Gas turbine gas seal gap measuring device

Abstract

The gas turbine gas seal gap measuring device comprises an outer shell, a first through hole is arranged on the side wall of the outer shell in the circumferential direction; a diffuser shell is arranged in the outer shell, a second through hole is arranged on the side wall of the diffuser shell in the circumferential direction; a rotor is arranged in the diffuser shell; a gas seal device comprises a gas seal ring, the gas seal ring is located between the rotor and the diffuser shell, a third through hole is arranged on the side wall of the gas seal ring in the circumferential direction; a distance measuring device comprises a mounting sleeve and a distance measuring sensor, the mounting sleeve is arranged in the corresponding first through hole, the corresponding second through hole and the corresponding third through hole, the distance measuring sensor is arranged at one end of the mounting sleeve adjacent to the rotor and located in the third through hole of the gas seal ring, and the connecting wire of the distance measuring sensor extends into the mounting sleeve from the outside of the outer shell and is connected with the distance measuring sensor. According to the gas turbine gas seal gap measuring device, the gas turbine grid gap can be measured in real time and accurately.

Description

Technical Field

[0001] This invention relates to the field of gas turbine technology, and more specifically to a gas turbine gas seal gap measuring device. Background Technology

[0002] In related technologies, grate seals are a widely used non-contact sealing device in gas turbines, commonly found in locations such as between shafts and in the turbine disk chamber. Measuring the grate clearance is a crucial aspect of gas turbine design, manufacturing, and maintenance. Real-time measurement of the grate clearance during gas turbine operation allows for a deeper understanding of its working behavior, optimization of seal design, and ensures efficient and safe operation of the gas turbine. Measuring the grate clearance at the exhaust diffuser of a heavy-duty gas turbine compressor presents challenges such as limited installation space, high operating temperatures, and a large measurement range. Furthermore, during the assembly of the compressor exhaust diffuser, certain structural components require liquid nitrogen cooling before assembly; if the sensor is installed first, it may be damaged. Therefore, a special measurement and sensor fixing structure must be designed. Summary of the Invention

[0003] This invention aims to at least partially solve one of the technical problems in related technologies. To this end, embodiments of this invention provide a gas turbine gas seal clearance measuring device.

[0004] The gas turbine gas seal clearance measuring device of this invention includes:

[0005] The outer casing has a first through hole on its circumferential sidewall; A diffuser housing is disposed within the outer shell. The outer peripheral surface of the diffuser housing and the inner peripheral surface of the outer shell define a diffuser cavity. A second through hole is provided on the circumferential sidewall of the diffuser housing. The rotor is disposed within the diffuser housing; An air-sealing device, comprising an air-sealing ring, the air-sealing ring being located between the rotor and the diffuser housing, the air-sealing ring being connected to the diffuser housing and defining an air-sealing ring cavity, and a third through hole being provided on the circumferential sidewall of the air-sealing ring; A ranging device includes a mounting sleeve and a ranging sensor. The mounting sleeve passes through a corresponding first through hole, a corresponding second through hole, and a corresponding third through hole. The ranging sensor is located at one end of the mounting sleeve adjacent to the rotor and within the third through hole of the air seal ring. A connecting wire of the ranging sensor extends from the outside of the housing into the mounting sleeve and is connected to the ranging sensor. The ranging sensor is used to measure the distance between the air seal ring and the rotor.

[0006] In some embodiments, the first through hole is a tapered hole or a stepped hole; The second through hole is a tapered hole or a stepped hole; The third through hole is a tapered hole or a stepped hole; The shape and size of the mounting sleeve are adapted to the shape and size of the first through hole, the second through hole and the third through hole.

[0007] In some embodiments, the mounting sleeve includes a sensor sleeve and a lead wire sleeve; The sensor sleeve includes a first end and a second end, the first end is inserted into the third through hole, the second end is inserted into the second through hole, and the ranging sensor is disposed at the first end of the sensor sleeve; The lead sleeve includes a third end and a fourth end. The third end of the lead sleeve is connected to the second end of the sensor sleeve, and the fourth end of the lead sleeve is located inside the first through hole.

