Radiation temperature measurement probe for turbine blade of gas turbine

Abstract

The radiation temperature measurement probe comprises a probe shell, a mounting base, a light machine assembly and an infrared detector, the probe shell is mounted on the mounting base, a light through hole is formed in the side face of one end of the probe shell, and a reflecting mirror is arranged in the light through hole; the light machine assembly is installed in the probe shell and comprises a light path pipe, an electric diaphragm and an adjustable lens group, an aperture diaphragm is arranged at one end of the light path pipe, the electric diaphragm is installed in the light path pipe, and the adjustable lens group and the light path pipe form a moving pair; the infrared detector is mounted at the other end of the probe shell; radiation light of the turbine blade enters the probe shell from the light through hole, is reflected by the reflecting mirror, penetrates through the aperture diaphragm, the electric diaphragm and the adjustable mirror group, and reaches the infrared detector. Compared with the prior art, the gas turbine blade surface temperature measuring probe has the advantages that the accuracy and the long-term working stability of the gas turbine blade surface temperature measuring probe are remarkably improved by using automatic focusing, variable view field and efficient cooling technologies, and the like.

Description

Technical Field

[0001] The invention relates to the field of non-contact infrared radiation temperature measurement, and in particular to a radiation temperature measurement probe for gas turbine turbine blades. Background Art

[0002] The gas turbine blades are the main components that are washed by high-temperature combustion gases. The service life of the gas turbine is closely related to the service life of the gas turbine blades. Accurately measuring the surface temperature of the turbine rotor blades and realizing temperature monitoring and life prediction of the turbine rotor blades are of great significance to ensure the safe operation of the gas turbine.

[0003] Temperature measurement methods are generally divided into contact temperature measurement and non-contact temperature measurement. In the working environment of gas turbine turbine blades, the gas environment is relatively harsh and the turbine blades are always in a high temperature and high-speed rotation state. Since the contact temperature measurement method requires the temperature measuring element to be fixedly installed on the temperature measurement surface, it cannot be applied to gas turbines in actual operation. Radiation temperature measurement is a non-contact temperature measurement method. The temperature measuring device does not need to be in direct contact with the turbine blades, which effectively avoids damage to the blade surface caused by the installation of temperature measuring elements in the contact measurement method. At the same time, the radiation temperature measurement equipment can achieve high-precision and fast real-time temperature measurement, and can quickly capture the temperature changes of the turbine blades, which is particularly important for the accurate and fast measurement of gas turbine turbine blades.

[0004] The prior art points out that the turbine blades in gas turbines have irregular shapes and the distance between adjacent blades is narrow. The traditional non-contact temperature measurement system will be limited in its temperature measurement accuracy by the high-speed rotation of the blades. An adjustable focal length device in which the collimating lens and the probe can move along the optical axis is proposed to adapt to different positions and shapes of the turbine blade surface. However, the prior art cannot adjust the field of view.

[0005] In summary, how to design a temperature measuring probe with an adjustable field of view is a technical problem that needs to be solved. Summary of the invention

[0006] The purpose of the present invention is to provide a radiation temperature measuring probe for gas turbine blades in order to overcome the defect of the above-mentioned prior art that the field of view cannot be adjusted.

[0007] The purpose of the present invention can be achieved by the following technical solutions:

[0008] According to one aspect of the present invention, there is provided a radiation temperature measuring probe for gas turbine blades, comprising a probe housing, a mounting base, an optical-mechanical assembly and an infrared detector, wherein the probe housing is mounted on the mounting base, and the end of the probe housing close to the turbine blade is a detection end, a light-through hole is provided on the side of the detection end, and a reflector is provided in the light-through hole; the optical-mechanical assembly is mounted inside the probe housing, and comprises an optical path tube, an electric diaphragm and an adjustable mirror group, an end of the optical path tube close to the detection end is provided with an aperture diaphragm, the electric diaphragm is mounted in the optical path tube, and the adjustable mirror group forms a moving pair with the optical path tube; the infrared detector is mounted on the end of the probe housing away from the turbine blade; the radiation light of the turbine blade enters the probe housing from the light-through hole, passes through the aperture diaphragm, the electric diaphragm and the adjustable mirror group after being reflected by the reflector, and reaches the infrared detector.

