Gas turbine disc cavity temperature measuring device, gas turbine and temperature measuring method

Abstract

The invention discloses a gas turbine disc cavity temperature measuring device, a gas turbine and a temperature measuring method.The gas turbine disc cavity temperature measuring device comprises a turbine stationary blade, a thermocouple assembly and a guide component, a temperature measuring flow channel is formed in a sealing ring of the turbine stationary blade and used for communicating an upstream disc cavity and a downstream disc cavity corresponding to the turbine stationary blade, and the temperature measuring flow channel is communicated with the upstream disc cavity and the downstream disc cavity; the temperature measuring flow channel is communicated with an inner cavity of the turbine stationary blade through a first hole channel; the thermocouple assembly is provided with a rod body and a sensing part located at one end of the rod body, and the rod body penetrates through an outer cylinder and an inner cylinder of the gas turbine, an inner cavity of the turbine stationary blade and the first hole channel so that the sensing part can be arranged in the temperature measurement flow channel and used for detecting the temperature of airflow flowing from the upstream disc cavity to the downstream disc cavity in the temperature measurement flow channel; and the guide part is arranged on the inner cylinder and / or the turbine stationary blade so as to guide the thermocouple assembly. According to the invention, the thermocouple assembly can be replaced without disassembling the machine, so that the replacement efficiency of the thermocouple is improved, and the operation difficulty and the maintenance cost are reduced.

Description

Technical Field

[0001] The present invention belongs to the technical field of gas turbines, and particularly relates to a gas turbine disk cavity temperature measurement device, a gas turbine, and a temperature measurement method. Background Art

[0002] In a gas turbine, after the high-temperature gas flow in the main flow path passes through the stationary and rotating blades, high and low pressure regions will be alternately formed circumferentially in the middle region between the stationary and rotating blades, resulting in non-uniform circumferential pressure. In the high-pressure region, the main flow pressure is greater than the disk cavity pressure, causing the phenomenon of high-temperature gas invading the disk cavity. In addition, due to the rotating pump effect of the turbine disk, when the seal flow rate is less than the pumped flow rate, high-temperature gas invasion will also occur. Gas invasion easily causes overheating failure of the turbine disk, thus threatening the operating safety of the gas turbine. Therefore, during the operation of the gas turbine, it is necessary to measure the temperature of the gas flow in the disk cavity to prevent overheating failure of the turbine disk caused by excessive temperature of the gas invading the disk cavity.

[0003] In the related art, the temperature of the gas turbine disk cavity is measured by laying armored thermocouples along the path, and the thermocouples need to be fixed by pressing and welding during the wiring path. During long-term operation, when the thermocouple is damaged, it is necessary to disassemble and replace the thermocouple locally for the gas turbine, and the replacement period is long. Summary of the Invention

[0004] The present invention aims to solve at least one of the technical problems in the related art to some extent.

[0005] To this end, an embodiment of the present invention provides a gas turbine disk cavity temperature measurement device capable of improving the replacement efficiency of the thermocouple.

[0006] An embodiment of the present invention further provides a gas turbine.

[0007] An embodiment of the present invention further provides a gas turbine disk cavity temperature measurement method.

[0008] The gas turbine disk cavity temperature measurement device according to the embodiment of the present invention includes:

[0009] A stationary blade of the turbine, a temperature measurement flow path is provided in the seal ring of the stationary blade of the turbine for communicating the upstream disk cavity and the downstream disk cavity corresponding to the stationary blade of the turbine, and the temperature measurement flow path is communicated with the inner cavity of the stationary blade of the turbine through a first hole;

[0010] A thermocouple assembly, the thermocouple assembly has a rod body and a sensing part located at one end of the rod body, the rod body passes through the outer cylinder, the inner cylinder of the gas turbine, and the inner cavity of the stationary blade of the turbine and the first hole, so that the sensing part is placed in the temperature measurement flow path for detecting the temperature of the gas flow flowing from the upstream disk cavity to the downstream disk cavity in the temperature measurement flow path;

[0011] A guiding component, which is arranged on the inner cylinder and / or the stationary turbine blade to guide the thermocouple assembly.

[0012] The gas turbine disk cavity temperature measuring device according to the embodiment of the present invention can replace the thermocouple assembly without disassembling the machine, improving the replacement efficiency of the thermocouple, reducing the operation difficulty and the maintenance cost.

[0013] In some embodiments, a connecting portion is provided at one end of the rod body away from the sensing portion, and the connecting portion is detachably connected to the outer cylinder of the gas turbine.

