Gas compressor convenient for external field maintenance and maintenance method thereof

Abstract

The invention discloses a gas compressor convenient for external field maintenance and a maintenance method thereof, and belongs to the technical field of aero-engines. The gas compressor convenient for external field maintenance comprises a front-end casing and a rear-end casing; the gas compressor convenient for external field maintenance further comprises a left casing assembly, a right casing assembly, a two-stage linkage ring assembly and an inspection hole sealing assembly, wherein the left casing assembly is connected with the front-end casing, the left casing assembly is connected with the rear-end casing, and the left casing assembly is connected with the right casing assembly; the two-stage linkage ring assembly is used for conducting circumferential concentric positioning on the left casing assembly and the right casing assembly. And a plurality of maintenance inspection holes are formed in the left casing assembly. The gas compressor casing with the long gas inlet channel can be designed into the left casing assembly and the right casing assembly which are half to half, the detachable layout of the long casing is achieved, positioning is stable and reliable, when gas compressor blades are damaged by foreign objects and need to be maintained, maintenance can be conducted on an external field, and the period and cost of returning to the center of an engine for maintenance are reduced.

Description

Technical Field

[0001] The present application relates to the field of aeroengine technology, and in particular, to a compressor that is easy to maintain in an off-site environment. In addition, the present application also relates to a maintenance method for the compressor that is easy to maintain in an off-site environment. Background Art

[0002] The information provided in this section is for the purpose of generally presenting the background of the present application. To the extent described in this section, the work of the presently named inventors and aspects of the description that may not constitute prior art at the time of filing are neither explicitly nor implicitly admitted to be prior art to the present application.

[0003] With the development of aircraft engines, especially civil aircraft, the requirements for low-cost design throughout the life cycle are becoming increasingly higher, and it is urgent to reduce maintenance and repair costs and improve competitiveness. The compressor is one of the three core components of the engine. The gas must first be compressed and pressurized by the compressor and then ignited in the combustion chamber before flowing to the turbine components. Therefore, when the aircraft engine is used in the field, the compressor is more likely to be damaged by foreign objects, among which the rotor blades of the compressor inlet stage are more likely to be damaged. The maintenance cost after damage must be considered in the design.

[0004] If the blades of an existing compressor with a long air inlet passage are damaged by foreign objects when used in the field on an installation platform, there are usually three ways to deal with it according to the model maintenance manual: 1. If the damage is acceptable, the engine continues to be used in the field; 2. If the damage is unacceptable and within the repairable range, it is returned to the engine center for repair and continued use; 3. If the damage is unacceptable and beyond the repair range, it is returned to the engine center for replacement of new components.

[0005] In existing compressors with long inlet passages, the casing corresponding to the inlet-stage rotor, which has the highest probability of being damaged by the compressor, has two structural forms. One is an integral annular casing that cannot be disassembled in the field, as shown in the attached manual. Figure 2 As shown in the figure; one is a segmented receiver, that is, an integral ring receiver + a split receiver structure. The split receiver is difficult to open in the field. Even if it can be opened in the field, it cannot be directly repaired in the field due to insufficient space due to the influence of the front integral ring receiver, as shown in the attached manual. Figure 3 shown.

[0006] Therefore, once the existing small and medium-sized aircraft engine compressor inlet stage rotor blades with long inlet ducts are damaged and the damage is within the repairable range, there are also the following problems: the structure cannot be directly repaired offsite, or it can be repaired offsite but the operation is complicated and the safety risk is high. Ultimately, the engine or the unit where the damaged part is located needs to be returned to the engine center for repair, which results in a long maintenance cycle and high cost.

[0007] It should be noted that the information disclosed in the above background technology section is only used to enhance the understanding of the background of the present application, and therefore may include information that does not constitute the prior art known to ordinary technicians in the field. Summary of the invention

[0008] In view of at least one of the above technical problems, the present application provides a compressor that is easy to maintain in the field. By designing the compressor casing with a long air inlet passage into a left casing assembly and a right casing assembly in half, a detachable layout of the long casing can be achieved, and the positioning is stable and reliable. When the compressor blades are damaged by foreign objects and need to be repaired, they can be repaired in the field, reducing the cycle and cost of returning to the engine center for maintenance.

[0009] The present application also provides a maintenance method for the above-mentioned compressor that is easy to maintain on site.

[0010] According to one aspect of the present application, a compressor that is easy to maintain on site is provided, including a front casing and a rear casing. The compressor that is easy to maintain on site also includes a left casing assembly, a right casing assembly, a first connecting bolt, a second connecting bolt, a third connecting bolt, a casing positioning bushing, a two-stage linkage ring assembly, and an inspection hole sealing assembly: The first connecting bolt is used to connect the left casing assembly with the front casing, the third connecting bolt is used to connect the left casing assembly with the rear casing, and the casing positioning bushing is used to axially position the left casing assembly and the right casing assembly, and then cooperates with the second connecting bolt to connect the left casing assembly and the right casing assembly; The two-stage linkage ring assembly comprises a first linkage ring and a second linkage ring. The first linkage ring and the second linkage ring are arranged at intervals on the outer walls of the left casing assembly and the right casing assembly and are used to position the left casing assembly and the right casing assembly concentrically in the circumferential direction.

