Turbine rim sealing system of gas turbine

Abstract

The invention provides a turbine rim sealing system of a gas turbine. The turbine rim sealing system of the gas turbine comprises a rotary disc, a static disc, a detection assembly and a cooling system. The turntable is provided with a turntable sealing ring; a sealing shoulder and a static disc sealing ring are arranged on one axial side of the static disc, and the sealing shoulder and the static disc sealing ring are connected and define a sealing cavity. The static disc sealing ring and the rotary disc sealing ring are arranged oppositely in the radial direction, and a sealing gap is formed between the static disc sealing ring and the rotary disc sealing ring. The detection assembly is arranged on the inner wall of the sealing cavity so as to be suitable for detecting thermal strain of the wall body of the sealing cavity. The cooling system is connected with the sealing cavity and is suitable for selectively introducing cooling airflow into the sealing cavity according to the detection result of the detection assembly so as to be suitable for adjusting the airflow temperature in the sealing cavity. According to the invention, reliable detection and judgment of thermal deformation of the turbine rim of the gas turbine can be realized; and meanwhile, effective coping and maintenance of thermal deformation of the turbine rim of the gas turbine can be achieved, and the service life of the turbine structure of the gas turbine can be prolonged.

Description

Technical Field

[0001] This application relates to the technical field of gas turbine sealing, and in particular to a turbine rim seal system for a gas turbine. Background Art

[0002] In the field of gas turbine turbine rim seals, optimizing the sealing efficiency and thermodynamically coupling the design of high-temperature components are the core research directions in recent years. Currently, related technologies mostly focus on optimizing the geometric parameters of the rim seal structure, such as radial clearance control and chamber flow path design, as well as the influence mechanism of turbine stage aerodynamic parameters (pressure ratio, rotational speed) on the sealing performance, and strive to improve the sealing effect.

[0003] However, during the operation of a gas turbine, the turbine rim seal structure is prone to thermal deformation, resulting in too small a sealing gap, which causes contact friction between the stationary disk and the rotating disk, leading to wear and gas turbine failures. According to research data in the gas turbine industry, for every 0.1 mm increase in the turbine seal gap, the gas turbine efficiency will decrease by 2% - 3%, and unplanned shutdowns caused by excessive wear of the turbine rim seal structure account for 35% of the total failure rate. While related technologies improve the sealing effect, it is difficult to take into account reducing the wear caused by thermal deformation.

[0004] In addition, existing thermal deformation detection schemes lack a reliable reference calibration method. Especially in a non-uniform temperature field, it is difficult to establish an effective reference system, making it difficult to dynamically and real-time obtain the thermal deformation data of the turbine rim seal structure and unable to timely and effectively solve a series of problems brought about by thermal deformation. Summary of the Invention

[0005] This application aims to at least solve one of the technical problems existing in the prior art. For this reason, an object of this application is to propose a turbine rim seal system for a gas turbine, which can real-time monitor the thermal deformation of the seal structure during high-temperature operation, efficiently maintain the gas turbine, and reduce wear.

[0006] This application proposes a turbine rim seal system for a gas turbine. The turbine rim seal system of the gas turbine includes a rotating disk, a stationary disk, a detection component, and a cooling system; the rotating disk is provided with a rotating disk seal ring; on one axial side of the stationary disk, there is a seal shoulder and a stationary disk seal ring, the seal shoulder is connected to the stationary disk seal ring and defines a seal chamber; the stationary disk seal ring is disposed opposite to the rotating disk seal ring in the radial direction, and a seal gap is formed between the stationary disk seal ring and the rotating disk seal ring; the detection component is disposed on the inner wall of the seal chamber to be adapted to detect the thermal strain of the seal chamber wall; the cooling system is connected to the seal chamber and is adapted to selectively introduce a cooling air flow into the seal chamber according to the detection result of the detection component to be adapted to adjust the air flow temperature in the seal chamber.

