CN110640620A - Grinding method for inner wall surface of 3D printing rocket engine combustion chamber - Google Patents
Grinding method for inner wall surface of 3D printing rocket engine combustion chamber Download PDFInfo
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- CN110640620A CN110640620A CN201910892997.9A CN201910892997A CN110640620A CN 110640620 A CN110640620 A CN 110640620A CN 201910892997 A CN201910892997 A CN 201910892997A CN 110640620 A CN110640620 A CN 110640620A
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- grinding
- combustion chamber
- mandrel
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B37/00—Lapping machines or devices; Accessories
- B24B37/02—Lapping machines or devices; Accessories designed for working surfaces of revolution
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B37/00—Lapping machines or devices; Accessories
- B24B37/27—Work carriers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B57/00—Devices for feeding, applying, grading or recovering grinding, polishing or lapping agents
- B24B57/04—Devices for feeding, applying, grading or recovering grinding, polishing or lapping agents for feeding of solid grinding, polishing or lapping agents
Abstract
The invention discloses a grinding method for the inner wall surface of a combustion chamber of a 3D printing rocket engine, which comprises the steps of installing the combustion chamber on a grinding device, filling boron carbide grinding paste between a core shaft of the grinding device and the inner wall of the combustion chamber for rough grinding, wherein the mesh number of the boron carbide grinding paste is 80-120 meshes, the rotating speed of the core shaft is 1300-1500 r/rad, the grinding time is 5-7 h, filling diamond grinding paste between the core shaft of the grinding device and the inner wall of the combustion chamber for fine grinding, the mesh number of the diamond grinding paste is 18-22 meshes, the rotating speed of the core shaft is 3000-4000 r/rad, and the grinding time is 1.5-2.5 h. The roughness of the surface of the inner wall of the whole combustion chamber is uniform after grinding is finished, the wall thickness of the inner wall of the combustion chamber can be guaranteed to be consistent, the phenomenon of uneven thickness is avoided, the cost is low, and the performance is stable.
Description
Technical Field
The invention relates to the technical field of rocket engine combustion chamber inner wall surface treatment methods, in particular to a 3D printing method for grinding the inner wall surface of a rocket engine combustion chamber.
Background
With the development of industrialization, the 3D printing technology is rapidly developed as a new industry, and brings great revolution to the traditional machining industry. Particularly, with the continuous development and improvement of 3D printing technology, the printing technology is applied to a plurality of complex structural members in the field of aerospace.
The combustion chamber is a key component of liquid rocket engines, in which the propellant is mixed and ignited and generates a high temperature of approximately 3000 ℃, so that complicated cooling channels are required between the inner and outer walls of the combustion chamber, and it takes months to manufacture, test and deliver conventional combustion chambers in the past. The 3D printing technology can improve the traditional process, provide new design and performance and greatly reduce the time, but the 3D printing technology is formed by stacking and sintering very fine metal powder, so that the surface of a molded product has granular sensation and cannot reach the surface roughness of the traditional machine. In particular, products having high requirements on the surface roughness of the inner wall of the combustion chamber must be further treated. The existing manual polishing method is easy to cause the phenomenon that products are unqualified due to uneven roughness or partial thickness out-of-tolerance.
Disclosure of Invention
The invention aims to provide a grinding method for the inner wall surface of a combustion chamber of a 3D printing rocket engine, aiming at overcoming the defects of the prior art, so that the roughness of the inner wall surface of the whole combustion chamber is uniform, and the wall thickness of the inner wall of the combustion chamber is consistent.
In order to achieve the purpose, the grinding method for the inner wall surface of the combustion chamber of the 3D printing rocket engine comprises the following steps:
1) mounting the combustion chamber on a grinding device;
2) filling boron carbide grinding paste between a core shaft of the grinding device and the inner wall of the combustion chamber for coarse grinding, wherein the mesh number of the boron carbide grinding paste is 80-120 meshes, the rotating speed of the core shaft is 1300-1500 r/rad, and the grinding time is 5-7 h;
3) and filling diamond grinding paste between a mandrel of the grinding device and the inner wall of the combustion chamber for fine grinding, wherein the mesh number of the diamond grinding paste is 18-22 meshes, the rotating speed of the mandrel is 3000-4000 r/rad, and the grinding time is 1.5-2.5 h.
