CN113618657A - Aeroengine blade clamping device - Google Patents
Aeroengine blade clamping device Download PDFInfo
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- CN113618657A CN113618657A CN202110963440.7A CN202110963440A CN113618657A CN 113618657 A CN113618657 A CN 113618657A CN 202110963440 A CN202110963440 A CN 202110963440A CN 113618657 A CN113618657 A CN 113618657A
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- 230000008093 supporting effect Effects 0.000 claims abstract description 140
- 230000007246 mechanism Effects 0.000 claims abstract description 65
- 238000000034 method Methods 0.000 claims abstract description 40
- 230000008569 process Effects 0.000 claims abstract description 37
- 210000002268 wool Anatomy 0.000 claims abstract description 13
- 238000007667 floating Methods 0.000 claims description 64
- 238000003754 machining Methods 0.000 abstract description 7
- 238000009434 installation Methods 0.000 description 17
- 239000000463 material Substances 0.000 description 14
- 230000009286 beneficial effect Effects 0.000 description 11
- 238000005516 engineering process Methods 0.000 description 6
- 230000000149 penetrating effect Effects 0.000 description 6
- 230000000694 effects Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
Abstract
The invention discloses an aero-engine blade clamping device, and particularly relates to the technical field of precision machining of aero-engine blades. An aircraft engine blade clamping device comprises a base, and a first pressing mechanism, a supporting and fastening mechanism and a second pressing mechanism which are sequentially arranged on the base along the longitudinal direction of the base; the first pressing mechanism comprises a first pressing seat, a first pressing frame, a first pressing cavity formed by the first pressing seat and the first pressing frame, and a circular table or a circular technological table for clamping the wool blanks; the second pressing mechanism comprises a second pressing seat, a second pressing frame, a second pressing cavity formed by the second pressing seat and the second pressing frame, and a mounting plate or a square process table for clamping the wool blank; the supporting and fastening mechanism comprises a supporting seat and a fastening frame, the supporting seat can transversely slide along the base, and a third pressing cavity formed by the supporting seat is used for clamping the blades of the wool blanks. The clamping device is simple in structure, has a large clamping range, and can prevent the blade from vibrating in the blade machining process, so that the blade is damaged.
Description
Technical Field
The invention relates to the technical field of precision machining of aero-engine blades, in particular to a clamping device for an aero-engine blade.
Background
The aeronautical industry is compared with the crown of modern industry, and the aeroengine is more called the pearl on the crown of modern industry, and is the heart of the airplane. During the use of the aircraft engine, the blade is used as a key component of the aircraft generator, and the processing quality of the blade of the aircraft engine determines the performance level and the service life of the aircraft engine.
The blade of the aircraft engine comprises a turbine blade, a compressor blade and a fan blade, wherein the fan blade is generally made of titanium alloy or aluminum alloy, the blade profile part is machined after the two ends of the blade are machined in the traditional machining route of the blade, the blade profile structure is easy to damage in the machining process of the blade profile part by adopting the traditional machining mode, and meanwhile, the structures at the two ends of the machined blade can also be influenced. In order to guarantee the precision of the blades and avoid major accidents caused by damage of the blades, the blades need to be clamped in the detection and processing processes, the existing clamping device is single in structure, cannot be suitable for the blades of different models, is inconvenient to operate, and the detection result is easily influenced.
Disclosure of Invention
The invention aims to provide a blade clamping device of an aircraft engine, which aims to solve the problems that the conventional clamping device is not universally applicable and damages a machined blade structure in the clamping process.
The technical scheme for solving the technical problems is as follows:
an aircraft engine blade clamping device comprising: the device comprises a base, a first pressing mechanism, a supporting and fastening mechanism and a second pressing mechanism, wherein the first pressing mechanism, the supporting and fastening mechanism and the second pressing mechanism are sequentially arranged on the base along the longitudinal direction of the base;
the first pressing mechanism comprises a first pressing seat and a first pressing frame which are respectively connected with the base, and a first pressing cavity is formed between the top of the first pressing frame and the top of the first pressing seat and used for holding a round table or a round process table for clamping the wool blanks;
the second pressing mechanism comprises a second pressing seat and a second pressing frame which are respectively connected with the base, and a second pressing cavity is formed between the top of the second pressing frame and the second pressing seat and used for clamping a mounting plate or a square technological table of the wool blank;
the supporting and fastening mechanism comprises a supporting seat and a fastening frame which are respectively connected with the base, the supporting seat can transversely slide along the base, and a third pressing cavity is formed between the fastening frame and the supporting seat and used for clamping the blades of the wool blanks.
The beneficial effects of adopting the above technical scheme are: the first/second pressing seats are longitudinally arranged on the base, two ends of the blank are arranged on the first/second pressing seats, and the blank is stably clamped on the first/second pressing seats through the first/second pressing frames, so that enough processing space is provided for a machine tool processing cutter; the first/second pressing frame and the first/second pressing seat form a first/second pressing cavity respectively, and the blank material can be stably clamped on the clamping device by placing the blank material in the first/second pressing cavity, so that the blank material is prevented from sliding and falling in the processing process. Through pressing the supporting seat setting at first pressing seat and second and pressing between the seat, for blank material provides the support, prevent when centre of a circle technology platform and the square technology platform at processing blank both ends, the phenomenon that the blade of blank material appears vibrating influences the machining precision of centre of a circle technology platform and square technology platform. Through setting the supporting seat to can follow base lateral sliding, make the supporting seat can be according to the model lateral shifting of actual aeroengine blade on the base, make the blade of supporting seat and blank can in close contact with, provide sufficient support for the blade of blank, improved this clamping device's universal relevance nature.
