Gas turbine compressor blade cleaning and inspection port plugging structure

Abstract

The application belongs to the technical field of gas turbine compressor structure design, and particularly relates to a gas turbine compressor blade cleaning and inspection hole plugging structure, which is installed by means of an inspection hole formed on a compressor casing, the size of the inspection hole can be designed according to the needs of structure installation, the compressor blade can be cleaned offline and online through a simple mode switching, the compressor blade can be cleaned in a large angle and range, has high cleaning effect and efficiency, and has a plug function, so that the related structure can be removed to check the inner side of the compressor casing, and the overall structure is compact and has great convenience.

Description

Technical Field

[0001] This application belongs to the technical field of gas turbine compressor structure design, specifically relating to a gas turbine compressor blade cleaning and inspection hole sealing structure. Background Technology

[0002] When a gas turbine is working, it will draw in impurities such as dust, smoke, salt spray, and oil from the air. These impurities will adhere to the compressor blades, corrode the compressor blades, and affect the compressor's aerodynamic performance. Therefore, it is necessary to clean the compressor blades to keep them clean.

[0003] Currently, the cleaning of compressor blades involves shutting down the gas turbine, allowing all components to cool, inserting cleaning nozzles into inspection holes in the compressor casing, introducing cleaning fluid, and then starting the gas turbine for cold running to perform offline cleaning of the compressor blades. This technical solution has the following drawbacks:

[0004] 1) The cleaning nozzle is installed by means of the inspection hole on the compressor casing. Each time the compressor blades are cleaned, the plug of the inspection hole needs to be removed first, the cleaning nozzle is installed in it, and after the compressor blades are cleaned, the cleaning nozzle is removed again and the inspection hole is resealed with the plug. The operation is cumbersome and the operation time is long.

[0005] 2) Due to the size limitation of the inspection hole on the compressor casing, the cleaning nozzles used are usually small in size, often using single-hole nozzles. The spray angle is small, the atomization effect is poor, the cleaning effect on the compressor blades is poor, and the cleaning efficiency is not high.

[0006] 3) It can only clean the compressor blades offline, and cannot clean the compressor blades online while the gas turbine is working. This requires frequent shutdowns of the gas turbine, which affects the continuous operation of the gas turbine.

[0007] This application is made in view of the aforementioned technical deficiencies. Summary of the Invention

[0008] The purpose of this application is to provide a gas turbine compressor blade cleaning and inspection hole sealing structure to overcome or mitigate at least one of the known technical defects.

[0009] The technical solution of this application is:

[0010] A gas turbine compressor blade cleaning and inspection hole sealing structure includes an inner cylinder, a nozzle, an inner spring, an outer cylinder, a lower plug, an inner plug, an upper plug, an intermediate spring, and an outer spring.

[0011] The lower end of the inner cylinder has an outward folded edge, which is connected to the compressor casing and surrounds the inspection hole opened on the compressor casing. The upper end of the inner cylinder has an inward folded edge.

[0012] The inner cylinder sidewall has a small-diameter online cleaning channel and a large-diameter offline cleaning channel. The small-diameter online cleaning channel and the large-diameter offline cleaning channel form the channel inlet at the outer annular folded edge of the inner cylinder, and the small-diameter online cleaning channel forms the channel outlet on the inner side of the upper sidewall of the inner cylinder, while the large-diameter offline cleaning channel forms the channel outlet on the inner side of the lower sidewall of the inner cylinder.

[0013] The nozzle has a cylindrical structure and is installed inside the inner cylinder. It has an outward folded edge at the upper end, which is attached to the inner wall of the inner cylinder. The lower end of the nozzle extends into the inspection hole.

[0014] The nozzle sidewall has a small-diameter online cleaning channel and a large-diameter offline cleaning channel. The small-diameter online cleaning channel and the large-diameter offline cleaning channel form a channel inlet at the outward folded edge of the nozzle. The small-diameter online cleaning channel forms a channel nozzle at the lower end of the nozzle, and the large-diameter offline cleaning channel forms multiple channel nozzles distributed along the axial direction on the outer wall of the lower end of the nozzle.

[0015] The inner spring is installed inside the inner cylinder and sleeved on the outer periphery of the nozzle. Its two ends abut against the annular boss of the compressor casing and the outward folded edge of the nozzle, so that the outward folded edge of the nozzle is pressed against the inward folded edge of the inner cylinder, making the lower end of the nozzle flush with the inner side of the compressor casing, and aligning the inlet of the small-diameter online cleaning channel with the outlet of the small-diameter online cleaning channel.

