High-rigidity positionable turbine blade radiation temperature measurement movable probe

Abstract

The utility model provides a high-rigidity positionable turbine blade radiation temperature measurement movable 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 universality, poor in flexibility and low in measurement precision are solved. The probe comprises a mounting seat assembly, a cylinder driving assembly, a probe body and an anti-reflux assembly, the cylinder driving assembly and the anti-reflux assembly are both arranged on one side of the mounting seat assembly, the anti-reflux assembly comprises an anti-reflux seat and an air pipe, and the cylinder driving assembly comprises a sliding table, a cylinder, a probe bending plate and a refrigeration air pipe. 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-rigidity positionable movable probe for radiation temperature measurement of turbine blades. Background Art

[0002] Temperature is a key factor that can significantly affect the properties of matter. At different temperatures, objects will exhibit different characteristics and responses. In some industrial processes or production environments that are extremely sensitive to temperature, accurate temperature monitoring is essential. For example, in industries such as aerospace and shipbuilding, my country has invested a lot of resources to improve the performance of aircraft engines and gas turbines. Among them, turbine blades play a key role in the engine, and their temperature is an important indicator reflecting the working state of the blades. However, these engines usually operate in harsh environments with high temperature, high pressure, and high-concentration airflow, which causes the turbine blades to often experience aging and wear problems internally. Therefore, accurately measuring the temperature of turbine blades under complex working conditions is crucial to extending the life of the engine.

[0003] At present, the temperature measurement methods are mainly divided into contact temperature measurement and non-contact temperature measurement. Contact temperature measurement requires the sensor to directly contact the surface of the object, which may cause damage to the object or affect its surface temperature distribution and cannot measure high-temperature surfaces or difficult-to-reach areas. It also has the disadvantages of slow response speed and high maintenance cost. It is not suitable for measuring the surface temperature of turbine blades. Radiation temperature measurement is a typical non-contact temperature measurement method. It is a method of measuring the surface temperature of an object by using the thermal radiation emitted by the object. The surface temperature of the object can be calculated by measuring the intensity of infrared radiation emitted by the object. Radiation temperature measurement has the advantages of high accuracy, fast response speed, and wide applicability. It does not require contact with the object and can measure temperature quickly and over a long distance. It is suitable for measuring difficult-to-reach or high-temperature objects.

[0004] There are many radiation temperature measurement devices on the market, but there are some problems: some devices are large in size and need to rely on complex post-data processing, some devices are only in the theoretical verification stage and have not yet been actually launched. Although some devices can achieve measurement, they are only suitable for specific engines and have poor versatility. Some devices have low measurement accuracy and limited applicable environments. In addition, the main challenges faced by radiation temperature measurement equipment designed for specific narrow environments at home and abroad also include the miniaturization of equipment structure and the cooling performance of key components. In a high-temperature, enclosed and narrow space, an oversized temperature measurement device will interfere with the working state of the target being measured, so the size of the device needs to be reduced as much as possible to achieve interference-free or minimal interference monitoring. In addition, instrument components entering a high-temperature environment need to work in a high-temperature and high-pressure environment of more than 1000°C for a long time, so cooling the core optical components and other structural components is also a key challenge. Utility Model Content

[0005] In view of this, the utility model aims to propose a high-rigidity and positionable turbine blade radiation temperature measurement movable probe to solve the problems of existing turbine blade temperature monitoring devices, such as large size, low applicability, poor versatility, poor flexibility and low measurement accuracy.

[0006] To achieve the above-mentioned purpose, the utility model adopts the following technical scheme: a high-rigidity positionable turbine blade radiation temperature measurement movable probe, which includes a mounting seat assembly, a cylinder drive assembly, a probe body and an anti-backflow assembly, wherein the cylinder drive assembly and the anti-backflow assembly are both arranged on one side of the mounting seat assembly, the anti-backflow assembly includes an anti-backflow seat and an air pipe, the upper half of the mounting seat assembly is provided with a cylindrical protrusion, the anti-backflow seat is matched and connected with the cylindrical protrusion of the mounting seat assembly, a gap is provided between the outer wall of the anti-backflow seat and the inner wall of the cylindrical protrusion, the air pipe is arranged at the bottom of the anti-backflow seat, and the air pipe is connected through the anti-backflow seat and the gap between the anti-backflow seat and the cylindrical protrusion, The cylinder drive assembly includes a slide, a cylinder, a probe bent plate and a refrigeration air pipe. One end of the cylinder is fixedly connected to one side of the bottom of the mounting seat assembly, and the other end of the cylinder is an output end. The slide is slidably arranged on the top of the cylinder, and the output end of the cylinder is connected to the slide and drives the movement of the slide. The probe bent plate is arranged on the top of the slide. One end of the probe body passes through the mounting seat assembly, the anti-backflow seat and the probe bent plate in sequence and is fixedly connected to the probe bent plate. The probe body is slidably connected to the mounting seat assembly and the anti-backflow seat. The refrigeration air pipe is connected to one side of the probe bent plate. The probe body is a hollow structure, and the refrigeration air pipe is connected to the inner cavity of the probe body through the probe bent plate.

[0007] Furthermore, a connecting plate is provided at one end of the probe body, and the probe body is connected to the probe bending plate via the connecting plate.

[0008] Furthermore, an optical fiber is connected to one side of the connecting plate, and the optical fiber is connected to the connecting plate via an optical fiber seat.

[0009] Furthermore, a fiber fixing plate is provided at the tail end of the probe bending plate, the bottom of the fiber fixing plate is connected to one side of the slide, and the optical fiber and the cooling air pipe are both arranged through the fiber fixing plate.

[0010] Furthermore, a first sealing member is disposed at one end of the anti-backflow seat, a first outer pressure ring is sleeved on the outer side of the first sealing member, and the probe body passes through the first sealing member and is cooperatively connected with the first sealing member.

[0011] Furthermore, a second sealing member is disposed at one end of the probe bending plate, a second outer pressure ring is sleeved on the outer side of the second sealing member, and the probe body passes through the second sealing member and is cooperatively connected with the second sealing member.

[0012] Furthermore, the cylinder drive assembly also includes a base plate, the bottom of the cylinder is connected to the base plate, and both ends of the base plate are connected to the mounting seat assembly.

[0013] Furthermore, a position measurement component is provided on the cylinder drive component, and the position measurement component includes a magnetic strip, a reading head and a head seat. The reading head is fixedly connected to one side of the cylinder through the head seat, and the magnetic strip is arranged on one side of the probe bend plate and cooperates with the reading head.

[0014] Furthermore, an imaging lens is disposed at one end of the probe body.

[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 probe bending plate 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-rigidity, positionable, movable probe for radiation temperature measurement of turbine blades. A cooling air pipe connected to the inner cavity of the probe body is provided, 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, high measurement accuracy, and rapid response capability. It 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-rigidity, positionable, movable probe for radiation temperature measurement of turbine blades, which can monitor the operating position information of the probe in real time, provide accurate data feedback, and help adjust and optimize the measurement process. In addition, an anti-backflow component is provided, which adds a high-pressure gas through the air pipe to prevent the high-pressure and high-temperature gas inside the measured equipment from flowing back into the optical probe, thereby protecting the probe body from damage, ensuring a stable working environment for the probe body, ensuring accurate measurement data, and improving the accuracy and reliability of the measurement. A sealing design is adopted between the anti-backflow component and the mounting seat, and a sealing member is used to seal between the anti-backflow component and the probe body, which can ensure the free extension and retraction of the optical component.

[0019] 3. The utility model provides a high-rigidity and positionable movable probe for measuring radiation temperature of turbine blades. The probe can be retracted and set through a cylinder drive assembly, and can be adjusted according to the size and shape of different turbine blades, thereby improving applicability and flexibility.

[0020] 4. The utility model provides a high-rigidity and positionable turbine blade radiation temperature measurement movable probe, which has a high-rigidity structure and can maintain stability in high airflow velocity or high temperature and high pressure environment to ensure measurement accuracy and reliability;

[0021] 5. The utility model provides a high-rigidity, positionable movable probe for turbine blade radiation temperature measurement, which is compact and light, easy to install, and convenient for measurement in a small space, does not affect the normal operation of the turbine blades, improves measurement accuracy, has strong durability, is adaptable to complex high-temperature and high-speed environments, and has long-term stable working performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] 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:

[0023] Figure 1 This is a schematic diagram of the overall structure of a high-rigidity, positionable movable probe for radiation temperature measurement of turbine blades according to the utility model;

[0024] Figure 2 It is a schematic diagram of the overall structure of a high-rigidity positionable turbine blade radiation temperature measurement movable probe according to the utility model from other viewing angles;

[0025] Figure 3 It is a schematic diagram of the overall structure of a high-rigidity positionable turbine blade radiation temperature measurement movable probe according to the utility model from other viewing angles;

[0026] Figure 4 It is a cross-sectional schematic diagram of a high-rigidity positionable movable probe for radiation temperature measurement of turbine blades according to the utility model;

[0027] Figure 5 This is an exploded view of the overall structure of a high-rigidity, positionable, movable probe for radiation temperature measurement of turbine blades described in the utility model;

[0028] Figure 6 It is a structural schematic diagram of a mounting seat assembly in a high-rigidity and positionable movable probe for radiation temperature measurement of turbine blades according to the utility model;

[0029] Figure 7 It is a structural schematic diagram of the assembly of a mounting seat component and an anti-backflow component in a high-rigidity and positionable turbine blade radiation temperature measurement movable probe according to the utility model;

[0030] Figure 8 It is an exploded view of a cylinder drive assembly in a high-rigidity and positionable movable probe for radiation temperature measurement of turbine blades described in the utility model;

[0031] Fig. 9 This is a schematic structural diagram of a probe body, an optical fiber holder and an optical fiber in a high-rigidity, positionable movable probe for measuring radiation temperature of turbine blades according to the utility model;

[0032] Fig.10 It is an exploded view of the anti-backflow component in a high-rigidity and positionable turbine blade radiation temperature measurement movable probe described in the utility model;

[0033] Fig.11 It is an exploded view of a position measurement component in a high-rigidity and positionable movable probe for radiation temperature measurement of turbine blades described in the utility model;

[0034] Fig.12 The utility model is a schematic diagram of a high-rigidity positionable movable probe for radiation temperature measurement of turbine blades in actual application.

[0035] 1-mounting seat assembly, 2-cylinder drive assembly, 3-probe body, 4-anti-backflow assembly, 5-position measurement assembly, 6-cylinder, 7-probe bending plate, 8-second external pressure ring, 9-optical fiber fixing plate, 10-bottom plate, 11-refrigeration air pipe, 12-optical fiber, 13-imaging lens, 14-connecting plate, 15-optical fiber seat, 16-air pipe, 17-anti-backflow seat, 18-first external pressure ring, 19-first seal, 20-magnetic strip, 21-reading head, 22-head seat, 23-second seal, 24-slide, 25-turbine blade. DETAILED DESCRIPTION

[0036] 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.

[0037] See also Figure 1-12The present embodiment is described, a high-rigidity positionable turbine blade radiation temperature measurement movable probe, which includes a mounting seat assembly 1, a cylinder drive assembly 2, a probe body 3 and an anti-backflow assembly 4, wherein the cylinder drive assembly 2 and the anti-backflow assembly 4 are both arranged on one side of the mounting seat assembly 1, the anti-backflow assembly 4 includes an anti-backflow seat 17 and an air pipe 16, the upper half of the mounting seat assembly 1 is provided with a cylindrical protrusion, the anti-backflow seat 17 is matched and connected with the cylindrical protrusion of the mounting seat assembly 1, a gap is provided between the outer wall of the anti-backflow seat 17 and the inner wall of the cylindrical protrusion, the air pipe 16 is provided at the bottom of the anti-backflow seat 17, the air pipe 16 is connected through the anti-backflow seat 17 and the gap between the anti-backflow seat 17 and the cylindrical protrusion, the cylinder drive assembly 2 includes a slide 24, cylinder 6, probe bent plate 7 and refrigeration air pipe 11, one end of the cylinder 6 is fixedly connected to one side of the bottom of the mounting seat assembly 1, and the other end of the cylinder 6 is the output end. The slide 24 is slidably arranged on the top of the cylinder 6, and the output end of the cylinder 6 is connected to the slide 24 and drives the movement of the slide 24. The probe bent plate 7 is arranged on the top of the slide 24. One end of the probe body 3 passes through the mounting seat assembly 1, the anti-backflow seat 17 and the probe bent plate 7 in sequence and is fixedly connected to the probe bent plate 7. The probe body 3 is slidably connected to the mounting seat assembly 1 and the anti-backflow seat 17. The refrigeration air pipe 11 is connected to one side of the probe bent plate 7. The probe body 3 is a hollow structure, and the refrigeration air pipe 11 is connected to the inner cavity of the probe body 3 through the probe bent plate 7.

[0038] The mounting base assembly 1 described in the present embodiment is used to fix the connection between the cylinder drive assembly 2, the anti-backflow assembly 4 and the probe body 3, and can provide a stable support structure for the device, ensuring that the probe body 3 is installed firmly and stably, not easy to move or loosen, and can also reduce the risk of falling off, ensuring that the probe body 3 can still maintain a stable connection in a high temperature, high pressure, and high air flow velocity environment. In addition, the present design is also easy to install and disassemble, convenient for maintaining the probe, and reduces maintenance time and cost.

[0039] The anti-backflow component 4 described in this embodiment can add high-pressure gas to the gap between the anti-backflow seat 17 and the cylindrical protrusion of the mounting seat assembly 1 through the air pipe 16 to prevent the backflow of high-pressure and high-temperature gas inside the measured equipment, thereby protecting the probe body from damage, ensuring a stable working environment for the probe body, and improving the accuracy and stability of the measurement data. By effectively preventing gas backflow, the efficiency and quality of optical signal acquisition can be improved, ensuring that the probe body 3 can accurately receive the radiated light information on the surface of the engine turbine blade 25, thereby improving the accuracy and reliability of the measurement.

[0040] The cylinder drive 2 component described in this embodiment realizes the retractable setting of the probe, which can be adjusted according to the size and shape of different turbine blades, so that the probe can be accurately aligned with the surface of the turbine blade in a small space or complex environment, thereby improving the accuracy and reliability of the measurement. In addition, the device can also be adapted to different engine models, and has strong applicability and flexibility.

[0041] In this embodiment, a connecting plate 14 is provided at one end of the probe body 3, and the probe body 3 is connected to the probe bending plate 7 through the connecting plate 14. An optical fiber 12 is connected to one side of the connecting plate 14. The optical fiber 12 and the connecting plate 14 are connected through an optical fiber seat 15. The connecting plate 14 is used for connecting the probe body 3 and the probe bending plate 7 and for connecting the probe body 3 and the optical fiber 12. The probe body 3 and the optical fiber 12 are connected through the optical fiber seat 15, which is used to fix and support the optical fiber 12, ensure the stability and position accuracy of the optical fiber 12, and avoid leakage of optical signals.

[0042] In this embodiment, the connecting plate 14 and the optical fiber seat 15 are connected via a connecting piece.

[0043] In this embodiment, a fiber optic fixing plate 9 is provided at the tail end of the probe bending plate 7, the bottom of the fiber optic fixing plate 9 is connected to one side of the slide 24, the optical fiber 12 and the cooling air pipe 11 are both arranged through the fiber optic fixing plate 9, and the fiber optic fixing plate 9 is mainly used for fixing the optical fiber 12 and providing effective support for the optical fiber 12.

[0044] In this embodiment, the slide 24 is driven by the cylinder 6, thereby driving the probe bent plate 7 on the top of the slide 24 to move, realizing the movement of the probe body 3, and a rigid guide rail is provided on the upper surface of the cylinder 6, and a slide groove matching the rigid guide rail is provided at the bottom of the slide 24, which can guide and limit the movement of the slide 24.

[0045] This embodiment is small and light in size, easy to install, convenient for measurement in a small space, does not affect the normal operation of the turbine blades, improves measurement accuracy, has strong durability, adapts to complex high-temperature and high-speed environments, and has long-term stable working performance.

[0046] In this embodiment, a first seal 19 is provided at one end of the anti-backflow seat 17, and a first outer pressure ring 18 is sleeved on the outer side of the first seal 19. The probe body 3 passes through the first seal 19 and is connected with the first seal 19. A sealing design is adopted between the anti-backflow component 4 and the mounting seat component 1, and the first seal 19 is used to seal between the probe body 3, which can ensure that the probe body 3 can freely retract and retract. The first outer pressure ring 18 is used to fix the first seal 19 and the anti-backflow seat 17.

[0047] In this embodiment, a second seal 23 is provided at one end of the probe bent plate 7, and a second outer pressure ring 8 is sleeved on the outer side of the second seal 23. The probe body 3 passes through the second seal 23 and is connected to the second seal 23. The second seal 23 prevents the refrigerant gas in the inner cavity of the probe bent plate 7 from flowing out, and plays a sealing role. The second outer pressure ring 8 is used to fix the second seal 23 and the probe bent plate 7.

[0048] In this embodiment, both the first sealing member 19 and the second sealing member 23 are polytetrafluoroethylene sealing members.

