CN115383156A - Machining method for aero-engine part and rectangular tool withdrawal groove machining tool - Google Patents
Machining method for aero-engine part and rectangular tool withdrawal groove machining tool Download PDFInfo
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- CN115383156A CN115383156A CN202211241239.9A CN202211241239A CN115383156A CN 115383156 A CN115383156 A CN 115383156A CN 202211241239 A CN202211241239 A CN 202211241239A CN 115383156 A CN115383156 A CN 115383156A
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- blade
- cutting edge
- inner hole
- tool
- withdrawal groove
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B27/00—Tools for turning or boring machines; Tools of a similar kind in general; Accessories therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- Engineering & Computer Science (AREA)
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- Finish Polishing, Edge Sharpening, And Grinding By Specific Grinding Devices (AREA)
Abstract
The invention provides a machining method of an aircraft engine part and a rectangular tool withdrawal groove machining cutter. In the fine turning process, a rectangular tool withdrawal groove is turned at a connecting corner of the bottom surface and the side wall of an inner hole, a special rectangular tool withdrawal groove turning tool is adopted, and the turning tool mainly comprises a blade H surface, a blade I surface, a blade J surface, a blade K surface, a blade L surface, a blade M surface, a blade N surface and a blade P surface which are sequentially connected in the anticlockwise direction. The invention solves the problem that the bottom surface and the side wall of the inner hole are difficult to machine to the size required by design when the surface of the inner hole of the part is provided with the strengthening layer, and further solves the problem that the rectangular tool withdrawal groove cannot be accurately formed (in shape and size) by adopting a common lathe tool.
Description
Technical Field
The invention belongs to the technical field of turning, and particularly relates to a machining method of an aircraft engine part and a cutter for turning a rectangular tool retracting groove.
Background
In order to improve the working performance of the aircraft engine, special treatment such as tin plating, phosphating and nitriding is required on the surface of part, and the treatment can result in the surface hardness of the part being improved, and the surface after strengthening is difficult to process by directly adopting a vehicle processing method.
As shown in fig. 1 and 2, a part diagram of an aircraft engine part is shown, in which an inner hole is formed, and the bottom surface and the side wall of the inner hole need to be subjected to surface strengthening treatment, however, when the bottom surface and the side wall of the inner hole form a strengthening layer surface, it is difficult to machine the inner hole to the designed size by turning only.
In view of the above problems, it is desirable to design a machining method capable of quickly machining a surface-strengthened part to a design-required size.
Disclosure of Invention
The invention aims to provide a processing method of an aircraft engine part, which solves the problem that the bottom surface and the side wall of an inner hole are difficult to be lathed to the design required size when the surface of the inner hole of the part is provided with a strengthening layer, and further aims to solve the problem that the forming shape and size are difficult to meet the requirements when a rectangular tool withdrawal groove at the connecting corner of the bottom surface and the inner wall of the inner hole is lathed in the processing method.
The invention adopts the following technical scheme:
a rectangular tool withdrawal groove processing cutter for aeroengine parts comprises a cutter blade,
the blade mainly comprises a blade H surface, a blade I surface, a blade J surface, a blade K surface, a blade L surface, a blade M surface, a blade N surface and a blade P surface which are sequentially connected in the anticlockwise direction, and the blade H surface, the blade I surface, the blade J surface, the blade K surface, the blade L surface, the blade M surface, the blade N surface and the blade P surface are all perpendicular to the same reference plane;
an included angle of 45 degrees is formed between the H surface of the blade and the I surface of the blade;
an included angle of 135 degrees is formed between the cutting edge I surface and the cutting edge J surface, and a first interval is formed between the cutting edge J surface and the blade H surface;
an included angle of 135 degrees is formed between the cutting edge K surface and the cutting edge J surface, and a second interval is formed between the cutting edge K surface and the cutting edge I surface;
the surface K of the cutting edge is vertical to the surface L of the cutting edge;
an included angle of 135 degrees is formed between the L surface of the cutting edge and the M surface of the cutting edge;
an included angle of 135 degrees is formed between the surface M of the cutting edge and the surface N of the cutting edge;
the cutting edge N surface is parallel to the cutting edge L surface, and a third interval is formed between the cutting edge N surface and the cutting edge L surface;
an included angle of 45 degrees is formed between the N surface of the cutting edge and the P surface of the blade;
the fillet is connected with the joint of the cutting edge I surface and the cutting edge J surface, the joint of the cutting edge J surface and the cutting edge K surface, the joint of the cutting edge K surface and the cutting edge L surface, the joint of the cutting edge L surface and the cutting edge M surface, and the cutting edge M surface and the cutting edge N surface.