[0009] As a preferred technical solution, the electric aperture comprises a piezoelectric motor, an aperture body and a plastic ring. The plastic ring is installed on the outer edge of the aperture, and the piezoelectric motor is against the plastic ring.

[0010] As a preferred technical solution, the adjustable lens group includes a front optical lens group and a rear optical lens group, and the front optical lens group, the electric aperture and the rear optical lens group are installed in the optical path tube in sequence starting from one end close to the detection end of the optical path tube; the rear optical lens group includes a lens barrel and a lens, and the lens is installed at one end of the lens barrel, and the lens barrel is connected to the optical path tube by a thread; the radiated light of the turbine blade passes through the front optical lens group, the electric aperture and the rear optical lens group in sequence.

[0011] As a preferred technical solution, the rear optical lens group further includes a first gear, a second gear and a stepping motor, the first gear is mounted on the lens barrel, the second gear is mounted on the stepping motor, and the first gear and the second gear are meshed with each other.

[0012] As a preferred technical solution, the probe also includes an optical path tube mounting seat and a sealing base, wherein one end face of the optical path tube mounting seat is connected to the end face of the probe housing, and the other end face is connected to the end face of the sealing base; one end of the optical path tube is mounted on the optical path tube mounting seat; a dichroic mirror is provided inside the end of the sealing base away from the optical path tube mounting seat, a silicon detector is provided on the side, and an infrared detector is installed on the end face; a part of the radiated light from the turbine blades passes through the dichroic mirror to reach the infrared detector, and the other part is reflected by the dichroic mirror to reach the silicon detector.

[0013] As a preferred technical solution, an air inlet is provided on the mounting base, and a cooling air inlet is provided on the probe housing; a cooling cavity is provided on the mounting base and the probe housing, and the cooling cavity and the cooling air inlet are connected; cooling air is passed through the air inlet, and the pressure of the cooling air is higher than the flue gas pressure inside the gas turbine.

[0014] As a preferred technical solution, a water cooling jacket is provided on the outside of the probe housing, a high-temperature heat pipe is provided on the outer surface of one end of the optical path tube close to the turbine blades, and a fin is provided on the other end of the high-temperature heat pipe and is located in the water cooling jacket.

[0015] As a preferred technical solution, the high-temperature heat pipe and the probe housing are sealed by a seal, and the water cooling jacket is provided with a water inlet on one side and a water outlet on the other side. Cooling water flows into the water cooling jacket from the water inlet and flows out from the water outlet.

[0016] As a preferred technical solution, the outer surface of the detection end of the probe housing is provided with a high temperature resistant coating, and the inner surface is provided with a micro-fin structure.

[0017] As a preferred technical solution, a thermocouple is provided on the outer surface of the optical path tube, and the thermocouple is led out from the end of the optical path tube away from the turbine blades to the outside of the probe housing; the reflector is made of heat-resistant alloy and is coated with a metal aluminum film on the surface.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] 1) The radiation light of the turbine blade of the present invention enters the probe housing from the light hole, passes through the aperture diaphragm and the adjustable mirror group after being reflected by the reflector, and reaches the infrared detector; automatic focusing is achieved through the adjustable mirror group; the electric diaphragm plays a role in adjusting the field of view, and can capture the bright spot phenomenon of ablation particles of different diameters attached to the turbine blade; by dynamically adjusting the size of the field of view, on the one hand, the probe has an appropriate spatial resolution, and on the other hand, it also avoids the bright spot being unclear due to the ablation particle size being too small, ensuring that the ablation particle can be accurately monitored;

[0020] 2) The lens barrel of the rear optical lens assembly of the present invention is threadedly engaged with the optical path tube, and can be moved forward or backward under the control of a stepping motor, and the probe can be focused on different temperature measurement points on the surface of the twisted turbine blade by changing the focal length;

