CN112828725B - Machining tool and machining method for ultra-large combustion engine turbine blade - Google Patents
Machining tool and machining method for ultra-large combustion engine turbine blade Download PDFInfo
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- CN112828725B CN112828725B CN202011528982.3A CN202011528982A CN112828725B CN 112828725 B CN112828725 B CN 112828725B CN 202011528982 A CN202011528982 A CN 202011528982A CN 112828725 B CN112828725 B CN 112828725B
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- 238000003754 machining Methods 0.000 title claims abstract description 47
- 238000002485 combustion reaction Methods 0.000 title claims description 25
- 238000000034 method Methods 0.000 title description 14
- 238000003825 pressing Methods 0.000 claims description 158
- 238000009966 trimming Methods 0.000 claims description 6
- 238000004140 cleaning Methods 0.000 claims description 3
- 238000003672 processing method Methods 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 8
- 238000009434 installation Methods 0.000 description 7
- 230000000694 effects Effects 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 4
- 230000008569 process Effects 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000010008 shearing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B19/00—Single-purpose machines or devices for particular grinding operations not covered by any other main group
- B24B19/14—Single-purpose machines or devices for particular grinding operations not covered by any other main group for grinding turbine blades, propeller blades or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B1/00—Processes of grinding or polishing; Use of auxiliary equipment in connection with such processes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B41/00—Component parts such as frames, beds, carriages, headstocks
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B41/00—Component parts such as frames, beds, carriages, headstocks
- B24B41/06—Work supports, e.g. adjustable steadies
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- Mechanical Engineering (AREA)
- Jigs For Machine Tools (AREA)
Abstract
The invention discloses a turbine blade machining tool for an oversized gas turbine, which comprises a rotary table, a first clamp and a second clamp, wherein the first clamp and the second clamp are fixed on the rotary table; the first clamp is positioned at the first end of the through hole and is used for positioning and clamping the extending root of the turbine blade; the second clamp is located at the second end of the through hole and used for locating and clamping the blade body of the turbine blade. According to the invention, the turntable is arranged in a hollow manner, the turbine blade is placed in the hollow through hole, and the first clamp and the second clamp are arranged at the two ends of the through hole so as to fix the extending root at the end where the tenon of the turbine blade is located and the blade body at the end where the blade shroud is located, so that the phenomenon of deviation is not generated when the tenon and the blade shroud of the turbine blade are machined, the machining precision of the tenon and the blade shroud of the turbine blade is further improved, the size of the whole machining tool is reduced, the machining range of a machine tool is effectively reduced, and the cost is saved.
Description
Technical Field
The invention relates to the technical field of turbine blade machining of gas turbines, in particular to a machining tool and a machining method for a turbine blade of an ultra-large gas turbine.
Background
The turbine blade of the combustion engine is one of the important parts of the gas turbine, and generally comprises four parts, namely a tenon, an extending root, a blade body and a blade crown, as shown in FIG. 1. At present, a large number of processing technical problems of the turbine blade of the combustion engine still need to be solved, such as key technologies of end processing (tenons and blade crowns) of the turbine blade of the combustion engine.
The tenon structure of the existing turbine blade of the gas turbine is complex, the surfaces to be machined are multiple, and the machining requirement precision is high, so the end part machining of the existing turbine blade of the gas turbine is usually carried out in a mode of step-by-step machining by adopting a plurality of clamps, the turbine blade is fixed by adopting one clamp firstly, then, the tenon is subjected to unilateral grinding for a plurality of times, then, the turbine blade is disassembled and is fixed again by adopting another clamp, then, the blade crown is subjected to unilateral grinding for a plurality of times, not only is the manual reversing alignment error exist, the machining precision is influenced, but also the turbine blade needs to be turned over ceaselessly when the surfaces of different parts of the tenon or the blade crown are actually machined, the whole machining process is complicated, the consumed time is long, and the labor intensity of an operator is increased.
Especially when processing aviation or marine super large gas turbine blade, because super large gas turbine blade is bulky, weight is high, and relevant equipment lags behind and has the technology bottleneck, adopt the implementation degree of difficulty of above-mentioned processing mode to carry out turbine blade tip processing bigger, probably cause movable vane skew, under-process or over-process processing, can't satisfy the assembly requirement in later stage thereby lead to the material to scrap.
Disclosure of Invention
Based on this, it is necessary to provide a processing frock and a processing method that can be applicable to the processing of the tenon of super large combustion engine turbine blade and blade shroud to the above-mentioned problem, effectively improve machining efficiency to can guarantee the machining precision, satisfy the assembly requirement in later stage.
The invention is realized by the following technical scheme:
the utility model provides an ultra-large combustion engine turbine blade processing frock, includes: the rotary table is provided with through holes which penetrate through two opposite ends of the rotary table and are used for accommodating turbine blades; the first clamp is positioned at the first end of the through hole, is fixed on the rotary table and is used for positioning and clamping the extending root of the turbine blade; and the second clamp is positioned at the second end of the through hole, is fixed on the rotary table and is used for positioning and clamping the blade body of the turbine blade.
In one embodiment, the height of the turntable in the direction of opening the through hole is smaller than the length of the blade body of the turbine blade, and the second clamp is arranged close to the blade crown of the turbine blade.