[0008] In some embodiments, the second end of the sensor sleeve is fixedly connected to the diffuser housing, and the fourth end of the lead sleeve is fixedly connected to the outer housing. The third end of the lead sleeve is inserted into or abuts against the second end of the sensor sleeve.

[0009] In some embodiments, the first through hole, the second through hole, and the third through hole are all stepped holes; The stepped hole includes a first sub-hole, an annular connecting surface, and a second sub-hole. The first sub-hole is located on the side of the second sub-hole adjacent to the rotor. The diameter of the second sub-hole is larger than the diameter of the first sub-hole. The inner edge of the connecting surface is connected to the circumferential surface of the first sub-hole, and the outer edge of the connecting surface is connected to the circumferential surface of the second sub-hole. The first end of the sensor sleeve is inserted into the second sub-hole of the third through hole, and a portion of the ranging sensor extends from the sensor sleeve into the first sub-hole of the third through hole; The second end of the sensor sleeve is provided with a first connecting ring on its periphery. The first connecting ring has a plurality of first connecting holes. A bolt passes through the first connecting holes and is connected to the threaded hole bolt on the connecting surface of the second through hole. The third end of the lead sleeve extends into the second sub-hole of the second through hole and abuts against the second end of the sensor sleeve; The fourth end of the lead sleeve is provided with a second connecting ring on its periphery. The second connecting ring has a plurality of second connecting holes. The bolt passes through the second connecting holes and is bolted to the threaded hole on the connecting surface of the first through hole.

[0010] In some embodiments, the wall thickness of the lead sleeve is greater than the wall thickness of the sensor sleeve; A limiting hole is provided at the first end of the sensor sleeve, and a part of the ranging sensor extends out of the sensor sleeve from the limiting hole; The sensor sleeve is provided with a limiting member, which is located on the side of the ranging sensor opposite to the limiting hole, and the limiting member is used to abut against the ranging sensor.

[0011] In some embodiments, a plurality of the first connection holes are spaced apart circumferentially along the sensor sleeve; Multiple second connection holes are spaced apart circumferentially along the lead sleeve; The axial direction of the limiting member is consistent with the axial direction of the sensor sleeve, and the limiting member is threadedly connected to the sensor sleeve.

[0012] In some embodiments, the extending direction of the mounting sleeve is the radial direction of the rotor, and the corresponding first through hole, the corresponding second through hole and the corresponding third through hole are coaxially arranged; The ranging device is multiple, and each air seal ring has multiple ranging devices spaced apart on its circumference.

[0013] In some embodiments, the gas seal ring includes a first gas seal ring and a second gas seal ring, the first gas seal ring and the second gas seal ring being arranged axially on the rotor, the first gas seal ring and the diffuser housing defining a first gas seal ring cavity, and the second gas seal ring and the diffuser housing defining a second gas seal ring cavity; Each of the first and second air-sealing rings has a plurality of distance measuring devices spaced apart in its circumferential direction.

[0014] In some embodiments, the diffuser housing includes an intermediate connecting ring, which is connected to the first air seal ring and the second air seal ring on both sides of the rotor in the axial direction, respectively. The intermediate connecting ring defines a first stepped groove and a second stepped groove, the first air seal ring is assembled in the first stepped groove, and the second air seal ring is assembled in the second stepped groove; The inner side of the air seal ring is provided with a toothed seal.

[0015] The beneficial effects of the present invention are as follows: The gas turbine gas seal gap measuring device according to the embodiment of the present invention provides an installation structure for real-time measurement of the gas turbine tooth gap. By opening an installation hole at the exhaust diffuser of the heavy-duty gas turbine compressor and setting an installation sleeve in the installation hole, the ranging sensor is protected and installed, thereby achieving effective installation of the ranging sensor. It can also be combined with a data acquisition and analysis system to achieve real-time and accurate measurement of the gas turbine tooth gap. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the first through hole, the second through hole, and the third through hole according to an embodiment of the present invention.

