A gas turbine compressor blade cleaning structure and method

Abstract

The application provides a gas turbine compressor blade cleaning structure and method, which can utilize an online cleaning state to perform online routine cleaning on the compressor during the operation of the gas turbine, so that the gas turbine can maintain high performance for a long time.

Description

Technical Field

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

[0002] The intake air of a gas turbine typically contains a large number of particles, mainly dust, soot, water droplets, hydrocarbon aerosols, pollen, and salt. These particles can adhere to the compressor surface, especially the compressor blades, which can seriously affect the compressor's performance and lead to a decline in the performance of the gas turbine. Therefore, it is necessary to clean the compressor regularly.

[0003] Currently, compressor cleaning is mostly done offline, requiring the gas turbine to be shut down and cooled to a safe temperature. This process is lengthy, and the gas turbine cannot operate during cleaning, affecting its efficiency. Furthermore, cleaning nozzles are typically installed through stencil holes at the front of the compressor casing to spray cleaning fluid into the casing. This method is only effective for cleaning the front-stage blades, with limited cleaning effect on the rear-stage blades. Additionally, the limited size of the stencil holes restricts the spraying capacity and angle of the cleaning nozzles, resulting in low cleaning efficiency and poor cleaning effect. Moreover, the cleaning nozzles must be removed after cleaning, making the process cumbersome and inconvenient.

[0004] This application is made in view of the aforementioned technical deficiencies. Summary of the Invention

[0005] The purpose of this application is to provide a structure and method for cleaning gas turbine compressor blades, so as to overcome or mitigate at least one of the known technical defects.

[0006] The technical solution of this application is:

[0007] A gas turbine compressor blade cleaning structure includes:

[0008] A rectangular support frame is connected to the outside of the compressor casing and is arranged along the axial direction of the gas turbine. A cleaning port communicating with the inside of the rectangular support frame is opened on the compressor casing. The rear edge of the rectangular support frame has a first inward positioning groove, the outer wall has a first sliding groove communicating with the first inward positioning groove, and the two side edges have support holes.

[0009] A rectangular flip frame is set inside a rectangular support frame. It has a mounting hole and a first outward locking groove on the rear edge, and support protrusions on the outer sides of both sides. The two support protrusions are inserted into the support holes, and a torsion spring is set between them.

[0010] The pipe fitting is connected to the mounting hole and can be connected to the cleaning fluid tank through a pipe.

[0011] A rectangular cover plate is set inside the rectangular flip frame. It is hollow inside and has multiple cleaning spray holes on its inner wall. A mounting pipe head is provided on the rear edge. The mounting pipe head is connected to the mounting hole.

[0012] The first spring is disposed in the first inward positioning groove;

[0013] The first locking pin is set in the first inward positioning groove and has a first slot on the side wall. Under the elastic force of the first spring, it extends out from the first inward positioning groove and is inserted into the first outward locking groove, so that the inner side of the rectangular flip frame and the inner side of the rectangular cover plate are flush with the inner side of the compressor casing, and the gas turbine compressor blade cleaning structure is in the online cleaning state.

[0014] The first slider is set in the first slide groove and locked in the first slot. Pushing the first slider can drive the first locking pin to slide against the elastic force of the first spring, so that the first locking pin retracts into the first inward positioning groove. The rectangular flipping frame together with the rectangular cover plate flips towards the inside of the compressor casing under the torsional force of the torsion spring. The cleaning nozzle faces the blades backward. The gas turbine compressor blade cleaning structure is in an offline cleaning state.

[0015] According to at least one embodiment of this application, in the above-described gas turbine compressor blade cleaning structure,

[0016] There are two sets of the first spring and its corresponding first locking pin and first slider, distributed on both sides of the pipe joint.

[0017] According to at least one embodiment of this application, in the above-described gas turbine compressor blade cleaning structure, the rectangular support frame has outward protrusions surrounding the support holes on both sides of its edge.

[0018] The gas turbine compressor blade cleaning structure also includes:

[0019] Two end caps are threaded onto two outward-facing bosses.

[0020] According to at least one embodiment of this application, in the above-described gas turbine compressor blade cleaning structure, a flipping positioning hole is provided on the front edge of the rectangular flipping frame.

[0021] The rectangular cover plate has a flip-positioning protrusion on its front edge. The flip-positioning protrusion is inserted into the flip-positioning hole and is coaxial with the mounting tube head.

[0022] The rectangular cover plate has multiple online cleaning nozzles on one side wall and multiple offline cleaning nozzles on the other side wall, wherein the size of the online cleaning nozzles is smaller than that of the offline cleaning nozzles;

[0023] The gas turbine compressor blade cleaning structure also includes:

[0024] An inner partition, installed inside a rectangular cover plate, protrudes into the pipe joint, dividing the internal space of the rectangular cover plate into an online cleaning chamber and an offline cleaning chamber. The online cleaning chamber is connected to each online cleaning nozzle, and the offline cleaning chamber is connected to each offline cleaning nozzle.

[0025] An inward baffle is installed inside the pipe joint to block part of the flow area of ​​the pipe joint.