[0021] 3) In the present invention, the light passing through the optical path tube is divided into two parts by the dichroic mirror, the radiation light reaching the infrared detector is not affected, and the light reaching the silicon detector is used to determine whether the optical path is focused;

[0022] 4) The mounting base of the present invention is provided with an air inlet, and the probe housing is provided with a cooling air inlet. The cooling air pressure is higher than the internal pressure of the gas turbine, providing pure cooling air for the optical path tube, realizing the cooling of the probe and blocking the gas from entering the front end of the probe and polluting the optical path; the high-temperature heat pipe is located on the inner wall of the optical path tube, one end of which absorbs heat on the optical path tube, and the other end extends into the water cooling jacket through the opening on the probe housing to release heat, so as to cool the optical path tube and its internal components; a fin is provided at one end of the high-temperature heat pipe located in the water cooling jacket, which can play a role in strengthening heat transfer and enhancing cooling effect;

[0023] 5) The present invention provides a high temperature resistant coating on the probe housing, so that the probe is more suitable for working in high temperature. A micro-fin structure is provided inside the probe, which can disturb the air and increase the heat exchange area, so that the high temperature area at the front end of the probe can be fully cooled; the reflector surface is coated to improve the reflectivity of the infrared band, so that the probe can collect more radiation energy and the measurement result is more accurate;

[0024] 6) The present invention detects the temperature of the optical path tube by means of a thermocouple, so as to facilitate real-time adjustment of the cooling condition; the reflector is made of a heat-resistant alloy material, suitable for high-temperature environments, and is coated with a metal aluminum film on the surface, so that the reflectivity in the infrared band is higher. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 A cross-sectional view of a radiation temperature measuring probe for a gas turbine blade according to the present invention;

[0026] Figure 2 This is a schematic diagram of the structure of the optical path tube mounting seat and the sealing base of the present invention;

[0027] Figure 3 It is a schematic diagram of the structure of the optical path tube of the present invention;

[0028] The numbers in the figure show:

[0029] 1. Light hole, 2. Reflector, 3. Detection end, 4. Cooling air inlet, 5. Probe housing, 6. Probe housing fixings, 7. Mounting base, 8. Air inlet, 9. High temperature resistant coating, 10. Micro-fin structure, 11. High temperature heat pipe evaporation end, 12. High temperature heat pipe condensation end, 13. Fins, 14. Water cooling jacket, 15. Water outlet, 16. Water inlet, 17. Seal, 18. First flange, 19. Optical path tube, 20. Thermocouple front end, 21. Thermocouple rear end, 22 , aperture diaphragm, 23, front optical lens group, 24, electric diaphragm, 25, rear optical lens group, 26, second gear, 27, dichroic mirror, 28, silicon detector, 29, infrared detector, 30, sealing base, 31, second flange, 32, lens barrel, 33, optical path tube mounting seat, 34, gas turbine casing detection port, 35, fixing part, 36, front stop block, 37, rear stop block, 38, first gear, 39, metal sheath, 40, piezoelectric motor, 41, plastic ring. DETAILED DESCRIPTION

[0030] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present invention.

[0031] like Figure 1 As shown, the present invention provides a radiation temperature measuring probe for gas turbine blades, a probe housing 5, a mounting base 7, an optical-mechanical assembly, an infrared detector 29, an optical path tube mounting base 33 and a sealing base 30. The present invention can significantly improve the accuracy and long-term working stability of the gas turbine blade surface temperature measuring probe by innovatively using automatic focusing, variable field of view and efficient cooling technology. Compared with the prior art, the present invention has obvious advantages in solving long-term reliability, automatic focusing, cooling and field of view adjustment in high temperature and high pressure environments, and can effectively solve the technical problem of accurate temperature measurement of turbine blade surfaces in high temperature gas turbine environments.

