CN110421024A - Blade of aviation engine corrector and its straightening method - Google Patents
Blade of aviation engine corrector and its straightening method Download PDFInfo
- Publication number
- CN110421024A CN110421024A CN201910697144.XA CN201910697144A CN110421024A CN 110421024 A CN110421024 A CN 110421024A CN 201910697144 A CN201910697144 A CN 201910697144A CN 110421024 A CN110421024 A CN 110421024A
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- blade
- fixed frame
- pressure
- outer cover
- corrector
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- 238000000034 method Methods 0.000 title claims abstract description 21
- 230000007246 mechanism Effects 0.000 claims abstract description 49
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims abstract description 26
- 230000005540 biological transmission Effects 0.000 claims abstract description 24
- 238000006073 displacement reaction Methods 0.000 claims description 18
- 238000003825 pressing Methods 0.000 claims description 9
- 230000013011 mating Effects 0.000 claims 1
- 238000003754 machining Methods 0.000 abstract description 2
- 238000012797 qualification Methods 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 8
- 230000008569 process Effects 0.000 description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 4
- 229910052782 aluminium Inorganic materials 0.000 description 4
- 238000009434 installation Methods 0.000 description 4
- 239000007787 solid Substances 0.000 description 4
- 238000012937 correction Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 239000004677 Nylon Substances 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 239000002519 antifouling agent Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 239000004922 lacquer Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 229920001778 nylon Polymers 0.000 description 1
- 239000003973 paint Substances 0.000 description 1
- 238000010422 painting Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- GOLXNESZZPUPJE-UHFFFAOYSA-N spiromesifen Chemical compound CC1=CC(C)=CC(C)=C1C(C(O1)=O)=C(OC(=O)CC(C)(C)C)C11CCCC1 GOLXNESZZPUPJE-UHFFFAOYSA-N 0.000 description 1
- 238000007592 spray painting technique Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
- B21C51/00—Measuring, gauging, indicating, counting, or marking devices specially adapted for use in the production or manipulation of material in accordance with subclasses B21B - B21F
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D3/00—Straightening or restoring form of metal rods, metal tubes, metal profiles, or specific articles made therefrom, whether or not in combination with sheet metal parts
- B21D3/10—Straightening or restoring form of metal rods, metal tubes, metal profiles, or specific articles made therefrom, whether or not in combination with sheet metal parts between rams and anvils or abutments
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D43/00—Feeding, positioning or storing devices combined with, or arranged in, or specially adapted for use in connection with, apparatus for working or processing sheet metal, metal tubes or metal profiles; Associations therewith of cutting devices
- B21D43/003—Positioning devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D53/00—Making other particular articles
- B21D53/78—Making other particular articles propeller blades; turbine blades
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Orthopedics, Nursing, And Contraception (AREA)
Abstract
The invention discloses a kind of blade of aviation engine corrector and its straightening methods, including pedestal, the supporting mechanism for location being separately positioned on pedestal and sliding equipment and the pressure shape rectifying mechanism being arranged on the sliding equipment；The pressure shape rectifying mechanism include the rotation axis being arranged on the sliding equipment, be cooperatively connected in the rotation axis fixed frame, be cooperatively connected on the fixed frame outer cover, be provided on limit graduated scale, the transmission component for driving the outer cover to slide along the fixed frame, the pressure gauge being arranged on the casing outer wall and the pressure head that the pressure gauge lower end is set of the outer cover, the fixed frame locking piece for locking fixed frame position；Its structure is reliable, easy to operate, and service performance is good, and effective solution blade ensure that the qualification rate of blade profile because type face offset dimensions caused by machining deformation are overproof and scrap.
Description
Technical field
The present invention relates to blade of aviation engine manufacturing technology fields, and in particular to a kind of aviation invention machine aluminum blades school shape
Device and its straightening method.
Background technique
In aero-engine, 1-3 grades of straightener(stator) blades of low pressure are thin-wall construction, because of cutting stress and zero in process
The effect of part internal stress itself causes deformable blade to reverse, and maximum deformation quantity reaches 1mm after numerical control mill blade profile, before polishing blade profile, sternly
(design code is up to 0.3mm) is required beyond design drawing again, causes part between process overproof because deforming, scrappage is higher, raw
It produces to deliver and be difficult to ensure.Blade is corrected without special equipment or device after deforming at present, it is simple by building
Workbench carries out, and leads to school shape low efficiency, quality not can guarantee, and stability is poor.
