CN113664456A - Combustion chamber barrel repairing method based on compensation structure - Google Patents
Combustion chamber barrel repairing method based on compensation structure Download PDFInfo
- Publication number
- CN113664456A CN113664456A CN202110914470.9A CN202110914470A CN113664456A CN 113664456 A CN113664456 A CN 113664456A CN 202110914470 A CN202110914470 A CN 202110914470A CN 113664456 A CN113664456 A CN 113664456A
- Authority
- CN
- China
- Prior art keywords
- welding
- shell
- ring
- lining
- combustion chamber
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
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
- B23P6/00—Restoring or reconditioning objects
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E30/00—Energy generation of nuclear origin
- Y02E30/30—Nuclear fission reactors
Abstract
The invention provides a combustion chamber barrel repairing method based on a compensation structure. Firstly, processing all ring grooves which are distributed along the axial direction on the surface of the lining and matched ring groove compensation rings; and a compensation ring at the igniter corresponding to the igniter mounting part is processed. And divides the housing into three lobes. After the operation is finished, assembling and welding the ring groove compensating ring and the compensating ring at the igniter on the lining to form a lining assembly; then carrying out thermal sizing on the split shell and the lining component together; because the annular groove compensation ring can enlarge the size of the lining assembly, in order to compensate the missing of the welding seam, the shell and the lining assembly are welded together by matching the compensation block and combining argon arc welding and vacuum brazing. After the ring groove compensating ring and the igniter compensating ring are assembled, the strength and the reliability of the lining assembly are well improved, and other parts which are disassembled previously are welded to complete the integral assembly of the combustion chamber cylinder.
Description
Technical Field
The invention belongs to the technical field of precision machining, and relates to a combustion chamber barrel repairing method based on a compensation structure.
Background
In the field of aerospace, a combustion chamber is a device in which fuel or propellant is combusted to generate high-temperature fuel gas, and is combustion equipment made of high-temperature-resistant alloy materials. The space between the top of the piston and the cylinder head after the piston reaches top dead center, where the fuel is burned. It is an important component of gas turbine engines, ramjets, rocket engines.
However, in the prior art, the leakage of the lining base material occurs in the repair and new manufacturing processes of the combustion chamber cylinder, so that the designed pressure test requirement of 5MPa cannot be met, and the bulge generally occurs at 3 MPa-4.5 MPa.
Disclosure of Invention
The invention provides a method for repairing a combustion chamber cylinder based on a compensation structure, which aims to solve the problem that a lining base material leaks in the repairing and new manufacturing processes of the combustion chamber cylinder in the prior art.
The invention is realized by the following technical scheme:
a combustion chamber cylinder repairing method based on a compensation structure comprises the following steps,
1) taking off a water inlet pipe and a water outlet pipe on the shell, a first water ring and a second water ring, then turning off the lining and an end face compensation ring in a pressing ring groove between two end faces of the shell and the lining, reserving the shell, polishing and taking off a water inlet flange and a water outlet flange, finally finely boring an igniter mounting hole on the shell, and then equally dividing the shell into three pieces along the circumferential direction;
2) after the materials are coiled into a cylindrical part again, a through hole penetrating the length of the cylindrical part is roughly drilled by a boring and milling machine, then step holes are respectively lathed at two ends of the cylindrical part, then chucks are installed at two ends, then an outer surface and a ring groove are finely lathed, and finally an outer arc surface of a partition wall of the ring groove is milled to obtain the lining; cutting a sheet material on line to form an inner hole and an outer circle, and then polishing to obtain an end face compensation ring;
milling the blank into strips with different lengths, and then rolling the strips into circular arcs after vacuum annealing to obtain the annular groove compensating ring; turning an inner hole and an outer circle on the rough material, and then linearly cutting a cambered surface which is matched with the outer surface of the igniter on the inner lining to obtain a compensation ring at the igniter;
the strips with different lengths are respectively adapted to the annular grooves at different positions on the liner;
3) assembling two ring groove compensating rings into corresponding ring grooves on the inner liner one by one along the axial direction of the inner liner, and assembling the compensating rings at the igniter to the igniter mounting position on the inner liner to obtain a liner assembly; then, putting the lining assembly into a furnace for vacuum brazing, performing finish machining on the lining assembly after the vacuum brazing is finished, and then milling a boss at the igniter matched with the igniter mounting hole;
4) putting the split shell and the lining component into a furnace together for thermal sizing so as to ensure that the split shell is attached to the lining component; after the thermal correction is finished, welding the welding seams between the split shells by using argon arc welding, then welding the split shells by using vacuum brazing and reinforcing the argon arc welding seams at the igniter; after welding, the outer circle of the shell is finished through turning, and then the water inlet flange and the water outlet flange are assembled on the shell and welded together through argon arc welding; finally, welding the igniter mounting seat on the shell through argon arc welding to obtain an assembly;
5) firstly, finish turning the inner surface and the pressure ring groove of the assembly, then assembling the end surface compensation ring, and then putting the assembly into a furnace for vacuum brazing;
6) welding the water inlet pipe, the water outlet pipe, the first water ring and the second water ring to corresponding positions on the shell by using argon arc welding to obtain a repaired combustion chamber cylinder body; and then carrying out a 5MPa pressure test on the repaired combustion chamber cylinder, if the repaired combustion chamber cylinder passes the test, finishing the repair, and if the repaired combustion chamber cylinder does not pass the test, carrying out the operation until the repaired combustion chamber cylinder passes the test.