[0017] Figure 2 This is a schematic diagram of a gas turbine gas seal gap measuring device according to an embodiment of the present invention.

[0018] Figure 3 This is a schematic diagram of the connecting wire on the outside of the lead sleeve according to an embodiment of the present invention.

[0019] Figure 4 This is a schematic diagram of a sensor sleeve according to an embodiment of the present invention.

[0020] Figure 5 This is a schematic diagram of a lead sleeve according to an embodiment of the present invention.

[0021] Figure 6 This is a schematic diagram of the diffuser housing according to an embodiment of the present invention.

[0022] Figure 7 This is a cross-sectional view of the diffuser housing and the gas seal ring according to an embodiment of the present invention.

[0023] Figure label: 1. Outer shell; 11. First through hole; 2. Diffuser housing; 21. Diffuser cavity; 22. Second through hole; 23. Intermediate connecting ring; 24. First step groove; 25. Second step groove; 3. Air seal ring; 31. Air seal ring cavity; 32. Third through hole; 33. First air seal ring; 34. Second air seal ring; 35. Grate seal element; 4. Sensor sleeve; 41. First end; 42. Second end; 43. First connecting ring; 44. First connecting hole; 45. Limiting hole; 5. Lead wire sleeve; 51. Third end; 52. Fourth end; 53. Second connecting ring; 54. Second connecting hole; 6. Distance sensor; 61. Connecting wires; 71. First sub-hole, 72. Connecting surface, 73. Second sub-hole. Detailed Implementation

[0024] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0025] The following description, with reference to the accompanying drawings, describes an embodiment of the gas turbine gas seal clearance measuring device of the present invention. Figures 1 to 7 As shown, the gas turbine gas seal gap measuring device according to an embodiment of the present invention includes an outer casing 1, a diffuser casing 2, a rotor, a gas seal device, and a distance measuring device.

[0026] A first through hole 11 is provided on the circumferential side wall of the outer casing 1. A diffuser housing 2 is disposed inside the outer casing 1. The outer circumferential surface of the diffuser housing 2 and the inner circumferential surface of the outer casing 1 define a diffuser cavity 21 for airflow. A second through hole 22 is provided on the circumferential side wall of the diffuser housing 2. A rotor is disposed inside the diffuser housing 2. The gas sealing device includes a gas sealing ring 3, which is located between the rotor and the diffuser housing 2. The gas sealing ring 3 is connected to the diffuser housing 2 and defines a gas sealing ring cavity 31. A third through hole 32 is provided on the circumferential side wall of the gas sealing ring 3.

[0027] Specifically, the outer casing 1, diffuser housing 2, gas sealing device, and rotor are arranged sequentially from the outside to the inside. The outer casing 1, diffuser housing 2, and gas sealing device are all provided with through holes (first through hole 11, second through hole 22, and third through hole 32). The first through hole 11, second through hole 22, and third through hole 32 are used to install the ranging device.

[0028] The ranging device includes a mounting sleeve and a ranging sensor 6. The mounting sleeve passes through the corresponding first through hole 11, the corresponding second through hole 22, and the corresponding third through hole 32. The ranging sensor 6 is located at one end of the mounting sleeve adjacent to the rotor and within the third through hole 32 of the air seal ring 3. The connecting wire 61 of the ranging sensor 6 extends from the outside of the outer casing 1 into the mounting sleeve and is connected to the ranging sensor 6. The ranging sensor 6 is used to measure the distance between the air seal ring 3 and the rotor. The outer end of the connecting wire 61 can be connected to a controller for data transmission.