[0007] For the turbine rim seal system of a gas turbine according to the present application, since the detection component can detect the thermal stress fluctuation of the stationary disk seal ring in real time, the contact friction condition between the stationary disk seal ring and the rotating disk seal ring can be judged according to the detection result, and reliable detection and judgment of the thermal deformation of the turbine rim of the gas turbine can be realized; at the same time, since the cooling system can introduce cooling air flow into the seal cavity based on the detection result of the detection component, the stationary disk seal ring can be cooled, the seal gap can be increased and wear can be reduced, effective response and maintenance of the thermal deformation of the turbine rim of the gas turbine can be realized, and the service life of the turbine structure of the gas turbine can be increased. The present application ensures the long-term operation of the gas turbine through thermal deformation stress monitoring and temperature control, and reduces wear while maintaining a good sealing effect.

[0008] According to some embodiments of the present application, the detection component includes sensors, and the sensors are configured to be at least eight and are arranged at intervals along the circumferential direction of the stationary disk seal ring.

[0009] According to some embodiments of the present application, the sensors are configured as high-temperature resistant fiber Bragg grating sensors.

[0010] According to some embodiments of the present application, the detection component further includes a control terminal, and the control terminal is arranged outside the gas turbine and is in wireless communication with each sensor.

[0011] According to some embodiments of the present application, the stationary disk is provided with a cooling channel communicating the seal cavity with the outside of the gas turbine; the cooling system includes a ceramic sleeve, and the ceramic sleeve is arranged in the cooling channel and is communicated with the seal cavity.

[0012] According to some embodiments of the present application, the ceramic sleeve is formed with honeycomb-shaped pores.

[0013] According to some embodiments of the present application, the rotating disk seal ring is detachably connected to the rotating disk.

[0014] According to some embodiments of the present application, an installation portion is formed on the rotating disk seal ring, and an installation groove is formed on the rotating disk and is in fit connection with the installation portion.

[0015] According to some embodiments of the present application, the rotating disk seal ring and the rotating disk are connected by bolts, and the bolts are installed radially outward of the gas turbine.

[0016] According to some embodiments of the present application, a labyrinth is arranged on the side of the stationary disk seal ring facing the rotating disk seal ring, and a honeycomb core grid is arranged on the side of the rotating disk seal ring facing the stationary disk seal ring, and the labyrinth and the honeycomb core grid define a seal gap.

[0017] Additional aspects and advantages of the present application will be given in part in the following description, become apparent in part from the following description, or be learned through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The above and / or additional aspects and advantages of the present application will become apparent and be readily understood from the following description of embodiments in conjunction with the accompanying drawings, where:

[0019] Figure 1 is a radial cross-sectional view of a gas turbine turbine structure according to some embodiments of the present application;

[0020] Figure 2 is a schematic structural view of a turbine rim seal system according to some embodiments of the present application;

[0021] Figure 3 is an axial cross-sectional view of a detection component according to some embodiments of the present application;

[0022] Figure 4 is a schematic structural view of a rotating disk seal ring according to some embodiments of the present application;

[0023] Figure 5 is a schematic structural view of a stationary disk seal ring according to some embodiments of the present application.

[0024] Reference numerals:

[0025] Rotating disk 10; Rotating disk seal ring 11; Mounting portion 111; Mounting groove 12; Honeycomb core grid 13;

[0026] Stationary disk 20; Sealing shoulder 21; Stationary disk seal ring 22; Labyrinth teeth 221; Jet holes 222; Sealing cavity 23; Cooling channel 24; Sealing ring 25; Sealing portion 26; Guide hole 27; Accommodating groove 28;

[0027] Detection component 30; First sensor 31; Second sensor 32; Third sensor 33; Fourth sensor 34; Fifth sensor 35; Sixth sensor 36; Seventh sensor 37; Eighth sensor 38;

[0028] Moving blade 40; Stationary blade 50; Main flow path 60; Disk cavity 70. Detailed description of the embodiments

[0029] Embodiments of the present application will be described in detail below. Examples of the embodiments are shown in the accompanying drawings, where the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the accompanying drawings are exemplary and are only used to explain the present application and should not be construed as a limitation of the present application.