The specific operation of the step 1) is as follows: cutting off a water inlet pipe and a water outlet pipe on the shell along an argon arc welding seam through pliers processing, and then polishing and disassembling the first water ring and the second water ring to avoid the water inlet flange and the water outlet flange from being damaged by collision in the disassembling process;
then taking out the shell through turning, wherein the wall thickness of the shell is required to be ensured not to be less than 4mm during turning;
then, the water inlet flange and the water outlet flange are disassembled by clamping, polishing and chamfering treatment are carried out at the welding seam of the water inlet flange and the water outlet flange;
and finally, supporting by using a V-shaped cushion block, finely boring a mounting hole at the position of an igniter on the shell, and dividing the shell into three parts along three argon arc welding lines to obtain the split shell.
The specific operation of vacuum annealing in the step 2) is as follows: and flatly placing the strips with different lengths on a workbench, loading into a vacuum furnace, heating to 550 ℃, inflating and cooling to 65 ℃, and discharging.
The step 3) of finely processing the shape of the lining component comprises the following specific operations: the outer circle of the lining component is subjected to finish turning treatment, and then the lining component is placed on a machining center to mill the outer arc surface of the partition wall between the bosses at the two igniters.
The specific operation after finishing hot alignment in the step 4) is as follows: after the inner wall of the split shell is preset with adhesive tape brazing filler metal, the split shell is hooped on the lining component by a bridle and three welding openings among the lining component are adjusted to be uniform; assembling compensation blocks in the three welding slits to compensate for weld joint loss, and then welding three split weld joints in a segmented priming and segmented welding mode through argon arc welding; coating and injecting brazing filler metal again to the unsaturated part of the welding seam, and putting the welding seam into a furnace for vacuum brazing;
the concrete operation after the welding is finished is as follows: firstly, the outer circle of the shell matched with the water inlet flange and the water outlet flange is precisely machined by turning, and then the water inlet flange is assembled at the upper end of the shell, the water outlet flange is assembled at the lower end of the shell and fixed by spot welding; the water inlet flange and the water outlet flange are tightened by using the positioning columns and then are fully welded; and finally, presetting brazing filler metal on the igniter mounting seat, and welding the igniter mounting seat on the shell through argon arc welding to obtain a combined piece.
The specific operation of vacuum brazing in the step 3), the step 4) and the step 5) is as follows: and (3) conveying the assembled workpiece and the tool into a vacuum furnace, heating to 1000-1050 ℃, keeping the pressure at 120-150 Pa, keeping the temperature for 60min, cooling to 700 ℃, closing the pressure, vacuum-cooling to 600 ℃, cooling to 65 ℃ along with the furnace, and discharging.
And after the vacuum brazing in the step 5) is finished, checking the compactness of the welding seam through a sealing test, if the welding seam is qualified, carrying out the next step, and if the welding seam is not qualified, carrying out brazing repair and carrying out the sealing test again until the welding seam is qualified.
The operating parameters of argon arc welding in the step 4) and the step 6) are as follows: selecting a 304 stainless steel welding wire of phi 2, and carrying out argon arc welding under the welding conditions of a welding voltage of 220V and a welding current of 100-120A and introducing 10-15L/min of air flow.
The pressure test in the step 6) is specifically operated as follows: and performing a pressure test on the repaired combustion chamber cylinder under the conditions that a test medium is pure water, the pressure is 5MPa and the time is 10min, wherein the repaired combustion chamber cylinder is required to have no deformation and no leakage.
Compared with the prior art, the invention has the beneficial effects that:
the combustion chamber cylinder is divided into a lining, a shell, a water inlet flange, a water outlet flange, a water inlet pipe, a water outlet pipe, a first water ring, a second water ring and the like. Then, according to all the ring grooves distributed along the axial direction on the surface of the lining, processing out the corresponding ring groove compensation rings; and the igniter position compensation ring matched with the igniter mounting position is processed. At the same time, the shell is divided into three lobes. After the operation is finished, assembling and welding the ring groove compensating ring and the compensating ring at the igniter on the lining to form a lining assembly; then carrying out thermal sizing on the split shell and the lining component together; since the annular groove compensation ring can enlarge the size of the lining assembly, in order to compensate the missing of the welding seam, the outer shell and the lining assembly are welded together by matching the compensation block and combining argon arc welding and vacuum brazing. After ring channel compensating ring and some firearm department compensating ring are gone up in the assembly, played fine promotion effect to the intensity and the reliability of lining subassembly, welded water inlet flange, play water flange, some firearm mount pad again to and parts such as inlet tube, outlet pipe, first water ring, second water ring, in order to accomplish the holistic assembly of combustion chamber barrel. The annular compensation ring and the compensation structure at the igniter compensation ring pair lining part and the igniter part are used, and finally, the product performance is verified through a pressure test, so that the problem that a combustion chamber cylinder product repaired through the compensation structure has no leakage and bulge within 30min under the pressure of 5MPa is solved, namely the repairing method provided by the invention is feasible and effective in operation.
Drawings
FIG. 1 is a schematic flow chart of a combustion chamber barrel repairing method based on a compensation structure according to the present invention;
FIG. 2 is a schematic structural view of a combustor can of the present invention prior to rework;
FIG. 3 is a cross-sectional view A-A of FIG. 2;
FIG. 4 is a schematic view of the turning of the liner of the present invention;
FIG. 5 is a fragmentary schematic view of the outer shell of the present invention;
FIG. 6 is a schematic view of the machining of the liner of the present invention;
FIG. 7 is a cross-sectional view A-A of FIG. 6;
FIG. 8 is a perspective view of a ring groove compensating ring according to the present invention;
FIG. 9 is a perspective view of the compensating ring at the igniter of the invention;
FIG. 10 is a perspective view of the liner assembly of the present invention;
FIG. 11 is a schematic view of the construction of the liner assembly of the present invention;
FIG. 12 is a schematic view (partially) of the structure of the weld between the split shells by argon arc welding in the present invention;
FIG. 13 is a schematic structural view of an assembly of the present invention;
FIG. 14 is a schematic structural view of a repaired combustor can of the present invention;
FIG. 15 is a cross-sectional view A-A of FIG. 14;
FIG. 16 is a schematic view of the welding of the igniter mount of the invention;
in the figure, 1-shell, 2-inlet pipe, 3-outlet pipe, 4-first water ring, 5-second water ring, 6-inner liner, 7-inlet flange, 8-outlet flange, 9-igniter mounting seat, 10-ring groove compensation ring, 11-igniter position compensation ring and 12-compensation block.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.
The terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The invention provides a combustion chamber barrel repairing method based on a compensation structure, which comprises the following steps of 1) removing 5 a water inlet pipe 2 and a water outlet pipe 3 on a shell 1, a first water ring 4 and a second water ring, then lathing off a lining 6 and an end face compensation ring in a pressure ring groove between two end faces of the shell 1 and the lining 6, reserving the shell 1, polishing and removing a water inlet flange 7 and a water outlet flange 8, finally finely boring an igniter mounting hole on the shell 1, and equally dividing the shell 1 into three halves along the circumferential direction.
2) After the materials are coiled into the cylindrical part again, a through hole penetrating the length of the cylindrical part is roughly drilled by a boring and milling machine, then step holes are respectively lathed at two ends of the cylindrical part, then chucks are installed at two ends, then an outer surface and a ring groove are finely lathed, and finally the outer arc surface of the partition wall of the ring groove is milled, so that the lining 6 is prepared; cutting a sheet material on line to form an inner hole and an outer circle, and then polishing to obtain an end face compensation ring; since the lining 6 and the end compensating ring are welded to the product before, and the lathe machining is difficult to remove and causes damage, the lining 6 and the end compensating ring need to be manufactured again.
Milling the blank into strips with different lengths, and then rolling the strips into circular arcs after vacuum annealing to obtain the annular groove compensating ring 10; turning an inner hole and an outer circle on the rough material, and then linearly cutting a cambered surface which is matched with the outer surface of the igniter on the inner lining to obtain a compensation ring 11 at the igniter;
wherein the strips of different lengths are adapted to the annular grooves at different positions on the liner, respectively.
3) Assembling two ring groove compensating rings 10 into corresponding ring grooves on the inner liner 6 in a group by ring along the axial direction of the inner liner 6, and assembling the compensating ring 11 at the igniter to an igniter mounting position on the inner liner 6 to obtain a liner assembly; and then, putting the lining assembly into a furnace for vacuum brazing, performing finish machining on the lining assembly after the vacuum brazing is finished, and then milling a boss at the igniter matched with the igniter mounting hole.
4) Putting the split shell and the lining component into a furnace together for thermal sizing so as to ensure that the split shell is attached to the lining component; after the thermal correction is finished, welding the welding seams between the split shells by using argon arc welding, then welding the split shells by using vacuum brazing and reinforcing the argon arc welding seams at the igniter; after welding, the outer circle of the shell 1 is finished through turning, and then the water inlet flange 7 and the water outlet flange 8 are assembled on the shell 1 and welded together through argon arc welding; and finally, welding the igniter mounting seat 9 on the shell 1 through argon arc welding to obtain an assembly.
5) And (3) firstly, finely turning the inner surface and the pressure ring groove of the assembly, then assembling the end surface compensation ring, and then putting the assembly into a furnace for vacuum brazing.
6) Welding the water inlet pipe 2, the water outlet pipe 3, the first water ring 4 and the second water ring 5 to corresponding positions on the shell 1 by argon arc welding to obtain a repaired combustion chamber cylinder body; and then carrying out a 5MPa pressure test on the repaired combustion chamber cylinder, if the repaired combustion chamber cylinder passes the test, finishing the repair, and if the repaired combustion chamber cylinder does not pass the test, carrying out the operation until the repaired combustion chamber cylinder passes the test.
The combustor cylinder is divided into a lining 6, a shell 1, a water inlet flange 7, a water outlet flange 8, a water inlet pipe 2, a water outlet pipe 3, a first water ring 4, a second water ring 5 and the like. Then, according to all the ring grooves distributed along the axial direction on the surface of the lining 1, a corresponding ring groove compensation ring 10 is processed; and, the igniter position compensation ring 11 corresponding to the igniter mounting portion is processed. At the same time, the housing 1 is divided into three lobes. After the above operations are completed, the ring groove compensating ring 10 and the igniter compensating ring 11 are assembled and welded to the liner 6 to form a liner assembly; then carrying out thermal sizing on the split shell 1 and the lining component together; since the annular groove compensation ring 10 enlarges the size of the lining assembly, the shell 1 and the lining assembly are welded together by matching the compensation blocks 12 and combining argon arc welding and vacuum brazing in order to compensate for the lack of welding seams. After assembling the ring slot compensation ring 10 and the igniter position compensation ring 11, the strength and reliability of the lining assembly are well improved, and then the water inlet flange 7, the water outlet flange 8, the igniter mounting seat 9, the water inlet pipe 2, the water outlet pipe 3, the first water ring 4, the second water ring 5 and other parts are welded to complete the whole assembly of the combustion chamber cylinder. Finally, product performance verification is carried out through a pressure test, and the problem that the combustion chamber cylinder product repaired through the compensation structure has no leakage bulge within 30min under the pressure of 5MPa is solved, namely the repairing method provided by the invention is feasible and effective in operation.