[0032] The probe housing 5 is mounted on the mounting base 7. The end of the probe housing 5 close to the turbine blade is the detection end 3. A light hole 1 is provided on the side of the detection end 3. A reflector 2 is provided inside the detection end 3. The light entering through the light hole 1 is reflected and propagated along the axial direction of the optical path tube 19. The reflector 2 is made of a heat-resistant alloy and is plated with a metal aluminum film on the surface to improve the reflectivity in the infrared band. The reflectivity of the directly polished mirror surface is 30% to 40%. After the reflector 2 is plated, the reflectivity in the infrared band can reach 90%, so that the probe can collect more radiation energy and make the temperature measurement result more accurate. The side wall of the probe housing 5 on the mounting base 7 is provided with a cooling air inlet 4. The high-pressure cooling air entering through the cooling air inlet 4 flows through the shell of the optical path tube 19, the surface of the high-temperature heat pipe, the micro-fin structure 10 and the surface of the reflector 2 in turn, and then flows into the gas turbine through the light hole 1. The high-pressure cooling air can achieve efficient cooling of the inside of the radiation temperature measurement probe and the optical path tube 19, providing safety protection for the radiation temperature measurement probe to work normally in the gas turbine for a long time.

[0033] The detection end 3 of the probe housing 5 needs to extend into the gas turbine casing, and the outer surface is provided with a high temperature resistant coating 9 to play a role in heat protection; the inner surface is provided with a micro-fin structure 10. The high temperature resistant coating 9 is formed by applying a high temperature resistant coating on the outer surface of the probe housing 5. The optional high temperature resistant coating is a yttria-stabilized zirconium oxide coating.

[0034] A water cooling jacket 14 is provided on the outside of the probe housing 5. A water inlet 16 is provided on the side of the water cooling jacket 14 close to the ground, and a water outlet 15 is provided on the side away from the ground. The high-temperature heat pipe condensation end 12 passes through the probe housing 5 and is located in the water cooling jacket 14. The high-temperature heat pipe and the probe housing 5 are sealed by a sealing member 17. Cooling water flows into the water cooling jacket 14 from the water inlet 16, and after heat exchange with the high-temperature heat pipe condensation end 12 in the water cooling jacket 14, it flows out from the water outlet 15 to cool the high-temperature heat pipe.

[0035] The mounting base 7 is mounted on the gas turbine casing detection port 34 through a flange using a fixing part 35, and is fixed to the probe housing fixing part 6 using a gasket and a second flange 31. An air inlet 8 is provided on the surface of the mounting base 7, and a cooling cavity is provided between the interior and the probe housing 5. High-pressure cooling air pressurized by the compressor enters the cooling cavity through the air inlet 8, and then enters the probe housing 5 along the cooling air inlet 4. The pressure of the cooling air is higher than the internal flue gas pressure of the gas turbine, which can prevent the flue gas from entering the front end of the probe and polluting the optical path.

[0036] like Figure 2 As shown, the optical-mechanical assembly is installed inside the probe housing 5, including an optical path tube 19, an electric diaphragm 24 and an adjustable lens group. An aperture diaphragm 22 is provided at one end of the optical path tube 19 close to the detection end 3.

[0037] A high-temperature heat pipe is welded to the outer surface of one end of the optical path tube 19 close to the turbine blades, and the evaporation end 11 of the high-temperature heat pipe is closely attached to the outer wall of the front end of the optical path tube 19. Fins 13 are provided on the condensation end and are located in the water cooling jacket 14. The fins 13 can enhance heat transfer and cooling effect on the condensation end of the high-temperature heat pipe. A thermocouple is also welded to the outer surface of the optical path tube 19. The front end 20 of the thermocouple is attached to the outer surface of the optical path tube, and the rear end 21 of the thermocouple is led out through the opening on the sealing base 30. The thermocouple is used to monitor the temperature of the optical path tube 19 in real time. The output of the thermocouple can be used as a control signal for the flow of cooling air and cooling water to ensure that the optical path tube and the adjustable mirror group can always be maintained within the operating temperature range.

