CN105252222B - A kind of processing method for small size spout sphere - Google Patents
A kind of processing method for small size spout sphere Download PDFInfo
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- CN105252222B CN105252222B CN201510760047.2A CN201510760047A CN105252222B CN 105252222 B CN105252222 B CN 105252222B CN 201510760047 A CN201510760047 A CN 201510760047A CN 105252222 B CN105252222 B CN 105252222B
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- 238000003672 processing method Methods 0.000 title abstract description 8
- 238000003754 machining Methods 0.000 claims abstract description 94
- 238000012545 processing Methods 0.000 claims abstract description 33
- 230000007704 transition Effects 0.000 claims abstract description 25
- 238000003801 milling Methods 0.000 claims abstract description 10
- 238000000034 method Methods 0.000 claims description 29
- 238000002347 injection Methods 0.000 claims description 20
- 239000007924 injection Substances 0.000 claims description 20
- 239000007921 spray Substances 0.000 claims description 9
- 238000007514 turning Methods 0.000 claims description 8
- 239000002994 raw material Substances 0.000 claims description 7
- 230000008569 process Effects 0.000 claims description 4
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 abstract description 26
- 229910052742 iron Inorganic materials 0.000 abstract description 12
- 238000005516 engineering process Methods 0.000 abstract description 4
- 239000000463 material Substances 0.000 abstract description 2
- 238000005520 cutting process Methods 0.000 description 11
- 230000007547 defect Effects 0.000 description 4
- 238000000227 grinding Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 241001391944 Commicarpus scandens Species 0.000 description 3
- 239000000110 cooling liquid Substances 0.000 description 3
- 239000002826 coolant Substances 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 235000011226 hei shi Nutrition 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 238000006748 scratching Methods 0.000 description 1
- 230000002393 scratching effect Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
Classifications
-
- 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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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Drilling And Boring (AREA)
- Milling Processes (AREA)
Abstract
The invention discloses a kind of processing method for small size sphere spout sphere, the interior lumen type face of nozzle opening and the sphere being connected with the nozzle opening for the variable cross-section spout to aero-engine swirl atomizer is processed, the processing method carries out roughing using turning-milling complex processing lathe to the two ends of raw bar material, transition arc is processed using smart burying so that variable cross-section nozzle area has identical allowance；Finally using the reverse hook boring processing of boring cutter.Processing method of the invention obtains identical allowance using smart burying processing, it is to avoid the even breaking accident brought of machining area became uneven, improves yield rate, has saved cost.Reverse hook boring processing technology is utilized simultaneously, is processed the iron filings for producing and is discharged outward, it is to avoid iron filings scratch finished type face, further increase machining accuracy and yield rate.
Description
Technical Field
The invention relates to a precision machining method, in particular to a machining method for precision machining of a small-size nozzle of an aircraft engine, and particularly relates to a machining method for a spherical surface of a small-size spherical nozzle.
Background
The nozzle of the centrifugal nozzle of the aircraft engine is structurally characterized in that the molded surface of an inner cavity is a variable cross section, the variable cross section is connected with a micro-size oil injection hole, the size precision is high, high technical requirements are mutually met between various molded surfaces, between an excircle and an end surface, multiple procedures such as turning, milling, grinding, clamping, grinding and polishing in the conventional machining process are difficult to machine, especially, the nozzle is small in size, the sizes of a positioning surface and a clamping surface of a part are small, the part is difficult to clamp, the size and the technical conditions of the part are difficult to guarantee for multiple times of clamping, and the part is very easy to scrap. In addition, the surface quality requirement of the oil spray hole and the inner cavity molded surface is high, the surface roughness is generally 0.4-0.2, and the surface quality can be seriously influenced by the micro cutter which has poor rigidity and generates a vibration cutter. And the quality of the surface quality directly influences the performance parameters of the flow test of the centrifugal nozzle. In the traditional method, the roughness is ensured by manually grinding the inner cavity, and the manual grinding has high operation level for workers, low processing efficiency, large workload and difficult control of size and technical conditions. Moreover, because of the complicated and small size of the internal profile structure of the nozzle, scrap iron is not easy to discharge, and a slight drag hook, scratch, burr and notch directly influence the spraying angle and the fuel unevenness of the centrifugal nozzle. Therefore, there is a need to provide an improved processing method to improve the processing efficiency and ensure the product quality.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a machining method for a small-size nozzle spherical surface, so as to reduce or avoid the problems mentioned above.