[0011] The left casing assembly is provided with a plurality of maintenance inspection holes, each of which is used for allowing a detection instrument to extend into the interior of the compressor to inspect parts, and the inspection hole sealing assembly is used to seal each maintenance inspection hole.

[0012] In some embodiments of the present application, the inspection hole sealing assembly includes a plugging cover bolt and a plugging cover, the plugging cover includes a mounting platform and a sealing column, the sealing column is used to seal the maintenance inspection hole, the bottom end of the sealing column is provided with a pneumatic flow path surface for being flush with the internal flow path surface of the left casing assembly, the mounting platform is used to abut and cooperate with a preset mounting boss on the left casing assembly, a limiting screw hole is provided on the mounting platform, and the plugging cover bolt is used to pass through the limiting screw hole and cooperate with the preset mounting screw hole on the mounting boss to connect the plugging cover to the left casing assembly.

[0013] In some embodiments of the present application, the diameters of the maintenance and inspection holes are different, and multiple plugging covers are provided, and each plugging cover is arranged one-to-one corresponding to each maintenance and inspection hole. Two limiting screw holes are provided on the mounting platform of each plugging cover, and the spans between the two limiting screw holes and the center point of the mounting platform are different, so as to correspond one-to-one with the mounting screw holes on each mounting boss, thereby ensuring that the pneumatic flow path surface of each sealing column is flush with the internal flow path surface of the left casing assembly.

[0014] In some embodiments of the present application, the two-stage linkage ring assembly also includes a locking bolt and a connecting plate assembly, the first linkage ring and the second linkage ring are both annular structures divided into half, the two halves of the first linkage ring are respectively connected to the left receiver assembly and the right receiver assembly, and the two halves of the second linkage ring are respectively connected to the left receiver assembly and the right receiver assembly, the connecting plate assembly is used to respectively abut against the opposite sides of the first linkage ring and cover the two halves of the first linkage ring at the seam, and the connecting plate assembly and the two halves of the first linkage ring are connected and fastened by the locking bolt; the connecting plate assembly is also used to respectively abut against the opposite sides of the second linkage ring and cover the two halves of the second linkage ring at the seam, and the connecting plate assembly and the two halves of the second linkage ring are connected and fastened by the locking bolt.

[0015] In some embodiments of the present application, the connecting plate assembly includes a first connecting plate, a second connecting plate, a third connecting plate and a fourth connecting plate, the first connecting plate and the second connecting plate are used to respectively abut against opposite sides of the first linkage ring and cover two halves of the seam of the first linkage ring, the locking bolt is used to sequentially pass through the preset connecting screw holes on the first connecting plate, the first linkage ring and the second connecting plate to connect and fasten the three, the third connecting plate and the fourth connecting plate are used to respectively abut against opposite sides of the second linkage ring and cover two halves of the seam of the second linkage ring, and the locking bolt is also used to sequentially pass through the preset connecting screw holes on the third connecting plate, the second linkage ring and the fourth connecting plate to connect and fasten the three.

[0016] In some embodiments of the present application, the first connecting plate, the second connecting plate, the third connecting plate and the fourth connecting plate have the same structure and all include an arc-shaped plate, on which a plurality of connecting screw holes are spaced apart, and a disassembly groove is provided on the arc-shaped plate, for allowing a disassembly tool to abut against the arc-shaped plate and limit the disassembly tool.

[0017] In some embodiments of the present application, the two-stage linkage ring assembly also includes a long positioning bushing, which is used to cooperate with the connecting screw holes on the arc plate, the first linkage ring and the second linkage ring to respectively perform circumferential concentric positioning of the two halves of the first linkage ring and the two halves of the second linkage ring.

[0018] According to another aspect of the present application, a maintenance method is also provided, which is applied to the maintenance of the above-mentioned compressor that is easy to maintain on site, and the maintenance method comprises the following steps: S100, disconnect the left casing assembly from the engine systems, and measure and record the rotational torque M1 of the combustion rotor before maintenance; S200, removing the first connecting bolt to disconnect the left casing assembly from the front casing, and removing the third connecting bolt to disconnect the left casing assembly from the rear casing; S300, removing the second connecting bolt to disconnect the left casing assembly from the right casing assembly, and disassembling the casing positioning bushing; S400, disassemble the first linkage ring and the second linkage ring, and then remove the left casing assembly from the engine body; S500. Maintenance personnel shall perform on-site protection according to the aircraft engine maintenance manual and carry out on-site repair of the damaged blades. During the repair process, the gas generator rotor may be rotated to move the damaged blades to the best repair position. S600. After maintenance, assemble the compressor components as they were, measure and record the rotational torque M2 of the rotor, and judge the maintenance effect by comparing M2 with M1.

[0019] In some embodiments of the present application, in step S400, the two-stage stationary blade rings of the engine can be fixed to the right casing assembly by a stop plate assembly to prevent blades from falling during disassembly and transportation.

[0020] In some embodiments of the present application, the assembly sequence in step S600 is to connect the left casing assembly and the right casing assembly, axially position the left casing assembly and the right casing assembly by means of casing positioning bushings, connect the left casing assembly and the right casing assembly by means of second connecting bolts; connect the left casing assembly and the front casing by means of first connecting bolts; connect the left casing assembly and the rear casing by means of third connecting bolts; connect and fasten the first linkage ring and the second linkage ring to the left casing assembly and the right casing assembly by means of locking bolts; and connect the left casing assembly to various engine systems.