[0038] The electric diaphragm 24 is installed in the optical path tube 19, and includes a piezoelectric motor 40, an diaphragm body and a plastic ring 41. The plastic ring 41 is installed on the outer edge of the diaphragm, and the piezoelectric motor 40 is against the plastic ring 41. By supplying power to the piezoelectric motor 40 in the electric diaphragm 24, the top end of the piezoelectric motor 40 is pressed against the plastic ring 41 on the outer edge of the electric diaphragm 24 under the control of the piezoelectric chip, and the size of the diaphragm aperture is changed, so as to achieve the purpose of adjusting the field of view size of the temperature measurement area. On the one hand, the probe has an appropriate spatial resolution, and on the other hand, it avoids the bright spot that is not obvious due to the small size of the ablation particles, and ensures that the ablation particles can be accurately monitored. By identifying the bright spot, an alarm can be issued for abnormal ablation of the combustion chamber components.

[0039] The adjustable lens group includes a front optical lens group 23 and a rear optical lens group 25. The front optical lens group 23, the electric aperture 24 and the rear optical lens group 25 are sequentially installed in the optical path tube 19 from one end close to the detection end 3 of the optical path tube 19; the rear optical lens group 25 includes a lens barrel 32, a lens, a first gear 38, a second gear 26 and a stepping motor. The lens is installed at one end of the lens barrel 32 close to the detection end 3 through a retaining ring and high-temperature resistant glue to ensure that the glue will not fail; the lens barrel 32 is connected to the optical path tube 19 through threads to form a moving pair, and the first gear 38 is installed on the lens barrel 32. A second gear 26 is installed on the stepper motor, and the first gear 38 and the second gear 26 are meshed with each other. The stepper motor drives the gears to rotate, and then drives the movement of the lens barrel 32 along the axis of the optical path tube 19 to realize the forward and backward movement of the rear optical lens group 25. The purpose is to avoid the defocusing problem caused by the change in the shape of the twisted turbine blades by changing the focal length, so that the energy radiated from the temperature measurement point can be accurately focused on the infrared detector 29, reduce the temperature measurement error, and improve the temperature measurement accuracy; front stop blocks 36 and rear stop blocks 37 are also provided at both ends of the lens barrel 32 to control the movement range of the lens barrel 32.

[0040] like Figure 3 As shown, one end surface of the optical path tube mounting seat 33 is connected to the end surface of the probe housing 5 , and the rear end of the optical path tube 19 (the other end opposite to the detection end 3 ) is mounted on the optical path tube mounting seat 33 .

[0041] The end face of the sealing base 30 is connected to the other end face of the optical path tube mounting seat 33. A dichroic mirror 27 is arranged inside the sealing base 30, and the dichroic mirror is fixed by a metal sheath 39. A silicon detector 28 is arranged on the side of the sealing base 30, and an infrared detector 29 is installed on the end face. A part of the radiation light of the turbine blade passes through the dichroic mirror 27 and is divided into two parts. The light with a wavelength greater than 1 micron reaches the infrared detector 29, and the light with a wavelength less than 1 micron is reflected and reaches the silicon detector 28. The silicon detector 28 generates different photoelectric signals according to the strength of the received radiation signal. The photoelectric signal generated by the silicon detector 28 can be used to determine whether the optical path is focused. The stepper motor is installed on the sealing base 30.

[0042] The probe housing 5, the optical path tube mounting seat 33 and the sealing base 30 are sealed with a gasket and connected through the first flange 18 to prevent the leakage of high-pressure cooling air, thereby ensuring the safety of the probe in use.

[0043] After the present invention is fixed on the gas turbine casing, the light hole 1 is aligned with the target blade to be measured, and the radiation light emitted from the surface of the turbine blade of the gas turbine is reflected to the optical path tube 19 by the reflector 2 at the front end of the probe. The aperture diaphragm 22 at the front end of the optical path tube 19 limits the angle range of the incident radiation light; the radiation light passes through the aperture diaphragm 22 to reach the front optical lens group 23, and the front optical lens group 23 will perform preliminary focusing on the light; the radiation light passes through the rear optical lens group 25, and the rear optical lens group 25 can adjust the front and rear positions as the distance from the temperature measurement point changes, to ensure that the radiation light can be focused on the surface of the infrared detector 29; the electric diaphragm 24 can adjust the field of view.