[0014] In some embodiments, the connecting portion is a flange, and the flange is connected to the outer cylinder through a connecting member.

[0015] In some embodiments, a sealing member is further included, and the sealing member is arranged between the rod body and the first channel to prevent the gas in the inner cavity of the stationary turbine blade from flowing into the temperature measuring channel;

[0016] And / or, the temperature measuring channel includes a first section, a second section and a third section arranged in sequence along the gas flow direction. The extending direction of the second section is parallel to the axial direction of the rod body, the sensing portion is arranged in the second section, and the extending directions of the first section and the third section both have a preset included angle with the extending direction of the second section, and there is a certain height difference at the connection positions of the first section and the third section with the second section, so that the temperature measuring channel is a zigzag channel.

[0017] In some embodiments, the guiding component includes a first guiding tube and a second guiding tube. Both the first guiding tube and the second guiding tube have a guiding section in the shape of a flared opening. The first guiding tube is connected to the inner cylinder and is used to guide the thermocouple assembly into the inner cavity of the stationary turbine blade. The second guiding tube is connected to the sealing ring of the stationary turbine blade and is used to guide the thermocouple assembly into the first channel.

[0018] In some embodiments, a bracket is further included. The bracket is connected to the inner cylinder, and the first guiding tube is fixed on the first bracket.

[0019] The gas turbine according to the embodiment of the present invention includes the gas turbine disk cavity temperature measuring device according to any one of the above embodiments.

[0020] The gas turbine disk cavity temperature measuring method according to the embodiment of the present invention includes:

[0021] A first channel and a temperature-measuring channel are formed on the sealing ring of the stationary stator vane. The temperature-measuring channel is used to connect the upstream disk cavity and the downstream disk cavity corresponding to the stationary stator vane, and the temperature-measuring channel is connected to the inner cavity of the stationary stator vane through the first channel;

[0022] A hole coaxial with and communicating with the first channel is formed on the outer cylinder and the inner cylinder of the gas turbine to form a second channel;

[0023] A thermocouple assembly is inserted into the first channel and the second channel, and the sensing part of the thermocouple assembly is located in the temperature-measuring channel;

[0024] The thermocouple assembly is fixedly connected to the outer cylinder of the gas turbine;

[0025] During the normal operation of the gas turbine, the thermocouple assembly measures the temperature of the gas flowing from the upstream disk cavity to the downstream disk cavity.

[0026] In some embodiments, the temperature-measuring channel includes a first section, a second section, and a third section arranged in sequence along the gas flow direction. The extending direction of the second section is parallel to the axis direction of the rod body, the sensing part is arranged in the second section, and the extending directions of the first section and the third section both have a preset included angle with the extending direction of the second section, so that the temperature-measuring channel is a zigzag channel;

[0027] And / or, the thermocouple assembly has a rod body, the sensing part is located at one end of the rod body, and the other end of the rod body has a connecting part for detachably connecting to the outer cylinder of the gas turbine;

[0028] And / or, guiding components are arranged in the inner cylinder and / or the stationary stator vane of the gas turbine to guide the thermocouple assembly to move directionally.

[0029] In some embodiments, it further includes a thermocouple replacement process, which specifically includes:

[0030] Stop the operation of the gas turbine;

[0031] Detach the thermocouple assembly from the outer cylinder of the gas turbine and take out the damaged thermocouple assembly;

[0032] Replace with a new thermocouple assembly, insert the thermocouple assembly into the first channel and the second channel, and make the sensing part of the thermocouple assembly located in the temperature-measuring channel;

[0033] Fix the new thermocouple assembly to the outer cylinder of the gas turbine;

[0034] Start the gas turbine. Description of the Drawings

[0035] Figure 1 It is a schematic diagram of the gas turbine disk cavity temperature measurement device according to an embodiment of the present invention.

[0036] Figure 2 It is a schematic diagram of the temperature measurement flow channel according to an embodiment of the present invention.

[0037] Reference numerals:

[0038] 1, stationary vane; 11, sealing ring; 12, temperature measurement flow channel; 121, first section; 122, second section; 123, third section; 13, first channel;

[0039] 2, thermocouple assembly; 21, rod body; 22, connecting part; 23, sensing part; 24, seal;

[0040] 31, first guide tube; 32, second guide tube; 33, bracket;

[0041] 4, outer cylinder; 41, second channel;

[0042] 5, inner cylinder;

[0043] 6, upstream turbine disk;

[0044] 7, downstream turbine disk;

[0045] 81, upstream disk cavity; 82, downstream disk cavity;

[0046] 91, upstream sealing piece; 92, downstream sealing piece. Detailed implementation manners

[0047] The embodiments of the present invention will be described in detail below. The examples of the embodiments are shown in the drawings. The embodiments described below with reference to the drawings are exemplary and are intended to explain the present invention, and should not be construed as limiting the present invention.

