Sealing system of aeroderivative gas turbine

Abstract

The utility model discloses an aeroderivative gas turbine sealing system, and relates to the technical field of gas turbines. The aeroderivative gas turbine sealing system comprises a switching device, and the output end of the switching device communicates with a bearing cavity of the gas compressor. The switching device has a first working state and a second working state; when the switching device is in a first working state, the input end of the switching device is communicated with the instrument gas source; and when the switching device is in the second working state, the input end of the switching device is communicated with the bleed air of the air compressor. The instrument gas source and the switching device are introduced, so that the aeroderivative gas turbine has good sealing performance within the range of all working conditions. And the phenomena of small sealing pressure margin, oil leakage and the like of the aeroderivative gas turbine under a low working condition are avoided.

Description

Technical Field

[0001] The present application relates to the technical field of gas turbines, and in particular to a sealing system for an aero-derivative gas turbine. Background Art

[0002] Aero-derivative gas engines refer to aircraft turbine engines that have been transformed into industrial gas turbines (also generally referred to as turbine gas engines or gas turbines). Specifically, aircraft-derivative gas engines are aircraft turbine engines that have been modified and equipped with power turbines so that their speed and power can meet the needs of land power generation or mechanical traction. During the modification process, except for the power turbine that requires special design, the remaining 60% to 80% of the parts can use the parts of the original aircraft turbine engine, which not only reduces the manufacturing cost, but also retains the excellent performance of the aircraft turbine engine. Due to their small size, light weight, high efficiency and ease of use, aero-derivative gas engines are widely used in power plants, large ships, large vehicles, oil and gas pipeline transportation, and offshore oil and gas platforms.

[0003] In the prior art, the bearing cavity seal of the compressor of the gas turbine is generally sealed with an air seal, and the sealing gas comes from the bleed air of the compressor itself. It should be clear that in the air seal sealing structure, the pressure requirements of the sealing gas are strict, and an appropriate sealing pressure can ensure a good sealing effect and oil and gas leakage, and the bleed air pressure of the compressor is positively correlated with the operating conditions of the gas turbine. In other words, if the gas turbine is under low operating conditions, the bleed air pressure of the compressor cannot achieve effective sealing. The bearing cavity seals of aero-derivative engines are mostly inherited from the prototype. When the aviation turbine engine is modified into a gas turbine, due to the different application characteristics, in order to meet the design requirements of the gas turbine, it is necessary to adjust the aerodynamic performance of the whole machine. The bleed air of the compressor of most aero-derivative engines after adjustment is relatively low under low operating conditions of the gas turbine, which can easily lead to small sealing pressure margin and oil leakage of the aero-derivative engine under low operating conditions. Utility Model Content

[0004] The purpose of the present application is to provide an aeroderivative gas engine sealing system to solve the technical problem that the bearing cavity of the aeroderivative gas engine is prone to oil leakage under low operating conditions.

[0005] To achieve the above objectives, this application provides the following technical solutions:

[0006] A sealing system for an aero-derivative fuel engine, the aero-derivative fuel engine comprising an instrument air source and a compressor, the sealing system comprising a switching device, the output end of the switching device being connected to a bearing cavity of the compressor; the switching device having a first working state and a second working state; when the switching device is in the first working state, the input end of the switching device is connected to the instrument air source; when the switching device is in the second working state, the input end of the switching device is connected to the bleed air of the compressor.

[0007] As a specific solution in the technical solution of the present application, the switching device includes a three-way valve.

[0008] As a specific solution in the technical solution of the present application, the three-way valve includes a solenoid valve; the switching device also includes a first pressure sensor arranged between the instrument air source and the three-way valve, and a second pressure sensor arranged between the bleed air of the compressor and the three-way valve.

[0009] As a specific solution in the technical solution of this application, the switching device includes:

[0010] An adjusting tube having an adjusting cavity arranged therein;

[0011] a first air inlet pipe, a second air inlet pipe and an air outlet pipe; wherein the first ends of the first air inlet pipe, the second air inlet pipe and the air outlet pipe are all connected to the regulating chamber; the second end of the first air inlet pipe is used to be connected to the instrument air source; the second end of the second air inlet pipe is used to be connected to the bleed air of the compressor; the second end of the air outlet pipe is used to be connected to the bearing chamber of the compressor;

[0012] A first sliding block is arranged in the regulating chamber and forms a sliding connection with the regulating pipe; when the switching device is in the first working state, the first sliding block blocks the first end of the second air intake pipe; when the switching device is in the second working state, the first sliding block blocks the first end of the first air intake pipe.

[0013] As a specific solution in the technical solution of the present application, the first sliding block forms a sliding connection with the regulating tube along a first direction, and the first direction is parallel to the axial direction of the regulating chamber; the switching device also includes a boosting structure, which is used to increase the sliding resistance of the first sliding block along the first direction.

[0014] As a specific solution in the technical solution of the present application, the boosting structure includes at least one elastic member, each of which stores a first elastic potential energy, and the first elastic potential energy is used to enable the elastic member to apply an elastic force along a first direction to the first sliding block.

[0015] As a specific solution in the technical solution of this application, the boosting structure includes:

[0016] A second sliding block is disposed inside the adjusting tube and is slidably connected with the adjusting tube along a first direction;

[0017] At least one elastic member disposed between the first sliding block and the second sliding block, each elastic member storing a first elastic potential energy, and the first elastic potential energy is used to enable the elastic member to apply an elastic force along a first direction to the first sliding block;

[0018] The driving member is used to drive the second sliding block to reciprocate along the first direction.

[0019] As a specific solution in the technical solution of the present application, the driving member includes an electric push rod or a hydraulic push rod, or the driving member includes a threaded rod, the threaded rod is threadedly connected to the second sliding block, and the axis of the threaded rod is parallel to the first direction.

[0020] As a specific solution in the technical solution of the present application, the inner wall of the adjusting tube is provided with at least one guide strip, and each guide strip extends along the first direction; the first sliding block is provided with guide grooves corresponding to each guide strip one by one; or, the inner wall of the adjusting tube is provided with at least one guide strip, and each guide groove extends along the first direction; the first sliding block is provided with guide strips corresponding to each guide groove one by one.

[0021] As a specific solution in the technical solution of the present application, a pressure regulating valve is also provided between the instrument air source and the switching device.

[0022] Compared with the prior art, the beneficial effects of this application are:

[0023] The present application introduces an instrument air source and a switching device, so that the aeroderivative gas engine has good sealing performance in the full range of operating conditions, thereby avoiding the occurrence of small sealing pressure margin and oil leakage in the aeroderivative gas engine under low operating conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is a schematic diagram of the structure of an aero-derivative engine sealing system proposed in an embodiment of the present application;

[0025] Figure 2 A three-dimensional schematic diagram of a switching device proposed in an embodiment of the present application;

[0026] Figure 3 A cross-sectional schematic diagram of a switching device proposed in an embodiment of the present application (the switching device is in a first working state);

[0027] Figure 4A cross-sectional schematic diagram of a switching device proposed in an embodiment of the present application (the switching device is in a second working state);

[0028] Figure 5 A cross-sectional schematic diagram of another switching device proposed in an embodiment of the present application;

[0029] Figure 6 A cross-sectional schematic diagram of another switching device proposed in an embodiment of the present application;

[0030] Figure 7 A schematic diagram of a regulating tube and a first sliding block limiting position proposed in an embodiment of the present application;

[0031] Figure 8 for Figure 6 Magnified view of part C.

[0032] In the figure: 1. instrument air source; 2. pressure regulating valve; 3. compressor; 4. switching device; 41. three-way valve; 42. first pressure sensor; 43. second pressure sensor; 44. regulating tube; 441. regulating cavity; 442. guide strip; 45. first air inlet pipe; 46. air outlet pipe; 47. second air inlet pipe; 48. first sliding block; 481. guide groove; 49. boost structure; 491. elastic member; 492. second sliding block; 493. threaded rod; 5. bearing cavity. DETAILED DESCRIPTION

[0033] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0034] It should be noted that, in the description of the present application, the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description. They do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore should not be understood as a limitation on the present application.

[0035] Furthermore, it should be understood that for the sake of ease of description, the sizes of the various components shown in the drawings are not drawn according to actual proportions. For example, the thickness or width of certain layers may be exaggerated relative to other layers.

[0036] It should be noted that like reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined or described in one drawing, it will not require further detailed discussion and description in the description of the subsequent drawings.

[0037] In order to solve the technical problems raised by the background technology, the present application proposes an embodiment of an aero-derivative engine sealing system. Specifically, the aero-derivative engine includes an instrument air source 1 and a compressor 3. Since the instrument air source 1 and the compressor 3 are mature technologies, they are not described here. Specifically, the aero-derivative engine sealing system includes a switching device 4. Among them, if Figure 1 As shown, the output end of the switching device 4 is connected to the bearing cavity 5 of the compressor 3. The switching device 4 has a first working state and a second working state. When the switching device 4 is in the first working state, the input end of the switching device 4 is connected to the instrument air source 1. When the switching device 4 is in the second working state, the input end of the switching device 4 is connected to the bleed air of the compressor 3.

[0038] When using, Figure 1 As shown, if the aircraft-derivative engine is in a high operating state, that is, the bleed air pressure of the compressor 3 in the aircraft-derivative engine can meet the sealing requirements of the bearing cavity 5 in the compressor 3, the switching device 4 can be switched to the second working state, that is, the input end of the switching device 4 is connected to the bleed air of the compressor 3. In other words, at this time, the bearing cavity 5 is sealed by the bleed air of the compressor 3. If the aircraft-derivative engine is in a low operating state, that is, the bleed air pressure of the compressor 3 in the aircraft-derivative engine cannot meet the sealing requirements of the bearing cavity 5 in the compressor 3, the switching device 4 can be switched to the first working state, that is, the input end of the switching device 4 is connected to the instrument air source 1. In other words, at this time, the bearing cavity 5 is sealed by the instrument air source 1. It is easy to understand that in the embodiments of the present application, the working state of the switching device 4 can be changed based on the real-time working condition of the aircraft-derivative engine, so that the bearing cavity 5 of the compressor 3 of the aircraft-derivative engine can have good sealing performance within the full range of working conditions.

[0039] It should be clear that the embodiments of the present application introduce instrument air sources and switching devices, so that the aeroderivative engine has good sealing performance in the full range of operating conditions, thereby avoiding the occurrence of small sealing pressure margin and oil leakage in the aeroderivative engine under low operating conditions.

[0040] It should be clear that in the embodiments of the present application, the switching device 4 can be any device that can switch the connectivity state of its input end. For example, in one embodiment of the present application, the switching device 4 can be a three-way valve 41. When in use, by switching the three-way valve 41, the instrument air source 1 or the bleed air of the compressor 3 can be freely selected to be connected to the input end of the three-way valve 41. In the embodiments of the present application, the three-way valve 41 can be a manually switched valve or an automatically switched valve. In order to enable the three-way valve 41 to be automatically controlled, in another embodiment of the present application, the three-way valve 41 can be a solenoid valve. The switching device 4 also includes a first pressure sensor 42 arranged between the instrument air source 1 and the three-way valve 41, and a second pressure sensor 43 arranged between the bleed air of the compressor 3 and the three-way valve 41. As Figure 1 As shown, the first pressure sensor 42 is used to monitor the pressure of the sealing gas provided by the instrument gas source 1; the second pressure sensor 43 is used to monitor the pressure of the sealing gas provided by the bleed air of the compressor 3. Figure 1 As shown, if the operating condition of the aeroderivative engine is relatively small, and the second pressure sensor 43 detects that the bleed air of the compressor 3 is insufficient to meet the sealing requirement of the bearing cavity 5, the electromagnetic valve can be automatically controlled to connect the input end of the electromagnetic valve with the instrument air source 1, that is, the bearing cavity 5 is sealed by the sealing gas provided by the instrument air source 1. The arrangement of the electromagnetic valve, the first pressure sensor 42 and the second pressure sensor 43 can realize the fully automatic control of the sealing of the bearing cavity 5 of the compressor 3.

[0041] It should be clear that in the automatic control process, with the increase of electronic equipment (such as solenoid valves and pressure sensors, etc.), the structure and function of the sealing system become more complex. This leads to an increase in the interactions and dependencies between the various parts of the sealing system, making the operation and maintenance of the entire sealing system more difficult. And each electronic device itself may have potential failure points. When the number of electronic devices in the sealing system increases, the probability of failure will also increase accordingly. Moreover, the failure of one electronic device may affect the normal operation of other electronic devices, and thus affect the stability of the entire sealing system. In order to improve the stability of the sealing system, in one embodiment of the present application, the switching device 4 includes a regulating tube 44, a first air inlet pipe 45, a second air inlet pipe 47, an air outlet pipe 46 and a first sliding block 48. Among them, as Figure 3 As shown, the interior of the regulating tube 44 is provided with a regulating chamber 441. Figure 2 and Figure 3 As shown, the first ends of the first air inlet pipe 45, the second air inlet pipe 47 and the air outlet pipe 46 are all connected to the regulating chamber 441; the second end of the first air inlet pipe 45 is used to be connected to the instrument air source 1; the second end of the second air inlet pipe 47 is used to be connected to the bleed air of the compressor 3; the second end of the air outlet pipe 46 is used to be connected to the bearing chamber 5 of the compressor 3. Figure 3 As shown, the first sliding block 48 is arranged in the regulating chamber 441 and forms a sliding connection with the regulating tube 44; when the switching device 4 is in the first working state, the first sliding block 48 blocks the first end of the second air inlet pipe 47; when the switching device 4 is in the second working state, the first sliding block 48 blocks the first end of the first air inlet pipe 45.

[0042] When using, Figure 3 As shown in FIG. 1 , if the operating condition of the aero-derivative engine is relatively small, the bleed air pressure of the compressor 3 is less than the gas pressure of the instrument gas source 1 (the friction between the first sliding block 48 and the regulating pipe 44 is negligible), then the first sliding block 48 moves toward the first end of the second air inlet pipe 47 under the action of the gas pressure of the instrument gas source 1 until the first end of the second air inlet pipe 47 is blocked. At this time, the gas provided by the instrument gas source 1 is as follows: Figure 3 , Figure 5 and Figure 6 As shown in the route A in FIG, the bearing cavity 5 of the compressor 3 is sealed. If the operating condition of the aircraft-derivative engine is large, the bleed air pressure of the compressor 3 is greater than the gas pressure of the instrument gas source 1 (the friction between the first sliding block 48 and the regulating pipe 44 is negligible), then the first sliding block 48 moves toward the first end of the first intake pipe 45 under the pressure of the bleed air of the compressor 3 until the first end of the first intake pipe 45 is blocked. At this time, the gas provided by the bleed air of the compressor 3 is as follows: Figure 4 As shown in route B in FIG. 1 , the bearing chamber 5 of the compressor 3 is sealed.

[0043] It should be clear that in the embodiment of the present application, the gas pressure (hereinafter referred to as the first pressure) provided by the instrument gas source 1 can be adjusted to be greater than the critical pressure required for the sealing of the bearing cavity 5 of the compressor 3. In other words, if the bleed air of the compressor 3 is less than the first pressure, the input end of the switching device 4 is automatically switched to be connected to the instrument gas source 1; if the bleed air of the compressor 3 is greater than the first pressure, the input end of the switching device 4 is automatically switched to be connected to the bleed air of the compressor 3. It can realize automatic switching without the help of any electronic equipment, which is conducive to improving the reliability of the sealing system.

[0044] In the embodiment of the present application, in order to stabilize the gas pressure provided by the instrument gas source 1, a pressure regulating valve 2 may be provided between the instrument gas source 1 and the switching device 4. Figure 1 As shown, by setting the pressure regulating valve 2, the instrument gas source 1 can provide sealing gas with stable pressure, further ensuring the stability of the sealing of the bearing cavity 5 of the compressor 3.

[0045] From the previous text, we can see that Figure 3 and Figure 4The switching device 4 shown realizes automatic control of the switching device 4 through the pressure difference between the bleed air of the compressor 3 and the gas provided by the instrument air source 1. In other words, during the long-term use of the aircraft-derivative fuel engine, if the bleed air pressure of the compressor 3 is greater than the critical pressure required for the sealing of the bearing cavity 5, and the bleed air pressure of the compressor 3 fluctuates repeatedly at the first pressure (that is, the bleed air pressure of the compressor 3 is similar to the gas pressure provided by the instrument air source 1), it will cause the first sliding block 48 to perform frequent reciprocating motions, thereby reducing the service life of the first sliding block 48. In order to make the pressure of the bleed air of the compressor 3 similar to that of the gas provided by the instrument air source 1, there is also a certain pressure difference on both sides of the first sliding block 48, thereby avoiding frequent reciprocating motions of the first sliding block 48, that is, increasing the service life of the first sliding block 48. In one embodiment of the present application, the first sliding block 48 forms a sliding connection with the regulating tube 44 along a first direction, and the first direction is parallel to the axial direction of the regulating chamber 441; the switching device 4 also includes a boosting structure 49, and the boosting structure 49 is used to increase the sliding resistance of the first sliding block 48 along the first direction. It should be clear that the pressure difference on both sides of the first sliding block 48 can be increased by setting the boosting structure 49. Figure 8 As shown, the pressure applied to the first sliding block 48 by the gas provided by the instrument air source 1 is F1, the pressure applied to the first sliding block 48 by the bleed air of the compressor 3 is F2, and the pressure applied to the first sliding block 48 by the boost structure 49 is F3. It is easy to understand that if the pressure of the bleed air of the compressor 3 is similar to that of the gas provided by the instrument air source 1 (that is, the pressure F1 is similar to the pressure F2), then under the action of the pressure F3, the position of the first sliding block 48 can also be fixed, that is, the first sliding block 48 will not perform frequent reciprocating motions.

[0046] In the embodiment of the present application, the boost structure 49 may include at least one elastic member 491. Figure 5 As shown, each elastic member 491 stores a first elastic potential energy, and the first elastic potential energy is used to enable the elastic member 491 to apply an elastic force along a first direction to the first sliding block 48. In the embodiment of the present application, the elastic member 491 may be a spring or an elastic sheet.

[0047] In order to adjust the pressure (i.e., pressure F3) generated by the boosting structure 49, in one embodiment of the present application, the boosting structure 49 may include a second sliding block 492, a driving member, and at least one elastic member 491 disposed between the first sliding block 48 and the second sliding block 492. Figure 6As shown, the second sliding block 492 is disposed inside the adjusting tube 44 and forms a sliding connection with the adjusting tube 44 along the first direction. Each elastic member 491 stores a first elastic potential energy, and the first elastic potential energy is used to enable the elastic member 491 to apply an elastic force along the first direction to the first sliding block 48. The driving member is used to drive the second sliding block 492 to reciprocate along the first direction.

[0048] When in use, the second sliding block 492 is driven by the driving member to move along the first direction. Figure 6 As shown, if the distance between the second sliding block 492 and the first end of the first air intake pipe 45 along the first direction is smaller, the pressure generated by the boost structure 49 is greater; if the distance between the second sliding block 492 and the first end of the first air intake pipe 45 along the first direction is larger, the pressure generated by the boost structure 49 is smaller.

[0049] In an embodiment of the present application, the first end of each elastic member 491 may be in contact with the first sliding block 48, and the second end of each elastic member 491 may be in contact with the second sliding block 492. At this time, the boosting structure 49 can only generate pressure from the second sliding block 492 to the first sliding block 48. In order to make the boosting structure 49 apply pressure from the first sliding block 48 to the second sliding block 492 to the first sliding block 48. In another embodiment of the present application, the first end of each elastic member 491 may be connected to the first sliding block 48, and the second end of each elastic member 491 may be connected to the second sliding block 492.

[0050] In an embodiment of the present application, the driving member may be any component that can drive the second sliding block 492 to reciprocate along the first direction. For example, in an embodiment of the present application, the driving member may include an electric push rod or a hydraulic push rod; Figure 6 As shown, the driving member may further include a threaded rod 493, which is threadedly connected to the second sliding block 492, and the axis of the threaded rod 493 is parallel to the first direction. When in use, the threaded rod 493 may be rotated manually or driven by a motor (not shown in the figure).

[0051] In order to prevent the first sliding block 48 from rotating circumferentially during the movement along the first direction, in one embodiment of the present application, Figure 7As shown, the inner wall of the adjusting tube 44 is provided with at least one guide bar 442, and each guide bar 442 extends along the first direction; the first sliding block 48 is provided with guide grooves 481 corresponding to each guide bar 442. The provision of the guide bars 442 and the guide grooves 481 can prevent the first sliding block 48 from rotating in the circumferential direction. It is easy to understand that in other embodiments of the present application, in order to achieve the above purpose, at least one guide groove 481 can be provided on the inner wall of the adjusting tube 44, and each guide groove 481 extends along the first direction; the first sliding block 48 is provided with guide bars 442 corresponding to each guide groove 481.

[0052] It should be clear that the embodiments of the present application introduce instrument air sources and switching devices, so that the aeroderivative engine has good sealing performance in the full range of operating conditions, thereby avoiding the occurrence of small sealing pressure margin and oil leakage in the aeroderivative engine under low operating conditions.

[0053] Although the embodiments of the present application have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present application, and that the scope of the present application is defined by the appended claims and their equivalents.

Claims

1. An aeroderivative gas engine sealing system, the aeroderivative gas engine comprising an instrument air source (1) and a compressor (3), characterized in that: The aero-derivative engine sealing system comprises a switching device (4), the output end of the switching device (4) is connected to the bearing cavity (5) of the compressor (3); the switching device (4) has a first working state and a second working state; when the switching device (4) is in the first working state, the input end of the switching device (4) is connected to the instrument air source (1); when the switching device (4) is in the second working state, the input end of the switching device (4) is connected to the bleed air of the compressor (3).

2. The aero-derivative engine sealing system according to claim 1, characterized in that: The switching device (4) comprises a three-way valve (41).

3. The aero-derivative engine sealing system according to claim 2, characterized in that: The three-way valve (41) comprises a solenoid valve; the switching device (4) further comprises a first pressure sensor (42) arranged between the instrument air source (1) and the three-way valve (41), and a second pressure sensor (43) arranged between the bleed air of the compressor (3) and the three-way valve (41).

4. The aero-derivative engine sealing system according to claim 1, characterized in that: The switching device (4) comprises: An adjusting tube (44) having an adjusting chamber (441) disposed therein; a first air inlet pipe (45), a second air inlet pipe (47) and an air outlet pipe (46); wherein the first ends of the first air inlet pipe (45), the second air inlet pipe (47) and the air outlet pipe (46) are all in communication with the regulating chamber (441); the second end of the first air inlet pipe (45) is used to be in communication with the instrument air source (1); the second end of the second air inlet pipe (47) is used to be in communication with the bleed air of the compressor (3); the second end of the air outlet pipe (46) is used to be in communication with the bearing chamber (5) of the compressor (3); A first sliding block (48) is arranged in the regulating chamber (441) and is slidably connected to the regulating pipe (44); when the switching device (4) is in a first working state, the first sliding block (48) blocks the first end of the second air intake pipe (47); when the switching device (4) is in a second working state, the first sliding block (48) blocks the first end of the first air intake pipe (45).

5. The aero-derivative engine sealing system according to claim 4, characterized in that: The first sliding block (48) forms a sliding connection with the regulating tube (44) along a first direction, and the first direction is parallel to the axial direction of the regulating chamber (441); the switching device (4) also includes a boosting structure (49), and the boosting structure (49) is used to increase the sliding resistance of the first sliding block (48) along the first direction.

6. The aero-derivative engine sealing system according to claim 5, characterized in that: The boost structure (49) comprises at least one elastic member (491), each elastic member (491) stores a first elastic potential energy, and the first elastic potential energy is used to enable the elastic member (491) to apply an elastic force along a first direction to the first sliding block (48).

7. The aero-derivative engine sealing system according to claim 5, characterized in that: The boost structure (49) comprises: A second sliding block (492) is disposed inside the adjusting tube (44) and is slidably connected with the adjusting tube (44) along a first direction; At least one elastic member (491) is disposed between the first sliding block (48) and the second sliding block (492), each elastic member (491) storing a first elastic potential energy, and the first elastic potential energy is used to enable the elastic member (491) to apply an elastic force along a first direction to the first sliding block (48); A driving member is used to drive the second sliding block (492) to reciprocate along a first direction.

8. The aero-derivative engine sealing system according to claim 7, characterized in that: The driving member includes an electric push rod or a hydraulic push rod, or the driving member includes a threaded rod (493), the threaded rod (493) is threadedly connected to the second sliding block (492), and the axis of the threaded rod (493) is parallel to the first direction.

9. The aeroderivative engine sealing system according to any one of claims 4 to 8, characterized in that: The inner wall of the adjusting tube (44) is provided with at least one guide bar (442), and each guide bar (442) extends along the first direction; the first sliding block (48) is provided with guide grooves (481) corresponding to each guide bar (442) one by one; or, the inner wall of the adjusting tube (44) is provided with at least one guide groove (481), and each guide groove (481) extends along the first direction; the first sliding block (48) is provided with guide bars (442) corresponding to each guide groove (481) one by one.

10. The aeroderivative engine sealing system according to any one of claims 1 to 8, characterized in that: A pressure regulating valve (2) is also provided between the instrument air source (1) and the switching device (4).

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