[0044] The advantages of the present invention are as follows:

[0045] 1. Automatic focus adjustment: The movement of the rear optical lens group 25 is controlled by a stepper motor to achieve adjustable focus of the probe. A dichroic mirror 27 is used after the rear optical lens group 25. The infrared signal used for temperature measurement can pass through the dichroic mirror 27 with high transmittance, while the visible light part is reflected by the dichroic mirror 27 to the silicon detector 28. The movement of the rear optical lens group 25 is controlled by a stepper motor, and the output signal of the silicon detector 28 is detected. When the output signal of the silicon detector 28 is the largest, the lens group in the probe is focused. This method can automatically adjust the focal length to ensure accurate measurement, significantly improve the adaptability of the probe under complex working conditions, and avoid the problem that traditional temperature measuring probes cannot be used for effective measurement under different conditions due to fixed focal length.

[0046] 2. The size of the field of view is controllable: The size of the field of view of traditional probes is fixed and cannot be changed. If the field of view is too small, although the spatial resolution is high, it may not be possible to measure the "bright spots" caused by the ablation particles in the combustion chamber deposited on the surface of the turbine blades. If the field of view is too large, the area occupied by the ablation particles in the field of view is limited, and it may also be impossible to measure the "bright spots" caused by the ablation particles. The present invention uses an electric aperture 24 to adjust the size of the field of view at the measuring point, thereby avoiding the inability to accurately capture the "bright spots" caused by the ablation particles in the combustion chamber deposited on the surface of the turbine blade due to the probe field of view being too small or too large. The size of the field of view can be dynamically changed during the measurement process to adapt to ablation particles of different sizes, and to capture the "bright spots" on the blade surface, which can improve the measurement accuracy of the probe in complex working environments.

[0047] 3. Improved cooling effect: The present invention increases the turbulence of the cooling air by adding a micro-fin structure 10 at the front end of the probe. The turbulent flow of the cooling air in the channel strengthens the heat exchange between the cooling air and the front end of the probe, thereby reducing the temperature of the front end of the probe. In order to further reduce the temperature of the optical tube 19 and the lens barrel 32 and protect the optical elements inside the optical tube 19 and the lens barrel 32 to work normally in a harsh environment with high temperature, high-temperature heat pipes and water cooling are used to achieve efficient cooling effects. The condensation end 12 of the high-temperature heat pipe is located outside the gas turbine, and all the water-cooling components are outside the gas turbine. Even if the water-cooling components leak, water will not enter the gas turbine casing, and will not affect the normal operation of the gas turbine. A thermocouple is attached to the wall of the optical tube 19, which can monitor the temperature of the optical tube 19 in real time, and adjust the water flow according to the temperature measured by the thermocouple, thereby achieving precise temperature control. The probe can maintain a low temperature in a high-temperature environment, avoiding the influence of overheating on the operation of the probe and the measurement results.

[0048] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can easily think of various equivalent modifications or replacements within the technical scope disclosed by the present invention, and these modifications or replacements should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention shall be based on the protection scope of the claims.

Claims

1. A radiation temperature measuring probe for a gas turbine blade, characterized in that: The invention comprises a probe housing (5), a mounting base (7), an optical-mechanical assembly and an infrared detector (29), wherein the probe housing (5) is mounted on the mounting base (7), an end of the probe housing (5) close to the turbine blade is a detection end (3), a light-through hole (1) is provided on the side of the detection end (3), and a reflector (2) is provided in the light-through hole (1); the optical-mechanical assembly is mounted inside the probe housing (5), and comprises an optical path tube (19), an electric aperture (24) and an adjustable lens group, wherein the optical path tube (19 ) is provided with an aperture diaphragm (22) at one end close to the detection end (3), the electric diaphragm (24) is installed in the optical path tube (19), and the adjustable mirror group and the optical path tube (19) form a moving pair; the infrared detector (29) is installed at the end of the probe housing (5) away from the turbine blades; the radiation light of the turbine blades enters the probe housing (5) from the light hole (1), passes through the aperture diaphragm (22), the electric diaphragm (24) and the adjustable mirror group after being reflected by the reflector (2), and reaches the infrared detector (29).

