end of the telescopic bellows is connected to the third mounting head.

[0011] Furthermore, a connecting seat is provided between the third mounting head and the telescopic bellows.

[0012] Furthermore, both ends of the telescopic bellows are provided with joints, the joint at one end of the telescopic bellows is cooperatively connected with the connecting seat, and the joint at the other end of the telescopic bellows is connected with the outer shell through the bellows mounting seat.

[0013] Furthermore, a bellows end plate is provided at one end of the telescopic bellows, and the bellows end plate is connected to the third mounting head.

[0014] Furthermore, one end of the air pipe is sequentially passed through the third mounting head and the inner cavity of the telescopic bellows.

[0015] Furthermore, an air hole is opened on the side wall of the probe body, and the inner cavity of the probe body is connected with the inner cavity of the air inlet seat through the air hole.

[0016] Compared with the prior art, the beneficial effects of the utility model are:

[0017] 1. The utility model provides a high-temperature resistant retractable turbine blade radiation temperature measuring probe. An air inlet seat and an air pipe are arranged on the probe body, and cold air is introduced into the probe body through the air pipe to keep the probe within a suitable temperature range, so that the probe can work stably in an extremely high temperature environment, ensuring the stability and durability of the device measurement, with high measurement accuracy and rapid response capability, and can timely monitor the temperature changes on the blade surface and timely feedback to the system for regulation;

[0018] 2. The utility model provides a high-temperature resistant retractable turbine blade radiation temperature measuring probe, which realizes the retractable setting of the probe through a single-axis component and a bellows component, and can be adjusted according to the size and shape of different turbine blades, thereby improving applicability and flexibility;

[0019] 3. The utility model provides a high-temperature resistant retractable turbine blade radiation temperature measuring probe, which is small and light, easy to install, does not affect the normal operation of the turbine blades, has strong durability, adapts to complex high-temperature and high-speed environments, and has long-term stable working performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation on the present invention. In the accompanying drawings:

[0021] Figure 1 It is a partial structural schematic diagram of a high temperature resistant and retractable turbine blade radiation temperature measuring probe according to the utility model;

[0022] Figure 2 This is a schematic diagram of the overall structure of a high-temperature resistant and retractable turbine blade radiation temperature measurement probe according to the utility model;

[0023] Figure 3 An exploded view of the overall structure schematic diagram of a high-temperature resistant and retractable turbine blade radiation temperature measuring probe according to the utility model;

[0024] Figure 4 It is an exploded view of a bellows assembly of a high-temperature resistant and retractable turbine blade radiation temperature measuring probe according to the utility model;

[0025] Figure 5 It is an exploded view of a single-axis component of a high-temperature resistant and retractable turbine blade radiation temperature measuring probe according to the utility model;

[0026] Figure 6 It is an exploded view of a probe assembly of a high-temperature resistant and retractable turbine blade radiation temperature measuring probe according to the utility model;

[0027] Figure 7 It is a cross-sectional view of the structure of a high-temperature resistant and retractable turbine blade radiation temperature measuring probe according to the utility model;

[0028] Figure 8 It is a schematic structural diagram of a probe bracket of a high-temperature resistant and retractable turbine blade radiation temperature measuring probe according to the utility model;

[0029] Fig. 9It is a structural schematic diagram of a probe body of a high-temperature resistant and retractable turbine blade radiation temperature measurement probe according to the utility model;

[0030] Fig.10 It is a structural schematic diagram of a connection seat of a high-temperature resistant and retractable turbine blade radiation temperature measuring probe according to the utility model;

[0031] Fig.11 It is a structural schematic diagram of a probe mounting seat of a high-temperature resistant and retractable turbine blade radiation temperature measurement probe according to the utility model;

[0032] Fig.12 It is a schematic diagram of a high temperature resistant retractable turbine blade radiation temperature measuring probe described in the utility model in actual application.