In order to solve the technical problem, the invention provides a processing method for a spherical surface of a small-size spherical nozzle, which is used for processing an oil injection hole of a variable-section nozzle of a centrifugal nozzle of an aircraft engine and an inner cavity profile of the spherical surface connected with the oil injection hole, wherein the nozzle is provided with the oil injection hole and the spherical surface with the diameter enlarged at one end of the oil injection hole, a first transition circular arc is arranged between the oil injection hole and the spherical surface, and the spherical surface comprises the following steps:
clamping a second end of the raw material bar on a jaw clamp of a turning and milling combined processing machine tool, processing a first end of the raw material bar opposite to the second end, and roughly processing a first variable cross-section nozzle area from the oil spray hole to the spherical surface, so that the first variable cross-section nozzle area has a first processing allowance;
processing the first transition arc by using a first precision bur so that the first transition arc has a second machining allowance, wherein the second machining allowance is equal to the first machining allowance;
and carrying out reverse hook boring processing from the oil injection hole to the outside along the first variable cross-section nozzle area by using a first boring cutter to finish processing.
Preferably, the first boring tool comprises a tool bar, a tool body and a tool tip, wherein the tool tip is located at the tail end of the tool body, the tool body is located between the tool tip and the tool bar, and in an axial projection view, a projection plane of the tool body is located inside a projection plane of the tool bar and is offset to one side of the center of the projection plane of the tool bar.
Preferably, the tool tip faces downward when the first boring tool is used for machining.
Preferably, the cross section of the cutter body has an upper arc surface and a lower arc surface, and the arc radiuses of the upper arc surface and the lower arc surface are the same.
Preferably, the tool tip has a tool tip rake angle and a tool tip relief angle, the tool tip rake angle is an angle at which the tool tip is tilted forward in the machining direction of the tool tip, the tool tip relief angle is an angle at which the tool tip is tilted backward away from the machining direction of the tool tip, the tool tip rake angle is 5 °, and the tool tip relief angle is 15 °.
Preferably, the tip has a principal deviation angle of 15 ° from vertical and a wedge angle of 15 ° from horizontal in its longitudinal direction.
Preferably, the maximum thickness of the tip is equal to the adjustment factor x (diameter of the oil spray hole/2 + radius of the spherical surface).
Preferably, the adjustment factor has a value in the range of 0.6 to 0.9. .
Preferably, a first transition conical surface spherical surface is arranged between the tool nose and the tool body.
Preferably, a second transition conical surface is arranged between the cutter body and the cutter rod, and the maximum taper angle of the second transition conical surface is 40 degrees.
The processing method of the invention obtains the same processing allowance by using the precision buried drill, avoids the cutter breaking accident caused by uneven thickness of the processing area, improves the yield and saves the cost. Meanwhile, by utilizing a reverse hook boring processing technology, scrap iron generated by processing is discharged outwards, the scrap iron is prevented from scratching the processed molded surface, and the processing precision and the yield are further improved.
Drawings
The drawings are only for purposes of illustrating and explaining the present invention and are not to be construed as limiting the scope of the present invention. Wherein,
FIG. 1 shows a cross-sectional view of an aircraft engine centrifugal nozzle according to an embodiment of the invention;
FIG. 2 is a schematic illustration of a first boring tool according to an embodiment of the present disclosure as applied to the machining of the centrifugal nozzle of the aircraft engine shown in FIG. 1;
FIG. 3 shows a left-hand axial projection view of the first boring tool of FIG. 2;
fig. 4 shows a schematic machining of a body of a first boring tool according to an embodiment of the present invention;
FIG. 5 shows an enlarged perspective view of a portion of the tip of FIG. 3;
fig. 6 shows an enlarged view of a portion of the tip of fig. 2.
Detailed Description
In order to more clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will now be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.
As mentioned in the background section, the machining method for the spherical surface of the small-size nozzle can be used for precisely machining the nozzle with the variable cross section of the centrifugal nozzle of the aircraft engine, and the machining process adopted in the prior art is particularly easy to break when machining the nozzle of the type, scrap iron is not easy to discharge, the rejection rate is high, and the machining method can not be applied to mass production basically, so the improved machining method is provided.