Furthermore, in the step 2), the mesh number of the boron carbide grinding paste is 100 meshes, the rotation speed of the mandrel is 1400r/rad, and the grinding time is 6 h.
Further, in the step 3), the mesh number of the diamond-filled grinding paste is 20 meshes, the rotation speed of the mandrel is 3500r/rad, and the grinding time is 2 h.
Further, the grinding device comprises a fixed support, a left support seat, a right support seat and a mandrel, the mandrel comprises a left mandrel and a right mandrel, the left mandrel and the right mandrel are connected into an integral mandrel in a spline structure, and the outer profile of the mandrel is consistent with the inner profile of the combustion chamber; the left supporting seat and the right supporting seat are symmetrically fixed on a left arm and a right arm of the fixed support; a left shaft of the left mandrel penetrates through the left supporting seat and then is connected with a left bearing seat, and the left bearing seat is fixed on the left supporting seat through a bolt; the right shaft of the right mandrel penetrates through the right supporting seat and then is connected with the right bearing seat, the right bearing seat is fixed on the right supporting seat through a bolt, and the right shaft is connected with the belt wheel through a synchronous belt.
Furthermore, one end of the combustion chamber is installed on the left supporting seat through the left fixing seat, an O-shaped sealing ring is lined between the end of the combustion chamber and the left supporting seat, the other end of the combustion chamber is installed on the right supporting seat through the right fixing seat, and the O-shaped sealing ring is lined between the end of the combustion chamber and the right supporting seat.
Furthermore, the outer profile of dabber has evenly arranged the bead along the circumferencial direction, every the one end of bead and the terminal surface parallel and level of left dabber, every the other end of bead and the terminal surface parallel and level of right dabber, and every the shape of bead is unanimous with combustion chamber cooling passage's shape.
Furthermore, a deep groove ball bearing is lined between the left shaft and the left bearing seat, and a lip-shaped sealing ring is lined between the left shaft and the left supporting seat; a deep groove ball bearing is lined between the right shaft and the right bearing seat, and a lip-shaped sealing ring is lined between the right shaft and the right supporting seat; the end part of the right shaft is connected with the retainer ring through a screw.
Compared with the prior art, the invention has the following advantages: the grinding method for the inner wall surface of the combustion chamber of the 3D printing rocket engine has the advantages of low cost and stable performance, the roughness of the inner wall surface of the whole combustion chamber is uniform after grinding is finished, the wall thickness and the size of the inner wall of the combustion chamber can be ensured to be consistent, and the phenomenon of uneven thickness is avoided.
Drawings
FIG. 1 is a schematic structural view of a 3D printing rocket engine combustion chamber inner wall surface grinding device;
fig. 2 is a schematic view of the mandrel structure of fig. 1.
Wherein: the device comprises a fixed support 1, a left arm 2, a left support seat 3, a right arm 4, a left bearing seat 5, a deep groove ball bearing 6, a lip-shaped seal ring 7, an O-shaped seal ring 8, a left shaft 10, a left core shaft 11, a right core shaft 12, a combustion chamber 13, a right support seat 14, a belt pulley 15, a synchronous belt 16, a check ring 17, a right shaft 18, a convex rib 19 and a right fixed seat 20.
Detailed Description
The invention is described in further detail below with reference to the figures and the specific embodiments.
The 3D printing belongs to the technical field of talent increasing manufacturing, and the selected high-temperature alloy material is a metal material which is prepared by taking iron, nickel and cobalt as bases and adding some alloy elements, can work at the high temperature of more than 800 ℃ and can reach the strength of 800 MPa. In recent years, the heat tide is raised in the global aerospace and military manufacturing industries, the 3D printing technology is applied to manufacture high-performance high-temperature alloy blank parts with the dimensional precision close to that of finished products, the process does not need a mould, and the utilization rate of materials is greatly improved, so that the manufacturing cost is reduced. A plurality of cooling channels are needed between the inner wall and the outer wall of the combustion chamber of the liquid rocket engine (when the liquid rocket engine works, the cooling liquid circularly flows from the channels to take away heat, so that the temperature of the combustion chamber is prevented from being overhigh), and the traditional electroforming or welding process is adopted, so that the cost is high, the period is long, and the yield is low. With the continuous development of 3D printing technology, the method can be directly applied to the field, not only can the cost be reduced, but also the period can be greatly shortened, and the yield is almost 100%.