[0048] As Figure 1 shown, the gas turbine disk cavity temperature measurement device according to an embodiment of the present invention includes a stationary vane 1, a thermocouple assembly 2 and a guiding component.

[0049] A temperature measurement flow channel 12 is formed in the sealing ring 11 of the stationary vane 1. The temperature measurement flow channel 12 is used to communicate the upstream disk cavity 81 and the downstream disk cavity 82 corresponding to the stationary vane 1. The temperature measurement flow channel 12 is communicated with the inner cavity of the stationary vane 1 through a first channel 13.

[0050] The thermocouple assembly 2 has a rod body 21 and a sensing part 23 located at one end of the rod body 21. The rod body 21 passes through the outer cylinder 4, the inner cylinder 5 of the gas turbine, and the inner cavity and the first channel 13 of the stationary blade 1, so that the sensing part 23 is placed in the temperature measuring channel 12. The sensing part 23 of the thermocouple assembly 2 is used to detect in real time the temperature of the air flow flowing from the upstream disk cavity 81 to the downstream disk cavity 82 in the temperature measuring channel 12. Wherein, when there is no channel coaxial with the first channel 13 on the outer cylinder 4 and the inner cylinder 5, through holes can be opened at the corresponding positions on the outer cylinder 4 and the inner cylinder 5 to ensure that the rod body 21 can pass through the outer cylinder 4 and the inner cylinder 5 and enter the inner cavity of the stationary blade 1, and then the sensing part 23 enters the temperature measuring channel 12 through the first channel 13. Wherein, the sensing part 23 is a thermocouple arranged at the end of the rod body 21, and the lead of the thermocouple can be led out of the outer cylinder 4 through the inside of the rod body 21. The guiding component is arranged on the inner cylinder 5 and / or the stationary blade 1 to guide the thermocouple assembly 2. The guiding component is used to guide the thermocouple assembly 2 to move directionally, avoiding that the sensing part 23 cannot be aligned with the first channel 13, resulting in the sensing part 23 not being able to enter the temperature measuring channel 12.

[0051] The gas turbine disk cavity temperature measuring device according to the embodiment of the present invention can replace the thermocouple assembly 2 without disassembling the machine. It only needs to draw out the rod body 21 and replace it with a new thermocouple assembly 2, which improves the replacement efficiency of the thermocouple, reduces the operation difficulty and the maintenance cost.

[0052] Compared with the related technology in which some components of the gas turbine are removed and then the thermocouple is replaced and the lead is armored and laid, the solution of this embodiment can greatly improve the operation efficiency, reduce the maintenance cost and the downtime.

[0053] The following further describes some other embodiments of the present invention with reference to the drawings.

[0054] As Figure 1 and Figure 2 shown, a gas turbine disk cavity temperature measuring device includes a stationary blade 1, a thermocouple assembly 2 and a guiding component.

[0055] A temperature measuring channel 12 is opened in the sealing ring 11 of the stationary blade 1. The temperature measuring channel 12 is used to connect the upstream disk cavity 81 and the downstream disk cavity 82 corresponding to the stationary blade 1. The temperature measuring channel 12 is communicated with the inner cavity of the stationary blade 1 through a first channel 13. There is an upstream turbine disk 6 upstream of the turbine blade, and a downstream turbine disk 7 downstream of the turbine blade. The air flow in the disk cavity of the upstream turbine disk 6 can flow through the temperature measuring channel 12 into the disk cavity of the downstream turbine disk 7. The thermocouple assembly 2 measures the temperature in the gas turbine disk cavity in real time by detecting the temperature of the air flow in the temperature measuring channel 12.

[0056] The temperature-measuring flow channel 12 includes a first section 121, a second section 122, and a third section 123 arranged in sequence along the gas flow direction. The extending direction of the second section 122 is parallel to the axial direction of the rod body 21. The sensing part 23 is arranged in the second section 122. The extending directions of the first section 121 and the third section 123 both have a preset included angle with the extending direction of the second section 122, and there is a certain height difference at the connection positions of the first section 121 and the third section 123 with the second section 122, so that the temperature-measuring flow channel 12 is a zigzag flow channel. In other words, the end of the first section 121 close to the second section 122 and the end of the third section 123 close to the second section 122 are arranged in a staggered manner, and there is a certain height difference between them. The section between the height differences is the extending length of the second section 122.