[0029] Specifically, the ranging sensor 6 and the connecting wire 61 are located inside the mounting sleeve, which forms a protective sleeve for the ranging sensor 6 and the connecting wire 61. A portion of the ranging sensor 6 is installed inside the mounting sleeve. After the mounting sleeve and the ranging sensor 6 are assembled and the wire is connected, the ranging device is sequentially passed through the first through hole 11, the second through hole 22, and the third through hole 32, and installed on at least one of the outer casing 1 and the diffuser housing 2, so that the ranging sensor 6 is close to the rotor, thereby facilitating the measurement of the gap change between the gas seal ring 3 and the rotor. Furthermore, during the measurement process, the mounting sleeve protects the ranging sensor 6 and the connecting wire 61, thereby improving the service life of the ranging sensor 6.

[0030] For example, one end of the ranging sensor 6 adjacent to the rotor is coplanar with the inner wall surface of the air seal ring 3. Alternatively, the ranging sensor 6 may be a laser ranging sensor, an ultrasonic ranging sensor, or an infrared ranging sensor.

[0031] In some embodiments, the first through hole 11 is a tapered hole or a stepped hole, the second through hole 22 is a tapered hole or a stepped hole, and the third through hole 32 is a tapered hole or a stepped hole. The shape and size of the mounting sleeve are adapted to the shape and size of the first through hole 11, the second through hole 22, and the third through hole 32.

[0032] like Figure 1 As shown, the first through hole 11, the second through hole 22, and the third through hole 32 can be tapered holes with diameters decreasing along the adjacent rotor. Alternatively, the first through hole 11, the second through hole 22, and the third through hole 32 can be stepped holes, comprising a first sub-hole 71, an annular connecting surface 72, and a second sub-hole 73. The first sub-hole 71 is located on the side of the second sub-hole 73 adjacent to the rotor, and the diameter of the second sub-hole 73 is larger than the diameter of the first sub-hole 71. The inner edge of the connecting surface 72 is connected to the circumferential surface of the first sub-hole 71, and the outer edge of the connecting surface 72 is connected to the circumferential surface of the second sub-hole 73. Therefore, when the mounting sleeve is assembled onto the first through hole 11, the second through hole 22, and the third through hole 32, the first through hole 11, the second through hole 22, and the third through hole 32 can limit the movement of the mounting sleeve and improve sealing.

[0033] like Figures 2 to 5 As shown, in some embodiments, the mounting sleeve includes a sensor sleeve 4 and a lead wire sleeve 5. Specifically, the lead wire sleeve 5 has a through hole for accommodating the connecting wire 61. The sensor sleeve 4 has a receiving cavity and openings at both ends for accommodating and mounting the ranging sensor 6. The wall thickness of the lead wire sleeve 5 is greater than the wall thickness of the sensor sleeve 4 to resist the airflow of the diffuser cavity 21.

[0034] In some embodiments, the extension direction of the mounting sleeve is the radial direction of the rotor, the extension direction of the sensor sleeve 4 and the lead sleeve 5 is the radial direction of the rotor, and the corresponding first through hole 11, the corresponding second through hole 22 and the corresponding third through hole 32 are coaxially arranged.

[0035] like Figure 2 and Figure 4 As shown, the sensor sleeve 4 includes a first end 41 and a second end 42, with the first end 41 being the end adjacent to the rotor. The first end 41 is inserted into the third through hole 32, and the second end 42 is inserted into the second through hole 22. The ranging sensor 6 is disposed at the first end 41 of the sensor sleeve 4. The sensor sleeve 4 passes through the third through hole 32 and the second through hole 22 for positioning.

[0036] like Figure 2 and Figure 5As shown, the lead sleeve 5 includes a third end 51 and a fourth end 52, with the third end 51 being the end adjacent to the rotor. The third end 51 of the lead sleeve 5 is connected to the second end 42 of the sensor sleeve 4, and the fourth end 52 of the lead sleeve 5 is located within the first through hole 11. The lead sleeve 5 passes through the first through hole 11 and the second through hole 22 for positioning.