However, the 3D printing technology is formed by stacking material powder, the surface of the inner wall of the formed combustion chamber has obvious granular feeling, the surface roughness does not meet the requirement, and the jetting of combustion airflow is influenced. The combustor inner wall is anomalous loudspeaker shape, and 3 mm's clearance is generally reserved with cooling channel to the combustor inner wall that 3D printed, and surface roughness is Ra 100. The formal product only has a gap of 2mm, and the surface treatment can be carried out only by adopting a manual grinding mode at present, but the manual grinding is difficult to ensure that the dimensional precision of the inner wall of the whole combustion chamber is completely consistent, so that the partial gap is less than 2mm and the product is easily scrapped. The grinding device and the grinding method can ensure that the clearance between the mandrel and the inner wall of the combustion chamber is completely consistent, and the grinding amount of the inner wall of the combustion chamber is completely consistent in the grinding process.
As shown in fig. 1 and 2, the 3D printing rocket engine combustion chamber inner wall surface grinding device comprises a fixed support 1, a left support base 3, a right support base 14 and a mandrel, wherein the mandrel comprises a left mandrel 11 and a right mandrel 12, the left mandrel 11 and the right mandrel 12 are connected into an integral mandrel in a spline structure, and the outer profile of the mandrel is consistent with the inner profile of a combustion chamber 13; the left support seat 3 and the right support seat 14 are symmetrically fixed on the left arm 2 and the right arm 4 of the fixed support 1 through bolts; a left shaft 10 of a left mandrel 11 passes through the left support seat 3 and then is connected with a left bearing seat 5, a deep groove ball bearing 6 is lined between the left shaft 10 and the left bearing seat 5, a lip-shaped sealing ring 7 is lined between the left shaft 10 and the left support seat 3, and the left bearing seat 5 is fixed on the left support seat 3 through bolts; a right shaft 18 of the right mandrel 12 penetrates through the right support seat 14 and then is connected with a right bearing seat, a deep groove ball bearing is lined between the right shaft 18 and the right bearing seat, a lip-shaped sealing ring is lined between the right shaft 18 and the right support seat 14, the right bearing seat is fixed on the right support seat 14 through a bolt, the right shaft 18 is connected with a belt wheel 15 through a synchronous belt 16, and the end part of the right shaft 18 is connected with a check ring 17 through a screw. In addition, ribs 19 are uniformly arranged on the outer profile of the mandrel along the circumferential direction, one end of each rib 19 is flush with the end face of the left mandrel, the other end of each rib 19 is flush with the end face of the right mandrel, and the shape of each rib 19 is consistent with that of the cooling channel of the combustion chamber.
The grinding paste is filled between profile and the combustion chamber inner wall outside the during operation dabber, the motor drives hold-in range 16 and band pulley 15 and rotates together, thereby drive second dabber 12 and first dabber 11 and rotate together, the epaxial bead structure of dabber drives the grinding paste and rotates together, when dabber speed reaches certain rotational speed, the grinding paste can be fast-speed grinds the combustion chamber inner wall, thereby make the roughness on combustion chamber inner wall surface reach the precision that needs, simultaneously because the dabber is the same with the clearance of combustion chamber inner wall, so whole combustion chamber inner wall surface roughness can be very even, uneven phenomenon of thickness can not appear in the wall thickness yet.
The grinding method for the inner wall surface of the 3D printing rocket engine combustion chamber comprises the following steps:
1) one end of a combustion chamber 13 is installed on a left supporting seat 3 of the grinding device through a left fixing seat 9, an O-shaped sealing ring 8 is lined between the end part of the combustion chamber 13 and the left supporting seat 3, similarly, the other end of the combustion chamber 13 is installed on a right supporting seat 14 of the grinding device through a right fixing seat 20, an O-shaped sealing ring is lined between the end part of the combustion chamber and the right supporting seat, then the left supporting seat and the right supporting seat are fixed on a fixed support 1 through the structure shown in figure 1, and a mandrel is installed on the left supporting seat and the right supporting seat, so that the gaps between the mandrel and the inner wall of the combustion chamber are completely consistent;
2) filling boron carbide grinding paste between the mandrel and the inner wall of the combustion chamber for coarse grinding, wherein the mesh number of the boron carbide grinding paste is 80-120 meshes, the mandrel rotating speed is 1300-1500 r/rad, and the grinding time is 5-7 h, preferably 100 meshes, 1400r/rad and 6 h;
3) and diamond grinding paste is filled between the mandrel and the inner wall of the combustion chamber for fine grinding, the mesh number of the diamond grinding paste is 18-22 meshes, the rotating speed of the mandrel is 3000-4000 r/rad, the grinding time is 1.5-2.5 h, and 20 meshes, 3500r/rad and 2h are preferred.
