Blade damper simulation device

Abstract

The application discloses a vane baffle simulation device, which is used for limiting the front end of a vane after the vane of a high-pressure turbine rotor is assembled to a turbine disc, and comprises a first connecting piece, a second connecting piece, the first connecting piece is used for being connected to the front end of the turbine disc, one side of the second connecting piece is connected with the first connecting piece, the other side of the second connecting piece extends towards the direction close to the vane, and the second connecting piece is used for abutting against the vane. The front end of the turbine disc is connected by the first connecting piece, so that the second connecting piece can be fixed by being connected with the first connecting piece, and then the other side of the second connecting piece can abut against the vane to limit the vane. The vane baffle simulation device can effectively reduce the assembling and disassembling time of the vane, and improve the assembling efficiency of the vane high-pressure turbine rotor. In addition, the vane baffle simulation device can avoid repeated deformation and disassembly of the front baffle disc, and improve the service life of the front baffle disc.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aero-engines, in particular to a vane baffle simulation device. BACKGROUND

[0002] An aero-engine is an important component of an aircraft. The aero-engine usually comprises a high-pressure turbine rotor. Figure 1 As shown in the figure, a structure of a conventional high-pressure turbine rotor of an aero-engine is shown. In the figure, a vane is mounted in a tenon slot of a turbine disc, and a front end is limited by a front baffle disc. Figure 1 The front baffle disc is connected to the turbine disc by a buckle structure, and an interference stop connection is usually used between the front baffle disc and the turbine disc.

[0003] The tool for installing the front baffle disc and the operation are extremely complex, and a hydraulic device is usually used to drive the front baffle disc to deform and to push the front baffle disc to rotate, so that the buckle between the front baffle disc and the turbine disc is effective.

[0004] Before the high-pressure turbine rotor is installed, the tip diameter needs to be qualified, so that a high-speed tip grinding process needs to be performed. According to the existing process, the high-pressure turbine rotor needs to be assembled and then the high-speed tip is ground, and after the high-speed tip is ground, the vane is disassembled and cleaned.

[0005] In view of the complexity of the assembly of the front baffle disc of the high-pressure turbine rotor, if the real front baffle disc is used to limit the vane during grinding, the assembly and disassembly period of the front baffle disc is relatively long, and it takes two workers 6 hours to complete the assembly and disassembly of the front baffle disc, and a total of about 12 hours is needed.

[0006] In addition, the repeated deformation and disassembly of the front baffle disc also affects the service life of the front baffle disc. SUMMARY

[0007] The technical problem to be solved by the present application is to overcome the above-mentioned defect that the time for limiting the vane by the front baffle disc is long after the vane of the high-pressure turbine rotor is assembled to the turbine disc in the prior art, and to provide a vane baffle simulation device.

[0008] The present application solves the above technical problems by the following technical solutions:

[0009] A vane baffle simulation device, which is used for limiting the front end of the vane after the vane of a high-pressure turbine rotor is assembled to a turbine disc, the vane baffle simulation device comprising:

[0010] A first connecting piece, which is used for connecting to the front end of the turbine disc;

[0011] A second connecting piece is connected to one side of the first connecting piece and extends to the direction close to the blade, and is used to abut against the blade.

[0012] In the scheme, by using the above structure, the front end of the turbine disc is connected by the first connecting piece, so that the second connecting piece can be fixed by connecting the first connecting piece, and the other side of the second connecting piece can abut against the blade to limit the blade. The blade baffle simulation device can effectively reduce the assembly and disassembly time of the blade, and improve the assembly efficiency of the blade high-pressure turbine rotor. It can also avoid repeated deformation and disassembly of the front baffle, and can improve the service life of the front baffle.

[0013] Preferably, the first connecting piece is a bottom ring, which is used to be arranged at the front end of the turbine disc, and the second connecting piece is connected to the bottom ring.

[0014] In the scheme, by using the above structure, the bottom ring is annular, which is convenient to match with the turbine disc, and can simplify the structure of the blade baffle simulation device.

[0015] Preferably, the inner circumferential surface of the bottom ring is an inner cylindrical surface, and the axis of the inner cylindrical surface coincides with the axis of the turbine disc.

[0016] And / or, the outer circumferential surface of the bottom ring is an outer cylindrical surface, and the axis of the outer cylindrical surface coincides with the axis of the turbine disc.

[0017] In the scheme, by using the above structure, the bottom ring coincides with the axis of the turbine disc, which is convenient to position the second connecting piece, and can abut against the blade more stably.

[0018] Preferably, the blade baffle simulation device further comprises an axial limiting piece, one end of the axial limiting piece is connected to the first connecting piece, the other end of the axial limiting piece extends along the radial direction of the turbine disc, and the other end of the axial limiting piece is used to abut against the inner side surface of the baffle table of the turbine disc.

[0019] In the scheme, by using the above structure, the first connecting piece can be effectively prevented from moving along the axis direction of the turbine disc, and the stability and reliability of the second connecting piece abutting against the blade can be improved.

[0020] Preferably, the number of the axial limiting pieces is multiple, and the multiple axial limiting pieces are uniformly spaced on the outer circumferential surface of the first connecting piece.

[0021] And / or, the axial limiting piece is an outward extending stop gear, which extends outward along the radial direction of the turbine disc from the outer circumferential surface of the first connecting piece.

[0022] In the scheme, by adopting the above structure, the overhanging tooth structure is simple and reliable.

[0023] Preferably, the vane baffle simulation device further comprises an axial connecting assembly, the axial connecting assembly is used for connecting the first connecting member and the second connecting member, the axial connecting assembly is arranged between the first connecting member and the second connecting member, and the axial connecting assembly extends outward from the side surface of the first connecting member.

[0024] Preferably, the number of the axial connecting assemblies is multiple, and the multiple axial connecting assemblies are uniformly spaced and connected to the outer side surface of the first connecting member.

[0025] In the scheme, by adopting the above structure, the axial connecting assembly can effectively improve the integrity of the first connecting member and the second connecting member, avoid displacement between the two, and improve the stability and reliability of the vane baffle simulation device.

[0026] Preferably, the second connecting member is a compression ring, the inner side of the compression ring is connected to the first connecting member, and the outer side of the compression ring is used for abutting against the vane.

[0027] In the scheme, by adopting the above structure, the compression ring is annular, which is convenient for matching with the vane and can simplify the structure of the vane baffle simulation device.

[0028] Preferably, the compression ring comprises a radial ring and a circumferential ring, the inner side surface of the circumferential ring is connected to the first connecting member, the outer side surface of the circumferential ring is connected to the circumferential ring, and the circumferential ring is used for abutting against the vane.

[0029] In the scheme, by adopting the above structure, the radial ring and the circumferential ring can simplify the structure of the compression ring and improve the stability and reliability of the compression ring.

[0030] Preferably, the vane baffle simulation device further comprises a circumferential positioning assembly, one end of the circumferential positioning assembly is connected to the first connecting member and / or the second connecting member, and the other end of the circumferential positioning assembly is used for being inserted into the gap between the blocking tables of the turbine disc.

[0031] In the scheme, by adopting the above structure, the circumferential positioning assembly can effectively avoid rotation of the vane baffle simulation device and improve the stability and reliability of the vane baffle simulation device.

[0032] Preferably, the circumferential positioning assembly comprises two groups of positioning bolts, the second connecting member is provided with corresponding threaded holes, and the two threaded holes are spaced apart by a plurality of blocking tables.

[0033] On the basis of common general knowledge in the art, the above-mentioned preferred conditions can be combined arbitrarily, thereby obtaining each preferred example of the present application.

[0034] The positive and progressive effects of this invention are as follows:

[0035] This invention utilizes a first connector to connect the front end of the turbine disk, allowing a second connector to be fixed by connecting to the first connector. Furthermore, the other side of the second connector abuts against the blade, thus limiting its movement. This blade baffle simulation device effectively reduces blade assembly and disassembly time, improving the assembly efficiency of the high-pressure turbine rotor. It also avoids repeated deformation and disassembly of the front baffle, extending its service life. Attached Figure Description

[0036] Figure 1 This is a schematic diagram of the structure of the front disc limiting blade in the prior art.

[0037] Figure 2 This is a schematic diagram of the exploded structure of the blade baffle simulation device according to a preferred embodiment of the present invention.

[0038] Figure 3 for Figure 2 A schematic diagram of the structure of the first connecting component of the blade baffle simulation device being installed on the turbine disk.

[0039] Figure 4 for Figure 2 A schematic diagram of the structure of the blade baffle simulation device installed on the cross-section of the turbine disk.

[0040] Figure 5 for Figure 2 A schematic diagram of the cross-section of the assembled blade baffle simulation device.

[0041] Explanation of reference numerals in the attached figures:

[0042] Blade baffle simulation device 100

[0043] Axial limiting component 11

[0044] Axial connection assembly 12

[0045] Circumferential positioning component 13

[0046] Threaded hole 14

[0047] First connector 20

[0048] Bottom ring 21

[0049] Inner cylindrical surface 22

[0050] outer cylindrical surface 23

[0051] Second connector 30

[0052] Pressure ring 31

[0053] Radial ring 32

[0054] Zhou Xianghuan 33

[0055] Leaf 91

[0056] Turbine disk 92

[0057] Block 93

[0058] Gap 94

[0059] Front gear 95 Detailed Implementation

[0060] The present invention will be described more clearly and completely below by way of embodiments and in conjunction with the accompanying drawings, but the present invention is not limited to the scope of the embodiments.

[0061] like Figures 2 to 5 As shown, this embodiment is a blade baffle simulation device 100. After the blade 91 of the high-pressure turbine rotor is assembled to the turbine disk 92, the blade baffle simulation device 100 is used to limit the front end of the blade 91. The blade baffle simulation device 100 includes: a first connecting member 20 and a second connecting member 30. The first connecting member 20 is used to connect to the front end of the turbine disk 92; one side of the second connecting member 30 is connected to the first connecting member 20, and the other side of the second connecting member 30 extends towards the blade 91, and the second connecting member 30 is used to abut against the blade 91. By using the first connecting member 20 to connect to the front end of the turbine disk 92, the second connecting member 30 can be fixed by connecting to the first connecting member 20, and then the other side of the second connecting member 30 can abut against the blade 91, thereby limiting the blade 91. The blade baffle simulation device 100 can effectively reduce the assembly and disassembly time of the blade 91 and improve the assembly efficiency of the high-pressure turbine rotor with blade 91. It can also avoid repeated deformation and disassembly of the front baffle 95, thereby improving the service life of the front baffle 95.

[0062] The first connecting member 20 is a bottom ring 21, which is used to be installed at the front end of the turbine disk 92. The second connecting member 30 is connected to the bottom ring 21. The bottom ring 21 is annular, which facilitates its adaptation to the turbine disk 92 and simplifies the structure of the blade baffle simulation device 100.

[0063] In this embodiment, the inner circumferential surface of the bottom ring 21 is an inner cylindrical surface 22, and the axis of the inner cylindrical surface 22 coincides with the axis of the turbine disk 92. The outer circumferential surface of the bottom ring 21 is an outer cylindrical surface 23, and the axis of the outer cylindrical surface 23 coincides with the axis of the turbine disk 92. The coincidence of the axes of the bottom ring 21 and the turbine disk 92 facilitates the positioning of the second connecting member 30 and allows it to more securely abut against the blade 91.

[0064] In other embodiments, the first connecting piece 20 can also have other structural forms, such as triangular shape, quadrilateral shape, pentagonal shape, hexagonal shape, etc., and of course, can also be irregular shape.

[0065] The vane baffle simulation device 100 further comprises an axial limiting piece 11, one end of the axial limiting piece 11 is connected to the first connecting piece 20, the other end of the axial limiting piece 11 extends along the radial direction of the turbine disc 92, and the other end of the axial limiting piece 11 is used to abut the inner side of the retaining table 93 of the turbine disc 92, which can effectively prevent the first connecting piece 20 from moving along the axial direction of the turbine disc 92, and can improve the stability and reliability of the second connecting piece 30 abutting against the vane 91.

[0066] The number of the axial limiting pieces 11 is multiple, and the multiple axial limiting pieces 11 are uniformly and spacedly arranged on the outer circumferential surface of the first connecting piece 20. The axial limiting piece 11 is an outward extending stop gear, which extends outward along the radial direction of the turbine disc 92 from the outer circumferential surface of the first connecting piece 20. The outward extending stop gear has simple structure and reliable effect. The structure of the turbine disc 92 can specifically extend outward along the radial direction of the turbine disc 92, and the cross section of the outward extending stop gear becomes smaller.

[0067] In other embodiments, the axial limiting piece 11 can also have other structural forms, such as a clamping structure capable of clamping the turbine disc 92, a structure capable of being embedded into the gap of the turbine disc 92, etc., which can play a role in limiting the axial direction of the turbine disc 92. Of course, the axial limiting piece 11 can also be a special abutting structure, which abuts against the first connecting piece 20 to achieve the axial limiting of the first connecting piece 20.

[0068] The vane baffle simulation device 100 further comprises an axial connecting assembly 12, which is used to connect the first connecting piece 20 and the second connecting piece 30, and is arranged between the first connecting piece 20 and the second connecting piece 30 and extends outward from the side surface of the first connecting piece 20. The number of the axial connecting assemblies 12 is multiple, and the multiple axial connecting assemblies 12 are uniformly and spacedly connected to the outer side surface of the first connecting piece 20. The axial connecting assembly 12 can effectively improve the integrity of the first connecting piece 20 and the second connecting piece 30, avoid displacement between the two, and improve the stability and reliability of the vane baffle simulation device 100.

[0069] In this embodiment, the axial connecting assembly 12 can be a bolt and nut assembly, and in other embodiments, the axial connecting assembly 12 can also be a buckle assembly, a magnetic assembly, etc., which can fix the first connecting piece 20 and the second connecting piece 30.

[0070] The second connecting member 30 is a compression ring 31, the inner side of the compression ring 31 is connected with the first connecting member 20, and the outer side of the compression ring 31 is used for abutting against the blade 91. The compression ring 31 is annular, facilitating the adaptation with the blade 91 and simplifying the structure of the blade baffle simulation device 100.

[0071] The compression ring 31 is connected with a radial ring 32 and a circumferential ring 33, the inner side of the circumferential ring 33 is connected with the first connecting member 20, the outer side of the circumferential ring 33 is connected with the circumferential ring 33, and the circumferential ring 33 is used for abutting against the blade 91. The radial ring 32 and the circumferential ring 33 can simplify the structure of the compression ring 31 and improve the stability and reliability of the compression ring 31. The cross section of the compression ring 31 can be L-shaped, the L-shaped compression ring 31 is simple in structure, can effectively connect the first connecting member 20, and can reliably abut against the blade 91.

[0072] In other embodiments, the second connecting member 30 can also have other structural forms, such as triangular shape, quadrilateral shape, pentagonal shape, hexagonal shape, etc., and of course, can also be irregular shape.

[0073] The blade baffle simulation device 100 further comprises a circumferential positioning assembly 13, one end of the circumferential positioning assembly 13 is connected with the first connecting member 20 and / or the second connecting member 30, and the other end of the circumferential positioning assembly 13 is used for being inserted into the gap 94 between the baffle tables 93 of the turbine disc 92. The circumferential positioning assembly 13 can effectively avoid the rotation of the blade baffle simulation device 100 and improve the stability and reliability of the blade baffle simulation device 100.

[0074] In this embodiment, the circumferential positioning assembly 13 comprises two groups of positioning bolts, the second connecting member 30 is provided with corresponding threaded holes 14, and the two threaded holes 14 are spaced apart by several baffle tables 93.

[0075] In other embodiments, the circumferential positioning assembly 13 can also have other structural forms, such as positioning pin, boss, pit, etc., which can cooperate with the turbine disc 92 to achieve positioning.

[0076] The vane baffle simulation device 100 of the embodiment can be used to replace the front baffle 95, and the vane baffle simulation device 100 can limit the front end of the vane 91. The vane baffle simulation device 100 can meet the tip grinding requirements of the vane 91 of the high-speed rotor. The vane baffle simulation device 100 can specifically include a bottom ring 21 and a pressing ring 31. The bottom ring 21 and the pressing ring 31 can be fixed on the baffle table 93 of the turbine disc 92 in a threaded pressing manner, so as to realize the axial limitation of the vane baffle simulation device 100. Two positioning bolts are installed on the pressing ring 31, and the bolts can be located in the gap 94 on both sides of the baffle table 93 of the turbine disc 92, so as to realize the circumferential limitation of the vane baffle simulation device 100. The vane baffle simulation device 100 has a simple structure and high installation efficiency. A single worker only needs 0.5 hours to realize the assembly and disassembly of the vane baffle simulation device 100. By using the vane baffle simulation device 100 to replace the front baffle 95 to limit the front end of the vane 91, the process preparation period of the high-speed tip grinding of the high-speed rotor can be greatly shortened, the disassembly and deformation frequency of the front baffle can be reduced, the service life of the front baffle 95 is not affected, and the process cost is greatly reduced.

[0077] By using the vane baffle simulation device 100 to replace the front baffle 95 to limit the front end of the vane 91, the assembly and disassembly of the front baffle 95 can be avoided, the process preparation period of the high-speed tip grinding of the high-speed rotor can be shortened, and the tip grinding process cost can be reduced.

[0078] The vane baffle simulation device 100 adopts a split structure. The vane baffle simulation device 100 includes a bottom ring 21 and a pressing ring 31. The bottom ring 21 is provided with an outward extending stop tooth, which can be screwed into the lower end of the baffle table 93 of the turbine disc 92. The bottom ring 21 and the pressing ring 31 are clamped at the upper and lower ends of the baffle table 93 of the turbine disc 92 in a threaded pressing manner, so as to realize the axial fixation of the vane baffle simulation device 100 on the turbine disc 92.

[0079] The axial height h of the pressing ring 31 can be customized based on a single size. The upper end surface of the baffle table 93 of the turbine disc 92 is used as a positioning reference. When installed, the pressing ring 31 is attached to the upper end surface of the baffle table 93 of the turbine disc 92, and the axial height h of the pressing ring 31 is consistent with the size H on the turbine disc 92. H is the axial height difference between the front end surface of the baffle table 93 of the turbine disc 92 and the front end surface of the tenon groove of the turbine disc 92, so as to realize simple positioning, single size, and easy accurate positioning and installation of the vane baffle simulation device 100.

[0080] The pressing ring 31 is provided with two threaded holes 14. After the positioning bolts are screwed in, the positioning bolts are located in the gap 94 on both sides of one or more baffle tables 93 of the turbine disc 92. After the positioning bolts are installed, the positioning bolts can be clamped on the baffle table 93 of the turbine disc 92, so as to realize the circumferential limitation of the vane baffle simulation device 100.

[0081] When high-speed tip grinding is performed, the blade baffle simulation device 100 can be used to eliminate the installation of the front baffle plate 95, thereby greatly reducing the process preparation period of high-speed tip grinding of the high-pressure turbine rotor.

[0082] The blade baffle simulation device 100 can replace the front baffle plate 95, thereby reducing the disassembly and deformation frequency of the front baffle plate, not affecting the service life of the front baffle plate 95, and greatly reducing the process cost.

[0083] The blade baffle simulation device 100 has a simple structure, is easy to install, and has low process cost.

[0084] As a specific use mode, the use mode of the blade baffle simulation device 100 can be as follows:

[0085] As shown in Figure 4 , the bottom ring 21 is placed on the front end surface of the turbine disc 92, and the outer extension stop teeth of the bottom ring 21 are located at the gap 94 between the two stop tables 93 of the turbine disc 92.

[0086] The bottom ring 21 is rotated at a small angle, so that the outer extension stop teeth of the bottom ring 21 are located below the stop table 93 of the turbine disc 92.

[0087] After aligning the installation holes, the compression ring 31 is installed on the front end surface of the stop table 93 of the turbine disc 92.

[0088] A plurality of compression nuts are installed, so that the compression ring 31 and the bottom ring 21 clamp the front and rear ends of the stop table 93 of the turbine disc 92.

[0089] Two positioning bolts are screwed into the installation holes of the compression ring 31, so that the two positioning bolts are located on both sides of one or more stop tables 93 of the turbine disc 92, and the blade baffle simulation device 100 is completed after assembly, as shown in Figure 5 .

[0090] Although the specific embodiments of the present application are described above, those skilled in the art should understand that this is only an example, and the protection scope of the present application is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present application, and these changes and modifications all fall within the protection scope of the present application.

Claims

1. A blade baffle simulation device, after a blade of a high-pressure turbine rotor is assembled to a turbine disc, the blade baffle simulation device is used to limit the front end of the blade when a blade tip grinding operation is performed, so as to reduce the disassembly and assembly deformation times of the front baffle; characterized in that, The blade baffle simulation device comprises: a first connecting piece for connecting to the front end of the turbine disc; a second connecting piece, one side of which is connected to the first connecting piece, and the other side of which extends towards the blade, for abutting against the blade; The blade baffle simulation device further comprises an axial limiting piece, one end of which is connected to the first connecting piece, and the other end of which extends along the radial direction of the turbine disc, for abutting against the inner side of the baffle platform of the turbine disc to limit the movement of the first connecting piece along the axial direction of the turbine disc; The blade baffle simulation device further comprises a circumferential positioning assembly, one end of which is connected to the first connecting piece and / or the second connecting piece, and the other end of which is used for inserting into the gap between the baffle platforms of the turbine disc; The blade baffle simulation device further comprises an axial connecting assembly for connecting the first connecting piece and the second connecting piece; The first connecting piece is a bottom ring, and the second connecting piece is a press ring, the inner side of which is connected to the first connecting piece, and the outer side of which is used for abutting against the blade.

2. The vane baffle simulation device of claim 1, wherein, The bottom ring is used for being arranged at the front end of the turbine disc, and the second connecting piece is connected to the bottom ring.

3. The vane baffle simulation device of claim 2, wherein, The inner circumferential surface of the bottom ring is an inner cylindrical surface, the axis of which coincides with the axis of the turbine disc; And / or, the outer circumferential surface of the bottom ring is an outer cylindrical surface, the axis of which coincides with the axis of the turbine disc.

4. The vane baffle simulation apparatus of claim 1, wherein The number of axial limiting pieces is multiple, and multiple axial limiting pieces are uniformly spaced on the outer circumferential surface of the first connecting piece; And / or, the axial limiting piece is an outward extending stop gear, which extends outward along the radial direction of the turbine disc from the outer circumferential surface of the first connecting piece.

5. The vane baffle simulation apparatus of claim 1, wherein, The axial connecting assembly is arranged between the first connecting piece and the second connecting piece, and extends outward from the side surface of the first connecting piece; And / or, the number of axial connecting assemblies is multiple, and multiple axial connecting assemblies are uniformly spaced on the outer side surface of the first connecting piece.

6. The vane baffle simulation apparatus of claim 1, wherein The press ring comprises a radial ring and a circumferential ring, the inner side surface of the circumferential ring is connected to the first connecting piece, and the outer side surface of the circumferential ring is connected to the circumferential ring, which is used for abutting against the blade.

7. The vane baffle simulation apparatus of claim 1, wherein The circumferential positioning assembly comprises two groups of positioning bolts, and the second connecting piece is provided with corresponding threaded holes, and the two threaded holes are spaced apart by several baffle platforms.

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