Summary of the invention
It is existing to solve the purpose of the present invention is to provide a kind of blade of aviation engine corrector and its straightening method
The problem of device can not carry out effective school shape to aero-engine aluminum blades.
The technical scheme to solve the above technical problems is that blade of aviation engine corrector, including pedestal,
The supporting mechanism for location and sliding equipment that are separately positioned on pedestal and the pressure shape-calibration machine being arranged on the sliding equipment
Structure；
The pressure shape rectifying mechanism includes the rotation axis being arranged on the sliding equipment, is cooperatively connected in the rotation axis
On fixed frame, the outer cover on the fixed frame of being cooperatively connected, through the limit graduated scale of the outer cover, described for driving
Outer cover is along the transmission component that the fixed frame slides, the pressure gauge being arranged on the casing outer wall and is arranged in the pressure
The pressure head of table lower end, the locking piece for locking fixed frame position is provided on the fixed frame, and the transmission component is located at institute
It states in fixed frame.
Further, the supporting mechanism for location includes the blade root support for being separately positioned on the pedestal both ends and being oppositely arranged
Blade root locating piece of the blade root support base on blade tip support base end face is arranged in and setting exists in seat and blade tip support base
Blade tip locating piece on the blade tip support base offers limiting slot on the blade root locating piece and blade tip locating piece, described
Backing plate is provided between blade root support base and blade root locating piece.
Further, the sliding equipment includes setting glide base on the base, is arranged in the glide base
On bottom plate and the pressing plate that is connected between the glide base and the bottom plate, be provided with for fixing on the pressing plate
State the first fixing piece of bottom plate and the glide base；
The both ends of the glide base offer annular groove respectively, and the annular groove with open up consolidating on the base
Determine hole to be connected, the second fixing piece be set on the annular groove, and the bottom end of second fixing piece through the annular groove and
It extends in the fixation hole, the quantity of the fixation hole is multiple and is set side by side.
Further, the transmission component includes the guide post through the outer cover, the driving column through the fixed frame, sets
The transmission gear setting the rack gear on the transmission column outer wall and being meshed in the fixed frame and with the rack gear, institute
State the press rods being connected on transmission gear for driving transmission gear to rotate.
Further, the fixed frame includes the casing being set in the rotation axis and is connected as one with described sleeve pipe
The framework of formula structure, the transmission gear are located in the framework, and the locking piece is arranged in described sleeve pipe.
Further, the outer cover includes top panel, lower panel and the side being connected between the top panel and lower panel
Plate, and the top panel, lower panel and side plate interconnection enclose " C " type structure；
The framework is arranged on the lower panel and is arranged with the top panel interval, the guide post and driving column point
Not Guan Chuan the top panel, framework and lower panel, the limit graduated scale runs through the top panel, and pressure gauge setting exists
The outer wall of the side plate.
The present invention also provides a kind of straightening methods using blade of aviation engine corrector, comprising the following steps:
Step is 1.: blade being placed on supporting mechanism for location, and makes deformable blade position towards pressure shape rectifying mechanism；
Step is 2.: according to deformable blade position, the position of sliding equipment is adjusted, so that sliding equipment band dynamic pressure shape-calibration machine
The surface at structure arrival deformable blade position；
Step is 3.: will limit graduated scale and pressure gauge numerical value zero, unscrew locking piece, adjust the position of pressure shape rectifying mechanism
It sets, so that the pressure head of pressure shape rectifying mechanism is in contact with deformable blade position, then tightens locking piece fixation pressure shape rectifying mechanism
Position；
Step is 4.: according to deformable blade size degree, adjusting the scale of limit graduated scale, then operating pressure bar drives outer cover
Entirety moves down, so that pressure head generates extruding to deformable blade position, the lower end up to limiting graduated scale is connected to solid
Numerical value until the upper surface for determining frame, and on recording manometer completes school shape.
Further, step 3. in, the method for limit graduated scale numerical value zero is to pass through to adjust limit graduated scale and fixed frame
The distance between, when make limit graduated scale be connected on fixed frame.
Further, step 4. in, school shape displacement be no more than 30mm.
Further, step 4. in, apply school shape power in a single direction to blade by pressure shape rectifying mechanism.