The grinding process of the invention is divided into coarse grinding and fine grinding, the grinding paste of the coarse grinding is boron carbide grinding paste, the grinding paste of the fine grinding is diamond grinding paste, and the mesh number and the mandrel rotation speed of the grinding paste are respectively compared and analyzed through a large number of experiments.
Boron carbide grinding paste is selected for use in the rough grinding, selects the grinding paste of different meshes to grind under different dabber rotation speeds, detects combustion chamber inner wall grinding volume and roughness, and the concrete result is as shown in Table 1:
TABLE 1
In the course of rough grinding, the surface roughness of the inner wall of the combustion chamber can meet the requirements when the rotating speed of the mandrel is 1400r/rad and the mesh number of the grinding paste is 100 meshes, reaches Ra1.6, and can grind 0.9mm only in six hours.
Diamond lapping paste is selected for use in the fine grinding, under different dabber rotation speeds, selects for use the lapping paste of different mesh numbers to grind equally, detects combustion chamber inner wall grinding volume and roughness, and the concrete result is as shown in Table 2:
TABLE 2
In the fine grinding process, the surface roughness of the inner wall of the combustion chamber can meet the requirement when the rotating speed of the mandrel is 3500r/rad and the mesh number of the grinding paste is 20 meshes, reaches Ra0.4, and can grind 0.1mm only in two hours.
In the grinding method of the invention, boron carbide (molecular formula B) with the granularity of 100 meshes is selected for coarse grinding4C) The boron carbide grinding paste has a good grinding effect on high-temperature alloy materials with high strength, when the rotation speed of the mandrel is 1400rad/min, the convex edges on the mandrel drive the grinding paste to rotate, the scouring force on the inner wall of a combustion chamber is most stable, so that rough grinding is performed, the grinding amount per hour can reach 0.15mm, the grinding amount per hour can reach 0.9mm in six hours, the surface roughness can also reach 1.6, and the requirements can be met;
the diamond grinding paste (molecular formula C) with the granularity of 20 meshes is selected for fine grinding, the diamond grinding paste is mainly used for processing a hard alloy material with high finish, the principle is the same as that of the diamond grinding paste, when the rotation speed of the mandrel is 3500rad/min, the scouring force on the inner wall of the combustion chamber is most stable, so that the fine grinding is carried out, the grinding amount per hour can reach 0.05mm, the grinding amount per hour can reach 0.1mm within two hours, the surface roughness can also reach 0.4, and the requirements can be met.
After the two-time grinding, the gap between the inner wall of the combustion chamber and the middle cooling channel can be ensured to be 2mm, and the surface roughness of the inner wall of the combustion chamber can be ensured to achieve a mirror surface effect of 0.4.
Claims (7)
1. A grinding method for the inner wall surface of a 3D printing rocket engine combustion chamber is characterized by comprising the following steps: the grinding method comprises the following steps:
1) mounting the combustion chamber on a grinding device;
2) filling boron carbide grinding paste between a core shaft of the grinding device and the inner wall of the combustion chamber for coarse grinding, wherein the mesh number of the boron carbide grinding paste is 80-120 meshes, the rotating speed of the core shaft is 1300-1500 r/rad, and the grinding time is 5-7 h;
3) and filling diamond grinding paste between a mandrel of the grinding device and the inner wall of the combustion chamber for fine grinding, wherein the mesh number of the diamond grinding paste is 18-22 meshes, the rotating speed of the mandrel is 3000-4000 r/rad, and the grinding time is 1.5-2.5 h.
2. The method for grinding the inner wall surface of a combustion chamber of a 3D printing rocket engine according to claim 1, wherein: in the step 2), the mesh number of the boron carbide grinding paste is 100 meshes, the rotating speed of the mandrel is 1400r/rad, and the grinding time is 6 hours.
3. The method for grinding the inner wall surface of a combustion chamber of a 3D printing rocket engine according to claim 1, wherein: in the step 3), the diamond-filled grinding paste has the mesh number of 20 meshes, the rotating speed of the mandrel is 3500r/rad, and the grinding time is 2 h.
4. The method for grinding the inner wall surface of a combustion chamber of a 3D printing rocket engine according to claim 1, wherein: the grinding device comprises a fixed support (1), a left support seat (3), a right support seat (14) and a mandrel, wherein the mandrel comprises a left mandrel (11) and a right mandrel (12), the left mandrel (11) and the right mandrel (12) are connected into an integral mandrel in a spline structure, and the outer profile of the mandrel is consistent with the inner profile of a combustion chamber (13); the left supporting seat (3) and the right supporting seat (14) are symmetrically fixed on the left arm (2) and the right arm (4) of the fixed support (1); a left shaft (10) of the left mandrel (11) penetrates through the left supporting seat (3) and then is connected with a left bearing seat (5), and the left bearing seat (5) is fixed on the left supporting seat (3) through a bolt; the right shaft (18) of the right mandrel (12) penetrates through the right support seat (14) and then is connected with the right bearing seat, the right bearing seat is fixed on the right support seat (14) through a bolt, and the right shaft (18) is connected with the belt wheel (15) through a synchronous belt (16).
5. The method for grinding the inner wall surface of a combustion chamber of a 3D printing rocket engine according to claim 4, wherein: the one end of combustion chamber (13) is installed on left supporting seat (3) through left fixing base (9), just O type sealing washer (8) have been lined in between the tip of combustion chamber (13) and left supporting seat (3), the other end of combustion chamber (13) is installed on right supporting seat (14) through right fixing base (20), just it has O type sealing washer to line in between the tip of combustion chamber and the right supporting seat.
6. The method for grinding the inner wall surface of a combustion chamber of a 3D printing rocket engine according to claim 4, wherein: the outer profile of the mandrel is uniformly provided with ribs (19) along the circumferential direction, one end of each rib (19) is flush with the end face of the left mandrel, the other end of each rib (19) is flush with the end face of the right mandrel, and the shape of each rib (19) is consistent with that of the cooling channel of the combustion chamber.
7. The method for grinding the inner wall surface of a combustion chamber of a 3D printing rocket engine according to claim 4, wherein: a deep groove ball bearing (6) is lined between the left shaft (10) and the left bearing seat (5), and a lip-shaped sealing ring (7) is lined between the left shaft (10) and the left supporting seat (3); a deep groove ball bearing is lined between the right shaft (18) and the right bearing seat, and a lip-shaped sealing ring is lined between the right shaft (18) and the right supporting seat (14); the end part of the right shaft (18) is connected with the retainer ring (17) through a screw.
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| CN108747795A (en) * | 2018-05-21 | 2018-11-06 | 浙江工业大学 | Liquid metal polishing fluid turns round inner surface polishing system |
| US20190168353A1 (en) * | 2019-02-11 | 2019-06-06 | Aref Azami Gilan | Rotational abrasive micro/nano-finishing |
| CN110026880A (en) * | 2019-04-15 | 2019-07-19 | 中国电子科技集团公司第二十研究所 | The inner surface abrasive Flow of 3D printing thin wall special-shaped electromagnetic horn polishes tooling |
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2019
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201824229U (en) * | 2010-10-27 | 2011-05-11 | 株洲湘火炬汽车密封有限责任公司 | Device for polishing internal and external surfaces of 95 porcelain bushing |
| CN104191349A (en) * | 2014-08-21 | 2014-12-10 | 益阳橡胶塑料机械集团有限公司 | Grinding method of dynamic ring and static ring in rotor sealing device of internal mixer and auxiliary grinding device |
| CN108326725A (en) * | 2017-12-28 | 2018-07-27 | 西安航天发动机有限公司 | A kind of 3D printing double shrouded wheel abrasive Flow finishing processing device |
| CN108747795A (en) * | 2018-05-21 | 2018-11-06 | 浙江工业大学 | Liquid metal polishing fluid turns round inner surface polishing system |
| US20190168353A1 (en) * | 2019-02-11 | 2019-06-06 | Aref Azami Gilan | Rotational abrasive micro/nano-finishing |
| CN110026880A (en) * | 2019-04-15 | 2019-07-19 | 中国电子科技集团公司第二十研究所 | The inner surface abrasive Flow of 3D printing thin wall special-shaped electromagnetic horn polishes tooling |
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