In particular, the improved machining method proposed by the invention is particularly suitable for machining the spherical inner cavity profile of a variable-section nozzle 1 of an aircraft engine centrifugal nozzle of the type shown in fig. 1, wherein fig. 1 shows a cross-sectional view of an aircraft engine centrifugal nozzle according to one specific embodiment of the invention.
The aircraft engine centrifugal nozzle in fig. 1 is characterized by comprising a nozzle 1 with a variable cross section and a spherical surface connected with the nozzle 1, wherein the nozzle 1 is provided with an oil injection hole 10 and a spherical surface 20 with an enlarged diameter at one end of the oil injection hole 10, and a first transition circular arc 3 is arranged between the oil injection hole 10 and the spherical surface 20. In a specific embodiment, the diameter of the oil injection hole 10 is in the range of 0.1-1mm, the radius R1 of the spherical surface 20 is in the range of 1-2mm, and the radius of the first transition circular arc 3 is very small, only 0.01-0.1mm, so that a person skilled in the art can imagine that the size of the whole area of the part to be machined is very small, and the area is very difficult to be reached by the conventional machining process and the cutter, and even if the area can be reached, the cutter in the normal state is basically in a concentric structure, namely similar to a thin needle, the rigidity of the cutter in machining is not good, the cutter is easy to break and shake in machining, and one cutter can only machine 1-2 parts, and the cutter can not be applied to mass production basically.
Based on the characteristics of the part to be machined, the invention provides an improved machining method, and additionally provides a machining tool with an improved structure by matching with the improved machining method.
The improved processing method utilizes the main processing equipment which is the turning and milling combined processing machine tool commonly adopted in the prior art, such as a seven-axis turning and milling combined processing center of Baume Switzerland or a turning and milling combined processing machine tool of a Heishi turning and milling combined processing center, the basic structure and the principle of the machine tool are known technologies, and the machine tool can be obtained from the Internet or known and public equipment specifications or a prior art manual by a person skilled in the art, and the description is omitted.
The process flow of the machining method of the invention is described in detail below with reference to the structure of the aircraft engine centrifugal nozzle of fig. 1, in particular as follows:
the second end of the raw material bar is clamped on a jaw clamp of the turning and milling combined machining machine tool, and the first end of the raw material bar opposite to the second end is machined. It should be noted that the two ends of the starting bar are substantially identical and may initially be clamped at either end. The first end and the second end are defined in the specification only for clarifying the positional relationship of various parts to be machined, so as to avoid confusion, when the machining is completed, the raw material rod becomes a finished part, and the first end becomes the profile of the finished part, so that a person skilled in the art should understand that the first end and the second end are only terms for indicating the directional positional relationship.
The machining of the first end may comprise many steps, such as machining of an outer circle, drilling, reaming, milling a groove, etc., which are, of course, rough machining, and the key point is the improvement of the machining process of the variable cross-section nozzle that the present invention particularly needs to solve, that is, in general, the machining of the first end requires rough machining of the first variable cross-section nozzle region between the oil injection hole 10 and the spherical surface 20, so that the first variable cross-section nozzle region has the first machining allowance.
After rough machining is finished, the junction of the oil injection hole 10 and the spherical surface 20 is not in smooth transition, a broken angle or a step usually exists, if finish machining is carried out by using a boring cutter at the moment, due to the existence of the non-smooth transition region, a region which is obviously thickened with the first machining allowance exists, the defect is fatal to the machining of the small-size nozzle, the boring cutter is usually machined to the region and is broken, and the broken cutter is easy to damage the profile of the part, so that the part is scrapped.
In order to solve the defect, the invention particularly provides an improved step, namely, a first transition arc 3 is processed by utilizing a first precision bur so that the first transition arc 3 has a second machining allowance, wherein the second machining allowance is particularly perfect and equal to the first machining allowance, so that an area with inconsistent machining allowance does not exist when a boring cutter is subsequently utilized for fine machining, the cutter breaking accident caused by uneven thickness of a machining area is avoided, the yield is improved, and the cutter cost is greatly reduced.
In a specific embodiment, in the previous rough machining step, if the first machining allowance of the first variable cross-section nozzle area is too large or the precision is not high, when the first transition arc 3 is machined by using the precision bur, the first variable cross-section nozzle area can be simultaneously subjected to fine machining by using the side portion of the precision bur, that is, the first variable cross-section nozzle area and the first transition arc 3 are machined with the same machining allowance at one time by using the precision bur, so that the defect of uneven thickness of the machined area can be avoided, the precision requirement of rough machining can be reduced, and the machining efficiency is improved.