Alternatively, the first interval is greater than the second interval and the third interval, and the second interval and the third interval are equal.
Alternatively, the cutting edge N surface and the blade P surface are connected through a right-angle surface, and the right-angle surface is perpendicular to a common reference plane of the cutting edge N surface and the blade P surface. The right-angle surface is used for preventing the blade P surface from colliding with the inner surface of the part.
As an option, the rectangular tool withdrawal groove machining tool for the aircraft engine parts further comprises a tool handle, the front end of the tool handle is rotatably connected with the blade through a clamping screw, and the included angle between the P surface of the blade and the length direction of the tool handle is 45 degrees.
A method for machining the part of aeroengine is disclosed, which includes an internal hole with a surface strengthened layer on its bottom and side walls,
turning the bottom surface and the side wall of an inner hole to a designed process size, wherein the designed process size comprises a grinding allowance;
turning a tool withdrawal groove at a connecting corner of the bottom surface and the side wall of the inner hole;
step three, carrying out surface strengthening treatment on the bottom surface, the side wall and the tool withdrawal groove of the inner hole to generate a surface strengthening layer;
and step four, grinding the surface strengthening layers on the bottom surface and the side wall of the inner hole until the required size of the inner hole is achieved.
As an option, in the first step,
machining the inner hole to a process design size along a direction perpendicular to the bottom surface of the inner hole by using a D-shaped lathe tool to form the bottom surface of the inner hole;
and machining the inner hole to the technological design size along the direction perpendicular to the side wall of the inner hole by using a D-type lathe tool to form the side wall of the inner hole.
It should be noted that the D-type turning tool is a diamond tool.
Optionally, in the second step, the tool withdrawal groove is a rectangular tool withdrawal groove, a 45-degree inclined plane is arranged at the joint of the rectangular tool withdrawal groove and the bottom surface of the inner hole, a 45-degree inclined plane is also arranged at the joint of the rectangular tool withdrawal groove and the side wall of the inner hole, and corners of the rectangular tool withdrawal groove are rounded.
Further, the rectangular tool withdrawal groove is turned by the tool along the direction forming an included angle of 45 degrees with the side wall of the inner hole.
Alternatively, in the third step, the surface strengthening treatment comprises tin plating, phosphating and nitriding.
Compared with the prior art, the invention has the following characteristics:
(1) A new solution is provided for how to process the part to the design required size when the surface of the part is provided with the strengthening layer;
(2) The method that the tool withdrawal groove is designed at the connecting corner of the bottom surface and the side wall of the inner hole is adopted to solve the problem that the corner connecting part can not be processed by grinding;
(3) The tool withdrawal groove with the rectangular cross section (provided with the chamfer and the bevel edge) is optimized, on one hand, the rectangular tool withdrawal groove is convenient for feeding during grinding, on the other hand, the rectangular tool withdrawal groove meets the pneumatic layout of parts, and on the premise that the structural strength is met compared with other tool withdrawal grooves (spherical tool withdrawal grooves), more materials are removed, so that the tool withdrawal groove is also an important means for the light-weight design of an engine, but the processing difficulty of the rectangular tool withdrawal groove is greatly improved;
(4) Aiming at the problems that the section of the rectangular tool withdrawal groove is complex, the size is small and the measurement is difficult, a special tool is designed, the rectangular tool withdrawal groove can be rapidly and accurately machined to the required shape and size, and the design requirement is met.
Drawings
FIG. 1 is a schematic view of an aircraft engine part relief groove of the present invention;
FIG. 2 is an enlarged, fragmentary view of region I of FIG. 1;
FIG. 3 is a schematic view of a tool shank of the present invention;
fig. 4 is a schematic view of the tool of the present invention.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter of the present invention is limited to the following embodiments, and various modifications, substitutions and alterations made based on the common technical knowledge and conventional means in the art without departing from the technical idea of the present invention are included in the scope of the present invention.
Referring to fig. 1 and 2, the present invention provides an aircraft engine component that requires machining, the component having an internal bore, and a surface strengthening layer (e.g., nitrided layer, tin-plated layer, chromium-plated layer, phosphorus oxide layer, etc.) on the bottom surface and sidewall surface of the internal bore. The letters G, F, E, Φ in fig. 2 represent different dimensions of the part, respectively.
The basic processing thought of the invention is as follows: firstly, turning for fine turning, then carrying out special surface treatment (strengthening treatment), and finally machining the inner hole to the size by adopting a grinding method.
Because the bottom surface and the side wall connecting corner of the inner hole are right angles, the grinding processing is difficult to remove the junction of the end surface of the part and the hole surface (namely the bottom surface and the side wall connecting corner of the inner hole), therefore, the junction needs a tool withdrawal groove to avoid the occurrence of the condition, the feeding convenience and the minimum influence on the part during the grinding processing are considered, the tool withdrawal groove adopts a more complex rectangular section shape, as shown in figure 2, the junction of the rectangular tool withdrawal groove and the bottom surface of the inner hole is provided with a 45 DEG +/-1 DEG inclined plane, the junction of the rectangular tool withdrawal groove and the side wall of the inner hole is also provided with a 45 DEG +/-1 DEG inclined plane, and the corner of the rectangular tool withdrawal groove is chamfered at a corner R0.3 +/-0.2.
If the rectangular tool withdrawal groove is turned incompletely, the junction of the end surface and the hole surface (namely the bottom surface and the side wall connecting corner of the inner hole) has accumulated lumps, so that the spraying and grinding processing of the post process are influenced, even the subsequent assembly is influenced, and if the tool withdrawal groove is turned excessively, the strength of parts is influenced, and further the performance of the whole engine is influenced.
At present, a spherical cutter is generally adopted for turning a tool withdrawal groove, the tool withdrawal groove can be machined, the assembly and mechanical properties of parts are met, the shape and the size of the tool withdrawal groove do not meet the design requirements of a rectangular tool withdrawal groove, and the machined tool withdrawal groove is an approximate rectangular tool withdrawal groove.
As shown in fig. 3 and 4, the invention designs a rectangular tool withdrawal groove processing tool with a special shape, the tool comprises a blade, the length of the blade is 46mm, as shown in fig. 4, the blade mainly comprises a blade H surface, a blade I surface, a blade J surface, a blade K surface, a blade L surface, a blade M surface, a blade N surface and a blade P surface which are connected in sequence in a counterclockwise direction, the blade H surface, the blade I surface, the blade J surface, the blade K surface, the blade L surface, the blade M surface, the blade N surface and the blade P surface are all perpendicular to the same reference plane, and the width distance between the blade H surface and the blade P surface is 5mm; an included angle of 45 degrees is formed between the surface H of the blade and the surface I of the blade; an included angle of 135 degrees is formed between the cutting edge I surface and the cutting edge J surface, a first interval is formed between the cutting edge J surface and the blade H surface, the first interval is the vertical distance between the cutting edge J surface and the blade H surface, and the included angle is 2mm in the embodiment; an included angle of 135 degrees is formed between the cutting edge K surface and the cutting edge J surface, a second interval is formed between the cutting edge K surface and the cutting edge I surface, the second interval is the vertical distance between the cutting edge K surface and the cutting edge I surface, and the second interval is 1mm; the surface K of the cutting edge is vertical to the surface L of the cutting edge; an included angle of 135 degrees is formed between the L surface of the cutting edge and the M surface of the cutting edge; an included angle of 135 degrees is formed between the surface M of the cutting edge and the surface N of the cutting edge; the cutting edge N surface is parallel to the cutting edge L surface, and a third interval is formed between the cutting edge N surface and the cutting edge L surface, wherein the third interval is the vertical distance between the cutting edge N surface and the cutting edge L surface, and is 1mm in the embodiment; an included angle of 45 degrees is formed between the N surface of the cutting edge and the P surface of the blade; the fillet of R0.3 is connected to cutting edge I face and cutting edge J face junction, cutting edge J face and cutting edge K face junction, cutting edge K face and cutting edge L face junction, cutting edge L face and cutting edge M face junction, cutting edge M face and cutting edge N face. The cutting edge N face is connected with the blade P face through a right-angle face, the right-angle face is perpendicular to a common reference plane of the cutting edge N face and the blade P face, and the length of the right-angle face is 5.5mm as shown in figure 4.
As shown in fig. 3, the cutter is clamped on the handle at an included angle of 45 °, that is, the included angle between the blade P surface of the blade and the handle is 45 °.
As shown in fig. 1, the method of machining an aircraft engine part comprises the steps of,
turning the bottom surface and the side wall of the inner hole to a designed process size, wherein the designed process size comprises a grinding allowance, and machining the inner hole to the designed process size along a direction (A direction in figure 1) perpendicular to the bottom surface of the inner hole by using a D-type cutter to form the bottom surface of the inner hole; machining the inner hole to a technological design size along a direction (B direction in figure 1) vertical to the side wall of the inner hole by using a D-type cutter to form the side wall of the inner hole;
step two, turning a tool withdrawal groove at the connecting corner of the bottom surface and the side wall of the inner hole along the direction (the angle between the C direction and the end surface is 45 degrees in figure 1, and the C direction is parallel to the H surface of the blade or the P surface of the blade in figure 4) forming an included angle of 45 degrees with the side wall of the inner hole by using the tool (the rectangular tool withdrawal groove processing tool), wherein the tool withdrawal groove is a rectangular tool withdrawal groove, a 45-degree +/-1-degree inclined surface is arranged at the connecting part of the rectangular tool withdrawal groove and the bottom surface of the inner hole, a 45-degree +/-1-degree inclined surface is also arranged at the connecting part of the rectangular tool withdrawal groove and the side wall of the inner hole, and a fillet of R0.3 +/-0.2 is chamfered at the corner of the rectangular tool withdrawal groove;
performing surface strengthening treatment on the bottom surface and the side wall of the inner hole and the rectangular tool withdrawal groove to generate a surface strengthening layer;
and step four, grinding the surface strengthening layers on the bottom surface and the side wall of the inner hole until the required size of the inner hole is achieved.
Those skilled in the art will appreciate that the invention may be practiced without these specific details. Although illustrative embodiments of the present invention have been described above to facilitate the understanding of the present invention by those skilled in the art, it should be understood that the present invention is not limited to the scope of the embodiments, and various changes may be made apparent to those skilled in the art as long as they are within the spirit and scope of the present invention as defined and defined by the appended claims, and all matters of the invention which utilize the inventive concepts are protected.
Claims (9)
1. The utility model provides an aeroengine part rectangle tool withdrawal groove processing cutter which characterized in that: comprises a blade, a cutter blade and a cutter blade,
the blade mainly comprises a blade H surface, a blade I surface, a blade J surface, a blade K surface, a blade L surface, a blade M surface, a blade N surface and a blade P surface which are sequentially connected in the anticlockwise direction, and the blade H surface, the blade I surface, the blade J surface, the blade K surface, the blade L surface, the blade M surface, the blade N surface and the blade P surface are all perpendicular to the same reference plane;
an included angle of 45 degrees is formed between the surface H of the blade and the surface I of the blade;
an included angle of 135 degrees is formed between the cutting edge I surface and the cutting edge J surface, and a first interval is formed between the cutting edge J surface and the blade H surface;
an included angle of 135 degrees is formed between the cutting edge K surface and the cutting edge J surface, and a second interval is formed between the cutting edge K surface and the cutting edge I surface;
the cutting edge K surface is vertical to the cutting edge L surface;
an included angle of 135 degrees is formed between the L surface of the cutting edge and the M surface of the cutting edge;
an included angle of 135 degrees is formed between the surface M of the cutting edge and the surface N of the cutting edge;
the cutting edge N surface is parallel to the cutting edge L surface, and a third interval is formed between the cutting edge N surface and the cutting edge L surface;
an included angle of 45 degrees is formed between the N surface of the cutting edge and the P surface of the blade;
the fillet is connected with the joint of the cutting edge I surface and the cutting edge J surface, the joint of the cutting edge J surface and the cutting edge K surface, the joint of the cutting edge K surface and the cutting edge L surface, the joint of the cutting edge L surface and the cutting edge M surface, and the cutting edge M surface and the cutting edge N surface.
2. The rectangular tool escape machining tool for the aircraft engine parts as set forth in claim 1, characterized in that: the first interval is greater than the second interval and the third interval, and the second interval and the third interval are equal.
3. The rectangular tool escape machining tool for the aircraft engine parts as set forth in claim 1, characterized in that: the cutting edge N face is connected with the blade P face through a right-angle face, and the right-angle face is perpendicular to a common reference plane of the cutting edge N face and the blade P face.
4. The rectangular tool for machining tool-withdrawal grooves in aircraft engine parts according to claim 1, wherein: the novel knife handle is characterized by further comprising a knife handle, the front end of the knife handle is rotatably connected with the blade through a clamping screw, and the included angle between the P surface of the blade and the length direction of the knife handle is 45 degrees.
5. A method for processing an aircraft engine part, wherein the part comprises an inner hole, and surface strengthening layers are arranged on the bottom surface and the side wall of the inner hole, and the method is characterized in that: the processing method comprises the following steps of,
turning the bottom surface and the side wall of an inner hole to a designed process size, wherein the designed process size comprises a grinding allowance;
turning a tool withdrawal groove at a connecting corner of the bottom surface and the side wall of the inner hole;
step three, carrying out surface strengthening treatment on the bottom surface, the side wall and the tool withdrawal groove of the inner hole to generate a surface strengthening layer;
and step four, grinding the surface strengthening layers on the bottom surface and the side wall of the inner hole until the required size of the inner hole is achieved.
6. A method of machining an aircraft engine part according to claim 1, characterised in that: in the first step of the method,
machining the inner hole to a process design size along a direction perpendicular to the bottom surface of the inner hole by using a D-shaped lathe tool to form the bottom surface of the inner hole;
and processing the inner hole to the technological design size along the direction vertical to the side wall of the inner hole by adopting a D-type lathe tool to form the side wall of the inner hole.
7. A method of machining an aircraft engine part according to claim 1, characterised in that: in the second step, the tool withdrawal groove is a rectangular tool withdrawal groove, a 45-degree inclined plane is arranged at the joint of the rectangular tool withdrawal groove and the bottom surface of the inner hole, a 45-degree inclined plane is also arranged at the joint of the rectangular tool withdrawal groove and the side wall of the inner hole, and the corner of the rectangular tool withdrawal groove is chamfered.
8. A method of machining an aircraft engine part according to claim 7, characterised in that: the use of the tool of claim 1 to turn a rectangular relief in a direction at 45 ° to the sidewall of the bore.
9. A method of machining an aircraft engine part according to claim 1, characterised in that: in the third step, the surface strengthening treatment comprises tin plating, phosphorization and nitriding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211241239.9A CN115383156A (en) | 2022-10-11 | 2022-10-11 | Machining method for aero-engine part and rectangular tool withdrawal groove machining tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211241239.9A CN115383156A (en) | 2022-10-11 | 2022-10-11 | Machining method for aero-engine part and rectangular tool withdrawal groove machining tool |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115383156A true CN115383156A (en) | 2022-11-25 |
Family
ID=84128552
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211241239.9A Pending CN115383156A (en) | 2022-10-11 | 2022-10-11 | Machining method for aero-engine part and rectangular tool withdrawal groove machining tool |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115383156A (en) |
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2022
- 2022-10-11 CN CN202211241239.9A patent/CN115383156A/en active Pending
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