[0030] Reference is made below to Figures 1-5 describe a turbine rim seal system of a gas turbine according to an embodiment of the present application.

[0031] The present application provides a turbine rim seal system for a gas turbine. The turbine rim seal system of the gas turbine includes a rotating disk 10, a stationary disk 20, a detection assembly 30, and a cooling system. The rotating disk 10 is provided with a rotating disk seal ring 11. On one axial side of the stationary disk 20, there is a seal shoulder and a stationary disk seal ring 22. The seal shoulder is connected to the stationary disk seal ring 22 and defines a seal cavity 23. The stationary disk seal ring 22 and the rotating disk seal ring 11 are arranged opposite to each other in the radial direction, and a seal gap is formed between the stationary disk seal ring 22 and the rotating disk seal ring 11. The detection assembly 30 is disposed on the inner wall of the seal cavity 23 to be adapted to detect the thermal strain of the wall of the seal cavity 23. The cooling system is connected to the seal cavity 23 and is adapted to selectively introduce a cooling air flow into the seal cavity 23 according to the detection result of the detection assembly 30 to be adapted to adjust the air flow temperature in the seal cavity 23.

[0032] According to the turbine rim seal system of the present application, a seal gap is formed between the stationary disk seal ring 22 and the rotating disk seal ring 11. During the operation of the gas turbine, due to the relatively high operating temperature, the seal shoulder, the stationary disk seal ring 22, and the rotating disk seal ring 11 will undergo thermal expansion deformation when heated. The stationary disk seal ring 22 generates thermal stress fluctuations, resulting in an excessively small seal gap, which to a certain extent causes contact friction between the stationary disk seal ring 22 and the rotating disk seal ring 11 and wear occurs. In the present application, by providing the detection assembly 30 to detect the stress change on the inner wall of the stationary disk seal ring 22 in real time, the deformation conditions of the stationary disk seal ring 22 and the rotating disk seal ring 11 can be judged accordingly, and whether there is contact friction between the stationary disk seal ring 22 and the rotating disk seal ring 11 can be judged. When contact friction occurs, a cooling air flow is introduced into the seal cavity 23 through the cooling system, the temperature of the seal cavity 23 can be adjusted and controlled, thereby changing the thermal expansion degree of the seal shoulder and the stationary disk seal ring 22, increasing the seal gap between the stationary disk seal ring 22 and the rotating disk seal ring 11, and reducing wear.

[0033] According to the turbine rim seal system of the present application, since the detection assembly 30 can detect the thermal stress fluctuations of the stationary disk seal ring 22 in real time, the contact friction condition between the stationary disk seal ring 22 and the rotating disk seal ring 11 can be judged according to the detection result, and reliable detection and judgment of the thermal deformation of the turbine rim of the gas turbine can be achieved. At the same time, since the cooling system can introduce a cooling air flow into the seal cavity 23 based on the detection result of the detection assembly 30, the stationary disk seal ring 22 can be cooled, the seal gap can be increased to reduce wear, and effective response and maintenance of the thermal deformation of the turbine rim of the gas turbine can be achieved, and the service life of the turbine structure of the gas turbine can be increased. The present application ensures the long-term operation of the gas turbine through thermal deformation stress monitoring and temperature control, and reduces wear while maintaining a good sealing effect.

[0034] According to some embodiments of the present application, the detection assembly 30 includes sensors, and the sensors are configured to be at least eight and are circumferentially spaced along the static disk seal ring 22. In this embodiment, by spacing at least eight sensors, the stress state of the static disk seal ring 22 can be reflected omni-directionally, comprehensively, and accurately. The fusion of multiple sensors can eliminate the phase difference caused by the thermal conduction lag effect, effectively cope with the non-uniformity of the stress change of the static disk seal ring 22, and ensure the reliability of the detection result.

[0035] In some embodiments, as Figure 3 shown, eight sensors, namely the first sensor 31, the second sensor 32, the third sensor 33, the fourth sensor 34, the fifth sensor 35, the sixth sensor 36, the seventh sensor 37, and the eighth sensor 38, are evenly spaced along the inner circumference of the static disk seal ring 22.