The clamping process of the blade of the aircraft engine comprises the following steps: firstly, fixedly installing the clamping device on a machine tool; then, the first/second pressing frame and the fastening frame are loosened, the circular technological table of the blank is placed on the first pressing seat, the square technological table of the blank is placed on the second pressing seat, and the blades of the blank are placed on the supporting seat; then, a first pressing frame and a second pressing frame are used for pressing the circle center process table and the square process table on the corresponding first/second pressing seats; then, the specific position of the supporting seat is transversely adjusted along the base, so that the supporting seat is in close contact with the blades of the blank material; and the fastening frame is used for pressing the blades of the rough blanks, so that the phenomenon that the blades vibrate in the processing process is prevented, and the processing precision is prevented from being influenced.
Furthermore, the supporting seat comprises a bearing seat and a mounting seat which are connected with each other, the mounting seat is connected with the base, a first floating supporting block is arranged at the top of the bearing seat, and the first floating supporting block inclines along the transverse direction of the base; the fastening frame comprises a fastening pressing plate, the fastening pressing plate is connected with the base, the fastening pressing plate and the connecting line direction of the bearing seat are located in the transverse direction of the base, the fastening pressing plate is arranged in an inclined mode in the direction where the bearing seat is located, a second floating supporting block is arranged on one side, close to the bearing seat, of the fastening pressing plate in an inclined mode, the second floating supporting block is also arranged in an inclined mode in the transverse direction of the base, and the first floating supporting block and the second floating supporting block are arranged oppositely to form a third pressing cavity.
The beneficial effects of adopting the above technical scheme are: the first floating supporting block is arranged on the bearing seat and is arranged along the transverse direction of the base in an inclined mode, so that blades of the blank materials are convenient to place and lift, and the bearing seat is prevented from being in large-area contact with the blades to cause certain damage to the blades; and the fastening clamp plate is transversely arranged along the base, and the fastening clamp plate is obliquely arranged towards the direction of the bearing seat, so that the fastening clamp plate can compress the blade, a second floating supporting block is obliquely arranged on one side of the fastening clamp plate close to the bearing seat, and the second floating supporting block is also obliquely transversely arranged along the base, so that the second floating supporting block is contacted with the blade, the blade of the blank is compressed under the action of the fastening clamp plate, the large-area contact of the fastening clamp plate and the blade is avoided, and the blade is damaged. The first/second floating supporting blocks are oppositely arranged and form a third pressing cavity for clamping the blade of the rough blank, and the first/second floating supporting blocks clamp the blade tightly, so that the damage of the bearing seat and the fastening pressing plate to the blade is reduced.
Furthermore, the first floating support block and the second floating support block are consistent in structure and respectively comprise a connecting surface and a positioning surface which are arranged oppositely, the connecting surface is connected with the corresponding bearing seat or the fastening pressing plate, the positioning surfaces are arranged oppositely and are arc-shaped, and ball head contact pins are respectively arranged at two ends of each positioning surface.
The beneficial effects of adopting the above technical scheme are: the positioning surfaces of the first/second floating supporting blocks are oppositely arranged and arc-shaped, so that the contact area between the first/second floating supporting blocks and the blade is reduced, and meanwhile, the first/second floating supporting blocks of the arc-shaped structure can enable the first/second floating supporting blocks to clamp the blade better; and the two ends of the positioning surface are respectively provided with a ball head contact pin which is in contact with the blade, and the blade is fastened under the pressing action of the first/second floating support block, so that the blade and the ball head contact pin are fastened in a point-surface contact manner, and the contact area between the first/second floating support block and the blade is further reduced.
Furthermore, the middle part of the connecting surface is provided with an arc-shaped bulge, the arc-shaped bulge extends into the corresponding bearing seat or the corresponding fastening pressure plate, the arc-shaped bulge is connected with the corresponding bearing seat or the corresponding fastening pressure plate through a pin, and the two ends of the connecting surface are respectively connected with the corresponding bearing seat or the corresponding fastening pressure plate through elastic pieces.
The beneficial effects of adopting the above technical scheme are: the arc-shaped bulge is arranged in the middle of the connecting surface of the first/second floating supporting block and is connected with the corresponding bearing seat or the corresponding fastening pressing plate through the pin, so that the first/second floating supporting block can rotate slightly around the pin, and the first/second floating supporting block can be contacted with the blade and pressed tightly more stably; and the two ends of the connecting surface are respectively connected with the corresponding bearing seat or the corresponding fastening pressure plate through the elastic parts, so that the first/second floating support block is prevented from operating and damaging the bearing seat or the fastening pressure plate in the fine adjustment process, and the first/second floating support block is carried out under the traction of the elastic parts in the fine adjustment process, so that the fine adjustment process is stable and slow.