[0021] This application has the following beneficial effects: The compressor of the present application is easy to maintain in the field. By designing the left casing assembly and the right casing assembly, the compressor casing with a long air inlet passage is set to a half-detachable structure, realizing an overall layout of a half-long casing with reliable assembly and disassembly positioning. At the same time, multiple maintenance inspection holes are opened on the left casing assembly. During the field test, the internal parts of the compressor can be regularly inspected through the maintenance inspection holes using detection instruments such as borescopes, so that abnormal parts can be found and corresponding measures can be taken to ensure flight safety; and each maintenance inspection hole is sealed by the inspection hole sealing assembly to reduce aerodynamic losses, so as to ensure that the maintenance inspection hole does not affect the normal function of the left casing assembly. In addition, the present application also uses the first linkage ring and the second linkage ring to perform circumferential concentric positioning of the left casing assembly and the right casing assembly, ensuring that frequent disassembly and assembly will not affect the integrity of the casing, and ensuring the connection stability of the casing.

[0022] The maintenance method of the present application also has the above-mentioned beneficial effects, and the maintenance method of the present application can realize that the compressor can be directly repaired on the installation platform. By disconnecting the left casing assembly from the front casing, the rear casing and the right casing assembly in sequence, and then disassembling the first linkage ring and the second linkage ring, the left casing assembly can be removed from the engine body, which is very convenient for maintenance personnel to repair related parts on site, greatly shortening the maintenance cycle brought about by returning the unit body where the damaged parts are located to the engine center and reducing maintenance costs, thereby improving the commercial competitiveness of civil engines.

[0023] Of course, any product implementing this application does not necessarily need to achieve all the advantages described above at the same time. In addition to the purposes, features and advantages described above, this application also has other purposes, features and advantages. The following will further describe this application in detail with reference to the figures. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The drawings constituting a part of the present application are used to provide a further understanding of the present application. The illustrative embodiments and descriptions of the present application are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings: Figure 1 It is a schematic diagram of the overall structure of the preferred embodiment of the present application; Figure 2 It is a schematic diagram of the design of a traditional compressor with a full annular shape and a long inlet passage; Figure 3 It is a schematic diagram of the design of a traditional compressor with a split casing and a long air inlet passage; Figure 4 This is a schematic structural diagram of a third blocking cover of a preferred embodiment of the present application; Figure 5 This is a schematic diagram of the installation of the third blocking cover of the preferred embodiment of the present application; Figure 6 It is a schematic diagram of the position of the left casing assembly and the engine system of the preferred embodiment of the present application; Figure 7 This is a schematic diagram of the installation of the left casing assembly and the engine body of the preferred embodiment of the present application; Figure 8 It is a schematic diagram of the position of the two-stage linkage ring of the preferred embodiment of the present application; Fig. 9 It is a structural schematic diagram of the disassembled left half casing assembly of the preferred embodiment of the present application; Fig.10 is a schematic structural diagram of a first stop plate in a preferred embodiment of the present application; Fig.11 It is a partial schematic diagram of the engine after the left casing assembly is removed according to the preferred embodiment of the present application; Fig.12 It is a schematic diagram of the installation position of the casing positioning bushing of the preferred embodiment of the present application; Fig.13 It is a schematic diagram of a two-stage linkage ring of a preferred embodiment of the present application; Fig.14 is a structural schematic diagram of a first connecting plate in a preferred embodiment of the present application; Legend: 1. Cover bolt; 2. First cover; 3. Sealing gasket; 4. First inspection hole; 5. Left casing assembly; 6. Right casing assembly; 7. Second cover; 8. Second inspection hole; 9. Third cover; 10. Third inspection hole; 11. Deflation valve control cable; 12. Air bleed pipe; 13. Adjustable guide vane control assembly; 14. Deflation valve air pipe; 15. Front casing; 16. Rear casing; 17. First connecting bolt; 18. Second connecting bolt; 19. Third connecting bolt; 20. Casing locating bushing; 21. Locking bolt; 22. First connecting plate; 23. Second connecting plate; 24. Third connecting plate; 25. Fourth connecting plate; 26. First linkage ring; 27. Second linkage ring; 28. Long locating bushing; 29. ​​First stop plate; 30. Countersunk screw; 31. Second stop plate. DETAILED DESCRIPTION

[0025] The embodiments of the present application are described in detail below in conjunction with the accompanying drawings, but the present application can be implemented in a variety of different ways defined and covered below.

[0026] Figure 1 It is a schematic diagram of the overall structure of the preferred embodiment of the present application; Figure 2 It is a schematic diagram of the design of a traditional compressor with a full annular shape and a long inlet passage; Figure 3 It is a schematic diagram of the design of a traditional compressor with a split casing and a long air inlet passage; Figure 4 This is a schematic structural diagram of a third blocking cover of a preferred embodiment of the present application; Figure 5 This is a schematic diagram of the installation of the third blocking cover of the preferred embodiment of the present application; Figure 6 It is a schematic diagram of the position of the left casing assembly and the engine system of the preferred embodiment of the present application; Figure 7 This is a schematic diagram of the installation of the left casing assembly and the engine body of the preferred embodiment of the present application; Figure 8 It is a schematic diagram of the position of the two-stage linkage ring of the preferred embodiment of the present application; Fig. 9 It is a structural schematic diagram of the disassembled left half casing assembly of the preferred embodiment of the present application; Fig.10 is a schematic structural diagram of a first stop plate in a preferred embodiment of the present application; Fig.11 It is a partial schematic diagram of the engine after the left casing assembly is removed according to the preferred embodiment of the present application; Fig.12 It is a schematic diagram of the installation position of the casing positioning bushing of the preferred embodiment of the present application; Fig.13It is a schematic diagram of a two-stage linkage ring of a preferred embodiment of the present application; Fig.14 It is a schematic structural diagram of the first connecting plate of the preferred embodiment of the present application.