[0033] 1- bellows assembly, 2- probe assembly, 3- single-axis assembly, 4- housing, 5- cover plate, 6- bellows end plate, 7- connector, 8- telescopic bellows, 9- bellows mounting seat, 10- workbench, 11- base, 12- ball screw, 13- linear guide, 14- motor bracket, 15- stepper motor, 16- imaging lens, 17- air inlet seat, 18- probe body, 19- connecting seat, 20- air pipe, 21- probe mounting seat, 22- probe bracket, 23- base, 24- first mounting head, 25- second mounting head, 26- third mounting head, 27- connecting plate, 28- turbine blade. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely explain the technical solutions in the embodiments of the utility model. It should be noted that the embodiments and features in the embodiments of the utility model can be combined with each other without conflict, and the described embodiments are only part of the embodiments of the utility model, not all of the embodiments.

[0035] See also Figure 1-12The present embodiment is described as a high temperature resistant retractable turbine blade radiation temperature measuring probe, which comprises a bellows assembly 1, a probe assembly 2, a single shaft assembly 3 and a shell 4, wherein a cover plate 5 is arranged on the top of the shell 4, wherein the bellows assembly 1 and the single shaft assembly 3 are both arranged in the shell 4, wherein the probe assembly 2 is slidably arranged above the single shaft assembly 3, wherein the probe assembly 2 comprises a probe body 18, an air pipe 20, an air inlet seat 17, a probe mounting seat 21 and a probe bracket 22, wherein the probe bracket 22 is slidably connected above the single shaft assembly 3, wherein the air inlet seat 17 and the probe mounting seat 21 are arranged in sequence at one end of the probe bracket 22, wherein the probe mounting seat 21 is slidably connected to one end of the shell 4 The air intake seat 17 is connected to the probe bracket 22, the probe body 18 is a hollow structure, one end of the probe body 18 passes through the probe mounting seat 21, the air intake seat 17 and the probe bracket 22 in sequence, and is fixedly connected to the probe bracket 22, one end of the air pipe 20 is connected to the air intake seat 17, and is connected to the inner cavity of the probe body 18 through the air intake seat 17, the other end of the air pipe 20 passes through the probe bracket 22 and the bellows assembly 1 in sequence, the bellows assembly 1 includes a telescopic bellows 8 and a bellows mounting seat 9, one end of the bellows assembly 1 is connected to the probe bracket 22, and the other end is connected to the other end of the shell 4 through the bellows mounting seat 9.

[0036] The bellows assembly 1 described in this embodiment is used for the pressure difference inside and outside the isolation cabin. The telescopic bellows 8 in the bellows assembly 1 is welded with elastic thin sheets, has high rigidity in the radial direction, can withstand a large pressure difference, and is flexible in the axial direction. When stretched or compressed by external force, it is easy to obtain a large deformation, which is manifested as overall elongation or shortening on a macro scale. One end of the telescopic bellows 8 is fixed by the bellows mounting seat 9, and the other end moves with the probe assembly 2. The probe bracket 22 drives the extension and contraction of the probe body 18 while driving the telescopic bellows 8 to extend and shorten, which utilizes the flexible characteristics of the bellows.

[0037] In this embodiment, the probe bracket 22 is used to fix the probe body 18 , and the probe body 18 is connected with the bellows assembly 1 and the single-axis assembly 3 through the probe bracket 22 .

[0038] The cover plate 5 and the outer shell 4 described in this embodiment are used to protect the key components and circuits inside the utility model from being affected by the external environment, such as high temperature, corrosion, etc., to ensure the normal operation of the probe, to prevent the probe from being damaged by collision or extrusion, to extend the service life of the probe, to prevent external substances such as dust and water vapor from entering and affecting the normal operation of the probe, and to provide stable mechanical support for the probe to ensure that the position of the probe is fixed.

[0039] In this embodiment, an air inlet seat 17 and an air pipe 20 are provided on the probe body 18, and cold air is introduced into the probe body 18 through the air pipe 20 to keep the probe within a suitable temperature range. This enables the probe to work stably in an extremely high temperature environment, ensures the stability and durability of the device's measurement, has high measurement accuracy, has a rapid response capability, can timely monitor changes in blade surface temperature, and promptly feed back to the system for regulation.

[0040] This embodiment realizes the retractable setting of the probe through the single-axis component 3 and the bellows component 1, which can be adjusted according to the size and shape of different turbine blades, thereby improving the applicability and flexibility.

[0041] The high-temperature resistant retractable turbine blade radiation temperature measuring probe described in this embodiment is small and light in size, easy to install, does not affect the normal operation of the turbine blades, has strong durability, can adapt to complex high-temperature and high-speed environments, and has long-term stable working performance.

[0042] The high-temperature resistant retractable turbine blade radiation temperature measuring probe described in this embodiment has high measurement accuracy and rapid response capability, and can timely monitor changes in blade surface temperature and provide timely feedback to the system for regulation.

[0043] The single-axis component 3 described in this embodiment includes a base 11, a stepper motor 15, a ball screw 12 and a workbench 10. The bottom of the probe bracket 22 is connected to the workbench 10. A groove is opened on the base 11. A ball screw 12 is rotatably arranged in the groove. The bottom of the workbench 10 is matched with the ball screw 12. The output end of the stepper motor 15 is connected to one end of the ball screw 12 and drives the workbench 10 to move through the ball screw 12. The single-axis component 3 described in this embodiment adopts a combination of a linear guide 13 and a ball screw 12, which is easy to use. The movement of the workbench 10 is controlled by the stepper motor 15. The workbench 10 is connected to the probe bracket 22, so that the probe can be partially extended or retracted to achieve the retractable advantage of the device. In addition, the precision and stability of the ball screw 12 can ensure that the telescopic movement of the probe body 18 is smooth and reliable, thereby improving the accuracy and reliability of temperature measurement.

[0044] In this embodiment, the base 11 is made of alloy. A sensor may be connected to the side of the base 11 , and corresponding sensor signal transmitting blocks are arranged on both sides of the workbench 10 to determine the telescopic length of the probe body 18 .

[0045] In this embodiment, linear guide rails 13 are provided on both sides of the groove, and the bottoms of both sides of the workbench 10 are slidably matched with the linear guide rails 13. The linear guide rails 13 play a role in limiting and guiding the workbench 10. In this embodiment, the linear guide rails 13 are of medium and heavy load type and are suitable for high load transmission applications.

[0046] In this embodiment, a motor bracket 14 is disposed at one end of the base 11 , and the stepper motor 15 is connected to the base 11 via the motor bracket 14 . A positioning hole is disposed on the motor bracket 14 for fixing and installing the stepper motor 15 .

[0047] In this embodiment, the single-axis assembly 3 can drive the workbench 10 to move forward and backward along the ball screw 12 on the linear guide 13 through the stepper motor 15, and the workbench 10 is connected to the probe bracket 22 through screws, thereby realizing the linkage between the workbench 10 and the probe assembly 2. The probe assembly 2 can collect the radiation light information on the surface of the turbine blade and transmit it.

[0048] In this embodiment, the probe bracket 22 includes a base 23, on which a first mounting head 24, a second mounting head 25 and a third mounting head 26 are arranged at intervals. A connecting plate 27 is provided at one end of the probe body 18. One end of the probe body 18 passes through the first mounting head 24 and the second mounting head 25 and is connected to the second mounting head 25 through the connecting plate 27. The air inlet seat 17 is connected to the first mounting head 24, and one end of the telescopic bellows 8 is connected to the third mounting head 26. In this embodiment, the connecting plate 27 is disc-shaped and has four circular through holes with a diameter of 5.5 mm. In this embodiment, the first mounting head 24 is used to connect to the air inlet seat 17, the second mounting head 25 is used to fix the probe body 18, and the third mounting head 26 is used to connect to the bellows assembly 1.

[0049] In this embodiment, an air hole is opened on the side wall of the probe body 18, and the inner cavity of the probe body 18 is connected with the inner cavity of the air inlet seat 17 through the air hole. The probe body 18 is a hollow structure, 300mm long and 9mm in diameter. The air hole is a circular through hole with a diameter of 2.8mm for the entry of cold air.

[0050] In this embodiment, an imaging lens 16 is disposed at one end of the probe body 18 . The imaging lens 16 is cylindrical in shape and is a convex lens. The imaging lens 16 is assembled and integrated by laser welding.

[0051] In this embodiment, a connecting seat 19 is provided between the third mounting head 26 and the telescopic bellows 8. In this embodiment, the connecting seat 19 adopts a connector of model FRNWF40, and the two ends of the connecting seat 19 are respectively used to cooperate with the probe bracket 22 and the telescopic bellows 8.

[0052] In this embodiment, joints 7 are provided at both ends of the telescopic bellows 8. The joint 7 at one end of the telescopic bellows 8 is connected to the connecting seat 19, and the joint 7 at the other end of the telescopic bellows 8 is connected to the housing 4 through the bellows mounting seat 9.

[0053] In this embodiment, a bellows end plate 6 is provided at one end of the telescopic bellows 8 . The bellows end plate 6 is connected to the third mounting head 26 . The bellows end plate 6 is used for connecting the telescopic bellows 8 and the probe bracket 22 .

[0054] In this embodiment, one end of the air pipe 20 passes through the third mounting head 26 and the inner cavity of the telescopic bellows 8 in sequence.

[0055] This embodiment also provides a method for assembling a high temperature resistant retractable turbine blade radiation temperature measuring probe, which comprises the following steps:

[0056] Step 1: Make sure the work area is clean and tidy to avoid dust and debris from interfering with the probe installation process. Check whether all parts of the probe are intact and prepare the tools and materials required for installation.

[0057] Step 2: Install the imaging lens 16 inside the probe body 18 and assemble and integrate it by laser welding;

[0058] Step 3: Connect the air inlet seat 17 to the probe body 18, ensuring that the connection is tight and the position is correct so that the air inlet is unobstructed;

[0059] Step 4: Connect the air pipe 20 to the air inlet seat 17, ensuring that the connection is firm and there is no air leakage;

[0060] Step 5: Connect the probe bracket 22 to the telescopic bellows 8, ensuring a firm connection and isolating the pressure difference inside and outside the cabin;

[0061] Step 6: Connect the probe bracket 22 to the single-axis component 3 through screws to drive the movement and position adjustment of the probe to ensure that the retractable function can be achieved;

[0062] Step 7: Place the installed device in the housing 4, and connect the probe mounting seat 21 and the bellows mounting seat 9 to both ends of the housing 4 respectively;

[0063] Step 8: Conduct a test, turn on the probe system, debug the position and connection of each component, ensure that the probe can accurately receive the radiation light signal of the turbine blade, verify whether the temperature measurement function of the device is normal, and ensure that the data collection is accurate and reliable;

[0064] Step 9: After confirming that the probe installation position and function are normal, fix the components and encapsulate the probe to prevent it from being affected by the external environment.

[0065] Fig.12This is a schematic diagram of the device in actual application. When performing real-time optical signal acquisition, first ensure that the probe is in a closed state, and check the state of the probe and whether the connecting parts are intact. Confirm that the telescopic part of the probe is in a retracted state, and ensure that the single-axis component 3 is in normal working condition. According to the actual situation, adjust the position of the probe so that the probe adapts to the size and shape of the turbine blade 28, and makes the temperature measuring probe face the surface of the turbine blade to ensure that the radiation light information on the surface of the turbine blade 28 can be accurately collected. In addition, it is necessary to connect the air pipe 20 to the probe body 18 to ensure perfect function. Finally, connect the probe to the outside of the engine through screws and nuts. The screws are added with flat washers of appropriate size to reduce the risk of falling off. Start the working state of the probe, and control the movement of the single-axis component through the stepper motor 15 to realize the extension and retraction of the probe. The radiation light information on the surface of the turbine blade 28 is first radiated to the probe assembly, and then transmitted to the inside of the probe along the light pipe inside the probe body 18 and received.

[0066] The embodiments of the utility model disclosed above are only used to help explain the utility model. The embodiments do not describe all the details in detail, nor do they limit the utility model to the specific implementation methods described. According to the content of this specification, many modifications and changes can be made. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the utility model, so that technicians in the relevant technical field can well understand and use the utility model.