[0026] The gas turbine compressor blade cleaning structure is located at:

[0027] In the online cleaning state, the side of the rectangular cover plate with the online cleaning nozzle flips inward, and the part of the inward baffle and the inner partition protruding into the pipe joint contacts and seals the offline cleaning chamber.

[0028] In offline cleaning mode, the side of the rectangular cover plate with the offline cleaning nozzle flips inward, and the inward baffle and the part of the inward partition protruding into the pipe joint contact and seal the online cleaning chamber.

[0029] According to at least one embodiment of this application, in the above-described gas turbine compressor blade cleaning structure, the front edge of the rectangular flipping frame has a second inward positioning groove, and the outer wall has a second sliding groove communicating with the second inward positioning groove.

[0030] The rectangular cover plate has a second outward locking groove at its front edge;

[0031] The gas turbine compressor blade cleaning structure also includes:

[0032] The second spring is disposed in the second inward positioning groove;

[0033] The second locking pin is set in the second inward positioning groove and has a second slot on the side wall. Under the elastic force of the second spring, it extends out from the second inward positioning groove and is inserted into the second outward locking groove to reliably lock the side of the rectangular cover plate with the online cleaning nozzle or offline cleaning nozzle to the inside.

[0034] The second slider is set in the second slide groove and locked in the second slot. Pushing the second slider can cause the second locking pin to slide against the elastic force of the second spring, so that the second locking pin retracts into the second inward positioning groove. At this time, it can push the rectangular cover plate to flip, so that the side with the online cleaning nozzle or offline cleaning nozzle is flipped to the inside. After the flip is completed, the second slider is released, and the second locking pin extends out of the second inward positioning groove under the elastic force of the second spring and re-inserts into the second outward locking groove to lock the rectangular cover plate.

[0035] According to at least one embodiment of this application, in the above-described gas turbine compressor blade cleaning structure, there are two sets of the second spring and its corresponding second locking pin and second slider, which are distributed on both sides of the mounting pipe head.

[0036] According to at least one embodiment of this application, in the above-described gas turbine compressor blade cleaning structure, the inner side of the rectangular flip frame has a cleaning window, the front and rear edges of the cleaning window have inward sliding grooves, and one side edge has an opening.

[0037] The gas turbine compressor blade cleaning structure also includes:

[0038] Two cleaning mounting plates have multiple cleaning nozzles. One cleaning mounting plate has smaller cleaning nozzles and is an online cleaning mounting plate with online cleaning nozzles. The other cleaning mounting plate has larger cleaning nozzles and is an offline cleaning mounting plate with offline cleaning nozzles.

[0039] The gas turbine compressor blade cleaning structure is located at:

[0040] In the online cleaning state, the online cleaning mounting plate is inserted into the cleaning window through the opening, and the front and rear edges are engaged in the inward sliding groove;

[0041] In offline cleaning mode, the offline cleaning mounting plate is inserted into the cleaning window through the opening, and its front and rear edges are engaged in the inward sliding groove.

[0042] According to at least one embodiment of this application, in the above-described gas turbine compressor blade cleaning structure, a flipping positioning hole is provided on the front edge of the rectangular flipping frame.

[0043] The rectangular cover plate has a flip positioning protrusion on its front edge. The flip positioning protrusion is inserted into the flip positioning hole and is coaxial with the mounting tube head. The rectangular cover plate can flip within the rectangular flip frame.

[0044] According to at least one embodiment of this application, in the above-described gas turbine compressor blade cleaning structure, a spring groove is provided on the edge of the cleaning window on the side opposite to the opening.

[0045] The rectangular flip frame has a third inward positioning groove on its front edge and a third sliding groove on its outer wall that communicates with the third inward positioning groove.

[0046] The rectangular cover plate has a third through hole at its front edge;

[0047] The two cleaning mounting plates have a third outward locking groove on their front edges;

[0048] The gas turbine compressor blade cleaning structure also includes:

[0049] The pop-out spring is set in the spring slot. Cleaning the mounting plate will press the pop-out spring tight.

[0050] The third spring is set in the third inward positioning groove;

[0051] The third locking pin is set in the third inward positioning groove and has a third slot on the side wall. Under the elastic force of the third spring, it extends out from the third inward positioning groove, passes through the third through hole, and is inserted into the third outward locking groove on the online cleaning mounting plate or the offline cleaning mounting plate.

[0052] The third slider is set in the third slide groove and is locked in the third slot. Pushing the third slider can drive the third locking pin to slide against the elastic force of the third spring, so that the third locking pin retracts into the third inward positioning groove. At this time, it can push the rectangular cover plate to flip, so that the edge of the rectangular cover plate with the opening side faces outward. Under the elastic force of the pop-out spring, the cleaning installation plate inside the cleaning window is partially popped out of the cleaning window.

[0053] On the other hand, a method for cleaning gas turbine compressor blades is provided, implemented based on any of the above-mentioned gas turbine compressor blade cleaning structures, including:

[0054] The gas turbine compressor blade cleaning nozzle structure is set to be in online cleaning mode, the gas turbine is running normally, and the compressor is cleaned online daily.

[0055] After the gas turbine is shut down and cooled to a safe temperature, the gas turbine compressor blade cleaning nozzle structure is set to an offline cleaning state. The gas turbine is then started by the starter to perform offline periodic cleaning of the compressor.

[0056] This application has at least the following beneficial technical effects:

[0057] A structure and method for cleaning gas turbine compressor blades are provided. The method allows for online daily cleaning of the compressor while the gas turbine is in operation, enabling the gas turbine to maintain high performance for extended periods. Offline periodic cleaning is only performed when the gas turbine's performance deteriorates significantly, thereby greatly reducing the frequency of offline compressor cleaning and improving the gas turbine's operating efficiency. Attached Figure Description

[0058] Figure 1 This is a schematic diagram of the gas turbine compressor blade cleaning structure provided in the embodiments of this application;

[0059] Figure 2 This is a schematic diagram of the first spring, the first locking pin, and the first slider in the gas turbine compressor blade cleaning structure provided in the embodiments of this application;

[0060] Figure 3 This is a schematic diagram of the gas turbine compressor blade cleaning structure provided in Embodiment 1 of this application in the online cleaning state;

[0061] Figure 4This is a schematic diagram of the gas turbine compressor blade cleaning structure provided in Embodiment 1 of this application in an offline cleaning state;

[0062] Figure 5 This is a schematic diagram of the inner diaphragm protruding into the pipe joint in the gas turbine compressor blade cleaning structure provided in Embodiment 1 of this application;

[0063] Figure 6 This is a schematic diagram of the inward baffle being installed inside the pipe joint in the gas turbine compressor blade cleaning structure provided in Embodiment 1 of this application;

[0064] Figure 7 This is a top view of the gas turbine compressor blade cleaning structure provided in Embodiment 1 of this application in the online cleaning state;

[0065] Figure 8 This is a schematic diagram of the second spring, the second locking pin, and the second slider in the gas turbine compressor blade cleaning structure provided in Embodiment 1 of this application;

[0066] Figure 9 This is a schematic diagram of the gas turbine compressor blade cleaning structure provided in Embodiment 2 of this application in the online cleaning state;

[0067] Figure 10 This is a schematic diagram of the cooperation between the third spring, the third locking pin and the third slider in the gas turbine compressor blade cleaning structure provided in Embodiment 1 of this application;

[0068] Figure 9 This is a top view of the gas turbine compressor blade cleaning structure provided in Embodiment 2 of this application in the online cleaning state;

[0069] in:

[0070] 1-Rectangular support frame; 2-Compressor casing; 3-Rectangular flip frame; 4-Torsion spring; 5-Pipe connector; 6-Rectangular cover plate; 7-First spring; 8-First locking pin; 9-First slider; 10-Inner partition; 11-Inner baffle; 12-Second spring; 13-Second locking pin; 14-Second slider; 15-Cleaning mounting plate; 16-Third spring; 17-Third locking pin; 18-Third slider; 19-Ejection spring; 20-End cap.

[0071] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0072] 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.

[0073] 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 terms indicating direction used in this application description are used only to indicate relative direction or positional relationship; when the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "comprising" as used in this application description indicates that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, but does not exclude other elements or objects.

[0074] Furthermore, it should 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.

[0075] This application provides a gas turbine compressor blade cleaning structure, such as... Figure 1 As shown, it includes:

[0076] A rectangular support frame 1 is connected to the outside of the compressor casing 2 and is arranged along the axial direction of the gas turbine. A cleaning port communicating with the inner side of the rectangular support frame 1 is opened on the compressor casing 2. The rear edge of the rectangular support frame 1 has a first inward positioning groove, the outer wall has a first sliding groove communicating with the first inward positioning groove, and the two side edges have support holes.

[0077] A rectangular flip frame 3 is set inside the rectangular support frame 1. It has a mounting hole and a first outward locking groove on the rear edge, and support protrusions on the outer sides of both sides. The two support protrusions are inserted into the support holes, and a torsion spring 4 is set between them.

[0078] Pipe connector 5 is connected in the mounting hole and can be connected to the cleaning fluid tank through a pipeline;

[0079] A rectangular cover plate 6 is set inside the rectangular flip frame 3. It is hollow inside and has multiple cleaning spray holes on its inner wall. It has a mounting pipe head on its rear edge. The mounting pipe head is connected to the mounting hole.

[0080] The first spring 7 is disposed in the first inward positioning groove;

[0081] The first locking pin 8 is disposed in the first inward positioning groove and has a first retaining groove on its side wall. Under the elastic force of the first spring 7, it extends out from the first inward positioning groove and inserts into the first outward locking groove. Figure 2 As shown, the inner sides of the rectangular flip frame 3 and the rectangular cover plate 6 are flush with the inner side of the compressor casing 2, and the gas turbine compressor blade cleaning structure is in an online cleaning state.

[0082] The first slider 9 is set in the first slide groove and locked in the first slot. Pushing the first slider 9 can drive the first locking pin 8 to slide against the elastic force of the first spring 7, so that the first locking pin 8 retracts back into the first inward positioning groove. The rectangular flipping frame 3 together with the rectangular cover plate 6 flips inward towards the compressor casing 2 under the torsional force of the torsion spring 4. The cleaning nozzle faces backward toward the blade. The gas turbine compressor blade cleaning structure is in the offline cleaning state. At this time, the first slider 9 is released, and the first locking pin 8 extends out from the first inward positioning groove under the elastic force of the first spring 7.

[0083] The gas turbine compressor blade cleaning structure disclosed in the above embodiments is designed with two working modes: online cleaning and offline cleaning. These correspond to two scenarios: online cleaning and offline cleaning of the compressor blades. When cleaning the compressor blades offline, the gas turbine needs to be shut down, cooled to below a safe temperature, and cold-run with a starter. This operation is complex, time-consuming, and the gas turbine cannot operate during this period, affecting its efficiency. In contrast, during online cleaning, the gas turbine can operate normally without affecting its use. Therefore, using the gas turbine compressor blade cleaning structure disclosed in the above embodiments to clean the compressor blades allows for routine online cleaning and periodic offline cleaning. Offline cleaning can be used only when the gas turbine's performance is severely degraded due to serious compressor blade contamination. Online cleaning ensures the gas turbine maintains high performance over a long period, reducing the frequency of offline cleaning and guaranteeing the gas turbine's efficiency.

[0084] The gas turbine compressor blade cleaning structure disclosed in the above embodiments allows cleaning fluid to be introduced into the rectangular cover plate 6 through the pipe joint 5 during online cleaning. The cleaning fluid can then be sprayed into the compressor casing 2 through cleaning nozzles, where it is atomized and mixed with the compressor intake airflow to sequentially flush each stage of the compressor blades, removing contaminants from the surface of each stage. After cleaning is completed, the introduction of cleaning fluid into the rectangular cover plate 6 through the pipe joint 5 is stopped. During online cleaning, the inner side of the rectangular flip frame 3 and the rectangular cover plate 6 is flush with the inner side of the compressor casing 2, which will not cause serious interference to the airflow and can ensure the performance of the gas turbine.

[0085] The gas turbine compressor blade cleaning structure disclosed in the above embodiments, when in offline cleaning mode, allows cleaning fluid to be introduced into the rectangular cover plate 6 through the pipe joint 5. The cleaning fluid can then be sprayed into the compressor casing 2 through cleaning nozzles, thereby sequentially rinsing each stage of the compressor blades and removing dirt from the surface of each stage. The resulting wastewater can be discharged from the drain hole opened on the compressor casing. After cleaning is completed, the drain hole is sealed with a plug to stop the introduction of cleaning fluid into the rectangular cover plate 6 through the pipe joint 5, and the first slider 9 can be pushed again to carry... The first locking pin 8 slides against the elastic force of the first spring 7, causing it to retract into the first inward positioning groove. Simultaneously, the rectangular flipping frame 3 is pressed, causing the rectangular cover plate 6 to overcome the torsional force of the torsion spring 4 and flip outwards towards the compressor casing 2, making the inner sides of the rectangular flipping frame 3 and the rectangular cover plate 6 flush with the inner side of the compressor casing 2. Then, the first slider 9 is released, allowing the first locking pin 8 to extend from the first inward positioning groove and insert into the first outward locking groove under the elastic force of the first spring 7, maintaining the gas turbine compressor blade cleaning structure in the online cleaning state. In the offline cleaning state, the cleaning nozzles on the rectangular cover plate 6 face backwards towards the blades, allowing cleaning fluid to be sprayed onto the blades over a wide radial range, achieving deep cleaning of the blades.

[0086] The gas turbine compressor blade cleaning structure disclosed in the above embodiments allows for offline cleaning of the blades. When the blades are cleaned offline, the rectangular flip frame 3 and the rectangular cover plate 6 flip inward toward the compressor casing 2, exposing the cleaning port on the compressor casing 2. The compressor can be inspected through this cleaning port without the need for additional inspection holes on the compressor casing 2. After the blade cleaning is completed, the components do not need to be disassembled; it is only necessary to restore the system to the online cleaning state, making it convenient to use.

[0087] To facilitate disassembly and assembly of the structure, the gas turbine compressor blade cleaning structure disclosed in the above embodiments can be further designed as a split structure for the rectangular support frame 1 and the rectangular flip frame 2, or as a detachable structure on one side edge, according to actual needs. Further details will not be provided here.

[0088] In the gas turbine compressor blade cleaning structure disclosed in the above embodiments, there are two sets of the first spring 7 and its corresponding first locking pin 8 and first slider 9, which are distributed on both sides of the pipe joint 5.

[0089] In the gas turbine compressor blade cleaning structure disclosed in the above embodiments, the rectangular support frame 1 has outward protrusions surrounding the support holes on both sides of its edges;

[0090] Two supporting protrusions extend outwards to stop the movement.

[0091] The gas turbine compressor blade cleaning structure also includes:

[0092] Two end caps 20 are threaded onto two outward protrusions, which have inward stop protrusions. When the gas turbine compressor blade cleaning structure is in the offline cleaning state, the two outward stop protrusions abut against the inward stop protrusions, so that the rectangular flipping frame 3 and the rectangular cover plate 6 are on the radial section of the gas turbine, preventing over-flipping.

[0093] Considering that when cleaning compressor blades online, the cleaning fluid needs to be atomized inside the compressor casing 2, and it is not advisable to spray a large amount of cleaning fluid into the compressor casing 2, while when cleaning compressor blades offline, a large amount of cleaning fluid needs to be sprayed into the compressor casing 2 to achieve deep cleaning of the blades, the cleaning nozzles on the rectangular cover plate 6 and their matching relationship with the rectangular cover plate 6 were further designed, as shown in the following Embodiment 1 and Embodiment 2.

[0094] Example 1:

[0095] The rectangular flip frame 3 has a flip positioning hole on its front edge;

[0096] The rectangular cover plate 6 has a flip-positioning protrusion on its front edge. The flip-positioning protrusion is inserted into the flip-positioning hole and is coaxial with the mounting tube head. The rectangular cover plate 6 can flip within the rectangular flip frame 3.

[0097] The rectangular cover plate 6 has multiple online cleaning nozzles on one side wall and multiple offline cleaning nozzles on the other side wall, wherein the size of the online cleaning nozzles is smaller than that of the offline cleaning nozzles;

[0098] The gas turbine compressor blade cleaning structure also includes:

[0099] The inner partition 10 is provided inside the rectangular cover plate 6 and protrudes into the pipe joint 5, such as... Figure 5 As shown, the internal space of the rectangular cover plate 6 is divided into an online cleaning chamber and an offline cleaning chamber. The online cleaning chamber is connected to each online cleaning nozzle, and the offline cleaning chamber is connected to each offline cleaning nozzle.

[0100] An inward baffle 11 is installed inside the pipe joint 5 to block part of the flow area of ​​the pipe joint 5, such as... Figure 6 As shown;

[0101] The gas turbine compressor blade cleaning structure is located at:

[0102] In the online cleaning state, the side of the rectangular cover plate 6 with the online cleaning nozzle flips inward, and the portion of the inward baffle 11 and the inner partition 10 protruding into the pipe joint 5 contacts and seals the offline cleaning chamber. At this time, the cleaning fluid introduced into the rectangular cover plate 6 from the pipe joint 5 flows into the online cleaning chamber and is then sprayed into the compressor casing 2 through the online cleaning nozzle. It is atomized and mixed with the compressor intake airflow, sequentially rinsing each stage of the compressor blades and removing dirt from the surface of each stage of the blades. Figure 3 As shown, due to the small size of the online cleaning nozzle, the amount of cleaning fluid injected into the compressor casing 2 can be controlled to be small, which facilitates atomization in the compressor casing 2.

[0103] In offline cleaning mode, the side of the rectangular cover plate 6 with the offline cleaning nozzle flips inward, and the portion of the inward baffle 11 and the inner partition 10 protruding into the pipe joint 5 contacts and seals the online cleaning chamber. At this time, the cleaning fluid introduced into the rectangular cover plate 6 from the pipe joint 5 flows into the offline cleaning chamber and is then sprayed into the compressor casing 2 through the offline cleaning nozzle, thereby sequentially flushing the compressor blades at each stage to remove dirt from the surface of each stage of the blades. Figure 4 As shown, due to the large size of the offline cleaning nozzle, a large amount of cleaning fluid can be controlled to be injected into the compressor casing 2, so as to perform deep cleaning of the blades.

[0104] In order to reliably keep the side of the rectangular cover plate 6 with the online cleaning nozzle inside when the gas turbine compressor blade cleaning structure is in the online cleaning state, and to reliably keep the side of the rectangular cover plate 6 with the offline cleaning nozzle inside when the gas turbine compressor blade cleaning structure is in the offline cleaning state, a second inward positioning groove is further designed on the front edge of the rectangular flip frame 3, and a second sliding groove communicating with the second inward positioning groove is provided on the outer wall.

[0105] The front edge of the rectangular cover plate 6 has a second outward locking groove;

[0106] The gas turbine compressor blade cleaning structure also includes:

[0107] The second spring 12 is disposed in the second inward positioning groove;

[0108] The second locking pin 13 is disposed in the second inward positioning groove and has a second slot on its side wall. Under the elastic force of the second spring 12, it extends out of the second inward positioning groove and inserts into the second outward locking groove. Figure 7 As shown, the side of the rectangular cover plate 6 with the online or offline cleaning nozzle is reliably locked to the inside.

[0109] The second slider 14 is set in the second slide groove and is locked in the second slot, such as Figure 8As shown, pushing the second slider 14 can cause the second locking pin 13 to slide against the elastic force of the second spring 12, causing the second locking pin 13 to retract into the second inward positioning groove. At this time, the rectangular cover plate 6 can be flipped, turning the side with the online cleaning nozzle or offline cleaning nozzle into the inside. After the flipping is completed, the second slider 14 is released, and the second locking pin 13 extends out of the second inward positioning groove under the elastic force of the second spring 12 and re-inserts into the second outward locking groove to lock the rectangular cover plate 6.

[0110] There are two sets of the second spring 12 and its corresponding second locking pin 13 and second slider 14, which are distributed on both sides of the mounting tube head.

[0111] Example 2:

[0112] The inner side of the rectangular flip frame 3 has a cleaning window, and the front and rear edges of the cleaning window have inward sliding grooves, and one side edge has an opening.

[0113] The gas turbine compressor blade cleaning structure also includes:

[0114] Two cleaning mounting plates 15 have multiple cleaning nozzles. One cleaning mounting plate 15 has smaller cleaning nozzles and is an online cleaning mounting plate with online cleaning nozzles. The other cleaning mounting plate 15 has larger cleaning nozzles and is an offline cleaning mounting plate with offline cleaning nozzles.

[0115] The gas turbine compressor blade cleaning structure is located at:

[0116] In online cleaning mode, the online cleaning mounting plate is inserted into the cleaning window through the opening, with its front and rear edges engaging in the inward sliding grooves. At this time, the cleaning fluid introduced from the pipe connector 5 into the rectangular cover plate 6 is sprayed into the compressor casing 2 through the online cleaning nozzles, atomizing and mixing with the compressor intake airflow to sequentially flush each stage of the compressor blades, removing contaminants from the surface of each stage of the blades. Figure 9 As shown, due to the small size of the online cleaning nozzle, the amount of cleaning fluid injected into the compressor casing 2 can be controlled to be small, which facilitates atomization in the compressor casing 2.

[0117] In offline cleaning mode, the offline cleaning mounting plate is inserted into the cleaning window through the opening, with its front and rear edges engaging in the inward sliding grooves. At this time, the cleaning fluid introduced from the pipe connector 5 into the rectangular cover plate 6 is sprayed into the compressor casing 2 through the offline cleaning nozzles, thereby sequentially flushing each stage of the compressor blades and removing contaminants from their surfaces. For specific results, please refer to [reference needed]. Figure 4 It is understood that, due to the large size of the offline cleaning nozzle, a large amount of cleaning fluid can be controlled to be injected into the compressor casing 2, so as to perform deep cleaning of the blades.

[0118] To facilitate the replacement of the cleaning mounting plate 15 and the switching of the working state of the gas turbine compressor blade cleaning structure, a rotating positioning hole is designed on the front edge of the rectangular flip frame 3.

[0119] The rectangular cover plate 6 has a flip positioning protrusion on its front edge. The flip positioning protrusion is inserted into the flip positioning hole and is coaxial with the mounting tube head. The rectangular cover plate 6 can flip within the rectangular flip frame 3.

[0120] When replacing the cleaning mounting plate 15, the rectangular cover plate 6 can be pushed to flip it over so that the edge of the rectangular cover plate 6 with the opening side faces outward, so that the original cleaning mounting plate 15 can be easily pulled out, the required cleaning mounting plate 15 can be installed into the cleaning window, and then the rectangular cover plate 6 can be pushed to flip it over so that the cleaning window flips to the inside.

[0121] To further facilitate the replacement of the cleaning mounting plate 15, switch the working state of the gas turbine compressor blade cleaning structure, and keep the cleaning mounting plate 15 inside in both online and offline cleaning states, a spring groove is further designed on the edge of the cleaning window facing away from the opening.

[0122] The rectangular flip frame 3 has a third inward positioning groove on its front edge and a third sliding groove on its outer wall that communicates with the third inward positioning groove.

[0123] The rectangular cover plate 6 has a third through hole at its front edge;

[0124] The two cleaning mounting plates 15 have a third outward locking groove on their front edges;

[0125] The gas turbine compressor blade cleaning structure also includes:

[0126] The pop-out spring 19 is positioned in the spring groove. Cleaning the mounting plate 15 will press the pop-out spring 19 into place. Figure 11 As shown;

[0127] The third spring 16 is disposed in the third inward positioning groove;

[0128] The third locking pin 17 is located in the third inward positioning groove and has a third slot on its side wall. Under the elastic force of the third spring 16, it extends out of the third inward positioning groove, passes through the third through hole, and is inserted into the third outward locking groove on the online or offline cleaning mounting plate. Figure 9 As shown, this locks the online or offline cleaning mounting plate to the inside.

[0129] The third slider 18 is set in the third slide groove and is locked in the third slot, such as Figure 10As shown, pushing the third slider 18 can cause the third locking pin 17 to slide against the elastic force of the third spring 16, causing the third locking pin 13 to retract into the third inward positioning groove. At this time, the rectangular cover plate 6 can be pushed to flip, so that the edge of the rectangular cover plate 6 with the opening side faces outward. The original cleaning mounting plate 15 can be partially popped out of the cleaning window under the elastic force of the pop-out spring 19, so that the original cleaning mounting plate 15 can be easily pulled out and the required cleaning mounting plate 15 can be installed in the cleaning window. Then push the rectangular cover plate 6 to flip, so that the cleaning window flips to the inside. After releasing the third slider 18, the third locking pin 17 can extend out of the third inward positioning groove again under the elastic force of the third spring 16, pass through the third through hole, and insert into the third outward locking groove of the cleaning mounting plate 15 installed in the cleaning window for locking.

[0130] On the other hand, a method for cleaning gas turbine compressor blades is provided, based on the gas turbine compressor blade cleaning structure disclosed in the above embodiments, including:

[0131] The gas turbine compressor blade cleaning nozzle structure is set to be in online cleaning mode. The gas turbine is running normally, and the compressor is cleaned online daily 3 to 4 times a week, with each cleaning time being 2 to 4 minutes.

[0132] After the gas turbine is shut down and cooled to a safe temperature, the gas turbine compressor blade cleaning nozzle structure is set to an offline cleaning state. The gas turbine is started by the starter and cold-run, so that the compressor speed varies between 600 r / m and 2500 r / m to perform offline periodic cleaning of the compressor. This is carried out after the gas turbine performance has degraded by 6%, with each cleaning lasting 5 minutes and the cleaning fluid flow rate between 10 L / min and 17 L / min.

[0133] The gas turbine compressor blade cleaning method disclosed in the above embodiments is implemented based on the gas turbine compressor blade cleaning nozzle structure disclosed in the above embodiments. The description is relatively simple. For specific details, please refer to the relevant description of the gas turbine compressor blade in-situ cleaning system. The technical effects can also be referred to the technical effects of the relevant parts of the gas turbine compressor blade in-situ cleaning system. It will not be repeated here.

[0134] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. Similar or identical parts between embodiments can be referred to mutually. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined to obtain new embodiments.

[0135] 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 gas turbine compressor blade cleaning structure, characterized in that, include: A rectangular support frame (1) is connected to the outside of the compressor casing (2) and is arranged along the axial direction of the gas turbine. A cleaning port communicating with the inside of the rectangular support frame (1) is opened on the compressor casing (2). The rear edge of the rectangular support frame (1) has a first inward positioning groove, the outer wall has a first sliding groove communicating with the first inward positioning groove, and the two sides have support holes. A rectangular flip frame (3) is set inside the rectangular support frame (1). It has a mounting hole and a first outward locking groove on the rear edge, and support protrusions on the outer sides of both sides. The two support protrusions are inserted into the support holes, and a torsion spring (4) is set between them. Pipe fitting (5) is connected in the mounting hole and can be connected to the cleaning fluid tank through a pipeline; A rectangular cover plate (6) is set inside the rectangular flip frame (3). It is hollow inside and has multiple cleaning spray holes on the inner wall. It has a mounting pipe head on the rear edge. The mounting pipe head is connected to the mounting hole. The first spring (7) is disposed in the first inward positioning groove; The first locking pin (8) is set in the first inward positioning groove and has a first slot on the side wall. Under the elastic force of the first spring (7), it extends out from the first inward positioning groove and is inserted into the first outward locking groove, so that the inner side of the rectangular flip frame (3) and the rectangular cover plate (6) are flush with the inner side of the compressor casing (2), and the gas turbine compressor blade cleaning structure is in the online cleaning state. The first slider (9) is set in the first slide groove and is stuck in the first slot. Pushing the first slider (9) can drive the first locking pin (8) to slide against the elastic force of the first spring (7), so that the first locking pin (8) retracts back into the first inward positioning groove. The rectangular flipping frame (3) together with the rectangular cover plate (6) flips towards the inside of the compressor casing (2) under the torsional force of the torsion spring (4). The cleaning nozzle faces the blades from the rear. The gas turbine compressor blade cleaning structure is in an offline cleaning state.

2. The gas turbine compressor blade cleaning structure according to claim 1, characterized in that, There are two sets of the first spring (7) and its corresponding first locking pin (8) and first slider (9), which are distributed on both sides of the pipe joint (5).

3. The gas turbine compressor blade cleaning structure according to claim 1, characterized in that, The rectangular support frame (1) has outward protrusions around the support holes on both sides of its edges; The gas turbine compressor blade cleaning structure also includes: Two end caps (20) are threaded onto two outward-facing bosses.

4. The gas turbine compressor blade cleaning structure according to claim 1, characterized in that, The rectangular flip frame (3) has a flip positioning hole on its front edge; The rectangular cover plate (6) has a flip-positioning protrusion on its front edge. The flip-positioning protrusion is inserted into the flip-positioning hole and is coaxial with the mounting tube head. The rectangular cover plate (6) has multiple online cleaning nozzles on one side wall and multiple offline cleaning nozzles on the other side wall, wherein the size of the online cleaning nozzles is smaller than that of the offline cleaning nozzles; The gas turbine compressor blade cleaning structure also includes: An inner partition (10) is provided inside a rectangular cover plate (6) and protrudes into a pipe joint (5), dividing the internal space of the rectangular cover plate (6) into an online cleaning chamber and an offline cleaning chamber. The online cleaning chamber is connected to each online cleaning nozzle, and the offline cleaning chamber is connected to each offline cleaning nozzle. An inward baffle (11) is installed inside the pipe joint (5) to block part of the flow area of ​​the pipe joint (5); The gas turbine compressor blade cleaning structure is located at: In the online cleaning state, the side of the rectangular cover plate (6) with the online cleaning nozzle is flipped to the inside, and the part of the inner baffle (11) and the inner partition (10) protruding into the pipe joint (5) contacts and blocks the offline cleaning chamber. In the offline cleaning state, the side of the rectangular cover plate (6) with the offline cleaning nozzle is flipped to the inside, and the inner baffle (11) and the inner partition (10) protrude into the pipe joint (5) to contact and block the online cleaning chamber.

5. The gas turbine compressor blade cleaning structure according to claim 4, characterized in that, The rectangular flip frame (3) has a second inward positioning groove on its front edge and a second sliding groove on its outer wall that communicates with the second inward positioning groove. The rectangular cover plate (6) has a second outward locking groove at its front edge; The gas turbine compressor blade cleaning structure also includes: The second spring (12) is disposed in the second inward positioning groove; The second locking pin (13) is set in the second inward positioning groove and has a second slot on the side wall. Under the elastic force of the second spring (12), it extends out from the second inward positioning groove and is inserted into the second outward locking groove to reliably lock the side of the rectangular cover plate (6) with the online cleaning nozzle or the offline cleaning nozzle to the inside. The second slider (14) is set in the second slide groove and is locked in the second slot. Pushing the second slider (14) can drive the second locking pin (13) to slide against the elastic force of the second spring (12), so that the second locking pin (13) retracts back into the second inward positioning groove. At this time, it can push the rectangular cover plate (6) to flip, flipping the side with the online cleaning nozzle or offline cleaning nozzle to the inside. After the flip is completed, the second slider (14) is released, and the second locking pin (13) extends out from the second inward positioning groove under the elastic force of the second spring (12) and is reinserted into the second outward locking groove to lock the rectangular cover plate (6).

6. The gas turbine compressor blade cleaning structure according to claim 5, characterized in that, There are two sets of the second spring (12) and its corresponding second locking pin (13) and second slider (14), which are distributed on both sides of the mounting tube head.

7. The gas turbine compressor blade cleaning structure according to claim 4, characterized in that, The inner side of the rectangular flip frame (3) has a cleaning window, and the front and rear edges of the cleaning window have inward sliding grooves, and one side edge has an opening; The gas turbine compressor blade cleaning structure also includes: Two cleaning mounting plates (15) have multiple cleaning nozzles. One cleaning mounting plate (15) has smaller cleaning nozzles and is an online cleaning mounting plate with online cleaning nozzles. The other cleaning mounting plate (15) has larger cleaning nozzles and is an offline cleaning mounting plate with offline cleaning nozzles. The gas turbine compressor blade cleaning structure is located at: In the online cleaning state, the online cleaning mounting plate is inserted into the cleaning window through the opening, and the front and rear edges are engaged in the inward sliding groove; In offline cleaning mode, the offline cleaning mounting plate is inserted into the cleaning window through the opening, and its front and rear edges are engaged in the inward sliding groove.

8. The gas turbine compressor blade cleaning structure according to claim 7, characterized in that, The rectangular flip frame (3) has a flip positioning hole on its front edge; The rectangular cover plate (6) has a flip positioning protrusion on the front edge. The flip positioning protrusion is inserted into the flip positioning hole and is coaxial with the mounting tube head. The rectangular cover plate (6) can flip within the rectangular flip frame (3).

9. The gas turbine compressor blade cleaning structure according to claim 8, characterized in that, The cleaning window has a spring groove on the edge of the side facing away from the opening. The rectangular flip frame (3) has a third inward positioning groove on its front edge and a third sliding groove on its outer wall that communicates with the third inward positioning groove. The rectangular cover plate (6) has a third through hole at its front edge; The two cleaning mounting plates (15) have a third outward locking groove on their front edge; The gas turbine compressor blade cleaning structure also includes: The pop-out spring (19) is set in the spring groove. The cleaning mounting plate (15) presses the pop-out spring (19) tightly. The third spring (16) is set in the third inward positioning groove; The third locking pin (17) is set in the third inward positioning groove and has a third slot on the side wall. Under the elastic force of the third spring (16), it extends out from the third inward positioning groove, passes through the third through hole, and is inserted into the third outward locking groove on the online cleaning mounting plate or the offline cleaning mounting plate. The third slider (18) is set in the third slide groove and is locked in the third slot. Pushing the third slider (18) can drive the third locking pin (17) to slide against the elastic force of the third spring (16), so that the third locking pin (17) retracts back into the third inward positioning groove. At this time, it can push the rectangular cover plate (6) to flip, so that the edge of the rectangular cover plate (6) with the opening side faces outward. Under the elastic force of the pop-out spring (19), the cleaning mounting plate (15) inside the cleaning window pops out of the cleaning window.

10. A method for cleaning gas turbine compressor blades, characterized in that, The gas turbine compressor blade cleaning structure according to any one of claims 1-9 includes: The gas turbine compressor blade cleaning nozzle structure is set to be in online cleaning mode, the gas turbine is running normally, and the compressor is cleaned online daily. After the gas turbine is shut down and cooled to a safe temperature, the gas turbine compressor blade cleaning nozzle structure is set to an offline cleaning state. The gas turbine is then started by the starter to perform offline periodic cleaning of the compressor.

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