[0057] For example, if the extending directions of the first section 121 and the third section 123 are perpendicular to the axial direction of the rod body 21, and the extending direction of the second section 122 is parallel to the axial direction of the rod body 21, then the temperature-measuring flow channel 12 forms an approximately zigzag temperature-measuring flow channel 12. When the gas flow passes through the second section 122, it is more convenient for the thermocouple assembly 2 to measure the temperature in real time.

[0058] The thermocouple assembly 2 has a rod body 21 and a sensing part 23 located at one end of the rod body 21. A connecting part 22 is arranged at the end of the rod body 21 far from the sensing part 23. The connecting part 22 is detachably connected to the outer cylinder 4 of the gas turbine. For example, the connecting part 22 is a flange, and the flange is connected to the outer cylinder 4 through a connecting piece.

[0059] A seal 24 is arranged between the rod body 21 and the first hole 13. The seal 24 can be structures such as an O-ring, a gasket, a ball head seal, or a tapered head seal, etc., for preventing the gas in the inner cavity of the stationary blade 1 from flowing into the temperature-measuring channel 12.

[0060] Specifically, the first hole 13 can be set as a stepped hole. The seal 24 is selected as a gasket. A shoulder is arranged on the rod body 21. The shoulder of the rod body 21 abuts against the shoulder of the stepped hole. The gasket is arranged between the two shoulders to improve the structural stability.

[0061] The rod body 21 passes through the outer cylinder 4, the inner cylinder 5 of the gas turbine, as well as the inner cavity and the first duct 13 of the stationary blade 1, so that the sensing part 23 is placed in the temperature measuring duct 12. The sensing part 23 of the thermocouple assembly 2 is used to detect in real time the temperature of the air flow flowing from the upstream disc cavity 81 to the downstream disc cavity 82 in the temperature measuring duct 12. Wherein, when there is no duct coaxially arranged with the first duct 13 on the outer cylinder 4 and the inner cylinder 5, through holes can be opened at corresponding positions on the outer cylinder 4 and the inner cylinder 5 to ensure that the rod body 21 can pass through the outer cylinder 4 and the inner cylinder 5 and enter the inner cavity of the stationary blade 1, and then the sensing part 23 enters the temperature measuring duct 12 through the first duct 13. Wherein, the sensing part 23 is a thermocouple arranged at the end of the rod body 21, and the lead wire of the thermocouple can be led out of the outer cylinder 4 through the inside of the rod body 21.

[0062] An upstream sealing piece 91 is arranged upstream of the through holes on the inner cylinder 5 and the outer cylinder 4, and a downstream sealing piece 92 is arranged downstream, which can seal the corresponding section.

[0063] The guiding component is arranged on the inner cylinder 5 and / or the stationary blade 1 to guide the thermocouple assembly 2. Specifically, the guiding component includes a first guiding tube 31 and a second guiding tube 32. The first guiding tube 31, the second guiding tube 32 and the first duct 13 are coaxially arranged. Both the first guiding tube 31 and the second guiding tube 32 have guiding sections in the shape of a flared opening. A bracket 33 is arranged on the inner cylinder 5, and the first guiding tube 31 is fixed on the first bracket 33. The thermocouple assembly 2 can be guided into the inner cavity of the stationary blade 1 through the first guiding tube 31. The second guiding tube 32 is connected to the sealing ring 11 of the stationary blade 1. The second guiding tube 32 is used to guide the thermocouple assembly 2 into the first duct 13, and the second guiding tube 32 can be welded and fixed to the sealing ring 11 of the stationary blade 1.

[0064] The guiding component in this embodiment is used to guide the thermocouple assembly to move in a fixed direction, avoiding the situation that the sensing part cannot be aligned with the first duct, resulting in the sensing part not being able to enter the temperature measuring duct.

[0065] The gas turbine according to an embodiment of the present invention includes the gas turbine disc cavity temperature measuring device according to any one of the above embodiments.