[0049] In this embodiment, the cylinder drive assembly 2 further includes a base plate 10 , the bottom of the cylinder 6 is connected to the base plate 10 , both ends of the base plate 10 are connected to the mounting seat assembly 1 , and the base plate 10 is used to provide effective support for the cylinder 6 .

[0050] In this embodiment, the cylinder drive assembly 2 is provided with a position measurement assembly 5, and the position measurement assembly 5 includes a magnetic stripe 20, a reading head 21 and a head seat 22. The reading head 21 is fixedly connected to one side of the cylinder 6 through the head seat 22. The magnetic stripe 20 is arranged on one side of the probe bend 7 and cooperates with the reading head 21. In this embodiment, the position measurement assembly 5 is a magnetic grating assembly. The magnetic stripe 20 has a width of 10 mm, a sensing area of ​​5 mm, and the length can be cut arbitrarily. The magnetic stripe 20 is provided with a zero mark every 5 mm, which is used for the absolute zero calibration of the system. After pasting, the nearest zero position can be quickly located, and the offset can be set for testing. When the object moves, the magnetic field generated by the magnetic grating will change accordingly, and then this change can be detected and converted into a corresponding electrical signal. Then, by analyzing the characteristics of these electrical signals, the position information of the object can be determined. Different reading heads 21 selections will affect the resolution, which can reach up to 1μm.

[0051] The position measurement component 5 in this embodiment can monitor the position change of the probe, provide real-time position information, and help the control system adjust and control the position of the probe. Real-time monitoring of the position of the temperature measuring probe can ensure that the probe is accurately aligned with the target measurement area, improve the accuracy and reliability of the measurement, and through the data provided by the position measurement component, the system can optimize the control strategy and improve the operating efficiency and performance of the temperature measuring probe.

[0052] In this embodiment, an imaging lens 13 is provided at one end of the probe body 3, and the imaging lens 13 and the probe body 3 are assembled by laser welding. The overall structural design enables the probe body 3 to reliably protect internal components during operation, ensuring its normal operation and improving work efficiency.

[0053] In this embodiment Fig.12 The turbine blade 25 is an aircraft engine turbine blade.

[0054] In this embodiment, air holes are provided on the side walls of the probe body 3 , and the inner cavity of the probe body 3 is connected with the inner cavity of the probe bent plate 7 through the air holes.

[0055] This embodiment also provides a method for a high-rigidity, positionable movable probe for radiation temperature measurement of turbine blades, which comprises the following steps:

[0056] Step 1: Prepare the components and make sure they are intact;

[0057] Step 2: Assemble the components to ensure that they are firmly connected and the overall structure is stable and reliable;

[0058] Step 3: Adjust the position of the device so that the probe body 3 faces the surface of the turbine blade 25 to ensure that the device can accurately collect the radiation light information on the surface of the turbine blade 25;

[0059] Step 4: Open the cylinder 6, which drives the probe body 3 to go deep into and approach the turbine blade 25 to be measured. After the probe body 3 reaches the temperature measurement station and can receive the radiation light information on the surface of the turbine blade 25, close the cylinder 6;

[0060] Step 5: The radiation light information on the surface of the turbine blade 25 is radiated to the probe body 3, and then the collected radiation light information is transmitted to the receiving end of the temperature measurement system through the optical fiber 12;

[0061] Step 6: After the collection is completed, the cylinder 6 is turned on, and the cylinder 6 drives the probe body 3 to exit the temperature measurement station and move away from the turbine blades 25, and then the cylinder 6 is closed to complete the temperature measurement.

[0062] In step 4 of this embodiment, the position measurement 5 component can determine the position information of the probe body 3 during the movement, and adjust the probe body 3 to improve the accuracy of the measurement result.

[0063] In step 4 of the present embodiment, when the probe body 3 penetrates into and approaches the turbine blade 25 to be measured, it is necessary to introduce anti-backflow high-pressure gas and refrigerant gas into the air pipe 16 and the refrigerant air pipe 11 respectively.

[0064] 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-rigidity, positionable movable probe for measuring radiation temperature of turbine blades, characterized in that: It comprises a mounting seat assembly (1), a cylinder drive assembly (2), a probe body (3) and an anti-backflow assembly (4), wherein the cylinder drive assembly (2) and the anti-backflow assembly (4) are both arranged on one side of the mounting seat assembly (1), the anti-backflow assembly (4) comprises an anti-backflow seat (17) and an air pipe (16), the upper half of the mounting seat assembly (1) is provided with a cylindrical protrusion, the anti-backflow seat (17) is matched and connected with the cylindrical protrusion of the mounting seat assembly (1), a gap is provided between the outer wall of the anti-backflow seat (17) and the inner wall of the cylindrical protrusion, the air pipe (16) is arranged at the bottom of the anti-backflow seat (17), the air pipe (16) is connected with the gap between the anti-backflow seat (17) and the cylindrical protrusion through the anti-backflow seat (17), and the cylinder drive assembly (2) comprises a slide (24), a cylinder (6), a probe bent plate (7) and a refrigeration air pipe (11), one end of the cylinder (6) is fixedly connected to one side of the bottom of the mounting seat assembly (1), the other end of the cylinder (6) is the output end, the slide (24) is slidably arranged on the top of the cylinder (6), the output end of the cylinder (6) is connected to the slide (24) and drives the movement of the slide (24), the probe bent plate (7) is arranged on the top of the slide (24), one end of the probe body (3) passes through the mounting seat assembly (1), the anti-backflow seat (17) and the probe bent plate (7) in sequence and is fixedly connected to the probe bent plate (7), the probe body (3) is slidably connected to the mounting seat assembly (1) and the anti-backflow seat (17), the refrigeration air pipe (11) is connected to one side of the probe bent plate (7), the probe body (3) is a hollow structure, and the refrigeration air pipe (11) is connected to the inner cavity of the probe body (3) through the probe bent plate (7).

2. The high-rigidity, positionable movable probe for measuring radiation temperature of turbine blades according to claim 1, characterized in that: A connecting plate (14) is provided at one end of the probe body (3), and the probe body (3) is connected to the probe bending plate (7) via the connecting plate (14).

3. The high-rigidity, positionable movable probe for measuring radiation temperature of turbine blades according to claim 2, characterized in that: An optical fiber (12) is connected to one side of the connection plate (14), and the optical fiber (12) and the connection plate (14) are connected via an optical fiber seat (15).

4. The high-rigidity, positionable movable probe for measuring radiation temperature of turbine blades according to claim 3 is characterized by: An optical fiber fixing plate (9) is arranged at the tail end of the probe bending plate (7), the bottom of the optical fiber fixing plate (9) is connected to one side of the slide table (24), and the optical fiber (12) and the cooling air pipe (11) are both arranged through the optical fiber fixing plate (9).

5. The high-rigidity, positionable movable probe for measuring radiation temperature of turbine blades according to claim 1, characterized in that: A first sealing member (19) is provided at one end of the anti-backflow seat (17), a first outer pressure ring (18) is sleeved on the outer side of the first sealing member (19), and the probe body (3) passes through the first sealing member (19) and is cooperatively connected with the first sealing member (19).

6. The high-rigidity, positionable movable probe for measuring radiation temperature of turbine blades according to claim 4, characterized in that: A second sealing member (23) is provided at one end of the probe bent plate (7), a second outer pressure ring (8) is sleeved on the outer side of the second sealing member (23), and the probe body (3) passes through the second sealing member (23) and is cooperatively connected with the second sealing member (23).

7. The high-rigidity, positionable movable probe for measuring radiation temperature of turbine blades according to claim 1, characterized in that: The cylinder drive assembly (2) further comprises a base plate (10), the bottom of the cylinder (6) is connected to the base plate (10), and both ends of the base plate (10) are connected to the mounting seat assembly (1).

8. The high-rigidity, positionable movable probe for measuring radiation temperature of turbine blades according to claim 1, characterized in that: The cylinder drive assembly (2) is provided with a position measurement assembly (5), the position measurement assembly (5) comprising a magnetic strip (20), a reading magnetic head (21) and a magnetic head seat (22), the reading magnetic head (21) being fixedly connected to one side of the cylinder (6) via the magnetic head seat (22), and the magnetic strip (20) being provided on one side of the probe bending plate (7) and cooperating with the reading magnetic head (21).

9. The high-rigidity, positionable movable probe for measuring radiation temperature of turbine blades according to claim 1, characterized in that: An imaging lens (13) is provided at one end of the probe body (3).

10. The high-rigidity, positionable movable probe for measuring radiation temperature of turbine blades according to claim 1, characterized in that: An air hole is provided on the side wall of the probe body (3), and the inner cavity of the probe body (3) is connected with the inner cavity of the probe bent plate (7) through the air hole.

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