[0037] like Figure 2 As shown, in some embodiments, the second end 42 of the sensor sleeve 4 is fixedly connected to the diffuser housing 2, and the fourth end 52 of the lead sleeve 5 is fixedly connected to the outer housing 1.

[0038] Specifically, the first through hole 11, the second through hole 22 and the third through hole 32 are all stepped holes.

[0039] like Figure 2 and Figure 4 As shown, a first connecting ring 43 is provided on the periphery of the second end 42 of the sensor sleeve 4. The first connecting ring 43 has multiple first connecting holes 44. Bolts pass through the first connecting holes 44 and are connected to the threaded holes on the connecting surface 72 of the second through hole 22. Thus, the sensor sleeve 4 (first connecting ring 43) can be connected to the connecting surface 72 of the second through hole 22 by bolts, thereby fixing the second end 42 of the sensor sleeve 4 to the diffuser housing 2. The first end 41 of the sensor sleeve 4 is inserted into the second sub-hole 73 of the third through hole 32, thereby fixing the first end 41 of the sensor sleeve 4. For example, the multiple first connecting holes 44 are spaced apart circumferentially along the sensor sleeve 4.

[0040] like Figure 2 and Figure 5 As shown, in some embodiments, a second connecting ring 53 is provided around the fourth end 52 of the lead sleeve 5. The second connecting ring 53 has multiple second connecting holes 54. Bolts pass through the second connecting holes 54 and are connected to the threaded holes on the connecting surface 72 of the first through hole 11. Thus, the lead sleeve 5 (second connecting ring 53) can be connected to the connecting surface 72 of the first through hole 11 by bolts, thereby fixing the fourth end 52 of the lead sleeve 5 to the outer casing 1. The third end 51 of the lead sleeve 5 is inserted into or abuts against the second end 42 of the sensor sleeve 4, thereby fixing the third end 51 of the lead sleeve 5.

[0041] In some embodiments, the third end 51 of the lead sleeve 5 extends into the second sub-hole 73 of the second through hole 22 and abuts against the second end 42 of the sensor sleeve 4. Specifically, the second end 42 of the sensor sleeve 4 defines a groove, or the second end 42 of the sensor sleeve 4 and the peripheral wall surface of the second sub-hole 73 of the second through hole 22 define a groove, and the third end 51 of the lead sleeve 5 is inserted into the groove and abuts against the second end 42 of the sensor sleeve 4, thereby fixing the third end 51 of the lead sleeve 5. For example, a plurality of second connecting holes 54 are arranged at intervals along the circumference of the lead sleeve 5.

[0042] In some embodiments, a portion of the ranging sensor 6 extends from the sensor sleeve 4 into the first sub-hole 71 of the third through hole 32. Specifically, a limiting hole 45 is formed at the first end 41 of the sensor sleeve 4, and a portion of the ranging sensor 6 extends out of the sensor sleeve 4 from the limiting hole 45. Specifically, the limiting hole 45 penetrates the first end 41 of the sensor sleeve 4 radially, and a limiting structure is formed on the inner side of the first end 41 of the sensor sleeve 4 to limit the portion of the ranging sensor 6 located at the first end 41, preventing the ranging sensor 6 from falling out of the sensor sleeve 4.

[0043] In some embodiments, a limiting member is provided inside the sensor sleeve 4. The limiting member is located on the side of the ranging sensor 6 opposite to the limiting hole 45 and is used to abut against the ranging sensor 6. Specifically, the axial direction of the limiting member is aligned with the axial direction of the sensor sleeve 4, and the limiting member is threadedly connected to the sensor sleeve 4. Thus, the limiting member can be rotated to move towards the adjacent ranging sensor 6 and abut against the ranging sensor 6, thereby limiting the ranging sensor 6 in the extending direction of the sensor sleeve 4.