[0066] The gas turbine disc cavity temperature measuring method according to an embodiment of the present invention includes:

[0067] S101. Open a first duct and a temperature measuring duct on the sealing ring of the stationary blade. The temperature measuring duct is used to communicate the upstream disc cavity corresponding to the stationary blade and the downstream disc cavity, and the temperature measuring duct is connected to the inner cavity of the stationary blade through the first duct. Wherein, the structure and arrangement form of the temperature measuring duct and the first duct are the same as those of the temperature measuring duct and the first duct in the gas turbine disc cavity temperature measuring device in the above embodiment.

[0068] The temperature measurement flow path in this embodiment includes a first section, a second section, and a third section arranged in sequence along the gas flow direction. The extension direction of the second section is parallel to the axis direction of the rod body, and the sensing part is arranged in the second section. The extension directions of the first section and the third section both have a preset included angle with the extension direction of the second section, so that the temperature measurement flow path is a zigzag flow path.

[0069] S102. Construct holes on the outer cylinder and inner cylinder of the gas turbine that are coaxial and connected to the first hole to form a second hole. When there is no channel on the outer cylinder and inner cylinder that is connected to the inner cavity of the stationary blade and the first hole, a through hole is opened on the outer cylinder and / or inner cylinder, so that the through holes on the outer cylinder and inner cylinder form a second hole, to ensure that the thermocouple assembly can be directly inserted into the temperature measurement flow path from the outside of the outer cylinder.

[0070] Furthermore, a guiding component is arranged in the inner cylinder and / or the stationary blade of the gas turbine to guide the directional movement of the thermocouple assembly.

[0071] S103. Insert the thermocouple assembly into the first hole and the second hole, and make the sensing part of the thermocouple assembly be inside the temperature measurement flow path. In this embodiment, the sensing part is used to measure the temperature of the gas flow flowing from the upstream disk cavity to the downstream disk cavity in the temperature measurement flow path in real time, and is led out through the lead arranged in the rod body and transmitted to the host computer.

[0072] The thermocouple assembly in this embodiment has a rod body, the sensing part is located at one end of the rod body, and the other end of the rod body has a flange, and the flange is used for detachable connection with the outer cylinder of the gas turbine.

[0073] S104. Fix the thermocouple assembly to the outer cylinder of the gas turbine. The outer end of the rod body in the thermocouple assembly is fixedly connected to the outer cylinder, and can seal the hole on the outer cylinder. For example, a sealing ring is arranged between the rod body and the outer cylinder.

[0074] S105. During the normal operation of the gas turbine, the thermocouple assembly measures the temperature of the gas flow flowing from the upstream disk cavity to the downstream disk cavity.

[0075] In this embodiment, by arranging the gas turbine disk cavity temperature measurement device as described in the above embodiment on the gas turbine, the replacement of the thermocouple assembly can be realized without disassembling the machine, and the replacement cycle is shortened.

[0076] In some embodiments, the gas turbine disk cavity temperature measurement method further includes a thermocouple replacement process, which specifically includes:

[0077] S201. Stop the operation of the gas turbine.

[0078] S202. Remove the thermocouple assembly from the outer cylinder of the gas turbine and take out the damaged thermocouple assembly.

[0079] S203. Replace the thermocouple assembly with a new one, insert the thermocouple assembly into the first and second channels, and place the sensing part of the thermocouple assembly in the temperature measurement flow channel.

[0080] S204. Fix the new thermocouple assembly to the outer cylinder of the gas turbine.

[0081] S205. Start the gas turbine.

[0082] In this embodiment, there is no need to arrange the thermocouple in the way of armored leads in the related art, and there is no need to fix it by welding with a pressing piece. This embodiment can replace the thermocouple without disassembling the machine, reducing the assembly and replacement difficulty of the thermocouple and improving the disassembly, installation and replacement efficiency of the thermocouple.

[0083] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0084] In addition, the terms "first" and "second" are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise specifically defined.

[0085] In the present invention, unless otherwise clearly specified and limited, the terms "install", "connect", "connection", "fix" and other terms should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection, an electrical connection or communication with each other; it can be directly connected, or indirectly connected through an intermediate medium, and can be the internal communication of two elements or the interaction relationship between two elements, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0086] In the present invention, the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms are not necessarily directed to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0087] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention.