Further, above-mentioned fastening frame still includes bracing piece, fastening bolt and connecting seat, and the bracing piece setting is kept away from the one side of fastening clamp plate at the base, and the bracing piece with bear the weight of the seat and be connected, the connecting seat setting is kept away from the one side of bearing the weight of the seat at the base, and the connecting seat is articulated with the bottom of fastening clamp plate, and fastening bolt's one end is articulated with the bracing piece, and fastening bolt's the other end can be dismantled with the fastening clamp plate and be connected.
The beneficial effects of adopting the above technical scheme are: the supporting rod is arranged on one side of the base, which is far away from the fastening pressure plate, and is connected with the bearing seat, so that the bearing seat is limited after sliding transversely along the base and then being tightly contacted with the blades, and the phenomenon that the bearing seat slides in the processing process is prevented from affecting the processing process and the processing precision; the connecting seat is connected with the bottom of the fastening pressing plate through a hinge, so that the fastening pressing plate can rotate on the connecting seat, and the fastening pressing plate is convenient to fasten; the fastening bolt and the fastening pressing plate are detachably connected, so that the fastening pressing plate can realize fastening operation under the action of the fastening bolt, and meanwhile, the fastening bolt and the fastening pressing plate are conveniently connected and fastened.
Further, the installation seat comprises a first installation seat and a second installation seat, the first installation seat and the second installation seat are arranged on the base along the transverse parallel direction of the base, a strip-shaped boss is arranged on one side, close to the second installation seat, of the top end of the first installation seat, the strip-shaped boss and the base form a sliding groove, and a sliding block matched with the sliding groove is transversely arranged at the bottom end of the bearing seat.
The beneficial effects of adopting the above technical scheme are: the first mounting seat and the second mounting seat are arranged on the base in parallel along the transverse direction of the base, so that the first mounting seat and the second mounting seat form a guide rail on the base, and the bearing seat can conveniently slide along the direction of the guide rail; and one side of the top end of the first mounting seat, which is close to the second mounting seat, is provided with a strip-shaped boss, so that a sliding groove is formed between the strip-shaped boss and the base, and the side surface, which corresponds to the bearing seat, is provided with a sliding block matched with the sliding groove, so that the sliding block on the bearing seat slides in the sliding groove, and meanwhile, the phenomenon of falling and loosening of the bearing seat in the process of clamping and processing parts is avoided.
Further, the bearing seat is of a wedge-shaped structure and comprises a vertical face and an inclined face, the vertical face is close to the supporting rod, the inclined face is close to the fastening pressing plate, the vertical face is provided with a T-shaped clamping groove along the horizontal direction, the supporting rod is connected with the clamping groove through a supporting screw, and the end portion of the supporting screw is provided with a T-shaped protrusion matched with the T-shaped clamping groove.
The beneficial effects of adopting the above technical scheme are: set up T type draw-in groove through the horizontal direction at vertical face to place support screw's T type arch in T type draw-in groove, make on the one hand bear the seat and can realize along base lateral sliding's purpose under support screw's effect, on the other hand makes and bears the seat and can realize spacing effect under support screw's effect, prevents to be fastening the in-process of operation, bears the seat and appears sliding and not hard up phenomenon, provides sufficient holding power for bearing the seat.
Furthermore, the second pressing seat is of a U-shaped structure and is transversely arranged on the base along the base, the second pressing seat comprises a positioning arm and a fastening arm, and a fastening screw is transversely arranged on the fastening arm along the base;
the second compresses tightly the frame and includes second support stud, second stud and second clamp plate, and the one end of second clamp plate is passed through the second support stud and is connected with the base, and the other end of second clamp plate and second compress tightly and form the second between the U die cavity body of seat and compress tightly the chamber for mounting panel or the square technology platform of centre gripping blank, the middle part of second clamp plate is provided with the bar through-hole, and the one end setting of second stud is on the base, and the other end of second stud is equipped with the nut after passing the bar through-hole.
The beneficial effects of adopting the above technical scheme are: the U-shaped second pressing seat is transversely arranged on the base along the base, so that the mounting plate or the square process table for clamping the blank can be stably clamped on the second pressing seat; one end of the second pressing plate is connected with the base through a second supporting stud to provide a certain supporting effect for the second pressing plate, so that the second pressing plate is arranged on the second pressing seat in a suspended mode, and a second pressing cavity is formed between the second pressing seat and the second pressing seat, and the mounting plate or the square technological table for clamping the blank can be fastened conveniently; and the middle part of the second pressing plate is provided with a strip-shaped through hole, so that the second stud bolt is sleeved with a nut after penetrating through the strip-shaped through hole, and the nut is used for fastening the second fastening pressing plate, thereby realizing the purpose of pressing and clamping a mounting plate or a square process table of a blank and facilitating the processing of the blade.
Further, an axial positioning mechanism is arranged between the second pressing seat and the supporting and fastening mechanism and comprises a positioning seat and a ball head positioning pin, the positioning seat is arranged on the base, the ball head positioning pin is arranged at the top of the positioning seat and close to the second pressing seat, and the ball head positioning pin is arranged along the longitudinal direction of the base.
The beneficial effects of adopting the above technical scheme are: an axial positioning mechanism is arranged between the second pressing seat and the supporting and fastening mechanism, so that the axial direction of the blank is positioned and limited, and the processing and positioning precision of the blank is ensured.
Further, the first pressing seat is provided with a V-shaped groove, the V-shaped groove is transversely formed in the base, the first pressing frame comprises a first supporting bolt, a first stud and a first pressing plate, one end of the first pressing plate is connected with the base through the first supporting stud, a first pressing cavity is formed between the other end of the first pressing plate and the V-shaped cavity of the first pressing seat and used for clamping a round table or a circular technological table of a blank, a strip-shaped through hole is formed in the middle of the first pressing plate, one end of the first stud is arranged on the base, and a nut is sleeved at the other end of the first stud after penetrating through the strip-shaped through hole.
The beneficial effects of adopting the above technical scheme are: the V-shaped first pressing seat is transversely arranged on the base along the base, so that a circular table or a circular technological table for clamping blank blanks can be stably clamped on the first pressing seat; one end of the first pressing plate is connected with the base through a first supporting stud to provide a certain supporting effect for the first pressing plate, so that the first pressing plate is arranged on the first pressing seat in a suspended mode, and a first pressing cavity is formed between the first pressing seat and the first pressing seat, and the fastening operation of a circular table or a circular technological table for clamping blank materials is facilitated; and the middle part of the first pressing plate is provided with the strip-shaped through hole, so that the first double-head bolt is sleeved with the nut after penetrating through the strip-shaped through hole, the first fastening pressing plate can be fastened by using the nut, the purpose of pressing a round table or a circular process table for clamping a blank is realized, and the processing of the blade is facilitated.
The invention has the following beneficial effects:
1. the invention has simple structure and extremely high universality, and simultaneously, the phenomenon of blade vibration is not easy to occur in the processes of clamping and processing, thereby influencing the processing precision of the blade.
2. The first pressing mechanism and the second pressing mechanism respectively provide enough supporting force for two ends of the blade of the aero-engine, and meanwhile, the clamping process is convenient and efficient.
3. The supporting and fastening mechanism is arranged between the first pressing mechanism and the second pressing mechanism, and provides a certain supporting force for the blades, so that the phenomenon that the blades are too long and vibrate in the processing process to further influence the processing precision is avoided; and the supporting seat of the supporting and fastening mechanism can move transversely on the base, so that the supporting and fastening mechanism can be in close contact with the blade, and the application range of the clamping device is expanded.
4. The first mounting seat and the second mounting seat are arranged in parallel along the transverse direction of the base, the strip-shaped boss is arranged on the side face, close to the top of the second mounting seat, of the first mounting seat, a sliding groove is formed between the strip-shaped boss and the base, the sliding block matched with the sliding groove is arranged on the bearing seat, the bearing seat can slide along the transverse direction of the base, and the bearing seat can stably clamp blank blades according to the actual rotation angle of the blank blades.
5. The first floating supporting block and the second floating supporting block are in point-surface contact with the blade of the rough blank, so that the blade is stably clamped, the contact area of the clamping device and the rough blank is reduced, and meanwhile, the bearing seat can better provide supporting force for the blade; and the first/second floating support block can automatically adjust the contact angle with the blade according to the rotation angle of the blade, so that the application range of the clamping device is greatly expanded.
6. The fastening frame is connected with the fastening pressure plate through the fastening bolt to realize the pressing operation, so that the blades are conveniently pressed on the bearing seat.
7. The fastening screw transversely arranged on the fastening arm of the second pressing seat is used for fastening one end of the aero-engine blade on the second pressing seat, so that the second pressing seat can adapt to aero-engine blades of different models, and the application range of the clamping device is further expanded.
Drawings
FIG. 1 is a schematic structural view of an aircraft engine blade clamping device according to the invention;
FIG. 2 is a schematic structural view of the support fastening mechanism of the present invention;
FIG. 3 is a schematic structural view of the supporting base of the present invention;
FIG. 4 is a schematic structural diagram of the first/second floating support block of the present invention;
FIG. 5 is a schematic structural view of the fastening frame of the present invention;
FIG. 6 is a schematic structural view of the fastening platen of the present invention;
fig. 7 is a schematic view of a clamping structure of the blank and the clamping device of the present invention.
In the figure: 1-a base; 2-a first hold-down mechanism; 3-a second hold-down mechanism; 4-supporting the fastening mechanism; 5-an axial positioning mechanism; 6-a chute; 21-a first compression seat; 22-a first hold-down frame; 31-a second compression seat; 32-a second hold-down frame; 41-a support seat; 42-a fastening frame; 43-a bar-shaped boss; 44-a first floating support block; 45-support screws; 46-a second floating support block; 411-a carrier; 412-a mount; 4111-a slider; 4112-vertical plane; 4113-inclined plane; 4114-a card slot; 4121-a first mount; 4122-a second mount; 4411-circular arc shaped protrusions; 441-the connection face; 442-positioning surface; 443-ball head contact pins; 421-a support bar; 422-fastening bolts; 423-fastening the pressure plate; 424-connecting seat; a 451-T shaped projection; 4231-a first U-shaped opening; 4232-second U-shaped opening; 51-a positioning seat; 52-ball head locating pin; 321-a second support stud; 322-second stud; 323-a second platen; 311-a positioning arm; 312-a fastening arm; 313-a fastening screw; 221-a first support stud; 222-a first stud; 223 — first platen.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.
Examples
Referring to fig. 1 and 7, an aircraft engine blade clamping device includes a base 1, a first pressing mechanism 2, a second pressing mechanism 3, and a supporting fastening mechanism 4, wherein the first pressing mechanism 2 and the second pressing mechanism 3 are respectively and longitudinally disposed at two ends of the base 1, the supporting fastening mechanism 4 is disposed between the first pressing mechanism 2 and the second pressing mechanism 3, and an axial positioning mechanism 5 is disposed between the first pressing mechanism 2 and the second pressing mechanism 3. And the blank material comprises a square process table, an installation plate, a blade, a round table and a round process table which are arranged in sequence. The first pressing mechanism 2 is used for clamping a round table or a round technological table of the wool blank, the supporting and fastening mechanism 4 is used for clamping a blade of the wool blank, the second pressing mechanism 3 is used for clamping a mounting plate and a square technological table of the wool blank, and the axial positioning mechanism 5 can longitudinally position and limit the mounting plate along the base 1. By arranging the supporting and fastening mechanism 4 between the first pressing mechanism 2 and the second pressing mechanism 3, on one hand, supporting force is provided for the blades of the blank, and on the other hand, the blades are fastened, so that the phenomenon that the blades slide down in the processing process is prevented.
The axial positioning mechanism 5 comprises a positioning seat 51 and a ball positioning pin 52, the positioning seat 51 is fixedly installed on the base 1 through a bolt, the ball positioning pin 52 is arranged at the top of the positioning seat 51 and close to the second pressing mechanism 3, and the ball positioning pin 52 is arranged along the longitudinal direction of the base 1, so that the surface of the mounting plate can be positioned by the ball positioning pin in the process of clamping blank materials, the blank materials are processed, and meanwhile, the processing precision of the blank materials can also be improved.
Referring to fig. 1 and 2, the supporting and fastening mechanism 4 includes a supporting seat 41 and a fastening frame 42, the supporting seat 41 and the fastening frame 42 are both fixedly mounted on the base 1 by bolts, and a third pressing cavity is formed between the fastening frame 42 and the supporting seat 41 for clamping the blade of the blank.
Fastening frame 42 includes bracing piece 421, fastening bolt 422, fastening clamp plate 423 and connecting seat 424, bracing piece 421 passes through the bolt fastening in the one side that base 1 is close to and bears seat 411, fastening clamp plate 423 passes through hinged joint with connecting seat 424, and connecting seat 424 keeps away from one side that bears seat 411 through bolt fixed mounting in base 1, fastening bolt 422 can be dismantled with the top of bracing piece 421 and be connected, and fastening bolt 422 passes and is connected with the nut behind fastening clamp plate 423, and will fasten clamp plate 423 and fastening bolt 422 through the nut and fasten the operation. A third pressing cavity is formed between the supporting seat 41 and the fastening pressing plate 423, and the fastening bolt 422 drives the fastening pressing plate 423 to change the size of the third pressing cavity and stably clamp the blade in the third pressing cavity.
Be provided with supporting screw 45 on the bracing piece 421, supporting screw 45 transversely sets up along base 1, and supporting screw 45 is connected with supporting seat 41, and through screw-thread fit between supporting screw 45 and the bracing piece 421, make supporting screw 45 can be along base 1's lateral adjustment on bracing piece 421, and then drive supporting seat 41 along base 1 lateral sliding, make supporting seat 41 can with the better contact of blade, use supporting screw 45 to fix a position supporting seat 41 simultaneously, prevent that the not hard up phenomenon of sliding from appearing in supporting seat 41 at the in-process of fastening operation, and then make fastening operation insecure.
Referring to fig. 2, fig. 3 and fig. 5, the supporting base 41 includes a bearing seat 411 and an installation seat 412, the bearing seat 411 is slidably connected with the installation seat 412, the installation seat 412 includes a first installation seat 4121 and a second installation seat 4122, the first installation seat 4121 and the second installation seat 4122 are disposed on the base 1 in parallel along the transverse direction of the base 1, and the first installation seat 4121 and the second installation seat 4122 disposed in parallel provide a guide rail for the sliding of the bearing seat 411, so that the bearing seat 411 can slide along the transverse direction of the base 1; one side that first mount pad 4121 top is close to second mount pad 4122 is provided with bar boss 43 to form spout 6 between bar boss 43 and the base 1, and transversely be provided with in the bottom of bearing seat 411 with spout matched with slider 4111, through the cooperation between spout 6 and the slider 4111, make and bear seat 411 and can slide along spout 6 steadily, avoid simultaneously bearing seat 411 to drop from mount pad 412.
An inward-concave arc-shaped structure is arranged on one side, close to the bearing seat 411, of the fastening pressing plate 423, a first U-shaped opening 4231 and a second U-shaped opening 4232 are arranged at two ends of the fastening pressing plate 423, the first U-shaped opening is used for placing the fastening bolt 422, and the fastening pressing plate 423 and the fastening bolt 422 are fastened and connected under the effect of nuts sleeved at the end of the fastening bolt 422. The second U-shaped opening 4232 is hinged to the connecting seat 424, so that the fastening pressing plate 423 can rotate on the connecting seat 424 around the hinge, and the fastening pressing plate 423 is further pressed conveniently.
Referring to fig. 3 and 4, a first floating supporting block 44 is disposed on the inclined surface 4113, the first floating supporting block 44 is disposed along a lateral direction of the base 1, a second floating supporting block 46 is disposed on a side of the fastening pressing plate 423 close to the bearing seat 411, and the first floating supporting block 44 and the second floating supporting block 46 are disposed opposite to each other and form a third pressing cavity. Through set up first unsteady supporting shoe 44 on bearing seat 411 and set up second unsteady supporting shoe 46 on fastening clamp plate 423, make first unsteady supporting shoe 44 and second unsteady supporting shoe 46 contact with the blade, reduce the area of contact of clamping device and blade, avoid the damage that clamping device caused the blade in the in-process of clamping. The first floating support block 44 and the second floating support block 46 have the same structure and respectively comprise a connecting surface 441 and a positioning surface 442 which are arranged oppositely, the connecting surface is connected with the corresponding bearing seat 411 or the fastening pressing plate 423, the middle part of the positioning surface 442 is of an arc structure which is sunken towards the connecting surface 441, ball head contact pins 443 are respectively arranged at two ends of the positioning surface 442, the ball head contact pins 443 are connected with two ends of the positioning surface 442 through springs, and the ball head positioning pins 443 are arranged at two ends of the positioning surface 442, so that the blade is in a point-surface contact mode in the process of clamping, and the surface of the blade is prevented from being damaged by large-area contact. The middle of the positioning surface 442 is configured to be an arc structure recessed toward the connecting surface 441, so that the first floating support block 44 and the second floating support block 46 reduce the chance of the surfaces of the first floating support block 44 and the second floating support block 46 contacting the blade during the clamping process.
The middle part of the connecting surface 441 is provided with an arc-shaped protrusion 4411 far away from the positioning surface 442, the arc-shaped protrusion 4411 extends into the inclined surface 4113 of the corresponding bearing seat 411 or the inside of an inwards recessed arc-shaped structure of the fastening pressing plate 423, the arc-shaped protrusion 4411 is connected with the bearing seat 411 or the fastening pressing plate 423 through a pin in the inclined surface 4113 or the fastening pressing plate 423, so that the first floating supporting block 44 and the second floating supporting block 46 can rotate around the pin, the contact angle between the first floating supporting block 44 and the second floating supporting block 46 and the blade is changed, and the first floating supporting block 44 and the second floating supporting block 46 can be in close contact with the blade better and clamp the blade stably in the third pressing cavity. The two ends of the connecting surface 441 are respectively connected with the corresponding bearing seat 411 or the corresponding fastening pressing plate 423 through springs, so that the connection relationship between the first floating supporting block 44 and the second floating supporting block 46 and the bearing seat 411 and the fastening pressing plate 423 is elastic connection, the damage of the connecting surface 441 on the surface of the inclined surface 4113 of the bearing seat 411 or the fastening pressing plate 423 is avoided when the first floating supporting block 44 and the second floating supporting block 46 rotate around pins, and meanwhile, the fine adjustment process of the first floating supporting block 44 and the second floating supporting block 46 is stable and slow, and the change of the angle is performed under the traction of the springs.
Referring to fig. 1, the second pressing mechanism 3 includes a second pressing base 31 and a second pressing frame 32, both the second pressing base 31 and the second pressing frame 32 are fixedly mounted on the base 1 through bolts and are arranged along the transverse direction of the base 1, so that a second pressing cavity is formed between the second pressing base 31 and the second pressing frame 32 for mounting a mounting plate or a square process table for clamping a blank; the second pressing frame 32 is arranged between the first fastening mechanism 2 and the second fastening mechanism 3, so that the clamping device has a compact structure, and can stably press the mounting plate or the square technological table for clamping the wool blank on the second pressing seat 31. In other embodiments of this embodiment, the second pressing frame 32 may also be disposed outside the second pressing base 31, so as to further provide a processing space, so that the machine tool has a sufficient space to process the blank, and the second pressing frame 32 is prevented from blocking the processing path of the processing tool and affecting the processing process.
The second compresses tightly seat 31 and is the U type structure, bolt fixed mounting is passed through on base 1 in the bottom of U type structure, the second that is the U type structure compresses tightly seat 31 and sets up along base 1's horizontal, and the second compresses tightly seat 31 and includes location arm 311 and fastening arm 312, be provided with fastening screw 313 on the fastening arm 312, fastening screw 313 sets up along base 1's horizontal, make fastening screw 313 can place the mounting panel after on the second that is the U type compresses tightly seat 31, fasten the operation to the mounting panel, make this clamping device can adapt to the clamping of the aeroengine blade blank of more models.
The second pressing frame 32 comprises a second supporting stud 321, a second stud 322 and a second pressing plate 323, one end of the second pressing plate 323 is connected with the base 1 through the second supporting stud 321, the other end of the second pressing plate 323 is connected with a U-shaped cavity of the second pressing seat 31 to form a second pressing cavity for clamping a mounting plate or a square technological table of blank materials, a strip-shaped through hole is formed in the middle of the second pressing plate 323, one end of the second stud 322 is arranged on the base 1, and a nut is sleeved on the other end of the second stud 322 after penetrating through the strip-shaped through hole. One end of the second pressing plate 323 is connected with the base 1 through the second supporting stud 321 to provide a certain supporting effect for the second pressing plate 323, so that the second pressing plate 323 is arranged on the second pressing seat 31 in a suspended manner, and a second pressing cavity is formed between the second pressing seat 31 and the second pressing seat, thereby facilitating the fastening operation of a mounting plate or a square process table for clamping blank materials; and the middle part of the second pressing plate 323 is provided with a strip-shaped through hole, so that the second stud bolt 322 is sleeved with a nut after penetrating through the strip-shaped through hole, and the second fastening pressing plate 323 is fastened by the nut, thereby realizing the purpose of pressing and clamping the mounting plate or the square process table of the blank and facilitating the processing of the blade.
The first pressing mechanism comprises a first pressing seat 21 and a first pressing frame 22, the first pressing seat 21 and the first pressing frame 22 are fixedly mounted on the base 1 through bolts and are arranged along the transverse direction of the base 1, so that a first pressing cavity is formed between the first pressing seat 21 and the first pressing frame 22 and is used for holding a circular truncated cone or a circular technological table for clamping a blank; the first pressing frame 22 is arranged between the first pressing seat 21 and the second pressing seat 31 and is arranged on the longitudinal side edge of the base 1 opposite to the second pressing frame 32, so that the clamping device is compact in structure and saves space of the clamping device. In other embodiments of this embodiment, the first pressing frame 22 may also be disposed outside the first pressing base 21, so as to avoid that the first pressing frame 22 blocks a processing path of a processing tool and affects a processing process; or the first pressing frame 22 and the second pressing frame 32 are arranged between the first pressing base 21 and the second pressing base 31 in a diagonal prevention manner.
First compressing tightly seat 21 is V type structure, and bolt fixed mounting is passed through on base 1 in the bottom of first compressing tightly seat 21 to first compressing tightly seat 21 that is V type structure transversely sets up along base 1 for place blank's round platform and circular technology platform.
The clamping process of the blank of the blade of the aircraft engine comprises the following steps: (1) firstly, clamping the aero-engine blade clamping device on a machine tool; (2) the first/second pressing plates of the first/second pressing frames are loosened, and the connection relation between the fastening bolts 422 and the fastening pressing plates 423 is disconnected; (3) placing the circular technological table of the blank on the first pressing seat 21, placing the square technological table of the blank on the second pressing seat 31, and placing the blade of the blank on the bearing seat 411; (4) the position of the bearing seat 411 is transversely adjusted along the base 1 by using a supporting screw 45, so that the first floating supporting block 44 is tightly contacted with the blade; (5) then, the fastening pressure plate 423 is rotated to the upper surface of the blade, the second floating support block 46 is in close contact with the upper surface of the blade, the fastening bolt 422 is clamped into the first U-shaped opening 4231 of the fastening pressure plate, and the fastening pressure plate 423 is pressed tightly by using a nut, so that the clamping is completed.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. An aircraft engine blade clamping device, comprising: the device comprises a base (1), and a first pressing mechanism (2), a supporting and fastening mechanism (4) and a second pressing mechanism (3) which are sequentially arranged on the base (1) along the longitudinal direction of the base (1);
the first pressing mechanism (2) comprises a first pressing seat (21) and a first pressing frame (22) which are respectively connected with the base (1), and a first pressing cavity is formed between the top of the first pressing frame (22) and the top of the first pressing seat (21) and is used for holding a circular table or a circular technological table for clamping wool blanks;
the second pressing mechanism (3) comprises a second pressing seat (31) and a second pressing frame (32) which are respectively connected with the base (1), and a second pressing cavity is formed between the top of the second pressing frame (32) and the second pressing seat (31) and is used for clamping a mounting plate or a square technological table of the wool blank;
the supporting and fastening mechanism (4) comprises a supporting seat (41) and a fastening frame (42) which are respectively connected with the base (1), the supporting seat (41) can slide transversely along the base (1), and a third pressing cavity is formed between the fastening frame (42) and the supporting seat (41) and used for clamping blades of the wool blanks.
2. The aircraft engine blade clamping device according to claim 1, wherein the supporting seat (41) comprises a bearing seat (411) and a mounting seat (412) which are connected with each other, the mounting seat (412) is connected with the base (1), a first floating supporting block (44) is arranged at the top of the bearing seat (411), and the first floating supporting block (44) is inclined along the transverse direction of the base (1);
the fastening frame (42) comprises a fastening pressing plate (423), the fastening pressing plate (423) is connected with the base (1), the connecting line direction of the fastening pressing plate (423) and the bearing seat (411) is located in the transverse direction of the base (1), the fastening pressing plate (423) is obliquely arranged towards the direction of the bearing seat (411), a second floating supporting block (46) is obliquely arranged on one side, close to the bearing seat (411), of the fastening pressing plate (423), the second floating supporting block (44) is also obliquely arranged along the transverse direction of the base (1), and the first floating supporting block (44) and the second floating supporting block (46) are oppositely arranged to form the third pressing cavity.
3. The aircraft engine blade clamping device according to claim 2, wherein the first floating supporting block (44) and the second floating supporting block (46) are consistent in structure and respectively comprise a connecting surface (441) and a positioning surface (442), the connecting surface (441) is connected with the corresponding bearing seat (411) or the corresponding fastening pressing plate (423), the positioning surface (442) is oppositely arranged and is arc-shaped, and two ends of the positioning surface (442) are respectively provided with a ball head contact pin (443).
4. The aircraft engine blade clamping device according to claim 3, characterized in that the middle of the connecting surface (441) is provided with a circular arc-shaped protrusion (4411), the circular arc-shaped protrusion (4411) extends into the corresponding bearing seat (411) or the fastening pressure plate (423), the circular arc-shaped protrusion (4411) is connected with the corresponding bearing seat (411) or the fastening pressure plate (423) through a pin, and the two ends of the connecting surface (441) are respectively connected with the corresponding bearing seat (411) or the fastening pressure plate (423) through elastic members.
5. The aircraft engine blade clamping device according to claim 3, wherein the fastening frame (42) further comprises a support rod (421), a fastening bolt (422) and a connecting seat (424), the support rod (421) is arranged on one side of the bearing seat (411) far away from the fastening pressure plate (423), the support rod (421) is connected with the bearing seat (411), the connecting seat (424) is arranged on one side of the base (1) far away from the bearing seat (411), the connecting seat (424) is hinged with the bottom of the fastening pressure plate (423), one end of the fastening bolt (422) is hinged with the support rod (421), and the other end of the fastening bolt (422) is detachably connected with the fastening pressure plate (423).
6. The aircraft engine blade clamping device according to claim 5, wherein the mounting seat (412) comprises a first mounting seat (4121) and a second mounting seat (4122), the first mounting seat (4121) and the second mounting seat (4122) are arranged on the base (1) in parallel along the transverse direction of the base (1), a strip-shaped boss (43) is arranged on one side, close to the second mounting seat (4122), of the top end of the first mounting seat (4121), the strip-shaped boss (43) forms a sliding groove (6) with the base (1), and a sliding block (4111) matched with the sliding groove (6) is arranged on the bottom end of the bearing seat (411) in the transverse direction.
7. An aircraft engine blade clamping device according to claim 6, characterised in that the bearing seat (411) is of a wedge structure comprising a vertical face (4112) and an inclined face (4113), the vertical face (4112) is close to the supporting rod (421), the inclined face (4113) is close to the fastening pressure plate (423), the vertical face (4112) is provided with a T-shaped clamping groove (4114) along the horizontal direction, the supporting rod (421) is connected with the clamping groove (4114) through a supporting screw (45), and the end of the supporting screw (45) is provided with a T-shaped protrusion (451) matched with the T-shaped clamping groove (4114).
8. The aeroengine blade clamping device of claim 1, wherein said second clamping seat (31) is of a U-shaped configuration and is disposed on said base (1) in a transverse direction of said base (1), said second clamping seat (31) comprising a positioning arm (311) and a fastening arm (312), said fastening arm (312) having a fastening screw (313) disposed thereon in a transverse direction of said base (1);
the second pressing frame (32) comprises a second supporting stud (321), a second stud (322) and a second pressing plate (323), one end of the second pressing plate (323) is connected with the base (1) through the second supporting stud (321), the other end of the second pressing plate (323) is connected with a U-shaped cavity of the second pressing seat (31) to form a second pressing cavity used for clamping a mounting plate or a square technological table of a blank, a strip-shaped through hole is formed in the middle of the second pressing plate (323), one end of the second stud (322) is arranged on the base (1), and a nut is sleeved behind the strip-shaped through hole and penetrates through the other end of the second stud (322).
9. The aeroengine blade clamping device of claim 1, wherein an axial positioning mechanism (5) is arranged between the second pressing seat (31) and the support fastening mechanism (4), the axial positioning mechanism (5) comprises a positioning seat (51) and a ball head positioning pin (52), the positioning seat (51) is arranged on the base (1), the ball head positioning pin (52) is arranged on the top of the positioning seat (51) and close to the second pressing seat (31), and the ball head positioning pin (52) is arranged along the longitudinal direction of the base (1).
10. The aeroengine blade clamping device of any one of claims 1 to 9, a V-shaped groove is arranged on the first pressing seat (21), the V-shaped groove is transversely arranged along the base (1), the first pressing frame (22) comprises a first supporting bolt (221), a first stud (222) and the first pressing plate (223), one end of the first pressure plate (223) is connected with the base (1) through the first supporting stud (221), a first pressing cavity is formed between the other end of the first pressing plate (223) and the V-shaped cavity body of the first pressing seat (21), a circular table or a circular process table for clamping the blank, wherein the middle part of the first pressing plate (223) is provided with a strip-shaped through hole, one end of the first stud (222) is arranged on the base (1), the other end of the first stud (222) penetrates through the strip-shaped through hole and then is sleeved with a nut.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110963440.7A CN113618657A (en) | 2021-08-20 | 2021-08-20 | Aeroengine blade clamping device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110963440.7A CN113618657A (en) | 2021-08-20 | 2021-08-20 | Aeroengine blade clamping device |
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| CN113618657A true CN113618657A (en) | 2021-11-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110963440.7A Pending CN113618657A (en) | 2021-08-20 | 2021-08-20 | Aeroengine blade clamping device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114749954A (en) * | 2022-04-13 | 2022-07-15 | 西安三航动力科技有限公司 | Self-adaptive clamping device for craft platform of aviation blade tip |
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Application publication date: 20211109 |