In one embodiment, the first clamp comprises a first bracket, a first positioning block, a second positioning block, a third positioning block and a first pressing assembly, wherein the first positioning block, the second positioning block and the third positioning block are arranged on the first bracket; the first positioning block is provided with a first supporting end which is used for being contacted with the back surface of the extending root, the second positioning block is provided with a second supporting end which is contacted with the front edge surface of the extending root, and the third positioning block is provided with a third supporting end which is used for being contacted with the bottom side surface of the extending root; one end of the first pressing component is hinged with the first support, and the other end of the first pressing component is detachably connected with the first support; a first cavity for accommodating the turbine blade is formed between the first pressing component and the first support, and the turbine blade is pressed and held on the first positioning block by the first pressing component in the first cavity.
In one embodiment, the first pressing assembly comprises a root-extending pressing plate, one side of the root-extending pressing plate, which faces the first positioning block, is movably connected with a root-extending pressing block, the root-extending pressing block is provided with a first fulcrum corresponding to the first supporting end and used for being in contact with the facing surface of the root-extending basin, and an elastic gasket is arranged between the root-extending pressing block and the root-extending pressing plate; a first threaded through hole is formed in the root stretching pressing plate on one side, close to the first fulcrum, of the elastic washer, a first jacking bolt penetrates through the first threaded through hole, and the first jacking bolt penetrates through the first threaded through hole and abuts against the root stretching pressing plate vertically; a limiting block is arranged at the bottom of the root stretching pressing plate at one side, far away from the first fulcrum, of the elastic gasket, and one end, close to the first positioning block, of the limiting block is buckled at the bottom of the root stretching pressing block.
In one embodiment, the second clamp comprises a second bracket, a fourth positioning block, a fifth positioning block and a second pressing assembly, wherein the fourth positioning block, the fifth positioning block and the second pressing assembly are arranged on the second bracket; the fourth positioning block is provided with a fourth supporting end used for being in contact with the back surface of the blade body, and the fifth positioning block is provided with a fifth supporting end used for being in contact with the front edge surface of the blade body; one end of the second pressing component is hinged with the second support, and the other end of the second pressing component is detachably connected with the second support; a second cavity for accommodating the turbine blade is formed between the second pressing component and the second support, and the turbine blade is pressed and held on the fourth positioning block by the second pressing component in the second cavity.
In one embodiment, the second pressing assembly comprises a blade body pressing plate, a blade body pressing block is movably connected to one side, facing the fourth positioning block, of the blade body pressing plate, and a second fulcrum used for being in contact with a basin-facing surface of the blade body is arranged at the corresponding fourth supporting end of the blade body pressing block; the blade body pressing plate is provided with a second threaded through hole, a second jacking bolt penetrates through the second threaded through hole, and the second jacking bolt penetrates through the second threaded through hole and is vertically abutted against the blade body pressing block.
In one embodiment, the blade body pressing block is further provided with a third fulcrum for contacting with the basin-facing surface of the blade body, the second support is provided with a third pressing assembly for contacting with the back-facing surface of the blade body, the third pressing assembly comprises a first connecting seat, a movable groove is formed in the first connecting seat corresponding to the third fulcrum, a movable block is arranged in the movable groove, and the movable block is connected with the groove bottom of the movable groove through an elastic piece; and a third threaded through hole is formed in one side of the first connecting seat, a third jacking bolt penetrates through the third threaded through hole, and the third jacking bolt penetrates through the third threaded through hole and abuts against the side face of the movable block.
In one embodiment, the side surface of the movable block is provided with a wedge-shaped groove which is obliquely and inwardly arranged from the opening direction of the movable groove to the bottom direction of the movable groove; the third threaded through hole is formed corresponding to the wedge-shaped groove and is perpendicular to the inclined surface of the wedge-shaped groove.
In one embodiment, the first clamp and/or the second clamp are/is further provided with a fourth pressing assembly; the fourth pressing component comprises a second connecting seat, and one side of the second connecting seat is hinged with a lateral pressing block used for being in contact with the rear edge face of the blade body; an extension part is formed on the other side of the second connecting seat, and the free end of the lateral pressing block is connected with the free end of the extension part through an elastic part; and a fourth threaded through hole is formed in the middle of the extending part, a fourth jacking bolt penetrates through the fourth threaded through hole, and the fourth jacking bolt penetrates through the fourth threaded through hole and abuts against the lateral pressing block.
A method for machining a turbine blade of an ultra-large combustion engine comprises the following steps:
s1, the turbine blade penetrates through the through hole of the rotary table, the tenon end of the turbine blade is fixed through a first clamp which is fixed on the rotary table and is positioned at the first end of the through hole, and the shroud end of the turbine blade is fixed through a second clamp which is fixed on the rotary table and is positioned at the second end of the through hole;
s2, starting the processing machine tool, rotating the rotary table until the end of the tenon of the turbine blade faces upwards, aligning and trimming the tenon of the turbine blade through the grinding wheel, and processing the basin-direction tenon tooth, the back-direction tenon tooth, the front edge tenon side face and the rear edge tenon side face;
s3, rotating the rotary table until the tip shroud of the turbine blade is upward, aligning and trimming the tenon of the turbine blade through the grinding wheel, and processing the tip shroud top surface, the leading edge tip shroud side surface and the trailing edge tip shroud side surface;
and S4, closing the processing machine tool, taking down the turbine blade, and cleaning, checking and finishing the processing.
Compared with the prior art, the technical scheme of the invention at least has the following advantages and beneficial effects:
according to the invention, the turntable is arranged in a hollow manner, the turbine blade is placed in the hollow through hole, and the first clamp and the second clamp are arranged at the two ends of the through hole so as to fix the extending root at the end where the tenon of the turbine blade is located and the blade body at the end where the blade shroud is located, so that the phenomenon of deviation is not generated when the tenon and the blade shroud of the turbine blade are machined, the machining precision of the tenon and the blade shroud of the turbine blade is further improved, the size of the whole machining tool is reduced, the machining range of a machine tool is effectively reduced, and the cost is saved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
FIG. 1 is a schematic structural view of a turbine blade provided in accordance with an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a turbine blade machining tool for an oversized combustion engine, provided by the embodiment of the invention;
FIG. 3 is a first assembly schematic view of a turbine blade and a turbine blade machining tool of an ultra-large combustion engine, provided by the embodiment of the invention;
FIG. 4 is a second assembly schematic view of the turbine blade and the turbine blade machining tool for the ultra-large combustion engine provided by the embodiment of the invention;
fig. 5 is a first schematic structural diagram of a first clamp according to an embodiment of the present invention;
fig. 6 is a second schematic structural diagram of the first fixture according to the embodiment of the present invention;
FIG. 7 is an enlarged schematic view at A in FIG. 6;
FIG. 8 is a schematic structural diagram of a second clamp according to an embodiment of the present invention;
FIG. 9 is a schematic structural diagram of a fourth positioning block according to an embodiment of the present invention;
FIG. 10 is a schematic structural diagram of a third pressing assembly provided in accordance with an embodiment of the present invention;
FIG. 11 is a schematic diagram illustrating an internal structure of a third compressing assembly according to an embodiment of the present invention;
fig. 12 is a schematic structural diagram of a fourth compressing assembly according to an embodiment of the present invention.
Icon:
1-a turntable, 11-a through hole,
2-a first clamp, 21-a first bracket, 22-a first positioning block, 221-a first supporting end, 23-a second positioning block, 231-a second supporting end, 24-a third positioning block, 241-a third supporting end, 25-a first pressing component, 251-a root-extending pressing plate, 2511-a first threaded through hole, 252-a root-extending pressing block, 2521-a first fulcrum, 2522-a tooth part, 253-an elastic washer, 254-a first jacking bolt, 255-a limiting block,
3-a second clamp, 31-a second bracket, 32-a fourth positioning block, 321-a fourth supporting end, 33-a fifth positioning block, 331-a fifth supporting end, 34-a second pressing component, 341-a blade body pressing plate, 342-a blade body pressing block, 3421-a second fulcrum, 3422-a third fulcrum, 343-a second jacking screw rod, 35-a third pressing component, 351-a first connecting seat, 3511-a movable groove, 3512-a third threaded through hole, 352-a movable block, 3521-a wedge-shaped groove and 353-a third jacking bolt,
4-a fourth pressing component, 41-a second connecting seat, 411-an extending part, 4111-a fourth threaded through hole, 42-a lateral pressing block, 43-a fourth jacking bolt,
5-the elastic piece is arranged on the upper surface of the shell,
6-mounting the pin on the base plate,
7-locking mechanism, 71-locking block, 72-locking rod, 73-locking groove,
8-turbine blade, 81-tenon, 82-tang, 83-blade, 831-leading edge side, 832-trailing edge side, 833-flaccid side, 834-dorsal side, 84-tip shroud.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, a machining tool and a machining method for a turbine blade of an ultra-large combustion engine will be more clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. The drawings show preferred embodiments of a tooling and a method for machining an oversized turbine blade for a combustion engine, however, the tooling and the method for machining an oversized turbine blade for a combustion engine can be implemented in many different forms and are not limited to the embodiments described herein. Rather, these embodiments are provided to make the disclosure of an oversized combustion engine turbine blade machining tool and machining method more thorough.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which the present invention belongs. The terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," and the like, when used in reference to an orientation or positional relationship indicated in the drawings, or as otherwise customary for use in the practice of the invention, are used merely for convenience in describing and simplifying the invention, and do not indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be considered as limiting the invention.
In the description of the present invention, it should be further noted that the terms "disposed," "mounted," "connected," and "connected" used herein should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
As shown in fig. 1, the turbine blade 8 to be machined according to the present invention mainly includes four parts, i.e., a tenon 81, an extension 82, a blade body 83 and a blade shroud 84, wherein the tenon 81 has a plurality of machined surfaces, including a basin-shaped tenon tooth, a back-shaped tenon tooth, a leading edge tenon side surface and a trailing edge tenon side surface, for later assembly with other parts, so that the machining precision requirement on the tenon is high; the extending root 82 is positioned between the tenon 81 and the blade body 83, and the extending root 82 is not processed in the invention, so the extending root 82 is used as a supporting point to clamp and fix the end of the turbine blade tenon, so as to complete the processing of the tenon part; the blade body 83 is a twisted blade with a variable cross section, the cross section area of which is gradually increased from the root to the top, and the concave side surface of the blade body 83 is generally called a basin-facing surface, and the convex side surface of the blade body 83 is called a back-facing surface; the other end of the blade body 83 is a blade shroud 84, and the blade shroud 84 also has a plurality of machined and formed surfaces, mainly including a blade shroud top surface, a leading edge blade shroud side surface and a trailing edge blade shroud side surface, so that the blade shroud part is machined by clamping and fixing the blade body 83 at the end where the blade shroud of the turbine blade 8 is located.