Further, the specific operation of step 1) is as follows: cutting off the water inlet pipe 2 and the water outlet pipe 3 on the shell 1 along the argon arc welding seam through pliers processing, and then polishing and disassembling the first water ring 4 and the second water ring 5 to avoid the water inlet flange 7 and the water outlet flange 8 from being damaged by collision in the disassembling process; then taking out the shell 1 through turning, wherein the wall thickness of the shell 1 is required to be ensured not to be less than 4mm during the turning; then, the water inlet flange 7 and the water outlet flange 8 are disassembled by clamping, polishing and chamfering treatment are carried out at the welding seam of the water inlet flange 7 and the water outlet flange 8; and finally, supporting by using a V-shaped cushion block, finely boring a mounting hole at the position of an igniter on the shell 1, and dividing the shell 1 into three parts along three argon arc welding lines to obtain the split shell. If the shell 1 is manufactured by three split shells through argon arc welding in the preorder step, finding the seam removing treatment of the argon arc welding in the previous step; if the housing 1 in the preceding step is a whole piece, the housing 1 is trisected with 120 ° as a dividing angle.
Further, the vacuum annealing in the step 2) specifically comprises the following operations: and flatly placing the strips with different lengths on a workbench, loading into a vacuum furnace, heating to 550 ℃, inflating and cooling to 65 ℃, and discharging.
Wherein, the step 3) of finishing the shape of the lining component comprises the following specific operations: the outer circle of the lining component is firstly subjected to finish turning treatment, and then the lining component is placed on a machining center to mill the outer arc surface of the partition wall between the lug bosses of the two igniters.
The specific operation after finishing hot alignment in the step 4) is as follows: after the inner wall of the split shell is preset with adhesive tape brazing filler metal, the split shell is hooped on the lining component by a bridle and three welding openings among the lining component are adjusted to be uniform; assembling compensation blocks 12 in the three welding openings to compensate for weld joint loss, and then welding three split weld joints in a segmented priming and segmented welding mode through argon arc welding; and (5) coating and injecting brazing filler metal again to the unsaturated part of the welding seam, and putting the welding seam into a furnace for vacuum brazing.
The concrete operation after the welding is finished is as follows: firstly, the excircle of the assembly is finely finished by turning to be matched with a water inlet flange 7 and a water outlet flange 8; then assembling a water inlet flange 7 at the upper end of the assembly, assembling a water outlet flange 8 at the lower end of the assembly and fixing the assembly through spot welding; wherein, the positioning columns are used for tensioning the water inlet flange 7 and the water outlet flange 8, and then the full welding is carried out.
The specific operation of vacuum brazing in the step 3), the step 4) and the step 5) is as follows: and (3) conveying the assembled workpiece and the tool into a vacuum furnace, heating to 1000-1050 ℃, keeping the pressure at 120-150 Pa, keeping the temperature for 60min, cooling to 700 ℃, closing the pressure, vacuum-cooling to 600 ℃, cooling to 65 ℃ along with the furnace, and discharging.
And after the vacuum brazing in the step 5) is finished, checking the compactness of the welding seam through a sealing test, if the welding seam is qualified, carrying out the next step, and if the welding seam is not qualified, carrying out brazing repair and carrying out the sealing test again until the welding seam is qualified.
The operating parameters of argon arc welding in the step 4) and the step 6) are as follows: selecting a 304 stainless steel welding wire of phi 2, and carrying out argon arc welding under the welding conditions of a welding voltage of 220V and a welding current of 100-120A and introducing 10-15L/min of air flow.
The pressure test in the step 6) is specifically operated as follows: and performing a pressure test on the repaired combustion chamber cylinder under the conditions that a test medium is pure water, the pressure is 5MPa and the time is 10min, wherein the repaired combustion chamber cylinder is required to have no deformation and no leakage.
Examples
The embodiment provides a method for repairing a combustion chamber cylinder based on a compensation structure, as shown in fig. 1, which includes the following steps:
the first step is as follows: the water inlet pipe 2 and the water outlet pipe 3 on the shell 1, the first water ring 4 and the second water ring 5 are taken off, the lining 6 is machined off by a lathe, the water inlet flange 7 and the water outlet flange 8 are ground by a clamp, and the shell 1 is divided into three sections by an upper boring and milling machine.
The second step is that: the inner liner 6 is reworked and the ring groove compensation ring 10 and the compensation ring at igniter 11 are machined.
The third step: and assembling the ring groove compensating ring 10 and the igniter position compensating ring 11 and welding the ring groove compensating ring and the igniter position compensating ring at corresponding positions on the lining 6 through vacuum brazing, thereby completing the welding of the lining assembly, and then finely turning the appearance of the lining assembly and milling a boss. The vacuum brazing in the third step comprises the following specific operations: and (3) mounting the mounted lining assembly on a tool, placing the tool on a workbench, loading the tool into a vacuum furnace, heating to 1030-1040 ℃, keeping the temperature at 120-150 Pa, keeping the temperature for 60 minutes, cooling to 700 ℃, closing the pressure, carrying out vacuum cooling to 600 ℃, cooling to 65 ℃ along with the furnace, and discharging.