[0036] According to some embodiments of the present application, the sensors are configured as high-temperature resistant fiber Bragg grating sensors. In this embodiment, high-temperature resistant fiber Bragg grating sensors (FBG sensors) are selected for stress detection. The high-temperature resistant fiber Bragg grating sensors can withstand high temperatures and are very sensitive to strain changes. They can detect strain changes at the micron level, monitor the strain of the inner wall of the sealing cavity 23 in real time through the wavelength shift amount, have high detection accuracy, fast response speed, and strong anti-interference ability. By setting high-temperature resistant fiber Bragg grating sensors in the present application, a strain sensing network with a level of 0.5 μm can be constructed, effectively improving the sensitivity and accuracy of the detection assembly 30. In some embodiments, as Figure 3 shown, the detection assembly 30 includes eight high-temperature resistant fiber Bragg grating sensors, which can withstand temperatures up to 1000 °C, and tests show that their detection error is less than ±0.5%.

[0037] In the above embodiments, due to reasons such as uneven thermal deformation of the static disk seal ring 22 and the rotating disk seal ring 11, the static disk seal ring 22 and the rotating disk seal ring 11 may be eccentric. At this time, local wear may occur between the static disk seal ring 22 and the rotating disk seal ring 11. The corresponding sensors can detect the stress change. According to the detection results of each sensor, it can be determined whether there is an eccentric problem, and the temperature can be adjusted through the cooling system to change the eccentric situation. Specifically, a three-dimensional coordinate system can be established with the axial end face of the mounting shoulder 21 on the static disk 20 as the reference plane, and the radial offset of the rotating disk 10 can be calculated through the strain phase difference of 8 groups of FBG sensors. When the amplitude difference detected by adjacent sensors exceeds 50 με and the phase lag exceeds 22.5°, it is determined as an eccentric fault.

[0038] Under the normal operation of the gas turbine, the monitoring waveform of the high-temperature resistant fiber Bragg grating sensor in the above embodiment is stable; when the rotating disk seal ring 11 rubs against the static disk seal ring 22, the monitoring waveform will have periodic mutations, and the contact situation between the rotating disk seal ring 11 and the static disk seal ring 22 can be judged according to the monitoring results.

[0039] According to some embodiments of the present application, the detection assembly 30 further includes a control terminal, which is arranged outside the gas turbine and communicates wirelessly with each sensor. In this embodiment, the selection of wireless communication for the control terminal can avoid the risk of wiring in a high-temperature environment. Further, the control terminal is embedded with a wireless transceiver module, which can realize the dynamic reconstruction of the stress field at a sampling frequency of 1 kHz and meet the requirements of dynamic monitoring. Furthermore, the control terminal is built-in with multi-sensor fusion algorithms, thermal expansion compensation algorithms, cooling system control algorithms, etc., which can automatically realize the monitoring process and the thermal compensation process, and improve the accuracy of thermal deformation monitoring and thermal compensation.

[0040] According to some embodiments of the present application, the static disk 20 is provided with a cooling channel 24 that communicates the sealing cavity 23 with the outside of the gas turbine; the cooling system includes a ceramic sleeve, which is arranged in the cooling channel 24 and communicates with the sealing cavity 23. In this embodiment, as Figure 1 , 2 shown, by providing the cooling channel 24, the conduction between the sealing cavity 23 at the turbine rim and the external environment of the gas turbine is realized. A ceramic sleeve is arranged in the cooling channel 24, which can maintain structural stability in a high-temperature environment and realize the effective transfer of cooling air flow.

[0041] According to some embodiments of the present application, the ceramic sleeve is formed with honeycomb-shaped pores. In this embodiment, the ceramic sleeve adopts a honeycomb-shaped porous structure, which can evenly disperse the cooling air flow and reduce the axial temperature gradient of the chamber.

