阅读说明：本技术 一种加工飞机发动机钛合金零件的高寿命涂层铣刀 (Long-service-life coating milling cutter for machining titanium alloy parts of aircraft engines ) 是由 咸志鹏 于 2021-07-15 设计创作，主要内容包括：本发明公开了一种加工飞机发动机钛合金零件的高寿命涂层铣刀,其包括切削部和柄部,切削部设有4个周刃且分别为一对短刃和一对长刃,短刃和长刃沿圆周方向交替设置,长刃与其面向切削旋转方向一侧的短刃所形成第一夹角,长刃与其背向切削旋转方向一侧的另一短刃形成第二夹角,第一夹角与第二夹角不相等,且第一夹角与第二夹角之和等于180度；分别与两个长刃相连的两个端刃在切削部的前端中心处相连,分别与两个短刃相连的两个端刃在切削部的前端相互间隔1/3以上的切削部外径。采用本发明,具有抗震性能好、使用寿命高、排屑方便、加工效果好、产品良品率高的优点。(The invention discloses a high-service-life coating milling cutter for processing titanium alloy parts of aircraft engines, which comprises a cutting part and a handle part, wherein the cutting part is provided with 4 peripheral edges which are respectively a pair of short edges and a pair of long edges, the short edges and the long edges are alternately arranged along the circumferential direction, the long edges and the short edges on one side facing to the cutting rotation direction form a first included angle, the long edges and the other short edges on one side facing away from the cutting rotation direction form a second included angle, the first included angle and the second included angle are not equal, and the sum of the first included angle and the second included angle is equal to 180 degrees; the two end blades connected with the two long blades are connected at the center of the front end of the cutting part, and the two end blades connected with the two short blades are mutually separated at the front end of the cutting part by more than 1/3 of the outer diameter of the cutting part. The invention has the advantages of good anti-seismic performance, long service life, convenient chip removal, good processing effect and high product yield.)

1. The utility model provides a processing aircraft engine titanium alloy part's high life coating milling cutter, its characterized in that, including coating cutting part and the stalk portion that has the high hard coating of nanometer level, the cutting part is right-handed cutting structure, the cutting part is equipped with 4 all sword chip grooves that set up to stalk portion spiral extension from its front end, all sword chip grooves are towards the face of cutting direction of rotation for the rake face, all sword chip grooves are the face of cutting direction of rotation dorsad for the back knife face, the rake face with the crossing all sword that forms of back knife face, all the sword is in the front end of cutting part corresponds and is connected with the end blade, adjacent two be formed with between the end blade with all sword chip grooves link to each other end sword chip groove, 4 all the sword is a pair of short edge and a pair of long edge respectively, the short edge with the long edge sets up along the circumferencial direction in turn, the long edge forms first contained angle rather than the short edge towards cutting direction of rotation one side, the long blade and the other short blade at one side of the long blade, which is opposite to the cutting rotation direction, form a second included angle, the first included angle is not equal to the second included angle, and the sum of the first included angle and the second included angle is equal to 180 degrees; the two end blades connected to the two long blades are connected to each other at the center of the front end of the cutting part, and the two end blades connected to the two short blades are spaced from each other at the front end of the cutting part by an outer diameter of the cutting part of 1/3 or more.

2. The milling cutter for machining titanium alloy parts for aircraft engines as claimed in claim 1, wherein the nanoscale high-hardness coating is AlTiN-Si.

3. The milling cutter for machining titanium alloy parts for aircraft engines as claimed in claim 1, wherein the peripheral edge has a helix angle of 38 to 42 degrees.

4. The milling cutter for milling a high-life coating on a titanium alloy part for an aircraft engine as claimed in claim 1, wherein the center of the edge height of the peripheral edge is 0.1 ± 0.02 mm.

5. The high-life coating milling cutter for machining titanium alloy parts for aircraft engines as recited in claim 1, wherein said peripheral edge is provided with a peripheral edge rake angle and a peripheral edge relief angle, said peripheral edge rake angle being 6 degrees; the peripheral edge back angle is provided with a first peripheral edge back angle and a second peripheral edge back angle in sequence from the cutting edge to the rear cutter face, the first peripheral edge back angle is 10-12 degrees, and the second peripheral edge back angle is 24-26 degrees; the width of the flank corresponding to the first peripheral edge relief angle is 0.6 mm-0.7 mm, and the width of the flank corresponding to the second peripheral edge relief angle is 1.9 mm-2.1 mm.

6. The high-life coating milling cutter for machining titanium alloy parts of aircraft engines as claimed in claim 1, wherein the cutting portion is provided with a first core thickness section at a front section and a second core thickness section at a rear section, the core thickness of the first core thickness section being smaller than the core thickness of the second core thickness section.

7. The milling cutter for machining titanium alloy parts for aircraft engines as claimed in claim 1, wherein the junction of the end edge and the peripheral edge is provided with a transition arc.

8. The milling cutter for milling a titanium alloy component of an aircraft engine as claimed in claim 1, wherein the end blade is provided with a reinforcing edge on a rake face thereof for protecting the end blade.

9. The milling cutter for milling a long-life coating on a titanium alloy part for an aircraft engine as claimed in claim 1, wherein the end edge is provided with an end edge rake angle and an end edge relief angle, and the end edge rake angle is 4-6 degrees; the end sword relief angle includes first end sword relief angle and the second end sword relief angle that arranges in proper order to the back knife face from its blade, first end sword relief angle is 8 degrees ~ 10 degrees, the second end sword relief angle is 20 degrees ~ 24 degrees, the width of the back knife face that first end sword relief angle corresponds is 1.2mm ~ 1.4 mm.

10. The milling cutter for milling long-life coatings on titanium alloy parts for aircraft engines as claimed in claim 6, wherein said end edge is provided with an inner inclination angle of 1.8-2.2 degrees.

Technical Field

The invention belongs to the technical field of machining tools, and particularly relates to a long-service-life coating milling cutter for machining titanium alloy parts of aircraft engines.

Background

Since the 20 th century, the aerospace engineering has been increasingly scaled up, the engineering technology has become more complex, and in the process of accelerating the rapid development of aerospace, the technical innovation of the engine is always the core of aerospace development, which mainly works in high-temperature, high-pressure and high-speed environments, and in order to meet the requirements of use safety performance of related parts, the precision and the working performance of related important parts are simultaneously ensured according to the industrial standards. Meanwhile, because the titanium alloy has small density, high heat strength and lasting strength, low sensitivity to crack propagation under the action of vibration load and impact load and good corrosion resistance, the titanium alloy material is preferentially adopted in the engine and shell structures. However, when an engine is machined and manufactured, because titanium alloy has the material characteristics of poor thermal conductivity, small elastic modulus, large elastic deformation and the like, the surface of a workpiece is deformed and vibrated, and if the titanium alloy is machined under a high-temperature condition, the titanium alloy tends to chemically react with a cutter, so that the problems of low quality of the machined surface, accelerated cutter abrasion and shortened service life of the cutter are caused.

Disclosure of Invention

The invention aims to provide a long-service-life coating milling cutter for machining titanium alloy parts of aircraft engines, which has the advantages of good anti-seismic performance, good heat dissipation performance, long service life, convenience in chip removal, good machining effect, high product yield and the like.

In order to achieve the purpose, the invention provides a high-service-life coating milling cutter for processing titanium alloy parts of an aircraft engine, which comprises a cutting part coated with a nanometer-level high-hardness coating and a handle part, wherein the cutting part is of a right-handed cutting structure, the cutting part is provided with 4 peripheral edge chip grooves spirally extending from the front end of the cutting part to the handle part, the surface of each peripheral edge chip groove facing to the cutting rotation direction is a front cutter surface, the surface of each peripheral edge chip groove facing away from the cutting rotation direction is a rear cutter surface, the front cutter surface and the rear cutter surface are intersected to form a peripheral edge, the peripheral edge is correspondingly connected with an end chip groove at the front end of the cutting part, and an end edge chip groove connected with the peripheral edge chip groove is formed between every two adjacent end cutters; the 4 peripheral edges are respectively a pair of short edges and a pair of long edges, the short edges and the long edges are alternately arranged along the circumferential direction, the long edges and the short edges on one side facing the cutting rotation direction form a first included angle, the long edges and the other short edges on one side back to the cutting rotation direction form a second included angle, the first included angle and the second included angle are not equal, and the sum of the first included angle and the second included angle is equal to 180 degrees; the two end blades connected to the two long blades are connected to each other at the center of the front end of the cutting part, and the two end blades connected to the two short blades are spaced from each other at the front end of the cutting part by an outer diameter of the cutting part of 1/3 or more.

As a preferable scheme of the invention, the nanoscale high-hardness coating is AlTiN-Si.

In a preferred embodiment of the present invention, the helix angle of the peripheral edge is 38 to 42 degrees.

In a preferred embodiment of the present invention, the height center of the cutting edge of the peripheral edge is 0.1 ± 0.02 mm.

In a preferred embodiment of the present invention, the peripheral edge has a peripheral edge rake angle and a peripheral edge relief angle, and the peripheral edge rake angle is 6 degrees; the peripheral edge back angle is provided with a first peripheral edge back angle and a second peripheral edge back angle in sequence from the cutting edge to the rear cutter face, the first peripheral edge back angle is 10-12 degrees, and the second peripheral edge back angle is 24-26 degrees; the width of the flank corresponding to the first peripheral edge relief angle is 0.6 mm-0.7 mm, and the width of the flank corresponding to the second peripheral edge relief angle is 1.9 mm-2.1 mm.

In a preferred embodiment of the present invention, the cutting portion is provided with a first core thickness section located at the front section and a second core thickness section located at the rear section, and the core thickness of the first core thickness section is smaller than the core thickness of the second core thickness section.

In a preferred embodiment of the present invention, a transition arc is provided at a connection point between the end blade and the peripheral blade.

In a preferred embodiment of the present invention, the rake surface of the end blade is provided with a reinforcing blade for protecting the end blade.

As a preferable scheme of the present invention, the end blade is provided with an end blade rake angle and an end blade relief angle, and the end blade rake angle is 4 degrees to 6 degrees; the end sword relief angle includes first end sword relief angle and the second end sword relief angle that arranges in proper order to the back knife face from its blade, first end sword relief angle is 8 degrees ~ 10 degrees, the second end sword relief angle is 20 degrees ~ 24 degrees, the width of the back knife face that first end sword relief angle corresponds is 1.2mm ~ 1.4 mm.

In a preferred embodiment of the present invention, the end blade has an inner inclination angle, and the inner inclination angle is 1.8 degrees to 2.2 degrees.

Compared with the prior art, the long-service-life coating milling cutter for processing the titanium alloy part of the aircraft engine provided by the invention has the beneficial effects that:

the invention designs the peripheral blades as a pair of short blades and a pair of long blades which are alternately arranged along the circumferential direction, and two included angles formed by one long blade and the two short blades are not equal, the sum of the two included angles is equal to 180 degrees, the design can alternately change the feed amount of each edge, so that the milling waveform of each edge is not the same, can effectively reduce or avoid cutting vibration lines when the cutter carries out side milling, enables the cutter to have good anti-seismic performance, adapts to deformation and vibration caused by rebound quantity of the processed surface of the titanium alloy, effectively reduces hardening phenomenon, inhibits poor surface roughness and breakage of the cutting edge of the cutter caused by vibration, has good cutting effect, the feeding amount of the short blade is smaller than that of the long blade, so that the short blade has a larger heat dissipation space compared with the long blade, the heat dissipation of the cutter is facilitated, the high-quality processing surface can be obtained, and the service life of the cutter can be prolonged; meanwhile, the pair of end blades opposite to the pair of long blades are connected at the center of the front end of the cutting part, so that the end blades can not bulge on a processing plane, and the processing quality and the processing efficiency during milling of the end blade plane are ensured; the two end edges connected with the pair of short edges are arranged at the outer diameter of the cutting part above 1/3 at the interval of the front end of the cutting part, so that the chip containing space of the chip removing groove of the end edge is increased, chips can be conveniently removed, and the chips are effectively prevented from being accumulated at the front end to damage the processing surface and the end edge. Therefore, the long-service-life coating milling cutter can be suitable for processing titanium alloy parts of aircraft engines, and has the advantages of good anti-seismic performance, good heat dissipation performance, long service life, convenience in chip removal, good processing effect, high product yield and the like.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings of the embodiments will be briefly described below.

FIG. 1 is a front view of a high life coated milling cutter for machining titanium alloy parts for aircraft engines provided by the present invention;

FIG. 2 is a left side view of the structure shown in FIG. 1;

FIG. 3 is a cross-sectional view of the cutting portion in the configuration shown in FIG. 1;

fig. 4 is an enlarged view of a portion of the end blade in the configuration shown in fig. 1.

Detailed Description

The following detailed description of embodiments of the present invention is provided in connection with the accompanying drawings and examples. The following examples are intended to illustrate the invention but are not intended to limit the scope of the invention.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are only for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the machine or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. It should be understood that the terms "first", "second", etc. are used herein to describe various information, but the information should not be limited to these terms, which are only used to distinguish one type of information from another. For example, "first" information may also be referred to as "second" information, and similarly, "second" information may also be referred to as "first" information, without departing from the scope of the present invention.

As shown in fig. 1 and 2, a long-life coated milling cutter for processing titanium alloy parts of aircraft engines according to a preferred embodiment of the present invention includes a cutting part 1 coated with a nano-grade high-hardness coating and a shank 2, wherein the cutting part 1 has a right-handed cutting structure, the cutting part 1 is provided with 4 peripheral edge flutes 3 spirally extending from a front end thereof to the shank 2, a surface of the peripheral edge flutes 3 facing a cutting rotation direction is a rake surface 31, a surface of the peripheral edge flutes 3 facing away from the cutting rotation direction is a flank surface 32, and the rake surface 31 intersects with the flank surface 32 to form a peripheral edge flute 3The cutting edge 4 is correspondingly connected with an end blade 5 at the front end of the cutting part 1, and an end blade chip groove 6 connected with the peripheral blade chip groove 3 is formed between two adjacent end blades 5; the 4 peripheral edges 4 are respectively a pair of short edges 4a and a pair of long edges 4b, the short edges 4a and the long edges 4b are alternately arranged along the circumferential direction, and a first included angle theta is formed between the long edges 4b and the short edges 4a facing one side of the cutting rotation direction₁(preferably 83 degrees), the long blade 4b and another short blade 4a on the side opposite to the cutting rotation direction form a second included angle theta₂(preferably 97 degrees), the first included angle theta₁At the second included angle theta₂Not equal, and the first included angle theta₁At the second included angle theta₂The sum of which equals 180 degrees; the two end blades 5 connected to the two long blades 4b are connected to each other at the center of the front end of the cutting part 1, and the two end blades 5 connected to the two short blades 4a are spaced apart from each other at the front end of the cutting part 1 by a cutting part outer diameter of 1/3 or more.

Therefore, in the embodiment of the invention, the peripheral edge 4 is designed into a pair of short edges 4a and a pair of long edges 4b which are alternately arranged along the circumferential direction, and two included angles formed by one long edge 4b and the two short edges 4a are not equal to each other, and the sum of the two included angles is equal to 180 degrees, so that the feeding amount of each edge can be alternately changed, the milling waveform of each edge is not the same any more, the cutting vibration lines of the cutter during side milling can be effectively reduced or avoided, the cutter has good anti-vibration performance, the cutter is suitable for deformation and vibration caused by the rebound amount of the processed surface of titanium alloy, the hardening phenomenon is effectively reduced, poor surface roughness and cutter edge breakage caused by vibration are inhibited, the cutting effect is good, and because the feeding amount of the short edge 4a is less than that of the long edge 4b, the short edge 4a has a larger heat dissipation space compared with the long edge 4b, the heat dissipation of the cutter is convenient, the method is favorable for obtaining a high-quality processing surface and prolonging the service life of the cutter; meanwhile, the pair of end blades 5 opposite to the pair of long blades 4b are connected at the center of the front end of the cutting part 1, so that the end blades 5 cannot bulge on a processing plane, and the processing quality and the processing efficiency of the end blades 5 during plane milling are ensured; the two end blades 5 connected with the pair of short blades 4a are arranged at the front end of the cutting part 1 at intervals of more than 1/3, so that the chip containing space of the chip removing groove 6 of the end blade is enlarged, chips can be conveniently removed, and the chips are effectively prevented from being accumulated at the front end to damage the processing surface and the end blade 5.

Illustratively, the nano-grade high-hardness coating is preferably AlTiN-Si, so that frictional wear of the cutter can be effectively reduced, the service life of the cutter can be prolonged, and the service life of the cutter can be prolonged by more than 50%.

Illustratively, as shown in fig. 1, the helix angle α of the peripheral edge 4 is 38 to 42 degrees. By the design, on one hand, the cutting edge of the peripheral edge 4 can be sharper, so that the cutting edge can be cut in conveniently, and the quality of the processed surface is improved; on the other hand, the chip removal capability of the peripheral edge chip removal groove 3 can be smoother;

illustratively, as shown in FIG. 2, the high center of the cutting edge of the peripheral edge 4 is 0.1. + -. 0.02mm (as indicated by "h" in FIG. 2). The design can enhance the support and firmness of the peripheral blade 4, the service life is long, the processed aperture is stable, and the surface roughness is excellent.

Illustratively, as shown in fig. 3, the peripheral edge 4 is provided with a peripheral edge rake angle 41 and a peripheral edge relief angle (421 and 422), and the peripheral edge rake angle 41 is 6 degrees; the peripheral edge back angle 42 is provided with a first peripheral edge back angle 421 and a second peripheral edge back angle 422 in sequence from the cutting edge to the flank 32, the first peripheral edge back angle 421 is 10 degrees to 12 degrees, and the second peripheral edge back angle 422 is 24 degrees to 26 degrees; the front angle 41 of the peripheral edge is designed to be 6 degrees, so that the material characteristics of the titanium alloy are met, the sharpness of the cutting edge is ensured, burrs, edge breakage and the like are avoided in the cutting process, the processing effect is good, and the product rejection rate is low; design into two relief angle angles with week sword relief angle (421 and 422), can guarantee that week sword 4 has sufficient rigidity, provide enough space of dodging for week sword 4 simultaneously, reduce the contact area of flank 32 of week sword 4 and the machined surface on the work piece, be favorable to the cutting into of week sword 4.

Illustratively, the width of the flank 32 corresponding to the first peripheral edge relief angle 421 is 0.6mm to 0.7mm, and the width of the flank 32 corresponding to the second peripheral edge relief angle 422 is 1.9mm to 2.1 mm. Such design can guarantee the life under the 4 normal cutting prerequisites of week sword, makes simultaneously week sword 4 have sufficient wearability and cutting force.

Illustratively, as shown in fig. 1, in order to satisfy the chip removal space of full milling, the cutting part 1 is provided with a first core thickness section 11 at the front section and a second core thickness section 12 at the rear section, wherein the core thickness of the first core thickness section 11 is smaller than that of the second core thickness section 12. Preferably, the core thickness of the first core thickness section 11 is designed to be about 60% of the outer diameter of the cutting part 1, and the core thickness of the second core thickness section 12 is designed to be about 75% of the outer diameter of the cutting part 1, so that the chip containing space at the front end can be enlarged, the smooth chip removal at the rear end can be ensured, and the chip removal difficulty caused by full-cutter machining can be avoided. In the embodiment, the length of the cutting part 1 is 70mm, and the outer diameter is 16 mm; the core thickness of the first core thickness section 11 is 9.9mm, and the length is 25 mm; the core thickness of the second core thickness section 12 is 12mm, and the length is 45 mm.

Illustratively, as shown in fig. 1, a transition arc 7 is provided at the junction of the end edge 5 and the peripheral edge 4 to prevent the tip from collapsing. In this embodiment, the radius of the transition arc 7 is 1 mm.

Illustratively, as shown in fig. 1, the rake surface 31 of the end blade 5 is provided with a reinforcing blade 8 for protecting the end blade 5.

Illustratively, as shown in fig. 4, the end edge 5 is provided with an end edge rake angle 51 and end edge relief angles (521 and 522), and the end edge rake angle 51 is 4 degrees to 6 degrees; the end edge relief angle includes a first end edge relief angle 521 and a second end edge relief angle 522 sequentially arranged from the cutting edge to the flank 32, the first end edge relief angle 521 is 8 degrees to 10 degrees, and the second end edge relief angle 522 is 20 degrees to 24 degrees. The front angle 51 of the end edge is designed to be 4-6 degrees, so that the material characteristics of the titanium alloy are met, the sharpness of the cutting edge is ensured, burrs, edge breakage and the like are avoided in the cutting process, the processing effect is good, and the product rejection rate is low; design end sword relief angle (521 and 522) for two relief angle angles, can guarantee that end sword 5 has sufficient rigidity, provide enough space of dodging for end sword 5 simultaneously, reduce the contact area of the clearance 32 of end sword 5 and the machined surface on the work piece, be favorable to cutting into of end sword 5.

Illustratively, the width of the flank surface 32 corresponding to the first end edge relief angle 521 is 1.2mm to 1.4 mm. Such design can guarantee the life under the end sword 5 normal cutting prerequisite, makes end sword 5 have sufficient wearability and cutting force simultaneously.

Illustratively, as shown in fig. 1, the end edge 5 is provided with an inner inclination angle 53, and the inner inclination angle 53 is 1.8 degrees to 2.2 degrees. Such design can reduce the area of contact of end sword 5 and machined surface, makes end sword 5 sharper, is favorable to cutting into of end sword 5, effectively prevents simultaneously that the smear metal from piling up in the front end, makes things convenient for the chip removal.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "connected" and "connected" are to be interpreted broadly, e.g., as being fixed or detachable or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and substitutions can be made without departing from the technical principle of the present invention, and these modifications and substitutions should also be regarded as the protection scope of the present invention.