2. A radiation temperature measuring probe for gas turbine blades according to claim 1, characterized in that: The electric aperture (24) comprises a piezoelectric motor (40), an aperture body and a plastic ring (41); the plastic ring (41) is installed on the outer edge of the aperture, and the piezoelectric motor (40) is against the plastic ring (41).

3. The radiation temperature measuring probe for gas turbine blades according to claim 1, characterized in that: The adjustable lens group comprises a front optical lens group (23) and a rear optical lens group (25); the front optical lens group (23), the electric aperture (24) and the rear optical lens group (25) are sequentially installed in the optical path tube (19) starting from one end close to the detection end (3) of the optical path tube (19); the rear optical lens group (25) comprises a lens barrel (32) and a lens, the lens is installed at one end of the lens barrel (32), and the lens barrel (32) is connected to the optical path tube (19) by means of threads; the radiation light of the turbine blade passes through the front optical lens group (23), the electric aperture (24) and the rear optical lens group (25) in sequence.

4. The radiation temperature measuring probe for gas turbine blades according to claim 3, characterized in that: The rear optical lens group (25) further comprises a first gear (38), a second gear (26) and a stepping motor; the first gear (38) is mounted on the lens barrel (32), the second gear (26) is mounted on the stepping motor, and the first gear (38) and the second gear (26) are meshed with each other.

5. The radiation temperature measuring probe for gas turbine blades according to claim 1, characterized in that: The probe also includes an optical path tube mounting seat (33) and a sealing base (30); one end face of the optical path tube mounting seat (33) is connected to the end face of the probe housing (5), and the other end face is connected to the end face of the sealing base (30); one end of the optical path tube (19) is mounted on the optical path tube mounting seat (33); a dichroic mirror (27) is provided inside the end of the sealing base (30) away from the optical path tube mounting seat (33), a silicon detector (28) is provided on the side, and an infrared detector (29) is installed on the end face; a part of the radiation light of the turbine blade passes through the dichroic mirror (27) to reach the infrared detector (29), and the other part is reflected by the dichroic mirror (27) to reach the silicon detector (28).

6. The radiation temperature measuring probe for gas turbine blades according to claim 1, characterized in that: The mounting base (7) is provided with an air inlet (8), and the probe housing (5) is provided with a cooling air inlet (4); the mounting base (7) and the probe housing (5) are provided with a cooling cavity, and the cooling cavity is connected to the cooling air inlet (4); the air inlet (8) passes cooling air, and the pressure of the cooling air is higher than the internal flue gas pressure of the gas turbine.

7. The radiation temperature measuring probe for gas turbine blades according to claim 1, characterized in that: A water cooling jacket (14) is provided on the outside of the probe housing (5); a high-temperature heat pipe is provided on the outer surface of one end of the optical path tube (19) close to the turbine blades; a fin (13) is provided on the other end of the high-temperature heat pipe and is located in the water cooling jacket (14).

8. The radiation temperature measuring probe for gas turbine blades according to claim 7, characterized in that: The high-temperature heat pipe and the probe housing (5) are sealed by a sealing member (17); a water inlet (16) is provided on one side of the water cooling jacket (14) and a water outlet (15) is provided on the other side; cooling water flows into the water cooling jacket (14) from the water inlet (16) and flows out from the water outlet (15).

9. The radiation temperature measuring probe for gas turbine blades according to claim 1, characterized in that: The outer surface of the detection end (3) of the probe housing (5) is provided with a high temperature resistant coating (9), and the inner surface is provided with a micro-fin structure (10).

10. The radiation temperature measuring probe for gas turbine blades according to claim 1, characterized in that: A thermocouple is provided on the outer surface of the optical path tube (19), and the thermocouple is led out from the end of the optical path tube (19) away from the turbine blades to the outside of the probe housing (5); the reflector (2) is made of a heat-resistant alloy and is coated with a metal aluminum film on the surface.

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