And then, carrying out reverse hook boring processing by using a first boring cutter from the oil injection hole 10 to the outside along the first variable cross-section nozzle opening area, and finishing the first end. The conventional technology is to machine hole-shaped parts from outside to inside, but for machining the spherical surface of the small-size spherical nozzle, the iron chips generated by machining from outside to inside scratch the machined profile due to too small size and high requirement on the precision of the profile, and the slight scratch and scratch of the profile directly influence the performance parameters such as flow, flow direction, unevenness and the like of the fuel nozzle of the assembly, so that the phenomenon is never allowed to occur. Therefore, the invention adopts the reverse hook boring process, and the scrap iron generated by processing is discharged outwards to contact with the profile which is not processed yet, thereby overcoming the defects of the prior art and improving the processing precision and the yield. The structure of the first boring cutter will be described in further detail later.
The structure of a boring tool of a preferred improved structure usable in the machining method of the present invention is described in further detail below. Referring to fig. 2 to 3, in which fig. 2 is a schematic view illustrating a first boring cutter 100 according to an embodiment of the present invention applied to machining of an aircraft engine centrifugal nozzle shown in fig. 1, fig. 3 is a left-side axial projection view of the first boring cutter 100 shown in fig. 2, and the aircraft engine centrifugal nozzle shown in fig. 3 is not shown in fig. 3 for clarity.
As shown in fig. 2 to 3, the first boring tool 100 is composed of a tool bar 11, a tool body 12, and a tool tip 13, wherein the tool tip 13 is located at the end of the tool body 12, the tool body 12 is located between the tool tip 13 and the tool bar 11, and a projection plane of the tool body 12 is located inside a projection plane of the tool bar 11 and is offset to one side of the center of the projection plane of the tool bar 11. That is, different from the conventional concentric cutter, the boring cutter of the present invention has a novel eccentric cutter body structure, which not only provides a larger space channel for scrap iron discharge and coolant delivery, but also can obtain a larger cutter body thickness, improve the rigidity of the cutter body 12, easily ensure the processing quality, one boring cutter can process 10 parts, provide 5-10 times of processing life compared with the prior art, ensure the requirement of mass production with high quality and high efficiency, and greatly reduce the processing cost and rejection rate. In detail, if the cutter body 12 is concentrically constructed, the cutter body can be formed with a very thin section and has a very small rigidity in order to make room for sufficient discharge of iron chips and conveyance of coolant. As is obvious from figure 3, the cutter body 12 with the eccentric structure is adopted, the lower part of the cutter body 12 can leave out the lower space of the whole aperture, a larger space channel is provided for scrap iron discharge and cooling liquid conveying, and the cutter is not easy to break due to scrap iron blockage and high-temperature incapability of cooling. It can also be seen from fig. 3 that the upper structure of the cutter body 12 substantially fills most of the upper space of the bore, greatly increasing the stiffness of the cutter body 12, and thus greatly increasing the life of the cutter body and even the entire cutter.
To facilitate the machining of the cutter body 12 having the eccentric structure as described above, fig. 4 is a schematic view showing the machining of the cutter body of the first boring cutter according to an embodiment of the present invention, and as shown in fig. 4, the cross-section of the cutter body 12 has an upper arc surface 112 and a lower arc surface 113, and the arc radii of the upper arc surface 112 and the lower arc surface 113 are the same. In one embodiment, the arc radius of the upper arc surface 112 and the lower arc surface 113 is 1.5 mm. Namely, during machining, two intersected circular machining surfaces are adopted for machining, for example, an upper arc surface 112 is turned by the circular machining surface with the diameter of 1.5mm, then the circular machining surface with the diameter of 1.5mm can be translated for a certain distance, and a lower arc surface 113 is also turned by the circular machining surface with the diameter of 1.5mm, so that the machining and positioning are particularly convenient, the method is particularly suitable for producing the wearing parts which need to be replaced only by using 10 times, and the production cost of the cutter is greatly reduced.