[0042] Further, the cooling system further includes a piezoelectric flow valve, which is connected to the cooling channel 24 to control the inflow speed of the cooling air flow, and can achieve precise regulation within the range of 0 - 500 L / min. By controlling the flow rate of the cooling air flow and combining with the honeycomb-shaped porous medium heat exchange technology of the ceramic sleeve, through testing, this embodiment can control the axial temperature gradient within 15 °C / m.

[0043] According to some embodiments of the present application, the rotating disk seal ring 11 is detachably connected to the rotating disk 10. In this embodiment, as Figure 2 shown, the rotating disk seal ring 11 is detachably connected to the rotating disk 10, which can be replaced when the rotating disk seal ring 11 is worn, so as to improve and maintain the performance of the gas turbine and extend the service life of the turbine structure of the gas turbine.

[0044] According to some embodiments of the present application, an installation portion 111 is formed on the rotating disk seal ring 11, and an installation groove 12 that cooperates with the installation portion is formed on the rotating disk 10. As Figure 4As shown, the rotary table sealing ring 11 of this embodiment is snap-connected to the rotary table 10 through the installation part 111 and the installation groove 12, which can realize the preliminary fixation of the rotary table sealing ring 11. Among them, the installation groove 12 can be configured as a dovetail groove, and the installation part 111 is configured as a dovetail tenon that matches the dovetail groove.

[0045] According to some embodiments of the present application, the rotary table sealing ring 11 and the rotary table 10 are connected by bolts, and the bolts are installed radially outward along the gas turbine. In this embodiment, the rotary table sealing ring 11 and the rotary table 10 are stably connected by high-temperature bolts, which improves stability and facilitates rapid disassembly and assembly.

[0046] Furthermore, the rotary table sealing ring 11 and the rotary table 10 can be connected and fixed by a composite locking structure combining a dovetail tenon and a dovetail groove and a high-temperature bolt. While maintaining the convenience of disassembly and assembly of the rotary table sealing ring 11, the stability of the rotary table sealing ring 11 during operation is effectively improved. Performance tests were carried out on the gas turbine turbine rim sealing system applying this embodiment, and the test results show that the fluctuation range of the sealing gap in this embodiment is reduced, and the frictional power consumption is lower; in some embodiments, the fluctuation range of the sealing gap is compressed to ±0.05 mm, and the frictional power consumption is reduced by 42%.

[0047] Disassembly and replacement tests were carried out on the rotary table sealing ring 11 of the above embodiment, and the test results show that the rotary table sealing ring 11 of this embodiment can be quickly disassembled and assembled in 15 minutes under the condition of 300 °C. Compared with replacing the entire rotary table 10, this embodiment can shorten the replacement time by 60% and reduce the maintenance cost by 40%.

[0048] According to some embodiments of the present application, a labyrinth tooth 221 is provided on the side of the stationary disk sealing ring 22 facing the rotary table sealing ring 11, and a honeycomb core grid 13 is provided on the side of the rotary table sealing ring 11 facing the stationary disk sealing ring 22. The labyrinth tooth 221 and the honeycomb core grid 13 define a sealing gap. In this embodiment, as Figure 2 、 Figure 5 shown, by setting the labyrinth tooth 221, the contact area between the stationary disk sealing ring 22 and the moving disk sealing ring can be reduced, thereby reducing the wear degree; by setting the honeycomb core grid 13 to change the flow direction of the air flow in the sealing gap, the sealing effect can be improved.

[0049] Furthermore, the labyrinth teeth 221 are configured in multiple numbers and are arranged at intervals along the axial direction of the gas turbine, which can form a multi-stage seal and improve the sealing effect. Furthermore, jet holes 222 are provided between adjacent labyrinth teeth 221, which can guide the air flow in the sealing cavity 23 to between adjacent labyrinth teeth 221 to realize temperature adjustment and improve the uniformity of heat reception of the stationary disk sealing ring 22.