The invention has the following advantages: blade of aviation engine corrector provided by the present invention and its school shape side
Method, structure is reliable, easy to operate, service performance is good, and effective solution blade deviates ruler because of type face caused by machining deformation
It is very little overproof and scrap, it ensure that the qualification rate of blade profile；Reliable and stable support is provided for blade by supporting mechanism for location
Positioning, avoids the blade appearance position deviation during shape of school and influences school shape effect；Guarantee blade by pressure shape rectifying mechanism
The accuracy and school shape effect of school shape, wherein ensure that the control of each school shape displacement by limiting graduated scale, improve school shape
Effect, while shape pressure value in school is recorded by pressure gauge, improve the accuracy of school shape；By movement of the bottom plate on pedestal and solid
It is fixed, the demand to blade different location school shape is effectively met, service performance is improved.
Detailed description of the invention
Fig. 1 is schematic structural view of the invention；
Fig. 2 is side view of the present invention；
Fig. 3 is pressure shape rectifying mechanism structural schematic diagram of the present invention；
Appended drawing reference shown in Fig. 1 to Fig. 3 respectively indicates are as follows: 1- pedestal, 2- supporting mechanism for location, 3- sliding equipment, 4-
Pressure shape rectifying mechanism, 40- rotation axis, 41- fixed frame, 42- outer cover, 43- limit graduated scale, 45- pressure gauge, 46- pressure head, 47-
Locking piece, 20- blade root support base, 21- blade tip support base, 22- blade root locating piece, 23- blade tip locating piece, 24- limiting slot, 25-
Backing plate, 30- glide base, 31- bottom plate, 32- pressing plate, the first fixing piece of 33-, 34- annular groove, 35- fixation hole, 36- second are solid
Determine part, 440- guide post, 441- driving column, 442- rack gear, 443- transmission gear, 444- press rods, 410- casing, 411- frame
Body, 420- top panel, 421- lower panel, 422- side plate, 415- return springs.
Specific embodiment
The principle and features of the present invention will be described below with reference to the accompanying drawings, and the given examples are served only to explain the present invention, and
It is non-to be used to limit the scope of the invention.
As shown in Figure 1 to Figure 3, blade of aviation engine corrector including pedestal 1, is separately positioned on pedestal 1 and determines
Position supporting mechanism 2 and sliding equipment 3 and the pressure shape rectifying mechanism 4 being arranged on the sliding equipment 3.Pedestal 1 is school shape dress
The reliable and stable base supports of whole offer are provided, offer multiple bolts hole thereon for sliding equipment 3 and positioning support machine
The installation of structure 2.Supporting mechanism for location 2 is used to be supported positioning to aluminum blades, and position during the shape of school is avoided to deviate, when
After blade is had good positioning, shape rectifying mechanism is driven to be moved at deformable blade position by sliding equipment 3, and then pass through shape rectifying mechanism pair
Blade corrects shape operation.
Pressure shape rectifying mechanism 4 includes the rotation axis 40 being arranged on sliding equipment 3, be cooperatively connected consolidating in rotation axis 40
Determine frame 41, the outer cover 42 on fixed frame 41 of being cooperatively connected, through the limit graduated scale 43 of outer cover 42, for driving 42 edge of outer cover
The transmission component of the sliding of fixed frame 41, the pressure gauge 45 being arranged on 42 outer wall of outer cover and the pressure that 45 lower end of pressure gauge is set
First 46, the locking piece 47 for locking 41 position of fixed frame is provided on fixed frame 41.Rotation axis 40 is cylindrical, rotation axis 40
Bottom end be fixed on sliding equipment 3, fixed frame 41 can be rotated according to deformable blade position, convenient for alignment blade need school morpheme
It sets.Outer cover 42 is c-type structure, and outer cover 42 is including top panel 420, lower panel 421 and is connected to top panel 420 and lower panel
Side plate 422 between 421.It controls and records simultaneously by the pushing total displacement that limit graduated scale 43 adjusts outer cover 42 or pressure head 46
School shape displacement, limit graduated scale 43 are threadedly attached on the upper surface of outer cover 42 plate 420, and bottom end passes through top panel 420
And there is spacing between fixed frame 41, which is the total displacement amount that outer cover 42 pushes or pressure head 46 pushes, and the displacement
Amount is blade school shape displacement.Pressure head 46 is made of nylon material, to reduce during squeezing school shape to blade table
The damage in face.
Preferably limit graduated scale 43 uses micrometer, by being fixedly connected on 42 top panel 420 of outer cover, micrometric screw
Threaded hole on 42 top panel 420 of outer cover protrudes into 42 top panel of outer cover, 420 inside, when operation transmission component makes outer cover 42
When pushing, micrometric screw protrudes into outer cover 42 prevents outer cover 42 that from can not continuing to push when being partially exposed to fixed frame 41, thus
Play the role of limit.It is worth mentioning that adjustable limiting graduated scale 43 of the invention or screw etc., under it must adjust
It is measured when pressing displacement with graduated scale, adjusts certain distance and equally play the role of limit.Specifically, when correcting shape, it will
Blade is stably fixed on supporting mechanism for location 2, according to deformable blade position, passes through sliding of the sliding equipment 3 on pedestal 1
And then the movement of shape rectifying mechanism in the horizontal direction is driven, so that the pressure head 46 of shape rectifying mechanism is directed at blade and needs school shaped position；Again
By movement of the fixed frame 41 in rotation axis 40, so that the pressure head 46 of shape rectifying mechanism needs school tee section to contact with blade, realize
The adjustment positioning of shape rectifying mechanism in the vertical direction, by locking piece 47 by fixed frame 41 with tightly in rotation axis 40；Adjust limit
Position graduated scale 43 and pressure gauge 45 are connected to the lower end for limiting graduated scale 43 on fixed frame 41, to guarantee to limit graduated scale
43 and pressure gauge 45 be zeroed, according to the size of deformable blade, adjust limit graduated scale 43, release the displacement that need to be pushed, in turn
It drives outer cover 42 to push by transmission component, so that pressure head 46 squeezes deformable blade position, realizes to the school shape of blade, read simultaneously
Take the reading and record on pressure gauge 45.
In order to improve the operating performance that outer cover 42 is slided along fixed frame 41, in the present invention, transmission component includes passing through respectively
Wear guide post 440 and driving column 441, the rack gear 442 that is arranged on 441 outer wall of driving column and position of outer cover 42 and fixed frame 41
It is connected on the transmission gear 443 being meshed in fixed frame 41 and with rack gear 442, transmission gear 443 for driving driving cog
The press rods 444 of 443 rotation of wheel.Guide post 440 helps to mention as the guiding parts slided between outer cover 42 and fixed frame 41
The smooth performance of high outer cover 42 opposite sliding with fixed frame 41.Under the driving effect of press rods 444, band moving gear is rotated, into
And the rack gear 442 engaged with gear is driven to move, under the transmission effect of rack gear 442, realize that outer cover 42 is opposite along fixed frame 41
Sliding, so that the pressure head 46 on 45 bottom surface of pressure gauge applies pressure to blade.
In order to improve the service performance of fixed frame 41, in the present invention, fixed frame 41 includes the set being set in rotation axis 40
Pipe 410 and the framework 411 that formula structure is connected as one with casing 410, transmission gear 443 are located in framework 411, locking piece 47
It is arranged on casing 410.Casing 410 is the penetrating semi-circular structure in both ends, and framework 411 is rectangular configuration.It is twisted in locking piece 47
Under loose state, casing 410 can be moved up and down along rotation axis 40.Preferably, locking piece 47 uses positioning pin, easy to operate,
Locking is reliable.
It sets back after being pushed for the ease of outer cover 42, in the present invention, between the upper surface of framework 411 and outer cover 42 plate 420
It is provided with return springs 415.Return springs 415 use reset spring, after the completion of outer cover 42 is pushed to blade school shape, In
Under the reversed elastic force effect of reset spring, so that outer cover 42 is restored to initial position, convenient and efficient, good operation performance.
In order to improve blade installation reliable and stable performance, the present invention in, supporting mechanism for location 2 include be separately positioned on institute
State 1 both ends of pedestal and be oppositely arranged blade root support base 20 and blade tip support base 21, setting it is close in the blade root support base 20
Blade root locating piece 22 on 21 end face of blade tip support base and the blade tip locating piece 23 being arranged on the blade tip support base 21, leaf
Limiting slot 24 is offered on root locating piece 22 and blade tip locating piece 23, is arranged between blade root support base 20 and blade root locating piece 22
There is backing plate 25.The bottom end of locating piece is in rectangular configuration, increases the contact area connecting with support base, improves the stability of connection,
The limiting slot 24 of locating piece upper end is V-structure, improves the fixing ability to blade, guarantees that blade can be stable is mounted on positioning
On block.Blade root locating piece 22 and blade tip locating piece 23 are detachably connected on respectively on blade root support base 20 and blade tip support base 21.
Preferably, which is connected by screw bolts.When in use, user can carry out pair according to the blade of different stage
The replacement of correspondingly sized locating piece, to improve the reliability and stability of blade installation.
It is sliding in the present invention for the ease of the movement in drive shape rectifying mechanism horizontal direction to be directed at deformable blade position
Motivation structure 3 includes the glide base 30 being arranged on pedestal 1, the bottom plate 31 being arranged on glide base 30 and is connected to sliding
Pressing plate 32 between pedestal 30 and bottom plate 31 is provided on pressing plate 32 first fixed for fixing bottom plate 31 and glide base 30
Part 33.The both ends of glide base 30 offer annular groove 34 respectively, and annular groove 34 and 35 phase of fixation hole that is provided on pedestal 1
It is connected to, the second fixing piece 36 is set on annular groove 34, and the bottom end of the second fixing piece 36 through annular groove 34 and extends to fixation
In hole 35, fixation hole 35 is multiple and is set side by side.Preferably, the first fixing piece 33 and the second fixing piece 36 are double end spiral shell
Column.Multiple and linearly arranged side by side location holes, the fixation hole 35 on the location hole and glide base 30 are offered on pedestal 1
It matches, user can select the location hole and fixation hole 35 of appropriate location as needed, and it is solid to penetrate the cooperation of the first fixing piece 33
It is fixed, so that glide base 30 can be slided and be fixed relatively along pedestal 1.Bottom plate 31 is under the action of pressing plate 32 along glide base 30
Annular groove 34 slides, and after position determines, passes through the position of the fixed bottom plate 31 of the second fixing piece 36.The sliding equipment 3 is realized
Sliding of the glide base 30 on pedestal 1, and realize movement of the bottom plate 31 on glide base 30, service performance is good, behaviour
Make convenient and reliable.
For the weight of alleviator itself, in the present invention, the engraved structure in symmetric form is offered on pedestal 1.It should
Engraved structure be in symmetrical rectangular configuration, and be located at pedestal 1 medium position, effectively alleviate device self weight, convenient for move
Dynamic transport.
The present invention also provides a kind of straightening methods using blade of aviation engine corrector, comprising the following steps:
Step is 1.: blade being placed on supporting mechanism for location 2, and makes deformable blade position towards pressure shape rectifying mechanism 4；
Different blade root locating pieces 22 and blade tip locating piece 23 are chosen according to the blade of different stage, the both ends of blade are individually positioned in leaf
In the limiting slot 24 of root locating piece 22 and in the limiting slot 24 of blade tip locating piece 23, to realize that the installation of blade is fixed.
Step is 2.: according to deformable blade position, the position of sliding equipment 3 is adjusted, so that sliding equipment 3 is with dynamic pressure school shape
The surface at the arrival of mechanism 4 deformable blade position；By sliding of the glide base 30 on pedestal 1 and bottom plate 31 in sliding base
Sliding on seat 30 drives the pressure head 46 of shape rectifying mechanism to be directed at deformable blade position, fixed by the first fixing piece 33 and second
Part 36 carries out reliable location.
Step is 3.: will limit graduated scale 43 and 45 numerical value of pressure gauge zero, unscrew locking piece 47, adjust pressure shape rectifying mechanism
47 fixation pressure of locking piece so that the pressure head 46 of pressure shape rectifying mechanism 4 is in contact with deformable blade position, then is tightened in 4 position
The position of shape rectifying mechanism 4；The distance between graduated scale 43 and fixed frame 41 are limited by adjusting, when limit graduated scale 43 is connected to
When on fixed frame 41, limit graduated scale 43 is in clean state.
Step is 4.: according to deformable blade size degree, the school shape displacement provided with reference to the following table 1, table 2 adjusts limit scale
The displacement that the scale of ruler 43, i.e. pressure head 46 push, then operating pressure bar 444 drive outer cover 42 is whole to move down, to make
It obtains pressure head 46 and extruding is generated to deformable blade position, until the upper surface that the lower end of limit graduated scale 43 is connected to fixed frame 41 is
Only, and the numerical value on recording manometer 45；
Step is 5.: after the completion of the shape of school, pressure shape rectifying mechanism 4 sets back.Effect of the shape rectifying mechanism in return springs 415
Lower return is in situ.
Blade school shape displacement is monitored during the shape of school, school shape displacement is no more than 30mm, school shape power duration
10min, following table list referential data when different distortion amount.
Table 1
Table 2
In school during shape, Aluminum piece school shape is divided into process school shape and finished product school shape.Process school shape nulling part is processed
It deforms to need to carry out molding surface size correction to blade in journey, finished product state becomes after finished product school shape refers to part spray painting
Shape causes not to be able to satisfy matching requirements and carry out molding surface size correction.The limitation of school shape number, school shape displacement are limited in the shape of school,
The limitation of school shape force direction and the protection of school shape.Wherein:
Limit school shape number: part school shape number does not allow more than 2 times, during practical school shape, a part quilt
Correction calculates primary school shape to code requirement is met.If only carried out primary school shape in the process, then becoming in the finished product stage
Shape allows to carry out primary school shape again.
School shape displacement limitation: in process school shape or finished product school shape, it is necessary to which strict control school shape displacement, displacement is not
It obtains more than 30mm.
The limitation of school shape force direction: in part school during shape, leaf basin (back) is applied according to blade practical distortion direction
School shape power is deformed as blade is deviated towards basin direction, and school shape power should be applied on leaf basin, if blade occurs backwards after school shape is qualified again
Offset deformation, then not allowing again to correct shape the blade.Forbid carrying out blade basin back alternately application school shape power, i.e., does not permit
Perhaps reversed school shape.
School shape protection: when being corrected shape to blade, it should be noted that prevent blade touches scuffing, especially for finished product school shape
When, it should be noted that protective paint layer avoids lacquer painting damage or paint layer from falling off.
The foregoing is merely presently preferred embodiments of the present invention, is not intended to limit the invention, it is all in spirit of the invention and
Within principle, any modification, equivalent replacement, improvement and so on be should all be included in the protection scope of the present invention.
Claims (10)
1. blade of aviation engine corrector, which is characterized in that including pedestal (1), the positioning being separately positioned on pedestal (1)
Supporting mechanism (2) and sliding equipment (3) and the pressure shape rectifying mechanism (4) being arranged on the sliding equipment (3)；
The pressure shape rectifying mechanism (4) includes the rotation axis (40) being arranged on the sliding equipment (3), is cooperatively connected described
Fixed frame (41), the outer cover (42) being cooperatively connected on the fixed frame (41), mating connection in rotation axis (40) is described
Limit graduated scale (43) on outer cover (42), the transmission group for driving the outer cover (42) to slide along the fixed frame (41)
The pressure head of part, the pressure gauge (45) being arranged on the outer cover (42) outer wall and setting in the pressure gauge (45) lower end
(46), the locking piece (47) for locking fixed frame (41) position, the transmission component position are provided on the fixed frame (41)
In the fixed frame (41).
2. blade of aviation engine corrector according to claim 1, which is characterized in that the supporting mechanism for location
(2) include be separately positioned on the pedestal (1) both ends and be oppositely arranged blade root support base (20) and blade tip support base (21), set
It sets the blade root locating piece (22) in the blade root support base (20) on blade tip support base (21) end face and is arranged described
Blade tip locating piece (23) on blade tip support base (21) offers on the blade root locating piece (22) and blade tip locating piece (23)
Limiting slot (24) is provided with backing plate (25) between the blade root support base (20) and blade root locating piece (22).
3. blade of aviation engine corrector according to claim 1, which is characterized in that sliding equipment (3) packet
It includes the glide base (30) being arranged on the pedestal (1), the bottom plate (31) being arranged on the glide base (30) and connects
The pressing plate (32) between the glide base (30) and the bottom plate (31) is connect, is provided on the pressing plate (32) for fixing
The first fixing piece (33) of the bottom plate (31) and the glide base (30)；
The both ends of the glide base (30) offer annular groove (34) respectively, and the annular groove (34) and are provided with the bottom
Fixation hole (35) on seat (1) is connected, and is arranged the second fixing piece (36) on the annular groove (34), and second fixing piece
(36) bottom end is through the annular groove (34) and extends in the fixation hole (35), and the quantity of the fixation hole (35) is more
It is a and be set side by side.