Claims

1. A high temperature resistant retractable turbine blade radiation temperature measuring probe, characterized in that: It comprises a bellows assembly (1), a probe assembly (2), a single-axis assembly (3) and a shell (4); a cover plate (5) is arranged on the top of the shell (4); the bellows assembly (1) and the single-axis assembly (3) are both arranged in the shell (4); the probe assembly (2) is slidably arranged above the single-axis assembly (3); the probe assembly (2) comprises a probe body (18), an air pipe (20), an air inlet seat (17), a probe mounting seat (21) and a probe bracket (22); the probe bracket (22) is slidably connected above the single-axis assembly (3); the air inlet seat (17) and the probe mounting seat (21) are arranged in sequence at one end of the probe bracket (22); the probe mounting seat (21) is connected to one end of the shell (4); the air inlet seat (17) is connected to the probe bracket (22); The probe body (18) is a hollow structure. One end of the probe body (18) is provided with an imaging lens (16). One end of the probe body (18) passes through a probe mounting seat (21), an air inlet seat (17) and a probe bracket (22) in sequence and is fixedly connected to the probe bracket (22). One end of the air pipe (20) is connected to the air inlet seat (17) and communicates with the inner cavity of the probe body (18) through the air inlet seat (17). The other end of the air pipe (20) passes through the probe bracket (22) and a bellows assembly (1) in sequence. The bellows assembly (1) includes a telescopic bellows (8) and a bellows mounting seat (9). One end of the bellows assembly (1) is connected to the probe bracket (22), and the other end is connected to the other end of the housing (4) through the bellows mounting seat (9).

2. A high temperature resistant retractable turbine blade radiation temperature measuring probe according to claim 1, characterized in that: The single-axis assembly (3) comprises a base (11), a stepper motor (15), a ball screw (12) and a workbench (10); the bottom of the probe bracket (22) is connected to the workbench (10); a groove is provided on the base (11), a ball screw (12) is rotatably arranged in the groove, the bottom of the workbench (10) is cooperatively connected to the ball screw (12), the output end of the stepper motor (15) is connected to one end of the ball screw (12) and drives the workbench (10) to move through the ball screw (12).

3. The high temperature resistant retractable turbine blade radiation temperature measuring probe according to claim 2, characterized in that: Linear guide rails (13) are provided on both sides of the groove, and the bottoms on both sides of the workbench (10) are slidably matched with the linear guide rails (13).

4. The high temperature resistant retractable turbine blade radiation temperature measuring probe according to claim 2, characterized in that: A motor bracket (14) is provided at one end of the base (11), and the stepping motor (15) is connected to the base (11) via the motor bracket (14).

5. The high temperature resistant retractable turbine blade radiation temperature measuring probe according to claim 1, characterized in that: The probe bracket (22) comprises a base (23), on which a first mounting head (24), a second mounting head (25) and a third mounting head (26) are arranged at intervals, one end of the probe body (18) is provided with a connecting plate (27), one end of the probe body (18) passes through the first mounting head (24) and the second mounting head (25) and is connected to the second mounting head (25) through the connecting plate (27), the air inlet seat (17) is connected to the first mounting head (24), and one end of the telescopic bellows (8) is connected to the third mounting head (26).

6. The high temperature resistant retractable turbine blade radiation temperature measuring probe according to claim 5, characterized in that: A connecting seat (19) is provided between the third mounting head (26) and the telescopic bellows (8).

7. The high temperature resistant retractable turbine blade radiation temperature measuring probe according to claim 5, characterized in that: Both ends of the telescopic bellows (8) are provided with joints (7); the joint (7) at one end of the telescopic bellows (8) is cooperatively connected to a connecting seat (19); and the joint (7) at the other end of the telescopic bellows (8) is connected to the housing (4) via a bellows mounting seat (9).

8. The high temperature resistant retractable turbine blade radiation temperature measuring probe according to claim 7, characterized in that: A bellows end plate (6) is provided at one end of the telescopic bellows (8), and the bellows end plate (6) is connected to a third mounting head (26).

9. The high temperature resistant retractable turbine blade radiation temperature measuring probe according to claim 7, characterized in that: One end of the air pipe (20) is sequentially passed through the inner cavity of the third mounting head (26) and the telescopic bellows (8).

10. The high temperature resistant retractable turbine blade radiation temperature measuring probe according to claim 1, characterized in that: An air hole is provided on the side wall of the probe body (18), and the inner cavity of the probe body (18) is connected with the inner cavity of the air inlet seat (17) through the air hole.

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