The fourth step: putting the split shell 1 and the lining component into a furnace together to shape the shell 1 so as to ensure that the shell 1 is attached to the lining component; welding seams between the split shells by using argon arc welding, then carrying out vacuum brazing on the shells 1, reinforcing the welding seams at the igniter, finishing the outer circle of the shell 1 on a lathe, assembling a water inlet flange 7 and a water outlet flange 8, and carrying out argon arc welding on the water inlet flange 7 and the water outlet flange 8; brazing filler metal is preset on the igniter mounting seat 9, and the igniter mounting seat 9 is welded on the shell 1 through argon arc welding to obtain an assembly. Wherein, the vacuum brazing in the fourth step comprises the following specific operations: and (3) mounting the mounted lining component and the housing 1 on a tool, placing the tool on a workbench, loading the tool into a vacuum furnace, heating to 1015-1025 ℃, carrying out partial pressure of 120-150 Pa, keeping the temperature for 60 minutes, cooling to 700 ℃, closing the partial pressure, carrying out vacuum cooling to 600 ℃, cooling to 65 ℃ along with the furnace, and discharging. The fourth step of argon arc welding of the outer shell comprises the following specific operations: wrapping the shell 1 on the lining component, matching with a compensation block 12 to compensate for weld joint loss, selecting a 304 stainless steel welding wire with phi 2, welding three split weld joints by argon arc welding under the welding voltage of 220V and the welding current of 100A-120A and the welding parameters of 10L/min-15L/min of air flow, and performing segmented bottoming and segmented welding, and finally performing full-length welding and cover face. The concrete operations of the argon arc welding water inlet flange 7, the water outlet flange 8 and the igniter mounting seat 9 are as follows: the water inlet flange 7 and the water outlet flange 8 are assembled on the outer circles of the two ends of the shell 1, the igniter mounting seat 9 is mounted on the shell as shown in figure 16, and argon arc welding is carried out in batches by adopting the welding parameters.
The fifth step: and (4) turning the inner shape of the assembly on a lathe, assembling an end face compensation ring, putting into a furnace for vacuum brazing, checking a welding line in a sealing test, and performing brazing filler metal supplement if the assembly is not qualified. Wherein, the vacuum brazing in the fifth step comprises the following specific operations: and (3) mounting the cylinder assembly with the end face compensation ring on a tool, placing the cylinder assembly on a workbench, loading the cylinder assembly into a vacuum furnace, heating to 1000-1010 ℃, keeping the temperature for 60 minutes at a partial pressure of 120-150 Pa, cooling to 700 ℃, closing the partial pressure, carrying out vacuum cooling to 600 ℃, cooling to 65 ℃ along with the furnace, and discharging.
And a sixth step: argon arc welds inlet tube 2, outlet pipe 3, first water ring 4 and second water ring 5, carries out 5MPa pressure test after the welding. The operation of argon arc welding in the sixth step is as follows: vertically placing each part on a tool, installing a first water ring 4 and a second water ring 5 as shown in fig. 14, selecting proper current and welding wires by an operator according to experience, continuously using the welding parameters, and then performing argon arc welding; then installing a water inlet pipe 2 and a water outlet pipe 3, and performing argon arc welding in the same way; and performing a pressure test after all welding is completed.
A combustion chamber cartridge that has not been reworked, as shown in fig. 2 and 3. The first step and the second step can be carried out simultaneously in the implementation process, and the specific processing steps are as follows:
first, the combustion chamber cylinder is disassembled. The water inlet pipe 2 and the water outlet pipe 3 are cut along the original argon arc welding seam, and the first water ring 4 and the second water ring 5 are removed and disassembled by clamping, processing and polishing. Wherein, the water inlet flange 7 and the water outlet flange 8 are not allowed to be damaged by collision in the disassembly process, as shown in the dotted line in figure 2. The lining 6 is removed by turning, and the welding seams of the water inlet flange 7 and the water outlet flange 8 are chamfered. The chamfering operation is the preprocessing of argon arc welding, so that the argon arc welding is convenient to weld thoroughly, and the strength is increased. During the turning process, it is first required to ensure that the wall thickness of the processed shell 1 is not less than 4mm, as shown in fig. 4. And then the water inlet flange 7 and the water outlet flange 8 are disassembled in a clamping and polishing mode. The shell 1 is placed on a V-shaped cushion block, igniter mounting holes are finely bored, then the shell 1 is divided into three lobes along three argon arc welding lines, the three lobes are shown in the dotted line position in fig. 5, namely, the angle is 120 degrees as a dividing angle, and two igniter mounting holes are covered in the middle position by one lobe of the shell 1.
The liner assembly is then machined and welded to form the liner assembly. And turning the reference by rough drilling, then installing a chuck, then finely turning the excircle and the groove, finally milling by a machining center, and finishing machining as shown in figures 6 and 7. Machining a ring groove compensation ring 10 and an igniter compensation ring 11: placing the blank in a processing center for milling, performing vacuum annealing, and rolling, as shown in FIG. 8; the rough material is firstly turned into an inner circle and an outer circle, and then is linearly cut into an arc surface, as shown in figure 9.
Subsequently, two ring groove compensating rings 10 of the same size are assembled in each ring groove in the axial direction of the liner 6, the compensating ring 11 at the igniter is assembled at the position of the igniter, and the assembly is vacuum brazed in a furnace after the assembly is completed, thereby obtaining a liner assembly, as shown in fig. 10 and 11. And after the vacuum brazing is finished, performing finish machining on the lining assembly, firstly performing finish turning on the excircle of the lining assembly, and then, feeding the machining center to mill the outer arc surface of the lining assembly.
