CN211161968U

CN211161968U - Special composite ceramic material cutter for machining aero-engine end face groove

Info

Publication number: CN211161968U
Application number: CN201921766666.2U
Authority: CN
Inventors: 李战会
Original assignee: Ningbo Xinhuili Precision Tool Co ltd
Current assignee: Ningbo Xinhuili Precision Tool Co ltd
Priority date: 2019-10-21
Filing date: 2019-10-21
Publication date: 2020-08-04
Anticipated expiration: 2029-10-21

Abstract

The utility model relates to a processing cutter technical field specifically relates to a special combined ceramic material cutter of processing aeroengine end face slot, including cutter arbor, blade and housing screw, the head of blade is equipped with the cutting edge of mountain peak form, the cutting edge includes more than one triangle-shaped cutting edge, the tip of triangle-shaped cutting edge is equipped with the radius and is 0.32-0.4 mm's cutting circular arc and constitutes the crest, and the bottom of two adjacent triangle-shaped cutting edges is connected and is constituted a root, is equipped with half root respectively on the both sides of cutting edge, the upper end of blade is equipped with first mounting hole, is equipped with the installation spacing groove that is used for installing the blade at the one end side of cutter arbor, the blade is through first mounting hole and housing screw threaded connection in the installation spacing groove. The utility model discloses a convenient dismantlement of blade is changed, avoids warping reduce cost.

Description

Special composite ceramic material cutter for machining aero-engine end face groove

Technical Field

The utility model relates to an alloy material machine tooling cutter technical field specifically, relates to a special combined ceramic material cutter of processing aeroengine terminal surface groove.

Background

Aeroengine's part adopts high temperature resistant alloy material mostly, uses ordinary cutter to process often because the contact surface is the single-point contact between cutter knife face and the work piece, leads to the contact surface little, and the tool bit warp easily, needs to change, leads to the later stage to need regularly to inspect whether the problem of cutter warp, if forget the detection in case, the cutter has appeared the cutter and warp slightly this moment and the naked eye sees not, and when continuing to use, leads to whole product condemned phenomenon easily.

SUMMERY OF THE UTILITY MODEL

The utility model provides a to prior art not enough, the utility model provides a special composite ceramic material cutter of processing aeroengine terminal surface groove.

The utility model discloses a special combined ceramic material cutter of processing aeroengine end face groove, including cutter arbor, blade and housing screw, the head of blade is equipped with the cutting edge of mountain peak form, the cutting edge includes more than one triangle-shaped cutting edge, the tip of triangle-shaped cutting edge is equipped with the cutting circular arc that the radius is 0.32-0.4mm and constitutes the crest, and the bottom of two adjacent triangle-shaped cutting edges is connected and is constituted a root, is equipped with half root respectively on the both sides of cutting edge, the upper end of blade is equipped with first mounting hole, is equipped with the installation spacing groove that is used for installing the blade at the one end side of cutter arbor, the blade is through first mounting hole and housing screw threaded connection at the installation spacing inslot.

Preferably, the root is a connecting circular arc with the radius of 0.2-0.4 mm.

Preferably, two sides of the triangular blade form an included angle R of 40 degrees.

Preferably, the distance between the crests of two adjacent triangular blades is 2.34-4.7 mm.

Preferably, an L-type limiting clamp for limiting the blade in the installation limiting groove is arranged on the outer side of the blade, and the L-type limiting clamp is in threaded connection with the compression screw.

Preferably, the distance from the crest to the root is 2.21-4.92 mm.

Has the advantages that: the utility model discloses a special combined ceramic material cutter of processing aeroengine end face slot, the cutter with original integrated into one piece sets up into the component structure, and make into the blade triangle-shaped structure, make into a plurality of triangle-shaped cutting edge end to end connection with the head of blade and constitute, and set up half root of a tooth in both sides, and the crest adopts the cutting circular arc to set up, guarantee to add the cutting plane that constitutes the multiarc to the product man-hour, improve the contact surface with the product, avoid the yielding problem of tool bit, be connected blade and guide arm dismantlement formula simultaneously, easy to assemble, and adjust the cutter angle slightly, the blade also conveniently is changed in the later stage, need not to trade whole cutter arbor, and the cost is reduced.

Drawings

The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the application and together with the description serve to explain the application and not to limit the application. In the drawings:

FIG. 1 is a schematic view of a blade according to the present invention;

FIG. 2 is a schematic structural view of the present invention;

fig. 3 is a side view of the present invention;

fig. 4 is a schematic view of the machining of the blade and the workpiece.

The reference numbers indicate a cutter bar 1, a blade 2, a compression screw 10, a cutting blade 3, a triangular blade 4, a cutting arc 5, a tooth top 6, a tooth bottom 7, a first mounting hole 8, a mounting limit groove 9, a compression screw 10, a connecting arc 11, an L-type limit clamp 12 and a workpiece 13.

Detailed Description

In the following description, numerous implementation details are set forth in order to provide a more thorough understanding of the present invention. It should be understood, however, that these implementation details should not be used to limit the invention. That is, in some embodiments of the invention, details of these implementations are not necessary. In addition, some conventional structures and components are shown in simplified schematic form in the drawings.

In addition, the descriptions related to "first", "second", etc. in the present invention are only for description purposes, not specifically referring to the order or sequence, and are not intended to limit the present invention, but only to distinguish the components or operations described in the same technical terms, and are not to be construed as indicating or implying any relative importance or implicit indication of the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, the technical solutions in the embodiments may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should not be considered to exist, and is not within the protection scope of the present invention.

Referring to fig. 1 to 3, the special composite ceramic material cutter for machining an aircraft engine end face groove comprises a cutter bar 1, a cutter blade 2 and a compression screw 10, wherein the head of the cutter blade 2 is provided with a peak-shaped cutting edge 3, the cutting edge 3 comprises more than one triangular cutting edge 4, the end of each triangular cutting edge 4 is provided with a cutting arc 5 with the radius of 0.32-0.4mm and forms a crest 6, the bottoms of two adjacent triangular cutting edges 4 are connected to form a root 7, two sides of each cutting edge 3 are respectively provided with a half root 7, the upper end of the cutter blade 2 is provided with a first mounting hole 8, one end side of the cutter bar 1 is provided with a mounting limiting groove 9 for mounting the cutter blade 2, and the cutter blade 2 is in the mounting limiting groove 9 through the first mounting hole 8 and the compression screw 10 in a threaded manner.

Preferably, the root 7 is a connecting circular arc 11 with a radius of 0.2-0.4 mm.

Preferably, the two sides of the triangular blade 4 form an included angle R of 40 °.

Preferably, the distance between the crests 6 of two adjacent triangular blades 4 is 2.34-4.7 mm.

Preferably, an L-type limit clip 12 for limiting the blade 2 in the installation limit groove 9 is arranged on the outer side of the blade 2, and the L-type limit clip 12 is in threaded connection with the compression screw 10.

Preferably, the distance between the crest 6 and the root 7 is 2.21-4.92 mm. The blade is made of ceramic materials.

The embodiment is formed by arranging the cutter which is originally integrally formed into a split structure, manufacturing the blade into a triangular structure, manufacturing the head of the blade into a plurality of triangular blades 4 and connecting the heads and the tails, and the half tooth bottoms 7 are arranged at the two sides, and the tooth tops 6 are arranged by adopting the cutting arcs 5, so that a multi-arc cutting surface is formed when a product is processed, the contact surface with the product is improved, the problem that a tool bit is easy to deform is avoided, meanwhile, the blade is detachably connected with the guide rod, so that the installation is convenient, the angle of the cutter is slightly adjusted, the blade is convenient to replace at the later stage, the whole cutter bar does not need to be replaced, the cost is reduced, meanwhile, the two sides are set to be the half tooth bottoms 7, so that the completeness of the product during processing can be ensured, for example, after half machining, the left-side half root 7 is connected with the machined workpiece 13, and finally the continuity after the whole machining is ensured, as shown in fig. 4.

The above description is only an embodiment of the present invention, and is not intended to limit the present invention. Various modifications and changes may occur to those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the scope of the claims of the present invention.

Claims

1. A special composite ceramic material cutter for machining an aircraft engine end surface groove is characterized by comprising a cutter bar (1), a blade (2) and a compression screw (10), the head of the blade (2) is provided with a peak-shaped cutting edge (3), the cutting edge (3) comprises more than one triangular cutting edge (4), the end part of the triangular cutting edge (4) is provided with a cutting arc (5) with the radius of 0.32-0.4mm and forms a tooth top (6), the bottoms of two adjacent triangular cutting edges (4) are connected to form a tooth bottom (7), the two sides of the cutting edge (3) are respectively provided with a half tooth bottom (7), the upper end of the blade (2) is provided with a first mounting hole (8), an installation limit groove (9) for installing the blade (2) is arranged at the side edge of one end of the cutter bar (1), the blade (2) is in threaded connection with the mounting limiting groove (9) through the first mounting hole (8) and the compression screw (10).

2. The special composite ceramic material cutter for machining an aircraft engine end face groove as claimed in claim 1, wherein: the tooth bottom (7) is a connecting circular arc (11) with the radius of 0.2-0.4 mm.

3. The special composite ceramic material cutter for machining an aircraft engine end face groove as claimed in claim 2, wherein: two sides of the triangular blade (4) form an included angle R of 40 degrees.

4. The special composite ceramic material cutter for machining an aircraft engine end face groove as claimed in claim 3, wherein: the distance between the crests (6) of two adjacent triangular blades (4) is 2.34-4.7 mm.

5. The special composite ceramic material cutter for machining the end face groove of the aircraft engine as claimed in claim 4, wherein an L-type limiting clamp (12) for limiting the blade (2) in the installation limiting groove (9) is arranged on the outer side of the blade (2), and the L-type limiting clamp (12) is in threaded connection with a compression screw (10).

6. The special composite ceramic material cutter for machining the aeroengine end surface groove as claimed in claim 1, 2, 3, 4 or 5, wherein: the distance between the crest (6) and the root (7) is 2.21-4.92 mm.