The detailed structure of the first boring cutter will be described with reference to a partially enlarged view of the first boring cutter. Wherein fig. 5 is an enlarged perspective view of a portion of the tip of fig. 3, as shown in fig. 5, the cutting tip 13 has a cutting tip rake angle 132 and a cutting tip relief angle 133, the cutting tip rake angle 132 is an angle at which the cutting tip 13 is tilted forward in the machining direction of the cutting tip, the cutting tip relief angle 133 is an angle at which the cutting tip 13 is tilted backward away from the machining direction of the cutting tip, and in one embodiment, the cutting tip rake angle 132 is 5 ° and the cutting tip relief angle 133 is 15 °. The front angle 132 of the tool nose is set to be forward-inclined by 5 degrees, so that the wear resistance of the tool can be improved, the rear angle 133 of the tool nose is set to be 15 degrees, so that scrap iron can be conveniently discharged, and the scrap iron is prevented from blocking a scratched processing surface.
Figure 6 shows an enlarged view of a portion of the tip of figure 2. as shown in figure 6, the tip 13 has a principal angle 136 in its longitudinal direction of 15 from vertical and a wedge angle 137 from horizontal of 15. The same angles are chosen for the lead angle 136 and the wedge angle 137 to facilitate machining of the tool, thereby reducing the cost of machining the tool. In another embodiment, the maximum thickness H of the tip 13 can be calculated by the formula H ═ K × (a/2+ R1); wherein
K is the adjusting coefficient of the material to be processed,
a is the diameter of the oil spray hole (10),
r1 is the radius of the spherical surface (20). Because the oil spray hole 10 of the nozzle 1 has a machining allowance, and due to the existence of the main deflection angle 136, the maximum thickness position of the tool nose 13 and the minimum section of the oil spray hole 10 are horizontally staggered by a certain distance, so that the interference can not be caused even if the maximum thickness of the tool nose 13 is the same as the minimum section of the oil spray hole 10, the maximum thickness of the tool nose 13 is basically set to reach the maximum rigidity thickness under the condition of no interference, and the structural life of the tool nose is prolonged. The adjustment coefficient K is an empirical parameter obtained by carrying out a plurality of tests according to the chip removal condition and the space required by the flowing of the cooling liquid, the numerical range of the adjustment coefficient K is 0.6-0.9, and the adjustment coefficient K is obtained by the following formula: the maximum thickness H of the tool nose 13 obtained by H ═ K × (A/2+ R1) can ensure the rigidity requirement and prolong the service life of the tool on one hand, and can meet the requirements of chip removal and cooling liquid flow in machining on the other hand.
In one embodiment, a first transition taper 125 is provided between the tip 13 and the body 12. As can be seen in fig. 6, the first transition taper 125 is a tapered taper that avoids tool interference.
In another embodiment, a second transition taper 115 is provided between the tool body 12 and the tool holder 11, the second transition taper 115 having a maximum taper angle of 40 °. The structural design of the present embodiment is also to avoid interference of the tool during machining.
In a further embodiment, in order to adapt to the reverse hook boring machining process of the invention, the invention preferably makes the tool tip 13 downward when the first boring tool 100 is machined, so that the eccentric rigidity of the tool back part is utilized, and the service life of the tool is prolonged.
It should be appreciated by those of skill in the art that while the present invention has been described in terms of several embodiments, not every embodiment includes only a single embodiment. The description is given for clearness of understanding only, and it is to be understood that all matters in the embodiments are to be interpreted as including technical equivalents which are related to the embodiments and which are combined with each other to illustrate the scope of the present invention.
The above description is only an exemplary embodiment of the present invention, and is not intended to limit the scope of the present invention. Any equivalent alterations, modifications and combinations can be made by those skilled in the art without departing from the spirit and principles of the invention.
Claims (10)
1. A method for machining a spherical surface of a small-size spherical nozzle, which is used for machining an oil injection hole (10) of a variable-section nozzle (1) of a centrifugal nozzle of an aircraft engine and an inner cavity profile of the spherical surface (20) connected with the oil injection hole (10), wherein the nozzle (1) is provided with the oil injection hole (10) and the spherical surface (20) with the diameter enlarged at one end of the oil injection hole (10), and a first transition circular arc (3) is arranged between the oil injection hole (10) and the spherical surface (20), and is characterized by comprising the following steps:
clamping a second end of the raw material bar on a jaw clamp of a turning and milling combined processing machine tool, processing a first end of the raw material bar opposite to the second end, and roughly processing a first variable cross-section nozzle area from the oil spray hole (10) to the spherical surface (20), so that the first variable cross-section nozzle area has a first processing allowance;
machining the first transition arc (3) by using a first precision bur so that the first transition arc (3) has a second machining allowance, wherein the second machining allowance is equal to the first machining allowance;
and (3) carrying out reverse hook boring machining by using a first boring cutter from the oil injection hole (10) to the outside along the first variable cross-section nozzle area to finish machining.