[0050] According to some embodiments of the present application, a part of the mounting shoulder 21 and a part of the stationary disk seal ring 22 overlap axially and are connected by bolts. A sealing ring 25 is provided between the mounting shoulder 21 and the stationary disk seal ring 22, and the sealing ring 25 is configured in multiple numbers, and the multiple sealing rings 25 are arranged at intervals in the radial direction.

[0051] It should be noted that as Figure 1 shown, the turbine structure of the gas turbine includes the turbine rim seal system of the present application, and also includes a stationary blade 50 and a moving blade 40. The stationary blade 50 is arranged on the stationary disk 20, and the moving blade 40 is arranged on the rotating disk 10. A main flow path 60 for high-temperature gas is formed between the moving blade 40 and the stationary blade 50, and a disk cavity 70 is formed between the rotating disk 10 and the stationary disk 20. The high-temperature gas has a tendency to invade from the main flow path 60 into the disk cavity 70, and the turbine rim seal system of the present application can play a role in sealing and blocking this invasion.

[0052] As Figure 1 、 2 shown, in some embodiments, the stationary disk 20 is further provided with a sealing portion 26. The sealing portion 26 and a part of the rotating disk seal ring 11 are radially aligned, and the sealing portion 26 and the stationary disk seal ring 22 are respectively arranged on the radial outer side and the radial inner side of the rotating disk seal ring 11; there is a second sealing gap between the sealing portion 26 and the rotating disk seal ring 11. Further, the stationary disk 20 further forms a receiving groove 28 communicating with the second sealing gap, and the receiving groove 28 communicates with the sealing cavity 23 through a guide hole 27. In this embodiment, when the high-temperature gas in the main flow path 70 invades the second sealing gap, the receiving groove 28 can store and buffer the high-temperature gas, so that the high-temperature gas will not easily invade the disk cavity 80 through the sealing gap; at the same time, the high-temperature gas in the receiving groove 28 is mixed with the airflow inside the disk cavity 80 in the receiving groove 28 to form a mixed airflow, and the mixed airflow is introduced into the sealing cavity 23 through the guide hole 27, and continues to be mixed with the cooling airflow in the sealing cavity 23, and then is sprayed into the space between multiple labyrinth teeth 221 through the jet holes 222, and returns to the receiving groove 28 through the sealing gap. The gas turbine turbine rim seal system of this embodiment can improve the sealing effect, and at the same time can make the cooling airflow flow through the seal system, which is convenient for temperature adjustment and improves the uniformity of heat reception.

[0053] When the turbine rim seal system of the present application is operating, a dual-reference axis can be selected to establish a dual-reference error separation model, and combined with the fusion of multi-sensor detection results, the phase difference caused by the heat conduction effect can be eliminated.

[0054] In the actual application of this application, taking the abnormal friction under the condition of 980 °C as an example: taking the axial end face of the mounting shoulder 21 and the guide hole 27 to establish a double reference axis, when the wall of the sealing cavity 23 expands due to heat, that is, the static disk sealing ring 22 and the mounting shoulder 21 expand due to heat, resulting in the sealing gap between the static disk sealing ring 22 and the rotating disk sealing ring 11 being less than 0.15 mm, the circumferentially evenly distributed high-temperature fiber Bragg grating sensor array detects a periodic stress mutation with an amplitude of up to 120 με, and the wireless transmission system transmits the strain waveform back to the control terminal in real time at a sampling frequency of 1 kHz; trigger the cooling system, and pass the honeycomb porous ceramic sleeve embedded in the static disk 20 into the sealing cavity 23 to introduce a cooling air flow, and increase the cooling air flow to 180% of the design value, which can reduce the axial temperature gradient of the cavity by 72% and restore the sealing gap to 0.23 mm. At the same time, replace the rotating disk sealing ring 11, use a high-temperature wrench set to disassemble the high-temperature bolts for locking, and the re-assembly of the dovetail groove positioning surface of the rotating disk sealing ring 21 can be achieved within 6 minutes.

[0055] In the actual application of this application, taking the eccentricity monitoring as an example: taking the axial end face of the mounting shoulder 21 to establish a reference axis, when the rotating disk 10 has an eccentricity of 0.08 mm, as Figure 3 shown, when the detection component 30 detects that the corresponding measuring points of the first sensor 31 and the fifth sensor 35 have a 180° anti-phase strain fluctuation (the amplitude difference reaches 85 με), and the corresponding measuring points of the third sensor 33 and the seventh sensor 37 show a 90° phase lag, the control terminal calls the thermal expansion compensation algorithm to correct the reference radius.

[0056] In the description of this application, 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. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing this application 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 to this application.

[0057] In the description of this application, the "first feature" and "second feature" may include one or more of such features.

[0058] In the description of this application, the meaning of "a plurality" is two or more.

[0059] In the description of this application, the first feature being "above" or "below" the second feature may include the first and second features being in direct contact, or may include the first and second features not being in direct contact but being in contact through additional features therebetween.

[0060] In the description of the present application, the first feature being "above", "over" or "on" the second feature includes the first feature being directly above and obliquely above the second feature, or merely indicating that the horizontal height of the first feature is higher than that of the second feature.

[0061] In the description of this specification, the description with reference to terms such as "one embodiment", "some embodiments", "schematic embodiments", "examples", "specific examples" or "some examples", etc. means 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 application. In this specification, the schematic representations of the above terms do not necessarily refer 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.

[0062] Although the embodiments of the present application have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present application, and the scope of the present application is defined by the claims and their equivalents.

Claims

1. A turbine rim seal system for a gas turbine, characterized in that, Comprising: A rotating disc, on which a rotating disc seal ring is provided. A stationary disc, on one axial side of which a sealing shoulder and a stationary disc seal ring are provided. The sealing shoulder is connected to the stationary disc seal ring and defines a sealing cavity. The stationary disc seal ring and the rotating disc seal ring are arranged opposite to each other in the radial direction, and a sealing gap is formed between the stationary disc seal ring and the rotating disc seal ring. A detection component, which is arranged on the inner wall of the sealing cavity to be adapted to detect the thermal strain of the sealing cavity wall. A cooling system, which is connected to the sealing cavity and is adapted to selectively introduce a cooling air flow into the sealing cavity according to the detection result of the detection component to adjust the air flow temperature in the sealing cavity.

2. The turbine rim seal system of a gas turbine according to claim 1, wherein The detection component includes: Sensors, which are configured to be at least eight and are arranged at intervals along the circumferential direction of the stationary disc seal ring.

3. The turbine rim seal system of a gas turbine according to claim 2, characterized in that, The sensors are configured as high-temperature resistant fiber Bragg grating sensors.

4. The turbine rim seal system of a gas turbine according to claim 2, characterized in that, The detection component further includes: A control terminal, which is arranged outside the gas turbine and communicates wirelessly with each of the sensors.

5. The turbine rim seal system of a gas turbine according to claim 1, characterized in that, The stationary disc is provided with a cooling channel communicating the sealing cavity with the outside of the gas turbine. The cooling system includes a ceramic sleeve, which is arranged in the cooling channel and communicates with the sealing cavity.

6. The turbine rim seal system of a gas turbine according to claim 5, characterized in that, The ceramic sleeve is formed with honeycomb-shaped pores.

7. The turbine rim seal system of a gas turbine according to claim 1, characterized in that, The rotating disc seal ring is detachably connected to the rotating disc.

8. The turbine rim seal system of a gas turbine according to claim 7, characterized in that, An installation part is formed on the rotating disc seal ring, and an installation groove for cooperating with the installation part is formed on the rotating disc.

9. The turbine rim seal system of a gas turbine according to claim 7, characterized in that, The rotating disc seal ring and the rotating disc are connected by bolts, and the bolts are installed radially outward along the gas turbine.

10. The turbine rim seal system of a gas turbine according to claim 1, characterized in that, On one side of the stationary disc seal ring facing the rotating disc seal ring, labyrinth teeth are provided. On one side of the rotating disc seal ring facing the stationary disc seal ring, a honeycomb core grid is provided. The labyrinth teeth and the honeycomb core grid define the sealing gap.

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