[0044] In some embodiments, there are multiple ranging devices, and each air seal ring 3 is provided with multiple ranging devices spaced apart in the circumferential direction, so as to measure multiple positions on the rotor circumference and the gap of the air seal ring 3.

[0045] In some embodiments, there are multiple air seal rings 3, which are arranged axially (at intervals) on the rotor.

[0046] like Figure 7 As shown, in some embodiments, the air seal ring 3 includes a first air seal ring 33 and a second air seal ring 34. The first air seal ring 33 and the second air seal ring 34 are arranged axially on the rotor. The first air seal ring 33 and the diffuser housing 2 define a first air seal ring cavity, and the second air seal ring 34 and the diffuser housing 2 define a second air seal ring cavity. For example, the second air seal ring cavity communicates with a cavity inside the rotor so that airflow from inside the rotor can enter the second air seal ring cavity. Each of the first air seal ring 33 and the second air seal ring 34 has a plurality of spaced-apart ranging devices arranged circumferentially.

[0047] In some embodiments, the diffuser housing 2 includes an intermediate connecting ring 23, which is connected to a first air seal ring 33 and a second air seal ring 34 on both sides of the rotor's axial direction, respectively. Specifically, the intermediate connecting ring 23 defines a first stepped groove 24 and a second stepped groove 25. The first air seal ring 33 is fitted into the first stepped groove 24, and the second air seal ring 34 is fitted into the second stepped groove 25, so as to limit the positioning of the first air seal ring 33 and the second air seal ring 34.

[0048] In some embodiments, a toothed seal 35 is provided on the inner side of the air-sealing ring 3. Specifically, the air-sealing device is a toothed air-sealing device.

[0049] According to an embodiment of the present invention, a gas turbine gas seal gap measuring device provides an installation structure for real-time measurement of the gas turbine tooth gap. By opening an installation hole at the exhaust diffuser of the heavy-duty gas turbine compressor and setting an installation sleeve in the installation hole, the distance measuring sensor is protected and installed, thereby achieving effective installation of the distance measuring sensor. It can also be combined with a data acquisition and analysis system to achieve real-time and accurate measurement of the gas turbine tooth gap.

[0050] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0051] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0052] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0053] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0054] In this invention, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0055] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled 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 gas seal clearance measuring device, characterized in that, include: The outer casing has a first through hole on its circumferential sidewall; A diffuser housing is disposed within the outer shell. The outer peripheral surface of the diffuser housing and the inner peripheral surface of the outer shell define a diffuser cavity. A second through hole is provided on the circumferential sidewall of the diffuser housing. The rotor is disposed within the diffuser housing; An air-sealing device, comprising an air-sealing ring, the air-sealing ring being located between the rotor and the diffuser housing, the air-sealing ring being connected to the diffuser housing and defining an air-sealing ring cavity, and a third through hole being provided on the circumferential sidewall of the air-sealing ring; A ranging device includes a mounting sleeve and a ranging sensor. The mounting sleeve passes through a corresponding first through hole, a corresponding second through hole, and a corresponding third through hole. The ranging sensor is located at one end of the mounting sleeve adjacent to the rotor and within the third through hole of the air seal ring. A connecting wire of the ranging sensor extends from the outside of the housing into the mounting sleeve and is connected to the ranging sensor. The ranging sensor is used to measure the distance between the air seal ring and the rotor.

2. The gas turbine gas seal clearance measuring device according to claim 1, characterized in that, The first through hole is a tapered hole or a stepped hole; The second through hole is a tapered hole or a stepped hole; The third through hole is a tapered hole or a stepped hole; The shape and size of the mounting sleeve are adapted to the shape and size of the first through hole, the second through hole and the third through hole.

3. The gas turbine gas seal gap measuring device according to claim 2, characterized in that, The mounting sleeve includes a sensor sleeve and a lead wire sleeve; The sensor sleeve includes a first end and a second end, the first end is inserted into the third through hole, the second end is inserted into the second through hole, and the ranging sensor is disposed at the first end of the sensor sleeve; The lead sleeve includes a third end and a fourth end. The third end of the lead sleeve is connected to the second end of the sensor sleeve, and the fourth end of the lead sleeve is located inside the first through hole.

4. The gas turbine gas seal clearance measuring device according to claim 3, characterized in that, The second end of the sensor sleeve is fixedly connected to the diffuser housing, and the fourth end of the lead sleeve is fixedly connected to the outer housing. The third end of the lead sleeve is inserted into or abuts against the second end of the sensor sleeve.

5. The gas turbine gas seal clearance measuring device according to claim 4, characterized in that, The first through hole, the second through hole, and the third through hole are all stepped holes; The stepped hole includes a first sub-hole, an annular connecting surface, and a second sub-hole. The first sub-hole is located on the side of the second sub-hole adjacent to the rotor. The diameter of the second sub-hole is larger than the diameter of the first sub-hole. The inner edge of the connecting surface is connected to the circumferential surface of the first sub-hole, and the outer edge of the connecting surface is connected to the circumferential surface of the second sub-hole. The first end of the sensor sleeve is inserted into the second sub-hole of the third through hole, and a portion of the ranging sensor extends from the sensor sleeve into the first sub-hole of the third through hole; The second end of the sensor sleeve is provided with a first connecting ring on its periphery. The first connecting ring has a plurality of first connecting holes. A bolt passes through the first connecting holes and is connected to the threaded hole bolt on the connecting surface of the second through hole. The third end of the lead sleeve extends into the second sub-hole of the second through hole and abuts against the second end of the sensor sleeve; The fourth end of the lead sleeve is provided with a second connecting ring on its periphery. The second connecting ring has a plurality of second connecting holes. The bolt passes through the second connecting holes and is bolted to the threaded hole on the connecting surface of the first through hole.

6. The gas turbine gas seal clearance measuring device according to claim 5, characterized in that, The wall thickness of the lead sleeve is greater than the wall thickness of the sensor sleeve; A limiting hole is provided at the first end of the sensor sleeve, and a part of the ranging sensor extends out of the sensor sleeve from the limiting hole; The sensor sleeve is provided with a limiting member, which is located on the side of the ranging sensor opposite to the limiting hole, and the limiting member is used to abut against the ranging sensor.

7. The gas turbine gas seal clearance measuring device according to claim 6, characterized in that, Multiple first connection holes are spaced apart along the circumference of the sensor sleeve; Multiple second connection holes are spaced apart circumferentially along the lead sleeve; The axial direction of the limiting member is consistent with the axial direction of the sensor sleeve, and the limiting member is threadedly connected to the sensor sleeve.

8. The gas turbine gas seal clearance measuring device according to any one of claims 1-7, characterized in that, The extension direction of the mounting sleeve is the radial direction of the rotor, and the corresponding first through hole, the corresponding second through hole and the corresponding third through hole are coaxially arranged; The ranging device is multiple, and each air seal ring has multiple ranging devices spaced apart on its circumference.

9. The gas turbine gas seal clearance measuring device according to claim 8, characterized in that, The gas sealing ring includes a first gas sealing ring and a second gas sealing ring, which are arranged axially on the rotor. The first gas sealing ring and the diffuser housing define a first gas sealing ring cavity, and the second gas sealing ring and the diffuser housing define a second gas sealing ring cavity. Each of the first and second air-sealing rings has a plurality of distance measuring devices spaced apart in its circumferential direction.

10. The gas turbine gas seal clearance measuring device according to claim 9, characterized in that, The diffuser housing includes an intermediate connecting ring, which is connected to the first air seal ring and the second air seal ring on both sides of the rotor's axial direction, respectively. The intermediate connecting ring defines a first stepped groove and a second stepped groove, the first air seal ring is assembled in the first stepped groove, and the second air seal ring is assembled in the second stepped groove; The inner side of the air seal ring is provided with a toothed seal.

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