Claims

1. A gas turbine disc cavity temperature measuring device, characterized in that: include: A turbine stator blade, wherein a temperature measuring channel is provided in a sealing ring of the turbine stator blade for connecting an upstream disc cavity and a downstream disc cavity corresponding to the turbine stator blade, and the temperature measuring channel is connected to an inner cavity of the turbine stator blade through a first hole; A thermocouple assembly, the thermocouple assembly comprising a rod body and a sensing portion located at one end of the rod body, the rod body passing through the outer cylinder, the inner cylinder, the inner cavity of the turbine stator blade and the first hole of the gas turbine, so that the sensing portion is placed in the temperature measuring flow channel, and is used to detect the temperature of the airflow flowing from the upstream disk cavity to the downstream disk cavity in the temperature measuring flow channel; A guide component is arranged on the inner cylinder and / or the turbine stator blade to guide the thermocouple assembly.

2. The gas turbine disc cavity temperature measuring device according to claim 1, characterized in that: A connecting portion is provided at one end of the rod body away from the sensing portion, and the connecting portion is detachably connected to the outer cylinder of the gas turbine.

3. The gas turbine disc cavity temperature measuring device according to claim 2, characterized in that: The connecting portion is a flange, and the flange is connected to the outer cylinder via a connecting piece.

4. The gas turbine disc cavity temperature measuring device according to claim 1, characterized in that: It also includes a sealing member, which is arranged between the rod body and the first hole to prevent the gas in the inner cavity of the turbine stator blade from flowing into the temperature measurement flow channel; And / or, the temperature measuring channel includes a first section, a second section and a third section arranged in sequence along the airflow direction, the extension direction of the second section is parallel to the axial direction of the rod body, the sensing part is arranged in the second section, the extension directions of the first section and the third section have a preset angle with the extension direction of the second section, and the connection positions of the first section and the third section with the second section have a certain height difference, so that the temperature measuring channel is a zigzag channel.

5. The gas turbine disk cavity temperature measuring device according to claim 1, characterized in that: The guide component includes a first guide tube and a second guide tube, each of the first guide tube and the second guide tube has a bell-shaped guide section, the first guide tube is connected to the inner cylinder, the first guide tube is used to guide the thermocouple assembly into the inner cavity of the turbine static blade, the second guide tube is connected to the sealing ring of the turbine static blade, and the second guide tube is used to guide the thermocouple assembly into the first channel.

6. The gas turbine disk cavity temperature measuring device according to claim 5, characterized in that: It also includes a bracket, which is connected to the inner cylinder, and the first guide tube is fixed on the first bracket.

7. A gas turbine, characterized in that: The device comprises the gas turbine disk cavity temperature measuring device according to any one of claims 1 to 6.

8. A method for measuring the temperature of a gas turbine disk cavity, characterized in that: include: A first hole and a temperature measuring channel are provided on the sealing ring of the turbine stator blade, wherein the temperature measuring channel is used to connect the upstream disc cavity and the downstream disc cavity corresponding to the turbine stator blade, and the temperature measuring channel is connected to the inner cavity of the turbine stator blade through the first hole; Constructing holes coaxial with and communicating with the first hole on the outer cylinder and the inner cylinder of the gas turbine to form a second hole; Inserting a thermocouple assembly into the first hole and the second hole, and placing the sensing portion of the thermocouple assembly in the temperature measuring flow channel; The thermocouple assembly is fixedly connected to the outer cylinder of the gas turbine; During normal operation of the gas turbine, the temperature of the airflow flowing from the upstream disk cavity to the downstream disk cavity is measured by the thermocouple assembly.

9. The method for measuring the temperature of a gas turbine disk cavity according to claim 8, characterized in that: The temperature measuring channel comprises a first section, a second section and a third section arranged in sequence along the airflow direction, the extension direction of the second section is parallel to the axial direction of the rod body, the sensing part is arranged in the second section, and the extension directions of the first section and the third section have a preset angle with the extension direction of the second section, so that the temperature measuring channel is a zigzag channel; And / or, the thermocouple assembly has a rod body, the sensing portion is located at one end of the rod body, and the other end of the rod body has a connecting portion, and the connecting portion is used to be detachably connected to the outer cylinder of the gas turbine; And / or, a guide component is arranged in the inner casing and / or turbine vane of the gas turbine to guide the thermocouple assembly to move in a directional manner.

10. The method for measuring the temperature of a gas turbine disk cavity according to claim 8 or 9, characterized in that: Also included is a thermocouple replacement process, specifically including: Stop gas turbine operation; Remove the thermocouple assembly from the outer casing of the gas turbine and take out the damaged thermocouple assembly; Replace a new thermocouple assembly, and insert the thermocouple assembly into the first hole and the second hole, and make the sensing part of the thermocouple assembly be in the temperature measuring flow channel; Securely connect the new thermocouple assembly to the outer casing of the gas turbine; Start the gas turbine.

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