Because the original shell 1 and the improved lining component have different sizes, the original shell 1 needs to be subjected to thermal correction. After thermal correction, firstly, brazing filler metal is pasted on the surface of each split shell for spot welding and fixing, the shell 1 is assembled to the lining component, three welding notches between the three split shells are adjusted, after the gap is controlled to be uniform, the upper tool is clamped, and argon arc welding operation is performed. The compensation blocks 12 are assembled among the welding slits to compensate for the lack of the welding seams, and then the split welding seams on the three welding slits are welded by argon arc welding in an operation mode of sectional backing and sectional welding, as shown in fig. 12. And after the argon arc welding is finished, coating brazing filler metal again at the unsaturated part of the front welding line, and eliminating argon arc welding stress while performing furnace vacuum brazing. This is to ensure that the outer shell 1 is tightly connected to the inner liner assembly for heat dissipation. The processing after the welding is concretely as follows: firstly, the outer circle is machined and repaired, then the water inlet flange 7 and the water outlet flange 8 are assembled and fixed through spot welding. Wherein, the water inlet flange 7 and the water outlet flange 8 are tightened by a positioning column with the length 955, and then are fully welded; finally, brazing filler metal is preset on the igniter mount 9, the igniter mount 9 is assembled on the housing 1, and argon arc welding is performed, thereby obtaining an assembly, as shown in fig. 13, 15.
After the operation is finished, the inner mold and the pressure ring groove of the assembly are finish-turned on a lathe; and (4) presetting brazing filler metal in the pressure ring groove, assembling the upper end face compensation ring, compressing by using a tool, and then putting into a furnace for vacuum brazing. In addition, after vacuum brazing, the leakage of the weld joint is checked by a sealing test in which 0.5MPa of air pressure is introduced. If leakage occurs, the brazing filler metal repairing operation is needed. The pressure ring groove is located at the large end and the small end of the joint of the lining assembly and the shell 1, and an end face compensation ring is installed at the position of the pressure ring groove as shown in fig. 13, so that the vacuum brazing area is increased, and the vacuum brazing strength is improved.
Finally, the water inlet pipe 2, the water outlet pipe 3, the first water ring 4 and the second water ring 5 are welded to the corresponding positions on the shell 1 through argon arc welding by using the tool positioning size, and accordingly the repaired combustion chamber cylinder is obtained, as shown in fig. 14 and 15. And 5MPa pressure test is carried out, and the barrel of the combustion chamber is required to have no leakage bulge within 30 min.
The invention is not limited to the examples, and any equivalent changes to the technical solution of the invention by a person skilled in the art after reading the description of the invention are covered by the claims of the invention.
Claims (9)
1. A combustion chamber cylinder repairing method based on a compensation structure is characterized by comprising the following steps,
1) taking off a water inlet pipe and a water outlet pipe on the shell, a first water ring and a second water ring, then turning off the lining and an end face compensation ring in a pressing ring groove between two end faces of the shell and the lining, reserving the shell, polishing and taking off a water inlet flange and a water outlet flange, finally finely boring an igniter mounting hole on the shell, and then equally dividing the shell into three pieces along the circumferential direction;
2) after the materials are coiled into a cylindrical part again, a through hole penetrating the length of the cylindrical part is roughly drilled by a boring and milling machine, then step holes are respectively lathed at two ends of the cylindrical part, then chucks are installed at two ends, then an outer surface and a ring groove are finely lathed, and finally an outer arc surface of a partition wall of the ring groove is milled to obtain the lining; cutting a sheet material on line to form an inner hole and an outer circle, and then polishing to obtain an end face compensation ring;
milling the blank into strips with different lengths, and then rolling the strips into circular arcs after vacuum annealing to obtain the annular groove compensating ring; turning an inner hole and an outer circle on the rough material, and then linearly cutting a cambered surface which is matched with the outer surface of the igniter on the inner lining to obtain a compensation ring at the igniter;
the strips with different lengths are respectively adapted to the annular grooves at different positions on the liner;
3) assembling two ring groove compensating rings into corresponding ring grooves on the inner liner one by one along the axial direction of the inner liner, and assembling the compensating rings at the igniter to the igniter mounting position on the inner liner to obtain a liner assembly; then, putting the lining assembly into a furnace for vacuum brazing, performing finish machining on the lining assembly after the vacuum brazing is finished, and then milling a boss at the igniter matched with the igniter mounting hole;
4) putting the split shell and the lining component into a furnace together for thermal sizing so as to ensure that the split shell is attached to the lining component; after the thermal correction is finished, welding the welding seams between the split shells by using argon arc welding, then welding the split shells by using vacuum brazing and reinforcing the argon arc welding seams at the igniter; after welding, the outer circle of the shell is finished through turning, and then the water inlet flange and the water outlet flange are assembled on the shell and welded together through argon arc welding; finally, welding the igniter mounting seat on the shell through argon arc welding to obtain an assembly;
5) firstly, finish turning the inner surface and the pressure ring groove of the assembly, then assembling the end surface compensation ring, and then putting the assembly into a furnace for vacuum brazing;
6) welding the water inlet pipe, the water outlet pipe, the first water ring and the second water ring to corresponding positions on the shell by using argon arc welding to obtain a repaired combustion chamber cylinder body; and then carrying out a 5MPa pressure test on the repaired combustion chamber cylinder, if the repaired combustion chamber cylinder passes the test, finishing the repair, and if the repaired combustion chamber cylinder does not pass the test, carrying out the operation until the repaired combustion chamber cylinder passes the test.
2. The combustor can rework method based on compensation structure as claimed in claim 1, wherein the specific operation of step 1) is: cutting off a water inlet pipe and a water outlet pipe on the shell along an argon arc welding seam through pliers processing, and then polishing and disassembling the first water ring and the second water ring to avoid the water inlet flange and the water outlet flange from being damaged by collision in the disassembling process;
then taking out the shell through turning, wherein the wall thickness of the shell is required to be ensured not to be less than 4mm during turning;
then, the water inlet flange and the water outlet flange are disassembled by clamping, polishing and chamfering treatment are carried out at the welding seam of the water inlet flange and the water outlet flange;
and finally, supporting by using a V-shaped cushion block, finely boring a mounting hole at the position of an igniter on the shell, and dividing the shell into three parts along three argon arc welding lines to obtain the split shell.
3. The combustion chamber barrel repairing method based on the compensation structure, as recited in claim 1, wherein the specific operation of vacuum annealing in step 2) is as follows: and flatly placing the strips with different lengths on a workbench, loading into a vacuum furnace, heating to 550 ℃, inflating and cooling to 65 ℃, and discharging.
4. The compensation structure-based combustor can rework method of claim 1, wherein the specific operations of finishing the profile of the liner assembly in step 3) are: the outer circle of the lining component is subjected to finish turning treatment, and then the lining component is placed on a machining center to mill the outer arc surface of the partition wall between the bosses at the two igniters.
5. The combustion chamber barrel repairing method based on the compensation structure, as recited in claim 1, wherein the specific operation after the thermal correction in the step 4) is: after the inner wall of the split shell is preset with adhesive tape brazing filler metal, the split shell is hooped on the lining component by a bridle and three welding openings among the lining component are adjusted to be uniform; assembling compensation blocks in the three welding slits to compensate for weld joint loss, and then welding three split weld joints in a segmented priming and segmented welding mode through argon arc welding; coating and injecting brazing filler metal again to the unsaturated part of the welding seam, and putting the welding seam into a furnace for vacuum brazing;
the concrete operation after the welding is finished is as follows: firstly, the outer circle of the shell matched with the water inlet flange and the water outlet flange is precisely machined by turning, and then the water inlet flange is assembled at the upper end of the shell, the water outlet flange is assembled at the lower end of the shell and fixed by spot welding; the water inlet flange and the water outlet flange are tightened by using the positioning columns and then are fully welded; and finally, presetting brazing filler metal on the igniter mounting seat, and welding the igniter mounting seat on the shell through argon arc welding to obtain a combined piece.
6. The combustion chamber barrel repairing method based on the compensation structure, as recited in claim 1, wherein the specific operations of vacuum brazing in the steps 3), 4) and 5) are as follows: and (3) conveying the assembled workpiece and the tool into a vacuum furnace, heating to 1000-1050 ℃, keeping the pressure at 120-150 Pa, keeping the temperature for 60min, cooling to 700 ℃, closing the pressure, vacuum-cooling to 600 ℃, cooling to 65 ℃ along with the furnace, and discharging.
7. The repair method of the combustion chamber cylinder based on the compensation structure, according to the claim 1 or 6, is characterized in that after the vacuum brazing in the step 5) is completed, the compactness of the welding seam is checked through a sealing test, if the compactness is checked, the next step is carried out, and if the compactness is not checked, the brazing is supplemented, and the sealing test is carried out again until the compactness is qualified.
8. The combustion chamber cylinder repairing method based on the compensation structure as claimed in claim 1, wherein the operating parameters of argon arc welding in the steps 4) and 6) are as follows: selecting a 304 stainless steel welding wire of phi 2, and carrying out argon arc welding under the welding conditions of a welding voltage of 220V and a welding current of 100-120A and introducing 10-15L/min of air flow.
9. The method for repairing a combustion chamber cylinder based on a compensation structure, according to claim 1, wherein the pressure test in the step 6) is specifically operated as follows: and performing a pressure test on the repaired combustion chamber cylinder under the conditions that a test medium is pure water, the pressure is 5MPa and the time is 10min, wherein the repaired combustion chamber cylinder is required to have no deformation and no leakage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110914470.9A CN113664456B (en) | 2021-08-10 | 2021-08-10 | Combustion chamber barrel repairing method based on compensation structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110914470.9A CN113664456B (en) | 2021-08-10 | 2021-08-10 | Combustion chamber barrel repairing method based on compensation structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113664456A true CN113664456A (en) | 2021-11-19 |
| CN113664456B CN113664456B (en) | 2022-09-06 |
Family
ID=78542144