[0027] A compressor that is easy to maintain on site, comprising a front casing 15 and a rear casing 16, the compressor that is easy to maintain on site also comprises a left casing assembly 5, a right casing assembly 6, a first connecting bolt 17, a second connecting bolt 18, a third connecting bolt 19, a casing positioning bushing 20, a two-stage linkage ring assembly and an inspection hole sealing assembly: The first connecting bolt 17 is used to connect the left casing assembly 5 with the front casing 15, the third connecting bolt 19 is used to connect the left casing assembly 5 with the rear casing 16, and the casing positioning bushing 20 is used to axially position the left casing assembly 5 and the right casing assembly 6, and then cooperate with the second connecting bolt 18 to connect the left casing assembly 5 and the right casing assembly 6; The two-stage linkage ring assembly includes a first linkage ring 26 and a second linkage ring 27. The first linkage ring 26 and the second linkage ring 27 are spaced apart on the outer walls of the left casing assembly 5 and the right casing assembly 6 and are used to position the left casing assembly 5 and the right casing assembly 6 concentrically in the circumferential direction.

[0028] The left casing assembly 5 is provided with a plurality of maintenance inspection holes, each of which is used for allowing a detection instrument to extend into the interior of the compressor to inspect parts, and the inspection hole sealing assembly is used to seal each maintenance inspection hole.

[0029] Here, the meaning of "first linkage ring 26 and second linkage ring 27" refers to the structure connected to the outer walls of the left receiver assembly 5 and the right receiver assembly 6. In some embodiments, the first linkage ring 26 and the second linkage ring 27 are both detachable circular rings with half structures, and the first linkage ring 26 and the second linkage ring 27 are both bolted or welded to the outer walls of the left receiver assembly 5 and the right receiver assembly 6.

[0030] The compressor of the present application is easy to maintain in the field. The left casing assembly 5 and the right casing assembly 6 are designed to set the compressor casing with a long air inlet passage into a half-detachable structure, so as to realize the overall layout of the half-long casing and reliable assembly and disassembly positioning. At the same time, multiple maintenance inspection holes are opened on the left casing assembly 5. During the field test, the internal parts of the compressor can be regularly inspected through the maintenance inspection holes using detection instruments such as borescopes, so as to find abnormal parts and take corresponding measures to ensure flight safety; and each maintenance inspection hole is blocked by the inspection hole sealing assembly to reduce aerodynamic losses, so as to ensure that the maintenance inspection hole does not affect the normal function of the left casing assembly 5. In addition, the present application also uses the first linkage ring 26 and the second linkage ring 27 to perform circumferential concentric positioning of the left casing assembly 5 and the right casing assembly 6, so as to ensure that frequent disassembly and assembly will not affect the integrity of the casing and ensure the connection stability of the casing.

[0031] Preferably, please refer to Figure 1 , 4 As shown in Figure 5, the inspection hole sealing assembly includes a plugging cover bolt 1 and a plugging cover. The plugging cover includes a mounting platform and a sealing column. The sealing column is used to seal the maintenance inspection hole. The bottom end of the sealing column is provided with a pneumatic flow path surface for being flush with the internal flow path surface of the left casing assembly 5. The mounting platform is used to abut and cooperate with the preset mounting boss on the left casing assembly 5. A limiting screw hole is provided on the mounting platform. The plugging cover bolt 1 is used to pass through the limiting screw hole and cooperate with the preset mounting screw hole on the mounting boss to connect the plugging cover to the left casing assembly 5.

[0032] It is understandable that the plug cover is connected to the left casing assembly 5 by the plug cover bolt 1, so that the sealing column of the plug cover can seal the maintenance inspection hole, thereby preventing the opening of the maintenance inspection hole from affecting the normal function of the left casing assembly 5. When it is necessary to check the condition of the components inside the compressor casing, the plug cover can be removed, and the detection instrument can be inserted into the maintenance inspection hole for inspection.

[0033] It should be noted that in order to prevent the sealing column from having too much impact on the aerodynamic performance of the flow channel inside the left casing assembly 5, an aerodynamic flow channel surface is provided at the bottom end of the sealing column to be flush with the internal flow channel surface of the left casing assembly 5, so as to prevent the bottom end of the sealing column from protruding and extending into the flow channel to cause interference and reduce the loss of aerodynamic performance.

[0034] Preferably, please refer to Figure 1 , 4 As shown in FIG. 5 , the diameters of the maintenance inspection holes are different, a plurality of plugging covers are provided, and each plugging cover is arranged one-to-one with each maintenance inspection hole, and two limiting screw holes are provided on the mounting platform of each plugging cover, and the spans between the two limiting screw holes and the center point of the mounting platform are different, so as to correspond one-to-one with the mounting screw holes on each mounting boss, thereby ensuring that the pneumatic flow path surface of each sealing column is flush with the internal flow path surface of the left casing assembly 5.

[0035] It can be understood that in order to achieve the error-proofing function and to ensure that the assembly positions of each plugging cover and each maintenance inspection hole are unique during the maintenance and disassembly process, so as to avoid the protrusion of the flow path surface of a plugging cover when it is reinstalled after maintenance, affecting the performance or causing scraping of the rotor and stator, by setting different diameters for each maintenance inspection hole, the corresponding sealing columns of each plugging cover also have different diameters to match them, which can facilitate workers to distinguish different plugging covers and ensure the sealing effect of the maintenance inspection holes; at the same time, the spans of the two limiting screw holes on the mounting platform of each plugging cover and the center point of the mounting platform are different, such as the spans are a and b respectively, so as to correspond one by one with the mounting screw holes on each mounting boss, so that the assembly position of the plugging cover is unique during each disassembly and assembly process, effectively improving the efficiency of disassembly and assembly and the stability and consistency of assembly.

[0036] Optionally, a sealing gasket 3 is provided between the mounting platform and the mounting boss, and the sealing gasket 3 can improve the sealing effect of the plugging cover on the maintenance inspection hole.

[0037] In some embodiments, three maintenance inspection holes are provided to minimize the impact of the maintenance inspection holes on the overall structure and performance of the left receiver assembly 5, which are respectively the first inspection hole 4, the second inspection hole 8 and the third inspection hole 10 at different positions on the outer wall of the left receiver assembly 5. There are also three corresponding plugging covers, which are respectively the first plugging cover 2, the second plugging cover 7 and the third plugging cover 9 corresponding to the three maintenance inspection holes. The structures of the plugging covers are the same, except that the diameter of the sealing column and the positions of the two limiting screw holes on the mounting platform are different, so as to avoid the plugging covers from being installed in the wrong position and to facilitate the workers to classify and label the plugging covers for storage.

[0038] Preferably, please refer to Figure 1 , 7 As shown in , 8 and 14, the two-stage linkage ring assembly also includes a locking bolt 21 and a connecting plate assembly. The first linkage ring 26 and the second linkage ring 27 are both annular structures divided into half. The two halves of the first linkage ring 26 are respectively connected to the left receiver assembly 5 and the right receiver assembly 6, and the two halves of the second linkage ring 27 are respectively connected to the left receiver assembly 5 and the right receiver assembly 6. The connecting plate assembly is used to respectively abut against the opposite sides of the first linkage ring 26 and shield the two halves of the seam of the first linkage ring 26, and the connecting plate assembly and the two halves of the first linkage ring 26 are connected and fastened by the locking bolt 21; the connecting plate assembly is also used to respectively abut against the opposite sides of the second linkage ring 27 and shield the two halves of the seam of the second linkage ring 27, and the connecting plate assembly and the two halves of the second linkage ring 27 are connected and fastened by the locking bolt 21.

[0039] It can be understood that the first linkage ring 26 and the second linkage ring 27 are both annular structures divided into halves. In order to achieve the connection and fastening of the half structures, so as to achieve the circumferential concentric positioning of the left casing assembly 5 and the right casing assembly 6 by the first linkage ring 26 and the second linkage ring 27, the joints of the first linkage ring 26 and the second linkage ring 27 are connected by a connecting plate assembly, so that the two halves of the first linkage ring 26 and the second linkage ring 27 are connected as a whole ring, that is, the circumferential concentric positioning of the left casing assembly 5 and the right casing assembly 6 is achieved to ensure the stability of the splicing of the two half casing assemblies.

[0040] Preferably, please refer to Figure 1 , 7As shown in , 8, and 14, the connecting plate assembly includes a first connecting plate 22, a second connecting plate 23, a third connecting plate 24, and a fourth connecting plate 25. The first connecting plate 22 and the second connecting plate 23 are used to respectively abut against the opposite sides of the first linkage ring 26 and cover the two halves of the seam of the first linkage ring 26. The locking bolt 21 is used to sequentially pass through the preset connecting screw holes on the first connecting plate 22, the first linkage ring 26, and the second connecting plate 23 to connect and fasten the three. The third connecting plate 24 and the fourth connecting plate 25 are used to respectively abut against the opposite sides of the second linkage ring 27 and cover the two halves of the seam of the second linkage ring 27. The locking bolt 21 is also used to sequentially pass through the preset connecting screw holes on the third connecting plate 24, the second linkage ring 27, and the fourth connecting plate 25 to connect and fasten the three.

[0041] It can be understood that the first connecting plate 22 and the second connecting plate 23 can be used to clamp the first linkage ring 26, and the joints of the first linkage ring 26 of the half structure can be connected and fastened, so that the first linkage ring 26 is connected to form a whole ring, thereby strengthening the connection stability of the left receiver assembly 5 and the right receiver assembly 6; similarly, the third connecting plate 24 and the fourth connecting plate 25 can also achieve the same connection and fastening effect on the second linkage ring 27, thereby ensuring the integrity of the half long receiver.

[0042] Preferably, please refer to Figure 7 , 8 As shown in FIG. 14 , the first connecting plate 22, the second connecting plate 23, the third connecting plate 24 and the fourth connecting plate 25 have the same structure and all include arc-shaped plates, on which a plurality of connecting screw holes are spaced apart, and on which a disassembly groove is provided, for allowing a disassembly tool to abut against the arc-shaped plate and to limit the disassembly tool.

[0043] It is understandable that the arc plate can better achieve the abutment and fit with the first linkage ring 26 and the second linkage ring 27, and the multiple connection screw holes arranged at intervals on the arc plate correspond to the connection screw holes on the first linkage ring 26 and the second linkage ring 27, so as to cooperate with the locking bolts 21 to lock and fix the arc plate on the opposite sides of the first linkage ring 26 and the second linkage ring 27, and at the same time achieve the effect that the arc plate connects the first linkage ring 26 and the second linkage ring 27 into a whole. In addition, the arc plate is provided with a disassembly groove, which can effectively prevent damage to parts during disassembly, and also facilitate workers to intuitively find the disassembly point, thereby improving the efficiency of disassembly and assembly.

[0044] Preferably, please refer to Figure 7 , 8 As shown, the two-stage linkage ring assembly also includes a long positioning bushing 28, which is used to cooperate with the connecting screw holes on the arc plate, the first linkage ring 26 and the second linkage ring 27 to respectively circumferentially concentrically position the two halves of the first linkage ring 26 and the two halves of the second linkage ring 27.

[0045] It can be understood that in order to improve the accuracy and stability of the circumferential concentric positioning of the two halves of the first linkage ring 26 and the two halves of the second linkage ring 27, the long positioning bushing 28 is cooperated with the connecting screw holes on the arc plate, the first linkage ring 26 and the second linkage ring 27 to achieve the guiding and positioning effects, while also strengthening the connection strength and improving the stability of the connection.

[0046] It should be noted that the present invention does not exclude the solution of multiple-stage linkage ring assemblies above the two-stage linkage ring assembly, which can enhance the circumferential concentric positioning effect of the left casing assembly 5 and the right casing assembly 6, and the number of parts of the corresponding connecting plate assembly can be increased synchronously.

[0047] According to another aspect of the present application, a maintenance method is also provided, which is applied to the maintenance of the above-mentioned compressor that is easy to maintain on site, and the maintenance method comprises the following steps: S100, disconnect the left casing assembly 5 from the engine systems, and measure and record the rotational torque M1 of the combustion rotor before maintenance; S200, dismantling the first connecting bolt 17 to disconnect the left casing assembly 5 from the front casing 15, and dismantling the third connecting bolt 19 to disconnect the left casing assembly 5 from the rear casing 16; S300, dismantling the second connecting bolt 18 to disconnect the left casing assembly 5 from the right casing assembly 6, and disassembling the casing positioning bushing 20; S400, disassembling the first linkage ring 26 and the second linkage ring 27, and then removing the left casing assembly 5 from the engine body; S500. Maintenance personnel shall perform on-site protection according to the aircraft engine maintenance manual and carry out on-site repair of the damaged blades. During the repair process, the gas generator rotor may be rotated to move the damaged blades to the best repair position. S600. After maintenance, assemble the compressor components as they were, measure and record the rotational torque M2 of the rotor, and judge the maintenance effect by comparing M2 with M1.

[0048] The "engine systems" here refer to the bleed valve control cable 11 connected to the left casing assembly 5; the air duct 12; the adjustable guide vane control assembly 13; and the bleed valve air pipe 14, which can be disassembled and disconnected by special on-site disassembly tools.

[0049] The maintenance method of the present application also has the above-mentioned beneficial effects, and the maintenance method of the present application can realize that the compressor can be directly repaired on the installation platform, by disconnecting the connection between the left casing assembly 5 and the front casing 15, the rear casing 16 and the right casing assembly 6 in sequence, and then disassembling the first linkage ring 26 and the second linkage ring 27, the left casing assembly 5 can be removed from the engine body, which is very convenient for maintenance personnel to repair related parts on site, greatly shortening the maintenance cycle brought by returning the unit body where the damaged parts are located to the engine center and reducing maintenance costs, thereby improving the commercial competitiveness of civil engines.

[0050] Preferably, in step S400, the two-stage stationary blade rings of the engine can be fixed to the right casing assembly 6 by a stop plate assembly to prevent blades from falling during disassembly and transportation.

[0051] Specifically, the stop plate assembly includes a first stop plate 29, a second stop plate 31 and a countersunk screw 30. The first stop plate 29 and the second stop plate 31 are both plate-like structures with a limiting hole at one end, so as to facilitate the countersunk screw 30 to limit and fix the zero-stage stationary blade ring and the first-stage stationary blade ring of the two-stage stationary blade ring to the right casing assembly 6 to prevent the blades from falling. Optionally, the two-stage stationary blade rings can also be bound and limited by using a pull rope or a rubber belt on site, which can be used according to the site conditions.

[0052] It is understandable that after the left casing assembly 5 is removed from the engine body, some movable parts are exposed and some may be in an unrestrained state. In order to avoid problems such as blades falling off during disassembly and transportation, the two-stage stationary blade rings can be respectively restrained and fixed on the right casing assembly 6 by the first stop plate 29, the second stop plate 31 and the countersunk screws 30, and then maintenance operations can be conveniently carried out.

[0053] It should be noted that when the left casing assembly 5 is removed, the inlet stage rotor and half of the second and third stage rotors are exposed in the space outside the right casing assembly 6, and there are no axial guide blades, so there is enough space for maintenance work. The maintenance personnel can perform on-site protection according to the relevant maintenance manual or documents, and perform on-site maintenance on the damaged blades. During the maintenance process, the gas generator rotor can be rotated to move the damaged blades to the best maintenance position. According to the blade disk hub ratio, the blade axial position and the maintenance operable space, the best maintenance angle of the blade is 7 to 9 o'clock.

[0054] Preferably, the assembly sequence in step S600 is to connect the left casing assembly 5 and the right casing assembly 6, axially position the left casing assembly 5 and the right casing assembly 6 by the casing positioning bushing 20, connect the left casing assembly 5 and the right casing assembly 6 by the second connecting bolt 18; connect the left casing assembly 5 and the front casing 15 by the first connecting bolt 17; connect the left casing assembly 5 and the rear casing 16 by the third connecting bolt 19; connect and fasten the first linkage ring 26 and the second linkage ring 27 to the left casing assembly 5 and the right casing assembly 6 by the locking bolt 21; and connect the left casing assembly 5 to various engine systems.

[0055] It can be understood that the overall assembly sequence is roughly the reverse operation of the disassembly sequence. The specific details of the casing locating bushing 20 being installed in an up and down cross sequence and the need to remove the stop plate assembly are not repeated here. Maintenance personnel can perform a complete restoration according to the disassembly sequence. The overall operation steps are much simpler than disassembling the entire machine, which is very helpful for maintenance personnel to greatly improve the efficiency of maintenance.

[0056] In summary, the compressor with a long air inlet channel of the present application realizes a half-casing layout with high casing function integration through the left casing assembly 5 and the right casing assembly 6. The compressor can be directly repaired on the installation platform, and the disassembly and assembly is simple, safe and reliable; by opening a maintenance inspection hole on the left casing assembly 5 and cooperating with the characteristic design of the inspection hole sealing assembly, that is, a gas flow path surface is designed at the bottom end of the plug cover and is sealed with a sealing gasket 3, aerodynamic losses are reduced; at the same time, the axial and circumferential error-proofing designs of the present application eliminate the engine operation risks caused by assembly and disassembly, the first linkage ring 26 and the second linkage ring 27 adopt a half structure, and cooperate with the connecting plate assembly to realize the connection of the two halves to form a whole, which can be disassembled and assembled multiple times and the positioning is reliable; multiple designs can smoothly realize that when the compressor blades are damaged by foreign objects and need to be repaired, they can be repaired in the field, which greatly shortens the maintenance cycle brought by the unit body where the damaged parts are located returning to the engine center and reduces the maintenance cost, thereby improving the economy and commercial competitiveness of civil engines.

[0057] It should be noted that, in this article, the terms "comprises", "includes" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or apparatus that includes a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or apparatus.

[0058] This article uses specific examples to illustrate the principles and implementation methods of this application. The above examples are only used to help understand the method and its core ideas of this application. The above is only the preferred implementation method of this application. It should be pointed out that due to the limitations of textual expression and the objective existence of infinite specific structures, ordinary technicians in this technical field can make several improvements, modifications or changes without departing from the principles of this application, and can also combine the above technical features in an appropriate manner; these improvements, modifications, changes or combinations, or the direct application of the inventive concept and technical solution to other occasions without improvement, should be regarded as the protection of this application.

Claims

1. A compressor that is easy to maintain on site, comprising a front casing (15) and a rear casing (16), It is characterized in that The compressor convenient for field maintenance also includes a left casing assembly (5), a right casing assembly (6), a first connecting bolt (17), a second connecting bolt (18), a third connecting bolt (19), a casing positioning bushing (20), a two-stage linkage ring assembly and an inspection hole sealing assembly: The first connecting bolt (17) is used to connect the left receiver assembly (5) and the front receiver (15), the third connecting bolt (19) is used to connect the left receiver assembly (5) and the rear receiver (16), and the receiver positioning bushing (20) is used to axially position the left receiver assembly (5) and the right receiver assembly (6), and then cooperate with the second connecting bolt (18) to connect the left receiver assembly (5) and the right receiver assembly (6); The two-stage linkage ring assembly comprises a first linkage ring (26) and a second linkage ring (27), wherein the first linkage ring (26) and the second linkage ring (27) are arranged at intervals on the outer walls of the left casing assembly (5) and the right casing assembly (6) and are used to position the left casing assembly (5) and the right casing assembly (6) concentrically in the circumferential direction; The left casing assembly (5) is provided with a plurality of maintenance inspection holes, each of which is used for allowing a detection instrument to extend into the interior of the compressor to inspect parts, and the inspection hole sealing assembly is used to seal each of the maintenance inspection holes.

2. The compressor that is easy to maintain on site according to claim 1, It is characterized in that The inspection hole sealing assembly comprises a plugging cover bolt (1) and a plugging cover, the plugging cover comprises a mounting platform and a sealing column, the sealing column is used to seal the maintenance inspection hole, the bottom end of the sealing column is provided with a pneumatic flow path surface for being flush with the internal flow path surface of the left casing assembly (5), the mounting platform is used to abut and cooperate with a preset mounting boss on the left casing assembly (5), a limiting screw hole is provided on the mounting platform, and the plugging cover bolt (1) is used to pass through the limiting screw hole and cooperate with the preset mounting screw hole on the mounting boss to connect the plugging cover to the left casing assembly (5).

3. The compressor that is easy to maintain on site according to claim 2, It is characterized in that The diameters of the maintenance inspection holes are different. A plurality of plugging covers are provided and each plugging cover is arranged in one-to-one correspondence with each maintenance inspection hole. Two limiting screw holes are provided on the mounting platform of each plugging cover, and the spans between the two limiting screw holes and the center point of the mounting platform are different, so as to correspond one-to-one with the mounting screw holes on each mounting boss, thereby ensuring that the pneumatic flow path surface of each sealing column is flush with the internal flow path surface of the left casing assembly (5).

4. The compressor that is easy to maintain on site according to claim 1, It is characterized in that The two-stage linkage ring assembly further comprises a locking bolt (21) and a connecting plate assembly. The first linkage ring (26) and the second linkage ring (27) are both ring structures divided into halves. The two halves of the first linkage ring (26) are respectively connected to the left receiver assembly (5) and the right receiver assembly (6). The two halves of the second linkage ring (27) are respectively connected to the left receiver assembly (5) and the right receiver assembly (6). The connecting plate assembly is used to respectively abut against opposite sides of the first linkage ring (26) and shield the seam between the two halves of the first linkage ring (26), and to connect and fasten the connecting plate assembly and the two halves of the first linkage ring (26) through the locking bolt (21). The connecting plate assembly is also used to respectively abut against opposite sides of the second linkage ring (27) and shield the seam between the two halves of the second linkage ring (27), and to connect and fasten the connecting plate assembly and the two halves of the second linkage ring (27) through the locking bolt (21).

5. The compressor that is easy to maintain on site according to claim 4, It is characterized in that The connecting plate assembly comprises a first connecting plate (22), a second connecting plate (23), a third connecting plate (24) and a fourth connecting plate (25); the first connecting plate (22) and the second connecting plate (23) are used to respectively abut against opposite sides of a first linkage ring (26) and cover two half seams of the first linkage ring (26); the locking bolt (21) is used to sequentially pass through the connection screw holes preset on the first connecting plate (22), the first linkage ring (26) and the second connecting plate (23) to connect and fasten the three; the third connecting plate (24) and the fourth connecting plate (25) are used to respectively abut against opposite sides of a second linkage ring (27) and cover two half seams of the second linkage ring (27); the locking bolt (21) is also used to sequentially pass through the connection screw holes preset on the third connecting plate (24), the second linkage ring (27) and the fourth connecting plate (25) to connect and fasten the three.

6. The compressor that is easy to maintain on site according to claim 5, It is characterized in that The first connecting plate (22), the second connecting plate (23), the third connecting plate (24) and the fourth connecting plate (25) have the same structure and all comprise an arc-shaped plate, a plurality of connecting screw holes are provided at intervals on the arc-shaped plate, and a disassembly groove is provided on the arc-shaped plate, the disassembly groove is used for a disassembly tool to abut against the arc-shaped plate and limit the disassembly tool.

7. The compressor that is easy to maintain on site according to claim 6, It is characterized in that The two-stage linkage ring assembly also includes a long positioning bushing (28) which is used to cooperate with the connecting screw holes on the arc plate, the first linkage ring (26) and the second linkage ring (27) to respectively position the two halves of the first linkage ring (26) and the two halves of the second linkage ring (27) in a circumferentially concentric manner.

8. A maintenance method, applied to the maintenance of a compressor that is easy to maintain on the field as claimed in any one of claims 1 to 7, It is characterized in that The repair method includes the following steps: S100, disconnect the left casing assembly (5) from the engine systems, and measure and record the rotational torque M1 of the combustion rotor before maintenance; S200, removing the first connecting bolt (17) to disconnect the left casing assembly (5) from the front casing (15), and removing the third connecting bolt (19) to disconnect the left casing assembly (5) from the rear casing (16); S300, removing the second connecting bolt (18) to disconnect the left casing assembly (5) from the right casing assembly (6), and disassembling the casing positioning bushing (20); S400, disassembling the first linkage ring (26) and the second linkage ring (27), and then removing the left casing assembly (5) from the engine body; S500. Maintenance personnel shall perform on-site protection according to the aircraft engine maintenance manual and carry out on-site repair of the damaged blades. During the repair process, the gas generator rotor may be rotated to move the damaged blades to the best repair position. S600. After maintenance, assemble the compressor components as they were, measure and record the rotational torque M2 of the rotor, and judge the maintenance effect by comparing M2 with M1.

9. The maintenance method according to claim 8, It is characterized in that In step S400, the two-stage stationary blade rings of the engine can be fixed to the right casing assembly (6) by means of a stop plate assembly to prevent blades from falling off during disassembly and transportation.

10. The maintenance method according to claim 8, It is characterized in that The assembly sequence in step S600 is to connect the left casing assembly (5) and the right casing assembly (6), axially position the left casing assembly (5) and the right casing assembly (6) by means of a casing positioning bushing (20), connect the left casing assembly (5) and the right casing assembly (6) by means of a second connecting bolt (18); connect the left casing assembly (5) and the front casing (15) by means of a first connecting bolt (17); connect the left casing assembly (5) and the rear casing (16) by means of a third connecting bolt (19); connect and fasten the first linkage ring (26) and the second linkage ring (27) to the left casing assembly (5) and the right casing assembly (6) by means of a locking bolt (21); and connect the left casing assembly (5) to various engine systems.

Images