In order to ensure that the tenon 81 and the blade crown 84 of the turbine blade 8 cannot deviate during machining and achieve the purposes of effective positioning and fixing, as shown in fig. 2 to 4, the invention provides a turbine blade machining tool for an oversized combustion engine, which comprises a rotary table 1, and a first clamp 2 and a second clamp 3 which are fixed on the rotary table 1, wherein the rotary table 1 is provided with through holes 11 which penetrate through two opposite ends of the rotary table 1 and are used for accommodating the turbine blade 8; the first clamp 2 is positioned at the first end of the through hole 11 and is used for positioning and clamping the extending root 82 of the turbine blade 8; the second clamp 3 is located at a second end of the through hole 11 for positioning and clamping the body 83 of the turbine blade 8. After turbine blade 8 passes through the through-hole 11 of revolving stage 1, utilize first anchor clamps 2 to fix a position and fix turbine blade 8's tenon 81 place end, reuse second anchor clamps 3 fixed turbine blade 8's tip shroud 84 place end again, thereby firmly fix turbine blade 8 on revolving stage 1, turbine blade 8 can not take place the skew when processing tenon 81 and tip shroud 84, and then improve turbine blade 8's tenon 81 and tip shroud 84's machining precision, whole processing frock volume has still been reduced, machine tool machining scope has effectively been reduced, and the cost is saved.
Further, as shown in fig. 3 and 4, the height of the rotary table 1 in the opening direction of the through hole 11 is smaller than the length of the blade body 83 of the turbine blade 8, so that when the turbine blade 8 is inserted into the through hole 11, both ends of the turbine blade 8 extend out of the rotary table 1, and the first clamp 2 and the second clamp 3 are convenient to operate so as to clamp and fix the turbine blade 8; and the second clamp 3 is arranged close to the tip shroud 84 of the turbine blade 8, so that the clamping stress point of the second clamp 3 can be close to the tip shroud 84 as much as possible on the premise of not influencing the machining of the tip shroud 84, thereby reducing the influence of the shearing force of the machining tool on the turbine blade 8 when the tip shroud 84 is machined.
Further, as shown in fig. 3 to 5, the first fixture 2 includes a first bracket 21, a first positioning block 22, a second positioning block 23, a third positioning block 24 and a first pressing assembly 25, wherein the first positioning block 22, the second positioning block 23, the third positioning block 24 and the first pressing assembly 25 are disposed on the first bracket 21; the first positioning block 22 is provided with a first supporting end 221 which is used for being in contact with the back surface of the extension root 82, the second positioning block 23 is provided with a second supporting end 231 which is in contact with the front edge surface of the extension root 82, the third positioning block 24 is provided with a third supporting end 241 which is used for being in contact with the bottom side surface of the extension root 82, and the turbine blade 8 can be spatially positioned in the three-axis directions of the X axis, the Y axis and the Z axis through the first supporting end 221, the second supporting end 231 and the third supporting end 241; one end of the first compressing assembly 25 is hinged with the first bracket 21, and the other end is detachably connected with the first bracket 21; be formed with the first cavity that is used for holding turbine blade 8 between first compress tightly subassembly 25 and first support 21, earlier when installing turbine blade 8 first compress tightly subassembly 25 and separate in the junction of dismantling, turbine blade 8 installs the back well, rotates first compress tightly subassembly 25 again and just can dismantle junction fixed connection as for it, and turbine blade 8 is pressed by first compress tightly subassembly 25 in first cavity and is held on first locating piece 22, realizes that preliminary compressing tightly of turbine blade 8 tenon place end is fixed.
Specifically, since the length direction of the extension root 82 is long, two first supporting ends 221 may be formed, and are distributed at two ends of the extension root 82 in the length direction, and are in contact with the back surface of the extension root 82, so as to play a role in stably and effectively positioning. The third support end 241 is embodied as a process ball for making point contact with the bottom side of the stub 82. As shown in fig. 3 and 5, the first pressing component 25 and the first bracket 21 can be detachably connected through the locking mechanism 7, the locking mechanism 7 includes a locking block 71 hinged on the first bracket 21 and a locking rod 72 in threaded connection with the locking block 71, one end of the first pressing component 25 for detachable connection is provided with a locking groove 73, the locking rod 72 can be placed in the locking groove 73 after the locking block 71 is rotated along the hinged position, and at the time, the locking rod 72 is perpendicular to one end of the first pressing component 25 for detachable connection, and the first pressing component 25 can be firmly fixed on the first bracket 21 at the detachable connection position by screwing the locking rod 72.
Further, as shown in fig. 5 to 7, the first pressing assembly 25 includes a root-extending pressing plate 251, one end of the root-extending pressing plate 251 is hinged to the first bracket 21, the other end of the root-extending pressing plate 251 is detachably connected to the first bracket 21, a root-extending pressing block 252 is movably connected to one side of the root-extending pressing plate 251 facing the first positioning block 22, a first supporting point 2521 for contacting with the basin facing surface of the root-extending 82 is arranged corresponding to the first supporting end 221 of the root-extending pressing block 252, and an elastic gasket 253 is arranged between the root-extending pressing block 252 and the root-extending pressing plate 251; a limiting block 255 is arranged at the bottom of the root-extending pressing plate 251 on one side of the elastic washer 253, which is far away from the first fulcrum 2521, one end of the limiting block 255, which is close to the first positioning block 22, is buckled at the bottom of the root-extending pressing block 252, and the limiting block 255 can limit the outward tilting of the bottom of the root-extending pressing block 252, so that the first fulcrum 2521 and the first supporting end 221 can effectively and preliminarily press the root 82 when the root is initially pressed and fastened; a first threaded through hole 2511 is formed in the root extension pressing plate 251 on one side of the elastic washer 253 close to the first fulcrum 2521, a first jacking bolt 254 penetrates through the first threaded through hole 2511, the first jacking bolt 254 penetrates through the first threaded through hole 2511 to vertically abut against the root extension pressing block 252, the first jacking bolt 254 is screwed inwards, the root extension pressing block 252 is pressed inwards, so that the turbine blade 8 is firmly pressed on the first positioning block 22, and the first fulcrum 2521 and the first supporting end 221 can effectively and preliminarily fix the root extension 82.
Specifically, when two first supporting ends 221 are formed, two first supporting points 2521 are correspondingly formed to balance the force. Stretch a briquetting 252 and stretch a swing joint mode of briquetting 251, specifically be, the side of stretching a briquetting 252 relative first locating piece 22 is equipped with the mounting hole, the side of stretching a briquetting 251 relative first locating piece 22 is equipped with the installation screw hole, pass mounting hole and elastic washer 253 in proper order through installation round pin 6 and insert in the installation screw hole and with installation screw hole threaded connection, installation round pin 6 is the polished rod with the contact site who stretches a briquetting 252, make stretch a briquetting 252 can be along the 6 axial activities of installation round pin on installation round pin 6, and realize the elasticity through elastic washer 253 and compress tightly the effect. Furthermore, the bottom of the root-extending pressing block 252 may be formed into a curved surface, and a tooth portion 2522 is formed on a side close to the first positioning block 22, so that when the root-extending pressing block 252 is pressed by the first pressing bolt 254, the tooth portion 2522 is clamped on the limiting block 255 to limit the top of the root-extending pressing block 252 to continue pressing the turbine blade 8, thereby avoiding deformation of the root 82 due to excessive pressing.
Further, as shown in fig. 3, 8 and 9, the second clamp 3 includes a second bracket 31, a fourth positioning block 32, a fifth positioning block 33 and a second pressing assembly 34, wherein the fourth positioning block 32, the fifth positioning block 33 and the second pressing assembly 34 are disposed on the second bracket 31; the fourth positioning block 32 is provided with a fourth supporting end 321 for contacting with the blade body 83 in a back-to-face manner, the fifth positioning block 33 is provided with a fifth supporting end 331 for contacting with the front edge surface of the blade body 83, and the turbine blade 8 can be positioned in the X-axis direction and the Y-axis direction through the fourth supporting end 321 and the fifth supporting end 331; one end of the second pressing component 34 is hinged with the second bracket 31, and the other end is detachably connected with the second bracket 31; a second cavity for accommodating the turbine blade 8 is formed between the second pressing component 34 and the second support 31, the second pressing component 34 is separated at the detachable joint when the turbine blade 8 is installed, after the turbine blade 8 is installed, the second pressing component 34 is rotated to be fixedly connected with the detachable joint, and the turbine blade 8 is pressed and held on the fourth positioning block 32 by the second pressing component 34 in the second cavity, so that the primary pressing and fixing of the tip end of the tip shroud of the turbine blade 8 are realized.
Specifically, the fourth supporting end 321 and the fifth supporting end 331 are pin rods respectively inserted into the fourth positioning block 32 and the fifth positioning block 33, and the circumferential surfaces thereof are arc surfaces to make point contact with the back surface of the blade body 83 and the front edge surface of the blade body 83, respectively, and are convenient to replace when the pin rods are worn to cause the reduction of the positioning accuracy. The second pressing component 34 and the second bracket 31 can also be detachably connected through the locking mechanism 7 in the same way as the first pressing component 25 and the first bracket 21, and will not be described again.
Further, as shown in fig. 8 and 9, the second pressing assembly 34 includes a blade pressing plate 341, one end of the blade pressing plate 341 is hinged to the second support 31, the other end is detachably connected to the second support 31, a blade pressing block 342 is movably connected to one side of the blade pressing plate 341 facing the fourth positioning block 32, and a second fulcrum 3421 for contacting with the basin of the blade 83 is arranged at the corresponding fourth supporting end 321 of the blade pressing block 342; the blade pressing plate 341 has a second threaded through hole 3411, a second pressing bolt passes through the second threaded through hole 3411, and the second pressing bolt passes through the second threaded through hole 3411 and abuts against the blade pressing block 342 vertically. After the blade pressing plate 341 and the second support 31 are fixed at the detachable connection position, the blade 83 is pressed and held at the fourth support end 321 by the blade pressing block 342, so that the blade 83 can be effectively and primarily pressed and fastened at the initial pressing and fastening timing by the second supporting point 3421 and the fourth support end 321, and then the second jacking bolt is screwed inwards, so that the blade pressing block 342 is pressed inwards to further press the turbine blade 8 on the fourth positioning block 32, and the blade 83 can be effectively and primarily fixed by the second supporting point 3421 and the fourth support end 321.
Specifically, the movable connection mode of the blade body pressing block 342 and the blade body pressing plate 341 is specifically that a mounting hole is formed in the side face of the blade body pressing block 342 opposite to the fourth positioning block 32, a mounting threaded hole is formed in the side face of the blade body pressing plate 341 opposite to the fourth positioning block 32, the mounting pin 6 penetrates through the mounting hole to be inserted into the mounting threaded hole and is in threaded connection with the mounting threaded hole, and the contact part of the mounting pin 6 and the blade body pressing block 342 is a polished rod, so that the blade body pressing block 342 can move axially on the mounting pin 6 along the mounting pin 6.
Further, as shown in fig. 8 to 11, the blade body pressing block 342 is further provided with a third fulcrum 3422 for contacting with the basin-facing surface of the blade body 83, the second support 31 is provided with a third pressing assembly 35 for contacting with the back-facing surface of the blade body 83, the third pressing assembly 35 includes a first connecting seat 351, a movable groove 3511 is formed on the first connecting seat 351 corresponding to the third fulcrum 3422, a movable block 352 is arranged in the movable groove 3511, and the movable block 352 is connected with the groove bottom of the movable groove 3511 through an elastic member 5; a third threaded through hole 3512 is formed in one side of the first connecting seat 351, a third pressing bolt 353 penetrates through the third threaded through hole 3512, and the third pressing bolt 353 penetrates through the third threaded through hole 3512 and abuts against the side face of the movable block 352. Preferably, the movable block 352 and the fourth supporting end 321 are located at the same level in the Z-axis, so as to achieve effective supporting and positioning, avoid generating shearing force, and cooperate with the second pressing assembly 34 to effectively and primarily press and fix the blade body 83.
Specifically, after the blade pressing plate 341 and the second support 31 are fixed at the detachable connection position, the blade 83 is pressed and held on the fourth support end 321 and the movable block 352 by the blade pressing block 342, the movable block 352 is pressed into the movable groove 3511, the movable block 352 is pressed against the back surface of the blade 83 through the elastic member 5, the blade 83 is effectively and primarily pressed by matching with the third fulcrum 3422, then the third pressing bolt 353 is screwed inwards to limit the displacement of the movable block 352 in the movable groove 3511, and finally the second pressing bolt is screwed inwards to enable the blade pressing block 342 to be pressed inwards so as to further press the turbine blade 8 on the fourth positioning block 32 and the third pressing assembly 35, so that the second fulcrum 3421 and the fourth support end 321, and the third fulcrum 3422 and the movable block 352 can effectively and fix the blade 83.
Further, as shown in fig. 11, a wedge-shaped groove 3521 is provided on a side surface of the movable block 352, and the wedge-shaped groove 3521 is formed from an opening direction of the movable groove 3511 to a groove bottom direction of the movable groove 3511, and is inclined inward (inside the movable block 352); the third threaded through hole 3512 is formed corresponding to the wedge-shaped groove 3521 and is perpendicular to the inclined surface of the wedge-shaped groove 3521, so that the third jacking bolt 353 can abut against the inclined surface of the wedge-shaped groove 3521 after being screwed inwards, and the effect of effectively limiting the displacement of the movable block 352 in the movable groove 3511 is achieved.
Further, as shown in fig. 2, 3, 8 and 12, a fourth pressing assembly 4 is further disposed on the first clamp 2 and/or the second clamp 3; the fourth pressing component 4 comprises a second connecting seat 41, and a lateral pressing block 42 used for being in contact with the rear edge face of the blade body 83 is hinged to one side of the second connecting seat 41; an extension part 411 is formed at the other side of the second connecting seat 41, and the free end of the lateral pressing block 42 is connected with the free end of the extension part 411 through an elastic part 5; a fourth threaded through hole 4111 is formed in the middle of the extending portion 411, a fourth jacking bolt 43 penetrates through the fourth threaded through hole 4111, and the fourth jacking bolt 43 penetrates through the fourth threaded through hole 4111 and abuts against the lateral pressing block 42. After the turbine blade 8 is installed, the fourth jacking bolt 43 is screwed inwards, so that the lateral pressing block 42 is pressed inwards to further press the turbine blade 8 on the second positioning block 23 or the fifth positioning block 33, and the lateral pressing block 42 and the second supporting end 231 or the fifth supporting end 331 can effectively press and fix the blade body 83.
The invention also provides a method for processing the ultra-large combustion engine turbine blade, which comprises the following steps:
s1, the turbine blade 8 penetrates through the through hole 11 of the rotary table 1, the tenon end of the turbine blade 8 is fixed through the first clamp 2 which is fixed on the rotary table 1 and is positioned at the first end of the through hole 11, and the tip shroud end of the turbine blade 8 is fixed through the second clamp 3 which is fixed on the rotary table 1 and is positioned at the second end of the through hole 11;
s2, starting the processing machine tool, rotating the rotary table 1 until the end where the tenon of the turbine blade 8 is located faces upwards, aligning and trimming the tenon 81 of the turbine blade 8 through the grinding wheel, and processing a basin-direction tenon tooth, a back-direction tenon tooth, a front edge tenon side face and a rear edge tenon side face;
wherein,
when the basin-direction tenon tooth is processed, the rotating turntable 1 enables the tenon basin-direction side 833 of the turbine blade 8 to face upwards;
when back tenon teeth are machined, the rotary table 1 is rotated to enable the tenon back sides 834 of the turbine blades 8 to face upwards;
when the side face of the front edge tenon is machined, the rotating turntable 1 is rotated to enable the tenon front edge side 831 of the turbine blade 8 to face upwards;
during machining of the leading edge dovetail side, the rotary turret 1 is rotated with the dovetail trailing edge side 832 of the turbine blade 8 facing upward;
s3, rotating the rotary table 1 until the tip shroud 84 of the turbine blade 8 is located at the upward end, aligning and trimming the tip shroud 84 of the turbine blade 8 through a grinding wheel, and processing a tip shroud top surface, a leading edge tip shroud side surface and a trailing edge tip shroud side surface;
wherein,
when the top surface of the blade crown is processed, the rotating table 1 is rotated to enable the top of the blade crown of the turbine blade 8 to face upwards;
when the front edge shroud side is machined, the rotating turntable 1 is rotated to enable the shroud front edge side 831 of the turbine blade 8 to face upwards;
when machining the trailing edge shroud side, the rotating turret 1 is rotated with the shroud trailing edge side 832 of the turbine blade 8 facing upwards;
s4, the machine tool is turned off, the turbine blade 8 is removed, and after cleaning, the positional accuracy is checked to complete the machining.
It can be understood that the turntable is arranged on the processing machine tool, can rotate in the horizontal direction on the processing machine tool by taking the axis of the through hole as a rotating shaft, and can rotate in the vertical direction on the processing machine tool by taking the horizontal mounting shaft as the rotating shaft, so that the effect of 360-degree rotation without dead angles is achieved. By adopting the processing method to process the turbine blade tenon and the blade shroud, the tenon and the blade shroud can be processed in a time-sharing way without replacing a clamp, so that errors caused by manual reversing alignment are avoided, the whole processing process is smoother, and the processing efficiency is higher; meanwhile, the labor intensity of an operator is reduced, the processed tenon has higher precision, and the later-stage assembling requirement is met.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. The utility model provides an ultra-large combustion engine turbine blade processing frock which characterized in that includes:
the rotary table is provided with through holes which penetrate through two opposite ends of the rotary table and are used for accommodating turbine blades;
the first clamp is positioned at the first end of the through hole, is fixed on the rotary table and is used for positioning and clamping the extending root of the turbine blade;
the second clamp is positioned at the second end of the through hole, is fixed on the rotary table and is used for positioning and clamping the blade body of the turbine blade;
the first clamp comprises a first support, a first positioning block, a second positioning block, a third positioning block and a first pressing assembly, wherein the first positioning block, the second positioning block and the third positioning block are arranged on the first support; the first positioning block is provided with a first supporting end which is used for being in contact with the back surface of the extending root, the second positioning block is provided with a second supporting end which is in contact with the front edge surface of the extending root, and the third positioning block is provided with a third supporting end which is used for being in contact with the bottom side surface of the extending root; one end of the first pressing component is hinged with the first support, and the other end of the first pressing component is detachably connected with the first support; a first cavity for accommodating a turbine blade is formed between the first pressing component and the first support, and the turbine blade is pressed and held on the first positioning block by the first pressing component in the first cavity;
the first pressing assembly comprises a root stretching pressing plate, one side of the root stretching pressing plate, which faces the first positioning block, is movably connected with a root stretching pressing block, the root stretching pressing block is provided with a first fulcrum corresponding to the first supporting end and used for being in contact with the facing surface of the root stretching basin, and an elastic gasket is arranged between the root stretching pressing block and the root stretching pressing plate; a first threaded through hole is formed in the root extension pressing plate on one side, close to the first fulcrum, of the elastic gasket, a first jacking bolt penetrates through the first threaded through hole, and the first jacking bolt penetrates through the first threaded through hole and abuts against the root extension pressing block vertically; a limiting block is arranged at the bottom of the root stretching pressing plate at one side, away from the first fulcrum, of the elastic gasket, and one end, close to the first positioning block, of the limiting block is buckled at the bottom of the root stretching pressing block.
2. The machining tool for the turbine blade of the ultra-large combustion engine according to claim 1, wherein the height of the turntable in the opening direction of the through hole is smaller than the length of the blade body of the turbine blade, and the second clamp is arranged close to the blade crown of the turbine blade.
3. The tooling for machining the turbine blade of the ultra-large combustion engine according to claim 1, wherein the second clamp comprises a second bracket, a fourth positioning block, a fifth positioning block and a second pressing assembly, wherein the fourth positioning block, the fifth positioning block and the second pressing assembly are arranged on the second bracket; the fourth positioning block is provided with a fourth supporting end used for being in contact with the back surface of the blade body, and the fifth positioning block is provided with a fifth supporting end used for being in contact with the front edge surface of the blade body; one end of the second compressing assembly is hinged with the second support, and the other end of the second compressing assembly is detachably connected with the second support; a second cavity for accommodating a turbine blade is formed between the second pressing component and the second support, and the turbine blade is pressed and held on the fourth positioning block by the second pressing component in the second cavity.
4. The machining tool for the turbine blade of the ultra-large combustion engine according to claim 3, wherein the second pressing assembly comprises a blade body pressing plate, a blade body pressing block is movably connected to one side, facing the fourth positioning block, of the blade body pressing plate, and a second fulcrum used for being in contact with a basin-facing surface of the blade body is arranged at the end, corresponding to the fourth supporting end, of the blade body pressing block; the blade pressing plate is provided with a second threaded through hole, a second jacking bolt penetrates through the second threaded through hole, and the second jacking bolt penetrates through the second threaded through hole and is vertically abutted to the blade pressing block.
5. The tooling for machining the turbine blade of the ultra-large combustion engine according to claim 4, wherein the blade body pressing block is further provided with a third fulcrum which is used for being in contact with the basin-shaped surface of the blade body, the second support is provided with a third pressing assembly which is used for being in contact with the back-shaped surface of the blade body, the third pressing assembly comprises a first connecting seat, a movable groove is formed in the first connecting seat corresponding to the third fulcrum, a movable block is arranged in the movable groove, and the movable block is connected with the groove bottom of the movable groove through an elastic piece; a third threaded through hole is formed in one side of the first connecting seat, a third jacking bolt penetrates through the third threaded through hole, and the third jacking bolt penetrates through the third threaded through hole and abuts against the side face of the movable block.
6. The tooling for machining the turbine blade of the ultra-large combustion engine as recited in claim 5, wherein a wedge-shaped groove is formed in the side surface of the movable block, and the wedge-shaped groove is formed from the opening direction of the movable groove to the bottom direction of the movable groove in an inclined inward manner; the third threaded through hole is formed corresponding to the wedge-shaped groove and is perpendicular to the inclined surface of the wedge-shaped groove.
7. The tooling for machining the turbine blade of the ultra-large combustion engine according to any one of claims 1 to 6, wherein a fourth pressing assembly is further arranged on the first clamp and/or the second clamp; the fourth pressing assembly comprises a second connecting seat, and a lateral pressing block used for being in contact with the rear edge face of the blade body is hinged to one side of the second connecting seat; an extension part is formed on the other side of the second connecting seat, and the free end of the lateral pressing block is connected with the free end of the extension part through an elastic part; a fourth threaded through hole is formed in the middle of the extending portion, a fourth jacking bolt penetrates through the fourth threaded through hole, and the fourth jacking bolt penetrates through the fourth threaded through hole and abuts against the lateral pressing block.
8. A processing method of a turbine blade of an ultra-large combustion engine adopts the turbine blade processing tool of the ultra-large combustion engine as claimed in any one of claims 1 to 7, and is characterized by comprising the following steps:
s1, the turbine blade penetrates through the through hole of the rotary table, the tenon end of the turbine blade is fixed through a first clamp which is fixed on the rotary table and is positioned at the first end of the through hole, and the shroud end of the turbine blade is fixed through a second clamp which is fixed on the rotary table and is positioned at the second end of the through hole;
s2, starting the processing machine tool, rotating the rotary table until the end where the tenon of the turbine blade is located faces upwards, aligning and trimming the tenon of the turbine blade through the grinding wheel, and processing basin-direction tenon teeth, back-direction tenon teeth, front edge tenon side faces and rear edge tenon side faces;
s3, rotating the rotary table until the tip shroud of the turbine blade is upward, aligning and trimming the tenon of the turbine blade through the grinding wheel, and processing the tip shroud top surface, the leading edge tip shroud side surface and the trailing edge tip shroud side surface;
and S4, closing the processing machine tool, taking down the turbine blade, and cleaning, checking and finishing the processing.
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| CN113182906B (en) * | 2021-06-16 | 2022-12-09 | 中国航发航空科技股份有限公司 | Aeroengine turbine blade machining clamp and clamping method thereof |
| CN113478262A (en) * | 2021-07-20 | 2021-10-08 | 中国航发航空科技股份有限公司 | Turbine blade sealing tooth machining clamp and clamping method thereof |
| CN113857563B (en) * | 2021-11-09 | 2024-04-30 | 浙江畅尔智能装备股份有限公司 | Broaching tool for blade tenon |
| CN117260588B (en) * | 2023-11-14 | 2024-01-30 | 中国航发沈阳黎明航空发动机有限责任公司 | Low vortex working vane three-coordinate detection universal positioning device |
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