[0016] The outer cylinder is fitted around the outer periphery of the inner cylinder, and has an inward folded edge at the upper end, forming an irregular hole between the inward folded edges. The lower end of the outer cylinder has an outward folded edge, which presses against the outward annular folded edge of the inner cylinder.

[0017] The lower plug has a cylindrical structure and is installed inside the outer cylinder. The lower end is sealed and extends into the nozzle. The upper end is open, and the side wall has two axial grooves distributed at 180 degrees. The upper end of the two axial grooves forms an opening at the upper end of the lower plug, and the lower end is connected to a circumferential groove. The ends of the two circumferential grooves have upward positioning openings.

[0018] The inner plug has a cylindrical structure and is installed inside the lower plug. The upper outer wall has two sliding protrusions that extend from two axial grooves and are located above the nozzle.

[0019] The upper plug is connected to the upper end of the lower plug. The outer wall has two opposing fins. The lower end extends into the lower plug, and the upper end has an irregular protrusion.

[0020] The middle spring is installed inside the lower plug and is sleeved on the outer circumference of the inner plug. Its two ends abut against the lower end of the lower plug and the two sliding protrusions of the inner plug, so that the upper end of the inner plug is pushed against the lower end of the upper plug.

[0021] The outer spring is installed inside the outer cylinder and sleeved on the outer circumference of the inner cylinder. Its two ends abut against the washer ring and the two wing edges, and the two wing edges are pressed against the inward folded edge of the outer cylinder, so that the irregular protrusion is stuck in the irregular hole.

[0022] According to at least one embodiment of this application, in the above-mentioned gas turbine compressor blade cleaning and inspection hole sealing structure, pressing down on the inner plug allows it to overcome the elastic force of the intermediate spring and slide downward along the axial groove, causing the two sliding protrusions to press against the upper end of the nozzle, thereby driving the nozzle to overcome the elastic force of the inner spring and slide downward, so that the lower end of the nozzle extends into the compressor casing. After the two sliding protrusions reach the lower end of the axial groove, turning the inner plug allows it to rotate along the circumferential groove, causing the sliding protrusions to enter the circumferential groove. After the sliding protrusions reach the end of the circumferential groove, releasing the inner plug allows the sliding protrusions to be inserted upward into the positioning port under the action of the inner spring, thereby achieving the positioning of the inner plug and the nozzle. At this time, the inlet of the large-diameter offline cleaning channel is aligned with the outlet of the large-diameter offline cleaning channel, and the nozzle of the large-diameter offline cleaning channel is exposed inside the compressor casing.

[0023] According to at least one embodiment of this application, in the above-described gas turbine compressor blade cleaning and inspection hole sealing structure, pressing down on the upper plug can cause the upper plug to overcome the elastic force of the outer spring and the middle spring, slide downward, and cause the irregular protrusion to dislodge from the irregular hole. Then, the upper plug can be turned and adjusted so that the fin of the upper plug is aligned with the irregular hole. Then, the upper plug, lower plug, inner plug, and middle spring can be removed through the irregular hole, exposing the internal space of the nozzle.

[0024] According to at least one embodiment of this application, in the above-described gas turbine compressor blade cleaning and inspection hole sealing structure, the outward folded edge of the inner cylinder is connected to the annular boss of the compressor casing and positioned with the annular boss by a stop, and the annular boss surrounds the inspection hole opened on the compressor casing.

[0025] Two sealing rings are set on the outward folded edge of the nozzle to form a seal with the inner cylinder. The inlet of the small-diameter online cleaning channel and the large-diameter offline cleaning channel is between the two sealing rings.

[0026] There are multiple small-aperture online cleaning channels and their corresponding small-aperture online cleaning flow channels.

[0027] According to at least one embodiment of this application, the above-described gas turbine compressor blade cleaning and inspection hole sealing structure further includes a gasket ring;

[0028] The gasket is fitted around the outer circumference of the inner cylinder and presses against the outward annular folded edge of the inner cylinder.

[0029] The outward folded edge of the outer cylinder presses against the gasket, and the gasket is positioned by a stop.

[0030] According to at least one embodiment of this application, in the above-mentioned gas turbine compressor blade cleaning and inspection hole sealing structure, the irregular hole formed between the inward folds of the outer cylinder is a flat oval hole.

[0031] The upper end of the inner plug is formed with a square groove.

[0032] The upper plug has a threaded through hole running vertically through it, with its lower end extending into the lower plug. The irregularly shaped protrusion on it is a square protrusion.