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110914470.9A Active CN113664456B (en) | 2021-08-10 | 2021-08-10 | Combustion chamber barrel repairing method based on compensation structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113664456B (en) |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1995002751A1 (en) * | 1993-07-14 | 1995-01-26 | United Technologies Corporation | Method for repairing a combustion chamber assembly |
| CA2512417A1 (en) * | 2004-07-27 | 2006-01-27 | General Electric Company | Method for repair and replacement of combustor liner panel |
| EP2113634A2 (en) * | 2008-05-02 | 2009-11-04 | United Technologies Corporation | Gas turbine engine case with replaced flange and method of repairing the same using cold metal transfer |
| CN204493009U (en) * | 2015-03-13 | 2015-07-22 | 华中科技大学 | A kind of For Single-chamber Double-thrust Solid Rocket Motors firing chamber |
| CN108343987A (en) * | 2018-01-31 | 2018-07-31 | 中国民航大学 | Residual stress removal device after a kind of REPAIR WELDING of aeroengine combustor buring room |
| US20190084894A1 (en) * | 2017-09-19 | 2019-03-21 | General Electric Company | Methods for repairing composite cylinders |
| CN109848659A (en) * | 2019-03-08 | 2019-06-07 | 任耀文 | A kind of axisymmetric nozzle integral welding method |
| CN110014264A (en) * | 2019-05-23 | 2019-07-16 | 国家能源投资集团有限责任公司 | Feed pump cylinder sealing surface method for repairing and mending |
| CN110732795A (en) * | 2019-11-19 | 2020-01-31 | 中国航发贵州黎阳航空动力有限公司 | aircraft engine exhaust casing welding method |
| CN110802337A (en) * | 2019-12-09 | 2020-02-18 | 西安航天发动机有限公司 | Method for sealing and welding end face of annular copper-steel brazing part with sandwich structure |
| CN111633374A (en) * | 2020-06-01 | 2020-09-08 | 湖北三江航天江北机械工程有限公司 | Method for repairing damage inside attitude control engine combustion chamber shell |
-
2021
- 2021-08-10 CN CN202110914470.9A patent/CN113664456B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1995002751A1 (en) * | 1993-07-14 | 1995-01-26 | United Technologies Corporation | Method for repairing a combustion chamber assembly |
| CA2512417A1 (en) * | 2004-07-27 | 2006-01-27 | General Electric Company | Method for repair and replacement of combustor liner panel |
| EP2113634A2 (en) * | 2008-05-02 | 2009-11-04 | United Technologies Corporation | Gas turbine engine case with replaced flange and method of repairing the same using cold metal transfer |
| CN204493009U (en) * | 2015-03-13 | 2015-07-22 | 华中科技大学 | A kind of For Single-chamber Double-thrust Solid Rocket Motors firing chamber |
| US20190084894A1 (en) * | 2017-09-19 | 2019-03-21 | General Electric Company | Methods for repairing composite cylinders |
| CN108343987A (en) * | 2018-01-31 | 2018-07-31 | 中国民航大学 | Residual stress removal device after a kind of REPAIR WELDING of aeroengine combustor buring room |
| CN109848659A (en) * | 2019-03-08 | 2019-06-07 | 任耀文 | A kind of axisymmetric nozzle integral welding method |
| CN110014264A (en) * | 2019-05-23 | 2019-07-16 | 国家能源投资集团有限责任公司 | Feed pump cylinder sealing surface method for repairing and mending |
| CN110732795A (en) * | 2019-11-19 | 2020-01-31 | 中国航发贵州黎阳航空动力有限公司 | aircraft engine exhaust casing welding method |
| CN110802337A (en) * | 2019-12-09 | 2020-02-18 | 西安航天发动机有限公司 | Method for sealing and welding end face of annular copper-steel brazing part with sandwich structure |
| CN111633374A (en) * | 2020-06-01 | 2020-09-08 | 湖北三江航天江北机械工程有限公司 | Method for repairing damage inside attitude control engine combustion chamber shell |
Non-Patent Citations (1)
| Title |
|---|
| 夏伦初: "燃气轮机燃烧室的焊修", 《机械工人热加工技术资料》 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113664456B (en) | 2022-09-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113210898B (en) | Composite tool for welding jacket section of thrust chamber spray pipe and welding process thereof | |
| US7441686B2 (en) | Friction stir welding apparatus | |
| US8448335B2 (en) | Method of manufacturing a wall structure and a machining tool | |
| EP1174209B1 (en) | Method of repairing combustion chamber liners | |
| CN110340528B (en) | Welding method for airborne small rocket shell | |
| CN110977338A (en) | Integration method of tailor-welded structure air inlet casing | |
| EP0921892B1 (en) | Linear friction welding process for making wheel rims | |
| CN106238939B (en) | The supporting tool and welding method of guide vane nozzle in a kind of hydraulic jet propulsion system | |
| CN107695137A (en) | Straightening method and fixture are deformed after a kind of annular flame tube high temperature enamel paint | |
| CN110202320A (en) | Composite tooling and thrust chamber preparation process for thrust chamber preparation process | |
| CN113664456B (en) | Combustion chamber barrel repairing method based on compensation structure | |
| CN114871676A (en) | Welding fixture for mounting seat on wall surface of combustion chamber casing and welding deformation control method | |
| KR20040048858A (en) | Methods for manufacturing a nozzle box assembly for a steam turbine | |
| CN110732795B (en) | Welding method for aero-engine exhaust casing | |
| CN111805078B (en) | Manufacturing method of 300 MW-level heavy-duty gas turbine nozzle swirler assembly | |
| CN209811495U (en) | Composite tool for welding thrust chamber | |
| US20030150899A1 (en) | Process for reconditioning worn or out-of-spec components | |
| CN113523735B (en) | Preparation method of injector | |
| CN113787307B (en) | Machining method for workpiece of pipe expanding and contracting section | |
| CN111015047B (en) | Welding tool and welding method for combustion chamber shell of gas turbine | |
| CN113352062B (en) | Preparation method of combustion chamber cylinder | |
| KR100477519B1 (en) | A jig for repairing and manufacturing a clamshell | |
| JPH04123865A (en) | Manufacture of combustor liner, depositing method and depositing device | |
| CN113664399B (en) | Processing method of K-shaped baffle cavity | |
| CN115846854A (en) | Special welding device and welding method for fuel tank of airplane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |