CN105538033B - The processing method of aero-engine fiber reinforcement type high-temperature composite material - Google Patents
The processing method of aero-engine fiber reinforcement type high-temperature composite material Download PDFInfo
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- CN105538033B CN105538033B CN201610084216.XA CN201610084216A CN105538033B CN 105538033 B CN105538033 B CN 105538033B CN 201610084216 A CN201610084216 A CN 201610084216A CN 105538033 B CN105538033 B CN 105538033B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q11/00—Accessories fitted to machine tools for keeping tools or parts of the machine in good working condition or for cooling work; Safety devices specially combined with or arranged in, or specially adapted for use in connection with, machine tools
- B23Q11/10—Arrangements for cooling or lubricating tools or work
- B23Q11/1038—Arrangements for cooling or lubricating tools or work using cutting liquids with special characteristics, e.g. flow rate, quality
- B23Q11/1061—Arrangements for cooling or lubricating tools or work using cutting liquids with special characteristics, e.g. flow rate, quality using cutting liquids with specially selected composition or state of aggregation
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B35/00—Methods for boring or drilling, or for working essentially requiring the use of boring or drilling machines; Use of auxiliary equipment in connection with such methods
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B51/00—Tools for drilling machines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B2215/00—Details of workpieces
- B23B2215/04—Aircraft components
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B2215/00—Details of workpieces
- B23B2215/24—Components of internal combustion engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B2226/00—Materials of tools or workpieces not comprising a metal
- B23B2226/27—Composites
- B23B2226/275—Carbon fibre reinforced carbon composites
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Drilling And Boring (AREA)
Abstract
The present invention provides a kind of processing method of aero-engine fiber reinforcement type high-temperature composite material, for often occurring tearing during processing, cleaving, being layered, fluffing and the defects of size is unstable, it is proposed that work in-process uses a kind of coolant, for water, glycerine, animal oil mixed liquor, volume ratio be 8 10:4‑5:45, existing lubricity and can well enough absorbs dust caused by processing, while also green.A kind of cutter is also used, shank diameter is thicker than common, and cutter carries out machining, the shock resistance for the lathe tool that can be effectively improved in cutting along with the machine direction of fiber reinforcement type high-temperature composite material plane at 45 °.In addition, when having the workpiece of larger curvature to drill to surface, the accessory being bonded completely with curved surface is made, drilling tool passes through from fitting bore, can so prevent workpiece in process because of vibrations, dimensional discrepancy caused by a small amount of displacement.
Description
Technical field
The present invention relates to the process technology of composite, especially with regard to a kind of aero-engine fiber reinforcement type high temperature
The processing method of composite, include two aspect process technologies of curved profile cutting and drilling.
Background technology
Aero-engine with fiber reinforcement type high-temperature composite material be with carbon, ceramics for matrix, add certain carbon fiber and
Ceramic fibre is the composite of reinforcement, has high specific strength, high ratio modulus, high temperature resistant, corrosion-resistant, endurance, creep resistant,
A series of excellent properties such as conductive, heat transfer and the coefficient of expansion are small, structural material carrying heavy burden is can not only be used for, but also as function material
Material plays a role.Aero-engine also has extensive use with fiber reinforcement type high-temperature composite material in aerospace field, but
It is due to its hardness height, intensity is big, anisotropy, poor thermal conductivity, and can not carry out liquid cooling, belongs to typical difficult processing
Material.Matrix and reinforcing fiber are the staples in working angles, while are cut also by the factor shadow such as fiber orientation distribution
To ring, the anisotropy of material causes composite product the defects of tear, splitting, layering, fluffing often occur in processing, these
The appearance of defect causes composite materials property reduction and surface roughness to be deteriorated, and the large-scale component of many materials needs
Carry out high-precision machining, and common turning has that machining accuracy is low, efficiency is low, tool wear is serious, cost is high etc. and lacked
Point, it is difficult to meet process requirements.
Therefore, a kind of processing method of aero-engine fiber reinforcement type high-temperature composite material how is designed, is improved
Dimensional accuracy, material property damage is reduced, is to need to solve the problems, such as.
The content of the invention
For the demand, the processing the invention provides a kind of aero-engine with fiber reinforcement type high-temperature composite material
Method, refer in particular to work in-process due to use special coolant and cutter, reduce abrasion of the cutter to workpiece in process,
The surface smoothness of workpiece is improved, dimensional accuracy, reduces the performance loss in process.
The purpose of the present invention is mainly achieved through the following technical solutions：A kind of aero-engine fiber reinforcement type height
The processing method of warm composite, it is characterised in that work in-process uses a kind of coolant, and the coolant is water, glycerine, moved
The mixed liquor of thing oil, volume ratio 8-10:4-5:4-5.
Further, the animal oil is lard.
Further, the water, glycerine, the volume ratio of animal oil are 2:1:1.
Further, the compound method of the coolant is：By volume ratio it is at room temperature first 3.2-5:1 water and sweet
Oil mixing, turns into mixed liquor one, and by volume ratio be 0.8-1.25:2 glycerine and animal oil mixing, turns into mixed liquor two；
Then on the basis of the glycerine of same volume, the mixed liquor one and mixed liquor two is well mixed and obtain the coolant.
Further, also including the use of a kind of cutter in the processing method, the cutter includes handle of a knife and blade, described
Handle of a knife uses hard alloy steel, and the shank diameter is 1.5-5 times of common shank diameter；The blade is using melting handle of a knife
Mode submerges the handle of a knife, and what the blade submerged shank portion is shaped as inverted trapezoidal.
Yet further, the cutter is in cutting, along the machine direction with the fiber reinforcement type high-temperature composite material
Plane at 45 ° carries out machining.
Yet further, the machined parameters of the cutter are：Amount of feeding f=(0.01-0.04) mm/r；Cutting depth ap=
(0.05-0.2)mm；Amplitude A=15-30 μm.Preferably, amount of feeding f=0.02mm/r；Cutting depth ap=0.1mm；Amplitude A
=25 μm.
Further, methods described also includes entering the curvature surface of the workpiece of the fiber reinforcement type high-temperature composite material
The method of row drilling：
The auxiliary accessories being bonded completely with the curvature surface of workpiece are made first, and the auxiliary accessories are drilled in advance,
As cutter access aperture；
Then the auxiliary accessories are bonded fixation with the workpiece, and by the position to be drilled on the auxiliary accessories and institute
The bore position stated on workpiece is corresponding；
Finally cutter is put on workpiece from the drill hole of the auxiliary accessories to be drilled.
Yet further, the bore dia on the auxiliary accessories is equal to or slightly greater than the hole to be bored on the workpiece.
Had the beneficial effect that obtained by the present invention：1st, the present invention is due to using special coolant, existing profit well
Slip and can enough effectively absorbs dust caused by processing, while also green.2nd, a kind of new structure cutter is provided, should
Tool strength is high, is suitable for processing as this kind of hard member of fiber reinforcement type high-temperature composite material.3rd, used in processing method
Cut, can effectively be cut along 45 degree of directions of fiber, and the institutional framework of fiber will not be destroyed, effectively reduced fiber and increase
The defects of tear that often occurs during strong high-temperature composite material processing, splitting, layering, unstable fluffing and size.4th, this hair
The bright a kind of method for additionally providing accurate finished surface and having the part drilling of larger curvature.
So the present invention is suitable for the structure processed under the fiber reinforcement type high-temperature composite material, such as aircraft engine
Structural member (such as interior centrum), the Moving plate of aeroplane brake discses, quiet disk, high ferro brake disc, advanced racing car brake disc and extraordinary use
Crucible etc..
Other features and advantages of the present invention will illustrate in the following description, also, partial become from specification
Obtain it is clear that or being understood by implementing the present invention.The purpose of the present invention and other advantages can be by the explanations write
Specifically noted structure is realized and obtained in book, claims and accompanying drawing.
Brief description of the drawings
Accompanying drawing is only used for showing the purpose of specific embodiment, and is not considered as limitation of the present invention, in whole accompanying drawing
In, identical reference symbol represents identical part.
Fig. 1 is the structure chart for the cutter that the present invention uses；
Fig. 2 is the implementation illustration in the drilling of cylindrical workpiece Surface Machining；
Fig. 3 is to coordinate auxiliary accessories figure boring on cylinder；
Fig. 4 is the installation diagram of cylindrical element and auxiliary accessories.
Embodiment
In order that those skilled in the art will better understand the technical solution of the present invention, and make the present invention above-mentioned mesh
, feature and advantage can be more obvious understandable, with reference to example, the present invention will be further described in detail, but this hair
It is bright to be not intended to be limited thereto, i.e. what technological thought of the invention was carried out deform, other constructions or forms, and is contained in this hair certainly
In bright.
A kind of processing method of aero-engine fiber reinforcement type high-temperature composite material provided by the invention, it is on the one hand special
Refer to and employ a kind of special self-control coolant in processing and carry out cooling and lubricating, reduce in process cutter to workpiece
Abrasion.
Due to fiber reinforcement type high-temperature composite material, itself possess that density is low, conductive, high-strength and Gao Mo characteristic, simultaneously
Minimum thin dirt is had in carbon fiber reinforcement and carbon base body process, and is difficult to mix with common coolant, so plus
It is readily adhered on sample in work vibration processes and floats in atmosphere, influences the precision in process and make the electricity in equipment
Subcomponent is damaged.Using new coolant, because it has good lubricity so effectiveness in vibration suppression is more preferable, to material in process
The damage of material and the edge of a knife is all more preferable, while a large amount of dust caused by composite processing, new coolant also have more excellent
Absorbent properties.
So the present invention uses a kind of new coolant, be formulated for water, glycerine, animal oil mixed liquor, volume ratio is
8-10:4-5:4-5, the preferred lard of animal oil, volume ratio preferably 2:1:1.
Glycerine and animal oil have outstanding lubricity and certain adsorption capacity, and the specific heat capacity of water is big, are coolants
Neccessary composition, abrasion of the cutter to workpiece when wherein animal oil more can effectively reduce processing, glycerine can be miscible with water,
It can be dissolved each other with animal oil, be important intermediate, meanwhile, glycerine can also improve the surface-active of mixed liquor, improve liquid pair and add
The absorbability of dust caused by man-hour, reduce the pollution to environment, it is more green.Ensureing that three can be effectively mutual
In the case of molten, the ratio is more suitable.
The process for preparation of the coolant is：By volume ratio it is first at room temperature 3.2-5:1 water and glycerine, and by volume
Than for 0.8-1.25:2 glycerine and animal oil is well mixed respectively, is referred to as mixed liquor one and mixed liquor two；Then with phase
On the basis of the glycerine of same volume, the mixed liquor one and mixed liquor two are well mixed and obtain the coolant.
After coolant prepares, the storage of room temperature shady place is placed on.
A kind of aero-engine processing method of fiber reinforcement type high-temperature composite material provided by the invention, also refers in particular to one
The method that kind is cut material.The present invention is directed to carbon, ceramics as matrix, adds certain carbon fiber and ceramic fibre to increase
The three-dimensional structure high-temperature composite material of strong body, in cutting, it is processed using the plane at 45 ° with machine direction, so may be used
To obtain best processing effect.
Further, a kind of homemade cutter is used in cutting.As shown in figure 1, the characteristics of cutter, is：First, this
Kind of tool selection hard alloy steel is as handle of a knife material, the overstriking of handle of a knife 1, and diameter is about 1.5-5 times of common shank diameter, overstriking
Handle of a knife 1 can effectively improve the vibration resistance of cutter, so as to reducing the damage to workpiece.Secondly, using the side of melting handle of a knife
Blade 2 is submerged handle of a knife 1 by formula, and concrete technology is that blade 2 then is pressed into knife first by the material molten of handle of a knife 1 using appropriate mould
In handle 1, then it is cooled and shaped.Again, the partial shape that blade 2 submerges handle of a knife 1 is inverted trapezoidal, as shown in figure 1, inverted trapezoidal embedding energy
Enough make the 2 stronger combination of handle of a knife 1 and blade.Again, hard alloy or synthetic diamond material, artificial gold can be selected in blade 2
Hard rock can more strengthen cutting hardness.
Further say, the processing design parameter for setting the cutter is：Amount of feeding f=(0.01-0.04) mm/r, preferably
0.02mm/r；Cutting depth ap=(0.05-0.2) mm, preferably 0.1mm；Amplitude A=15-30 μm, preferably 25 μm.These
Parameter is to sum up the data come by specific processing, and the too low then efficiency of rotating speed is low, and too meeting attacking material in itself, is processed simultaneously soon
Planar defect becomes more；Rotating speed is faster, and cutting is deeper, and amplitude can be bigger, and amplitude is too big, then machined surface meeting out-of-flatness, is damaged to blade
Become big.
The processing method of aero-engine provided by the invention fiber reinforcement type high-temperature composite material, it is a kind of right also to refer in particular to
The method that such material is drilled.When the present invention is drilled for the workpiece that there is larger curvature on surface, as shown in Figure 2
Cylinder, when being drilled in cylindrical workpiece 3, the processing method taken is：Making is bonded auxiliary completely with drum surface first
Help accessory 4, as shown in figure 3, and auxiliary accessories 4 are drilled in advance, as cutter access aperture；Then again by auxiliary accessories 4 and work
The fitting of part 3 is fixed, and the position to be drilled on auxiliary accessories 4 is corresponding with the bore position on workpiece 3；Finally from auxiliary accessories
4 drill hole puts in cutter and drilled on workpiece 3.Such processing method can prevent workpiece 3 from splitting in process
Split and because of vibration, dimensional discrepancy caused by a small amount of displacement.Further, auxiliary accessories 4 are metalwork, can so prevent from boring
Accessory is caused to cleave because drilling force is excessive during hole, or deformation.
Further, the hole on auxiliary accessories 4 is equal to or slightly greater than the hole to be bored on workpiece 3 so that cutter can be put in i.e.
Can.
For the fixed form of auxiliary accessories 4 and workpiece 3, can using it is any it is feasible by the way of, for example consolidated using fixture
It is fixed, either connected or using measures such as rope bindings using pin.
In order to verify technology of the present invention in above several respects, the invention provides following examples.
Embodiment one：The processing of aeroplane brake discses
Before the processing of aeroplane brake discses, 1, carry out special cutter in advance：From hard alloy steel as handle of a knife material,
Handle of a knife overstriking, thick 1.5 times of a diameter of 9mm, about same specification universal cutter handle of a knife；Handle of a knife is melted, blade is submerged into handle of a knife,
The partial shape that blade submerges handle of a knife is inverted trapezoidal, and blade selects synthetic diamond material.2nd, according to volume ratio 2:1:1 by water,
It is stand-by that glycerine and lard are mixed into coolant.
In process, cutter, workpiece are fixed, sets working process parameter and be processed, setting is thick, essence
Two steps are processed, are all to use special cutter, are processed along the plane at 45 ° with machine direction, the design parameter of processing is
Amount of feeding f=0.02mm/r, cutting depth ap=0.1mm, amplitude A=25 μm.The machining accuracy for measuring workpiece is：Error is less than
30μm。
Embodiment two：The processing of diaphragm seal
As embodiment one, special cutter and coolant are carried out in advance, fix workpiece with fixture in processing；Processing
Shi Xianyong hard alloy vehicle body carries out roughing, is processed along the direction at 45 ° with fiber orientation, the design parameter of processing is
Amount of feeding f=0.02mm/r, cutting depth ap=0.1mm, amplitude A=25 μm；After roughing, then use diamond glomerocryst instead
Vehicle body is finished, and is equally processed using the face at 45 ° with fiber orientation, working process parameter is still amount of feeding f
=0.02mm/r, cutting depth ap=0.1mm, amplitude A=25 μm.
Embodiment three：Cylinder type workpiece drills
The preparation of cutter and coolant with embodiment one as.This part is to be drilled side on cylinder, then needs to add first
Work goes out the semicircle auxiliary accessories 4 for a metal material being engaged with cylindrical workpiece 3 shown in Fig. 2, then in auxiliary accessories 4
On process the circular hole of intended size, this circular hole is equal to or slightly greater than the hole to be bored on workpiece 3 so that cutter can be put in i.e.
Can.Remarks：When processing metal fittings and drilling without using special cutter.Then, by the semicircular auxiliary of metal material
Accessory 4 is fixed on cylinder and is bonded with fixture so that the drilling on auxiliary accessories 4 coincides with the bore position on workpiece 3.
Finally, drilled using electroplated diamond bit, the special coolant of the present invention is poured into drilling, the specific ginseng of processing is set
Number is amount of feeding f=0.01mm/r, cutting depth ap=0.2mm, amplitude A=20 μm.
Hole simply is processed in the side of prebored hole cylinder shown in Fig. 3, so only needing the semicircular can of auxiliary accessories 4
.Certainly processing full-circle spray pattern auxiliary accessories are also possible, and simply such consumptive material can increase, and since it is desired that be bonded in the extreme,
The hoop of full circle may be not easy from a headgear up, to take off also aspect, frictional force is not very strong.One side fitting of semicircle, it is another
Side is using the tightening way for closing hoop formula, no matter installing or removing and be all more convenient.
If it is desired to all processing drilling (such as radial direction through hole) in the both sides of cylinder, then two semicircular auxiliary can be used
Accessory 4, then two semicircular accessories are fastened on workpiece, reprocess the hole of both sides.
The present invention is only to provide a kind of processing method of fiber reinforcement type high-temperature composite material from specific several respects, one
There is provided a kind of coolant specifically for this kind of material because such material has a high-strength and high-modulus, and reinforcement fiber with
The features such as substrate performance gap is big, and processing dust is more, thus using this coolant can existing good lubricity and can reach
Dust caused by processing is effectively absorbed, at the same it is also green.Second, independent design has made cutter, with universal cutter phase
Than the handle of a knife is thicker, can so improve the freedom from vibration of cutter, and other sizes improve according to sample shape and size design
Machining accuracy.In the material selection of blade, we select two kinds of materials, and one kind is hard alloy, are mainly used to carry out slightly to add
Work, another kind are diamond glomerocryst lathe tools, are mainly used in finishing sample, reduce surface roughness.Third, this
Invention is directed to the fiber-reinforced composites woven using three-dimensional structure, using the direction with machine direction angle at 45 °
Face be processed, can so obtain best processing effect.Fourth, the present invention is directed to the drilling of cylinder type workpiece, formulate
Special auxiliary accessories, it can ensure that processing object position is stable in boring procedure, so as to ensureing that aperture size is accurate.
The foregoing is only a preferred embodiment of the present invention, but protection scope of the present invention be not limited thereto,
Any one skilled in the art the invention discloses technical scope in, the change or replacement that can readily occur in,
It should all be included within the scope of the present invention.
Claims (6)
1. a kind of aero-engine processing method of fiber reinforcement type high-temperature composite material, it is characterised in that work in-process makes
With a kind of cutter and a kind of coolant,
The cutter includes handle of a knife and blade, and the handle of a knife uses hard alloy steel；The blade is hard alloy or artificial gold
Hard rock；The blade submerges the handle of a knife by the way of handle of a knife is melted, and what the blade submerged shank portion is shaped as down ladder
Shape；
The cutter is carried out in cutting along with the machine direction of fiber reinforcement type high-temperature composite material plane at 45 °
Machining；
The machined parameters of the cutter are：Amount of feeding f=(0.01-0.04) mm/r；Cutting depth ap=(0.05-0.2) mm；Shake
A=15-30 μm of width；
The coolant is water, glycerine, the mixed liquor of animal oil, volume ratio 8-10:4-5:4-5；
The compound method of the coolant is：
By volume ratio it is at room temperature first 3.2-5:1 water and glycerine mixing, turns into mixed liquor one, and be by volume ratio
0.8-1.25:2 glycerine and animal oil mixing, turns into mixed liquor two；
Then on the basis of the glycerine of same volume, the mixed liquor one and mixed liquor two is well mixed and obtain the cooling
Liquid.
2. the aero-engine according to claim 1 processing method of fiber reinforcement type high-temperature composite material, its feature
It is, the animal oil is lard.
3. the aero-engine according to claim 1 processing method of fiber reinforcement type high-temperature composite material, its feature
It is, the water, glycerine, the volume ratio of animal oil are 2:1:1.
4. the aero-engine according to claim 1 processing method of fiber reinforcement type high-temperature composite material, its feature
It is, the machined parameters of the cutter are：Amount of feeding f=0.02mm/r；Cutting depth ap=0.1mm；Amplitude A=25 μm.
5. the processing method of the aero-engine fiber reinforcement type high-temperature composite material according to right wants 1, its feature exist
In, in addition to the method that is drilled of curvature surface to material for the workpiece of the fiber reinforcement type high-temperature composite material：
The auxiliary accessories being bonded completely with the curvature surface of workpiece are made first, and the auxiliary accessories are drilled in advance, as
Cutter access aperture；
Then the auxiliary accessories are bonded fixation with the workpiece, and by the position to be drilled on the auxiliary accessories and the work
Bore position on part is corresponding；
Finally cutter is put on workpiece from the drill hole of the auxiliary accessories to be drilled.
6. the processing method of the aero-engine fiber reinforcement type high-temperature composite material according to right wants 5, its feature exist
In the bore dia on the auxiliary accessories is equal to or slightly greater than the hole to be bored on the workpiece.
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