[0033] According to at least one embodiment of this application, in the above-mentioned gas turbine compressor blade cleaning and inspection hole sealing structure, there are multiple large-diameter offline cleaning channels and large-diameter offline cleaning flow channels, specifically designed as 6, with 3 in the forward direction and 3 in the backward direction, and distributed at a 30° interval between each other.

[0034] The inner cylinder and the nozzle are connected by an axial track.

[0035] According to at least one embodiment of this application, in the above-mentioned gas turbine compressor blade cleaning and inspection hole sealing structure, the sliding protrusion on the inner plug is stuck in the irregular opening formed by the inward folding edge of the inner cylinder. The lower plug and the upper plug are rotatably connected. The outer wall at the upper end of the lower plug has an outward boss, and the lower part of the upper plug has an annular groove surrounding the outward boss. A torsion spring is provided in the annular groove. The two ends of the torsion spring are connected to the outward boss and the annular groove, so that the wing edge on the upper plug and the sliding protrusion on the lower plug remain aligned in the natural state.

[0036] According to at least one embodiment of this application, in the above-mentioned gas turbine compressor blade cleaning and inspection hole sealing structure, the upper plug and the lower plug are connected by a limiting protrusion and a limiting groove.

[0037] A blocking plate is fitted onto the lower plug, which is connected to the lower part of the upper plug to seal the annular groove. The blocking plate is made of two semi-circular plates joined together.

[0038] The lower end of the lower plug has a through hole, and the lower end of the inner plug is inserted into the through hole, flush with the inner side of the compressor casing.

[0039] According to at least one embodiment of this application, in the above-mentioned gas turbine compressor blade cleaning and inspection hole sealing structure, the lower plug and the inner cylinder are connected by an axial stop groove and a stop protrusion, or the lower plug and the nozzle are connected by an axial slide rail, or the sliding protrusion on the plug is stuck in the limiting groove opened on the upper end face of the nozzle.

[0040] This application has at least the following beneficial technical effects:

[0041] A gas turbine compressor blade cleaning and inspection hole sealing structure is provided. It is installed using an inspection hole opened on the compressor casing. The size of the inspection hole can be designed according to the structural installation requirements. It can perform offline and online cleaning of compressor blades through simple mode switching, and can clean compressor blades at a large angle and within a wide range. It has high cleaning effect and efficiency, and integrates a plugging function. The relevant structure can be removed to inspect the inside of the compressor casing. The overall structure is compact and has great convenience. Attached Figure Description

[0042] Figure 1 This is a schematic diagram of the gas turbine compressor blade cleaning and inspection hole sealing structure provided in the embodiments of this application;

[0043] Figure 2 This is a schematic diagram of the inner cylinder provided in an embodiment of this application;

[0044] Figure 3 yes Figure 1 Top view;

[0045] Figure 4 This is a schematic diagram of the nozzle provided in an embodiment of this application;

[0046] Figure 5 yes Figure 4 Top view;

[0047] Figure 6 This is a top view of the outer cylinder provided in the embodiment of this application;

[0048] Figure 7 This is a schematic diagram of the lower plug, inner plug, upper plug, and intermediate spring provided in the embodiments of this application;

[0049] Figure 8 This is a top view of the inner plug and the upper plug provided in the embodiments of this application;

[0050] Figure 9 This is a top view of the inner plug provided in an embodiment of this application;

[0051] Figure 10 This is a schematic diagram of the lower plug provided in an embodiment of this application;

[0052] Figure 11 This is a schematic diagram of the gas turbine compressor blade cleaning and inspection hole sealing structure provided in the embodiments of this application for online cleaning of compressor blades;

[0053] Figure 12 This is a schematic diagram of the gas turbine compressor blade cleaning and inspection hole sealing structure provided in the embodiments of this application for offline cleaning of compressor blades;

[0054] Figure 13 This is a schematic diagram of the gas turbine compressor blade cleaning and inspection hole sealing structure provided in the embodiments of this application for inspecting the inside of the compressor;

[0055] Figure 14 This is a partial structural schematic diagram of a further improvement to the gas turbine compressor blade cleaning and inspection hole sealing structure provided in the embodiments of this application;

[0056] Figure 15 This is a schematic diagram of the blocking plate provided in an embodiment of this application;

[0057] Figure 16 This is a schematic diagram of the connection between the lower plug and the upper plug, and the limiting protrusion and limiting groove provided in the embodiments of this application;

[0058] Figure 17 This is a schematic diagram of the improved gas turbine compressor blade cleaning and inspection hole sealing structure provided in this application embodiment for online cleaning of compressor blades;

[0059] Figure 18 This is a schematic diagram of the improved gas turbine compressor blade cleaning and inspection hole sealing structure provided in the embodiments of this application for offline cleaning of compressor blades;

[0060] Figure 19 This is a schematic diagram of the improved gas turbine compressor blade cleaning and inspection hole sealing structure provided in the embodiments of this application, which is used for offline cleaning of compressor blades and subsequent structural reassembly.

[0061] in:

[0062] 1-Inner cylinder; 2-Compressor casing; 3-Nozzle; 4-Inner spring; 5-Washer ring; 6-Outer cylinder; 7-Lower plug; 8-Inner plug; 9-Upper plug; 10-Intermediate spring; 11-Outer spring; 12-Compressor blade; 13-Torsion spring; 14-Plug plate;

[0063] a-Small aperture online cleaning channel; b-Large aperture offline cleaning channel;

[0064] c - Small-aperture online cleaning channel; d - Large-aperture offline cleaning channel.

[0065] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0066] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0067] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0068] Furthermore, the terms indicating location used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0069] A gas turbine compressor blade cleaning and inspection hole sealing structure includes an inner cylinder 1, a nozzle 3, an inner spring 4, a washer 5, an outer cylinder 6, a lower plug 7, an inner plug 8, an upper plug 9, an intermediate spring 10, and an outer spring 11. Figure 1 As shown.

[0070] Inner cylinder 1 Figures 2-3 As shown, the lower end has an outward-facing flange, which is connected to the annular boss of the compressor casing 2 and positioned with the annular boss by a stop. The annular boss surrounds the inspection hole opened on the compressor casing 2. The upper end of the inner cylinder 1 has an inward-facing flange.

[0071] The inner cylinder 1 has a small-diameter online cleaning channel a and a large-diameter offline cleaning channel b on its side wall. The small-diameter online cleaning channel a and the large-diameter offline cleaning channel b form channel inlets at the outer annular folded edge of the inner cylinder 1. The small-diameter online cleaning channel a forms a channel outlet on the inner side of the upper side wall of the inner cylinder 1, and the large-diameter offline cleaning channel b forms a channel outlet on the inner side of the lower side wall of the inner cylinder 1.

[0072] Nozzle 3, such as Figures 4-5As shown, it is a cylindrical structure installed inside the inner cylinder 1, with an outward folded edge at the upper end. The outward folded edge is attached to the inner wall of the inner cylinder 1, and the lower end of the nozzle 3 extends into the inspection hole.

[0073] The nozzle 3 has a small-diameter online cleaning channel c and a large-diameter offline cleaning channel d inside its sidewall. The small-diameter online cleaning channel c and the large-diameter offline cleaning channel d form a channel inlet at the outward folded edge of the nozzle 3. The small-diameter online cleaning channel c forms a channel nozzle at the lower end of the nozzle 3, and the large-diameter offline cleaning channel d forms multiple channel nozzles distributed axially on the outer wall of the lower end of the nozzle 3.

[0074] Two sealing rings are provided on the outward folded edge of nozzle 3 to form a seal with the inner cylinder 1. The inlet of the small-diameter online cleaning channel c and the large-diameter offline cleaning channel d is between the two sealing rings.

[0075] The inner spring 4 is installed inside the inner cylinder 1 and sleeved on the outer periphery of the nozzle 3. Its two ends abut against the annular boss of the compressor casing 2 and the outward folded edge of the nozzle 3, so that the outward folded edge of the nozzle 3 is pressed against the inward folded edge of the inner cylinder 1, making the lower end of the nozzle 3 flush with the inner side of the compressor casing 2, and aligning the inlet of the small-diameter online cleaning channel c with the outlet of the small-diameter online cleaning channel a.

[0076] There are multiple small-aperture online cleaning channels a and their corresponding small-aperture online cleaning channels c, which can be specifically designed as two, arranged at 180°, distributed at the 12 o'clock and 6 o'clock directions.

[0077] The gasket 5 is fitted around the outer periphery of the inner cylinder 1 and presses against the outward annular folded edge of the inner cylinder 1.

[0078] Outer tube 6 Figure 6 As shown, the outer cylinder 6 is fitted around the outer periphery of the inner cylinder 1, and has an inward folded edge at the upper end. An irregular hole is formed between the inward folded edges. Specifically, the irregular hole can be a flat oval hole. The lower end of the outer cylinder 6 has an outward folded edge, which presses on the gasket 5 and is positioned with the gasket 5 by a stop.

[0079] Lower plug 7 Figure 10 As shown, it is a cylindrical structure, installed inside the outer cylinder 6, with the lower end sealed and extending into the nozzle 3. The upper end is open, and the side wall has two axial grooves distributed at 180 degrees. The upper ends of the two axial grooves form openings at the upper end of the lower plug 7, and the lower ends are connected to circumferential grooves. The ends of the two circumferential grooves have upward positioning ports.

[0080] Internal plug 8 Figure 9 As shown, it is a cylindrical structure installed inside the lower plug 7. The upper outer wall has two sliding protrusions that extend from two axial grooves and are located above the nozzle 3. The upper end of the inner plug 8 is formed with a square groove.

[0081] The upper plug 9 is connected to the upper end of the lower plug 7. It has a threaded through hole that runs vertically through the plug. The outer wall has two opposing wing edges. The lower end extends into the lower plug 7, and the upper end has an irregular protrusion, which can be a square protrusion.

[0082] The intermediate spring 10 is installed inside the lower plug 7, sleeved on the outer periphery of the inner plug 8, with both ends abutting against the lower end of the lower plug 7 and the two sliding protrusions of the inner plug 8, thus pressing the upper end of the inner plug 8 against the lower end of the upper plug 9. Figures 7-8 As shown.

[0083] The outer spring 11 is installed inside the outer cylinder 6 and sleeved on the outer periphery of the inner cylinder 1. Its two ends abut against the washer ring 5 and the two wing edges, and the two wing edges are pressed against the inward folded edge of the outer cylinder 6, so that the irregular protrusion is stuck in the irregular hole.

[0084] The gas turbine compressor blade cleaning and inspection hole sealing structure disclosed in the above embodiments can perform online cleaning of the compressor blades 12. The specific process is as follows:

[0085] When the gas turbine is operating, the inlet of the small-aperture online cleaning channel a is connected to a cleaning fluid source, specifically clean water or a cleaning fluid mixed with detergent. The cleaning fluid is introduced into the small-aperture online cleaning channel a, flows through the outlet of channel a and the inlet of channel c, and then into channel c. It is then sprayed into the compressor casing 2 through the nozzle of channel c. Under the action of the airflow within the compressor, the compressor blades 12 are cleaned online. Figure 11 As shown.

[0086] In the gas turbine compressor blade cleaning and inspection hole sealing structure disclosed in the above embodiments, pressing down on the inner plug 8 allows it to overcome the elastic force of the intermediate spring 10 and slide downward along the axial groove, causing the two sliding protrusions to press against the upper end of the nozzle 3. This, in turn, causes the nozzle 3 to overcome the elastic force of the inner spring 4 and slide downward, allowing the lower end of the nozzle 3 to extend into the compressor casing 2. After the two sliding protrusions reach the lower end of the axial groove, turning the inner plug 8 allows it to rotate along the circumferential groove, causing the sliding protrusions to... The nozzle 3 enters the circumferential groove. After the sliding protrusion reaches the end of the circumferential groove, the inner plug 8 is released. Under the action of the inner spring 4, the sliding protrusion will move upward and lock into the positioning port, thereby achieving the positioning of the inner plug 8 and the nozzle 3. At this time, the inlet of the large-aperture offline cleaning channel d is aligned with the outlet of the large-aperture offline cleaning channel b. At the same time, the nozzle of the large-aperture offline cleaning channel d is exposed inside the compressor casing 2. In this way, the compressor blades 12 can be cleaned offline. The specific process is as follows:

[0087] After the gas turbine is shut down and all components have cooled, a square rod is inserted into the threaded hole, and the inner plug 8 is pressed down and then turned to make the sliding protrusion engage with the positioning port. Then, the inlet of the large-aperture offline cleaning channel b is connected to the cleaning fluid source, and cleaning fluid is introduced into the large-aperture offline cleaning channel b. The fluid flows through the outlet of the large-aperture offline cleaning channel b and the inlet of the large-aperture offline cleaning channel d, into the large-aperture offline cleaning channel d, and is sprayed into the compressor casing 2 through the nozzle of the large-aperture offline cleaning channel d, spraying towards the compressor blades 12. The gas turbine is then started for cold operation to perform offline cleaning of the compressor blades 12. Figure 12 As shown.

[0088] Multiple large-aperture offline cleaning channels b and d can be designed, specifically 6 channels, 3 forward and 3 backward, distributed at 30° intervals between each other, to increase the angle, range, effect and efficiency of offline cleaning of compressor blades 12.

[0089] The inner cylinder 1 and the nozzle 3 can be designed to be connected by an axial track to avoid relative circumferential rotation between them.

[0090] After the compressor blades 12 are cleaned offline, the square rod can be inserted into the threaded hole again, and the inner plug 8 can be pressed down to make the sliding protrusion disengage from the positioning port and return to the circumferential groove. Then, the inner plug 8 can be rotated in the opposite direction to make the sliding protrusion return to the axial groove. The inner plug 8 can be slowly released to allow the nozzle 3 and the inner plug 8 to reset under the action of the inner spring 4 and the intermediate spring 10.

[0091] In the gas turbine compressor blade cleaning and inspection hole sealing structure disclosed in the above embodiment, pressing down on the upper plug 9 allows it to overcome the elastic force of the outer spring 11 and the middle spring 10, sliding downwards and causing the irregular protrusion to disengage from the irregular hole. Then, the upper plug 9 can be rotated and adjusted to align its fins with the irregular hole. This allows the upper plug 9, lower plug 7, inner plug 8, and middle spring 10 to be removed through the irregular hole, exposing the internal space of the nozzle 3. This enables inspection of the compressor casing 2. The specific process is as follows:

[0092] After the gas turbine is shut down and all components have cooled, screw the threaded rod into the threaded hole, press down on the upper plug 9, and then turn the upper plug 9 to remove the upper plug 9, lower plug 7, inner plug 8, and intermediate spring 10, exposing the internal space of the nozzle 3. Then, using relevant measuring instruments, inspect the inside of the compressor casing 2 through the internal space of the nozzle 3, such as... Figure 13 As shown.

[0093] After the compressor casing 2 is inspected, the threaded rod can be screwed into the threaded hole again, and the fins of the upper plug 9 can be aligned with the irregular hole. The upper plug 9, lower plug 7, inner plug 8, and intermediate spring 10 can be inserted into the outer cylinder 6 through the irregular hole. The lower plug 7 can be inserted into the nozzle 3, so that the fins of the upper plug 9 contact the outer spring 11. Overcome the elastic force of the outer spring 11 and intermediate spring 10 and press the upper plug 9 down, so that the irregular protrusion enters the outer cylinder 6. Then, the upper plug 9 can be screwed down, so that the fins of the upper plug 9 deviate from the irregular hole. The upper plug 9 can be slowly released, and the upper plug 9 and inner plug 8 can be reset under the action of the outer spring 11 and intermediate spring 10.

[0094] The gas turbine compressor blade cleaning and inspection hole sealing structure disclosed in the above embodiments is installed by means of an inspection hole opened on the compressor casing 2. The size of the inspection hole can be designed according to the structural installation requirements. It can perform offline and online cleaning of the compressor blade 12 through simple mode switching, and can clean the compressor blade 12 at a large angle and range, with high cleaning effect and efficiency. It also integrates the plugging function, allowing the relevant structure to be removed for inspection of the inside of the compressor casing 2. The overall structure is compact and has great convenience.

[0095] To improve its application, the gas turbine compressor blade cleaning and inspection hole sealing structure disclosed in the above embodiments can be further improved.

[0096] The sliding protrusion on the inner plug 8 is engaged in the irregular opening formed by the inward folding edge of the inner cylinder 1. The lower plug 7 and the upper plug 9 are rotatably connected. The upper outer wall of the lower plug 7 has an outward protrusion, and the lower part of the upper plug 9 has an annular groove surrounding the outward protrusion. A torsion spring 13 is installed in the annular groove, and the two ends of the torsion spring 13 are connected to the outward protrusion and the annular groove, so that the wing on the upper plug 9 and the sliding protrusion on the lower plug 7 remain aligned in their natural state. Figure 14 As shown.

[0097] To prevent excessive rotation of the upper plug 9, the upper plug 9 and the lower plug 7 are connected by a limiting protrusion and a limiting groove, such as... Figure 16 As shown.

[0098] A blocking plate 14 is fitted onto the lower plug 7, and the blocking plate 14 is connected below the upper plug 9 to seal the annular groove. The blocking plate 14 is formed by the butt joint of two semi-circular plates, such as... Figure 15 As shown.

[0099] The lower end of the lower plug 7 has a through hole, and the lower end of the inner plug 8 is inserted into the through hole, flush with the inner side of the compressor casing 2.

[0100] The lower plug 7 and the inner cylinder 1 can be designed to be connected by an axial stop groove and a stop protrusion, or the lower plug 7 and the nozzle 3 can be connected by an axial slide rail, or the sliding protrusion of the inner plug 8 can be designed to be stuck in the limiting groove opened on the upper end face of the nozzle 3 to prevent the lower plug 7 and its inner plug 8 from rotating circumferentially.

[0101] The improved gas turbine compressor blade cleaning and inspection hole sealing structure can be used as described above, and will not be elaborated further here. This will be used for online cleaning, offline cleaning, and post-offline cleaning reinstallation of the compressor blades 12. Figures 17-19 As shown.

[0102] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A structure for cleaning gas turbine compressor blades and sealing its inspection holes, characterized in that, It includes an inner cylinder (1), a nozzle (3), an inner spring (4), an outer cylinder (6), a lower plug (7), an inner plug (8), an upper plug (9), a middle spring (10), and an outer spring (11); The lower end of the inner cylinder (1) has an outward folded edge, which is connected to the compressor casing (2) and surrounds the inspection hole opened on the compressor casing (2). The upper end of the inner cylinder (1) has an inward folded edge. The inner cylinder (1) has a small-diameter online cleaning channel (a) and a large-diameter offline cleaning channel (b) inside its side wall. The small-diameter online cleaning channel (a) and the large-diameter offline cleaning channel (b) form channel inlets at the outward annular folded edge of the inner cylinder (1), and the small-diameter online cleaning channel (a) forms a channel outlet on the inner side of the upper side wall of the inner cylinder (1), while the large-diameter offline cleaning channel (b) forms a channel outlet on the inner side of the lower side wall of the inner cylinder (1). The nozzle (3) has a cylindrical structure and is installed inside the inner cylinder (1). The upper end has an outward folded edge, which is attached to the inner wall of the inner cylinder (1). The lower end of the nozzle (3) extends into the inspection hole. The nozzle (3) has a small-diameter online cleaning channel (c) and a large-diameter offline cleaning channel (d) inside its sidewall. The small-diameter online cleaning channel (c) and the large-diameter offline cleaning channel (d) form a channel inlet at the outward folded edge of the nozzle (3). The small-diameter online cleaning channel (c) forms a channel nozzle at the lower end of the nozzle (3). The large-diameter offline cleaning channel (d) forms multiple channel nozzles distributed along the axial direction on the lower outer wall of the nozzle (3). The inner spring (4) is installed inside the inner cylinder (1) and sleeved on the outer periphery of the nozzle (3). Both ends abut against the annular boss of the compressor casing (2) and the outward folded edge of the nozzle (3), so that the outward folded edge of the nozzle (3) is pressed against the inward folded edge of the inner cylinder (1), so that the lower end of the nozzle (3) is flush with the inner side of the compressor casing (2), and the inlet of the small aperture online cleaning channel (c) is aligned with the outlet of the small aperture online cleaning channel (a). The outer cylinder (6) is fitted around the outer periphery of the inner cylinder (1), and has an inward folded edge at the upper end, forming an irregular hole between the inward folded edges. The lower end of the outer cylinder (6) has an outward folded edge, which presses against the outward annular folded edge of the inner cylinder (1). The lower plug (7) is a cylindrical structure, installed inside the outer cylinder (6), with the lower end sealed and inserted into the nozzle (3), the upper end open, and the side wall has two axial grooves distributed at 180 degrees. The upper ends of the two axial grooves form an opening at the upper end of the lower plug (7), and the lower ends are connected to circumferential grooves. The ends of the two circumferential grooves have upward positioning openings. The inner plug (8) is a cylindrical structure and is installed inside the lower plug (7). The upper outer wall has two sliding protrusions, which extend from two axial sliding grooves and are located above the nozzle (3). The upper plug (9) is connected to the upper end of the lower plug (7), and the outer wall has two opposing wing edges. The lower end extends into the lower plug (7), and the upper end has an irregular protrusion. The intermediate spring (10) is installed inside the lower plug (7), sleeved on the outer periphery of the inner plug (8), with both ends abutting against the lower end of the lower plug (7) and the two sliding protrusions of the inner plug (8), so that the upper end of the inner plug (8) is pushed against the lower end of the upper plug (9); The outer spring (11) is installed inside the outer cylinder (6) and sleeved on the outer periphery of the inner cylinder (1). Its two ends abut against the washer ring (5) and the two wing edges, and the two wing edges are pressed against the inner folded edge of the outer cylinder (6), so that the irregular protrusion is stuck in the irregular hole.

2. The gas turbine compressor blade cleaning and inspection hole sealing structure according to claim 1, characterized in that, Pressing down on the inner plug (8) allows it to overcome the elastic force of the intermediate spring (10) and slide downward along the axial groove, causing the two sliding protrusions to press against the upper end of the nozzle (3). This, in turn, causes the nozzle (3) to overcome the elastic force of the inner spring (4) and slide downward, allowing the lower end of the nozzle (3) to extend into the compressor casing (2). After the two sliding protrusions reach the lower end of the axial groove, turning the inner plug (8) allows it to rotate along the circumferential groove, causing the inner plug (8) to slide downward. The sliding protrusion enters the circumferential groove. After the sliding protrusion reaches the end of the circumferential groove, the inner plug (8) is released. Under the action of the inner spring (4), the sliding protrusion will be inserted upward into the positioning port, thereby achieving the positioning of the inner plug (8) and the nozzle (3). At this time, the inlet of the large-diameter offline cleaning channel (d) is aligned with the outlet of the large-diameter offline cleaning channel (b), and the nozzle of the large-diameter offline cleaning channel (d) is exposed inside the compressor casing (2).

3. The gas turbine compressor blade cleaning and inspection hole sealing structure according to claim 2, characterized in that, Pressing down on the upper plug (9) allows it to overcome the elastic force of the outer spring (11) and the middle spring (10) and slide downwards, causing the irregular protrusion to dislodge from the irregular hole. Then, the upper plug (9) can be turned to adjust the wing edge of the upper plug (9) to align with the irregular hole. Then, the upper plug (9), lower plug (7), inner plug (8), and middle spring (10) can be removed through the irregular hole, exposing the internal space of the nozzle (3).

4. The gas turbine compressor blade cleaning and inspection hole sealing structure according to claim 3, characterized in that, The outward folded edge of the inner cylinder (1) is connected to the annular boss of the compressor casing (2), and is positioned with the annular boss by a stop. The annular boss surrounds the inspection hole opened on the compressor casing (2). Two sealing rings are provided on the outward folded edge of the nozzle (3) to form a seal with the inner cylinder (1). The inlet of the small-diameter online cleaning channel (c) and the large-diameter offline cleaning channel (d) is between the two sealing rings. There are multiple small-aperture online cleaning channels (a) and their corresponding small-aperture online cleaning channels (c).

5. The gas turbine compressor blade cleaning and inspection hole sealing structure according to claim 4, characterized in that, It also includes a washer ring (5); The gasket (5) is fitted around the outer periphery of the inner cylinder (1) and presses against the outward annular folded edge of the inner cylinder (1); The outward fold of the outer cylinder (6) presses against the washer (5) and is positioned with the washer (5) by a stop.

6. The gas turbine compressor blade cleaning and inspection hole sealing structure according to claim 5, characterized in that, The irregular hole formed between the inward folds of the outer cylinder (6) is a flat oval hole; The upper end of the inner plug (8) is formed with a square groove; The upper plug (9) has a threaded through hole running vertically through it, and its lower end extends into the lower plug (7), with a square protrusion on it.

7. The gas turbine compressor blade cleaning and inspection hole sealing structure according to claim 6, characterized in that, There are multiple large-aperture offline cleaning channels (b) and large-aperture offline cleaning flow channels (d), specifically designed as 6 channels, with 3 in the forward direction and 3 in the backward direction, distributed at 30° intervals between them; The inner cylinder (1) and the nozzle (3) are connected by an axial track.

8. The gas turbine compressor blade cleaning and inspection hole sealing structure according to claim 3, characterized in that, The sliding protrusion on the inner plug (8) is engaged in the irregular opening formed by the inward folding edge of the inner cylinder (1). The lower plug (7) and the upper plug (9) are rotatably connected. The upper outer wall of the lower plug (7) has an outward protrusion. The lower plug (9) has an annular groove around the outward protrusion. A torsion spring (13) is installed in the annular groove. The two ends of the torsion spring (13) are connected to the outward protrusion and the annular groove, so that the wing on the upper plug (9) and the sliding protrusion on the lower plug (7) remain aligned in the natural state.

9. The gas turbine compressor blade cleaning and inspection hole sealing structure according to claim 8, characterized in that, The upper plug (9) and the lower plug (7) are connected by a limiting protrusion and a limiting groove; A blocking plate (14) is fitted on the lower plug (7). The blocking plate (14) is connected below the upper plug (9) to seal the annular groove. The blocking plate (14) is formed by the butt joint of two semi-circular plates. The lower end of the lower plug (7) has a through hole, and the lower end of the inner plug (8) is inserted into the through hole, flush with the inner side of the compressor casing (2).

10. The gas turbine compressor blade cleaning and inspection hole sealing structure according to claim 9, characterized in that, The lower plug (7) is connected to the inner cylinder (1) through an axial stop groove and a stop protrusion, or the lower plug (7) is connected to the nozzle (3) through an axial slide rail, or the sliding protrusion on the plug (8) is stuck in the limiting groove opened on the upper end face of the nozzle (3).

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