4. blade of aviation engine corrector according to claim 1, which is characterized in that the transmission component includes passing through
The guide post (440) for wearing the outer cover (42), is arranged in the driving column driving column (441) for running through the fixed frame (41)
(441) rack gear on outer wall (442) and driving cog that is interior positioned at the fixed frame (41) and being meshed with the rack gear (442)
It takes turns (443), the press rods (444) for driving transmission gear (443) to rotate is connected on the transmission gear (443).
5. blade of aviation engine corrector according to claim 4, which is characterized in that the fixed frame (41) includes
The casing (410) that is set on the rotation axis (40) and the framework that formula structure is connected as one with described sleeve pipe (410)
(411), the transmission gear (443) is located in the framework (411), and the locking piece (47) is arranged in described sleeve pipe (410)
On.
6. blade of aviation engine corrector according to claim 5, which is characterized in that the outer cover (42) includes upper
Panel (420), lower panel (421) and the side plate (422) being connected between the top panel (420) and lower panel (421), and
The top panel (420), lower panel (421) and side plate (422) interconnection enclose " C " type structure；
The framework (411) is arranged on the lower panel (421) and is spaced with the top panel (420) and is arranged, the guiding
Column (440) and driving column (441) extend through the top panel (420), framework (411) and lower panel (421), the limit
Graduated scale (43) runs through the top panel (420), outer wall of pressure gauge (45) setting in the side plate (422).
7. a kind of straightening method using blade of aviation engine corrector as claimed in any one of claims 1 to 6, feature
It is, comprising the following steps:
Step is 1.: blade being placed on supporting mechanism for location (2), and deformable blade position is towards pressure shape rectifying mechanism (4)；
Step is 2.: according to deformable blade position, the position of sliding equipment (3) is adjusted, so that sliding equipment (3) band dynamic pressure school shape
The surface at mechanism (4) arrival deformable blade position；
Step is 3.: limit graduated scale (43) and pressure gauge (45) numerical value being zeroed, unscrewed locking piece (47), adjusting pressure shape-calibration machine
Locking piece so that the pressure head (46) of pressure shape rectifying mechanism (4) is in contact with deformable blade position, then is tightened in the position of structure (4)
(47) position of fixation pressure shape rectifying mechanism (4)；
Step is 4.: according to deformable blade size degree, adjusting the scale of limit graduated scale (43), then operating pressure bar (444) band
Dynamic outer cover (42) integrally move down, so that pressure head (46) generates extruding to deformable blade position, until limit graduated scale
(43) until lower end is connected to the upper surface of fixed frame (41), and the numerical value on recording manometer (45), complete school shape.
8. the straightening method according to claim 7 using blade of aviation engine corrector, which is characterized in that step
3. in limit graduated scale (43) numerical value zero method be by limit the distance between graduated scale (43) and fixed frame (41), when
It is connected to limit graduated scale (43) on fixed frame (41).
9. the straightening method according to claim 8 using blade of aviation engine corrector, which is characterized in that step
4. in, school shape displacement is no more than 30mm.
10. the straightening method according to claim 9 using blade of aviation engine corrector, which is characterized in that step
Suddenly 4. in, apply school shape power in a single direction to blade by pressure shape rectifying mechanism.
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| CN201910697144.XA CN110421024A (en) | 2019-07-30 | 2019-07-30 | Blade of aviation engine corrector and its straightening method |
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| CN110421023A (en) * | 2019-07-30 | 2019-11-08 | 中国航发航空科技股份有限公司 | Blade of aviation engine corrector |
| CN112474878A (en) * | 2020-09-22 | 2021-03-12 | 成都飞机工业（集团）有限责任公司 | Constant force pressing device for part deformation correction and part deformation correction method |
| CN112517675A (en) * | 2020-11-16 | 2021-03-19 | 中国航发沈阳黎明航空发动机有限责任公司 | Be applied to device that rolling blade profile was rectified |
| CN112829147A (en) * | 2020-12-25 | 2021-05-25 | 季华实验室 | Aeroengine blade mould school type adjustment mechanism |
| CN113618657A (en) * | 2021-08-20 | 2021-11-09 | 中国航发航空科技股份有限公司 | Aeroengine blade clamping device |
| DE102023113726A1 (en) | 2022-05-27 | 2023-11-30 | Wuhan University Of Technology | Process for the controlled electromagnetic impact composite forming of blades made of titanium alloy |
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