2. The machining method according to claim 1, characterized in that the first boring tool (100) is composed of a tool shank (11), a tool body (12), and a tool tip (13), wherein the tool tip (13) is located at a distal end of the tool body (12), the tool body (12) is located between the tool tip (13) and the tool shank (11), and a projection plane of the tool body (12) is located inside a projection plane of the tool shank (11) and offset to one side of a center of the projection plane of the tool shank (11) in an axial projection view.
3. The machining method according to claim 2, wherein the tip is directed downward when the first boring tool is machining.
4. The machining method as claimed in claim 2, characterized in that the cross section of the tool body (12) has an upper arc surface (112) and a lower arc surface (113), and the arc radii of the upper arc surface (112) and the lower arc surface (113) are the same.
5. The method of claim 2, wherein the tip (13) has a tip rake angle (132) and a tip relief angle (133), the tip rake angle (132) being an angle at which the tip (13) is tilted forward in the machine direction, and the tip relief angle (133) being an angle at which the tip (13) is tilted backward away from the machine direction, wherein the tip rake angle (132) is 5 ° and the tip relief angle (133) is 15 °.
6. A method of machining according to claim 2, characterized in that the tip (13) has a principal deviation angle (136) in its longitudinal direction of 15 ° from vertical and a wedge angle (137) of 15 ° from horizontal.
7. The machining method according to claim 6, characterized in that the maximum thickness H of the tip (13) is obtained by the following formula: h × (a/2+ R1); wherein,
k is the adjustment coefficient K, and K is the adjustment coefficient,
a is the diameter of the oil spray hole (10),
r1 is the radius of the spherical surface (20).
8. The process according to claim 7, characterized in that the adjustment factor K has a value ranging from 0.6 to 0.9.
9. The machining method according to claim 2, characterized in that a first transition taper (125) is provided between the tip (13) and the body (12).
10. The machining method according to claim 2, characterized in that a second transition taper (115) is provided between the tool body (12) and the tool shank (11), the second transition taper (115) having a maximum taper angle of 40 °.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510760047.2A CN105252222B (en) | 2015-11-10 | 2015-11-10 | A kind of processing method for small size spout sphere |
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| CN201510760047.2A CN105252222B (en) | 2015-11-10 | 2015-11-10 | A kind of processing method for small size spout sphere |
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| CN105252222B true CN105252222B (en) | 2017-06-09 |
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| CN106239049A (en) * | 2016-08-19 | 2016-12-21 | 江苏大学 | A kind of device realizing flow visual in diesel nozzeles and processing method thereof |
| CN112676772A (en) * | 2020-11-30 | 2021-04-20 | 山东齐鲁电机制造有限公司 | Method for machining spherical coupling hole of generator coupler |
| CN113059331B (en) * | 2021-04-02 | 2022-06-07 | 中国航发南方工业有限公司 | Method for machining tiny special-shaped inner hole of oil nozzle |
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| US6205661B1 (en) * | 1999-04-15 | 2001-03-27 | Peter John Ring | Method of making a rocket thrust chamber |
| CN101323077A (en) * | 2007-06-14 | 2008-12-17 | 沈阳黎明航空发动机(集团)有限责任公司 | Restrike nozzle body mechanical workout technique |
| CN102069352A (en) * | 2010-12-23 | 2011-05-25 | 成都四威高科技产业园有限公司 | Method for processing small nozzle |
| CN102489953A (en) * | 2011-12-02 | 2012-06-13 | 上海电气电站设备有限公司 | Processing method of pressure spray nozzle set in steam turbine |
| CN102806443A (en) * | 2012-08-14 | 2012-12-05 | 沈阳黎明航空发动机(集团)有限责任公司 | Numerically-controlled processing method of nozzle housing piece |
| CN103008986A (en) * | 2012-11-30 | 2013-04-03 | 沈阳黎明航空零部件制造有限公司 | Numerical control boring and milling machining method of internal spherical surface |
| CN103586636A (en) * | 2013-11-11 | 2014-02-19 | 中国南方航空工业(集团)有限公司 | Machining method and machining device of jet nozzle |
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Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |