Method of processing a flame tube assembly for an aeroengine

Abstract

The application discloses an aero-engine flame tube assembly processing method and belongs to the technical field of aero-engine processing. The method comprises the following steps: processing the gas film holes on the head ring of the flame tube assembly and the gas film holes on the bevel; welding the head ring and the inner wall of the flame tube assembly; converting the axial reference and the central reference of the part; converting the angular reference of the blank to the angular reference of the machined part; taking the angular hole on the mounting edge as the reference to process the mounting edge lace; processing the lace on the mounting edge by using the wire cutting process; processing the ring groove gas film hole by high-speed electric spark machining; supporting the second supporting surface by using the second supporting clamp to process the gas film holes on the annular groove; spraying the inner wall; and processing the inner wall mixing hole by laser. The application has the advantages of reducing the risk of deformation and size out-of-tolerance of the flame tube assembly in processing.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft engine processing, in particular to an aircraft engine flame tube assembly processing method. BACKGROUND

[0002] The flame tube assembly is an important part of the combustion chamber of the aircraft engine, mainly serving to organize combustion and maintain a stable flame source. The size of the part is thin in wall thickness and complex in profile, and is formed by welding several flame tube single pieces together, which needs to go through the welding process and subsequent machining to ensure the size. The processing of such parts mainly has the following difficulties: 1. After electron beam welding, the deformation is large, the conversion error between the axial machining reference of the part, and the large deviation of the part head boss machining will exist, and the parallelism will be out of tolerance; 2. The deformation of the part supporting surface is large, which will cause the deformation of the reference surface and the length out of tolerance during machining; 3. The part is poor in rigidity, which will cause the vibration of the tool during machining; 4. After welding and aging, the deformation of each installation edge of the part is about 0.5-0.6mm, which increases the difficulty of part processing and makes it difficult to ensure the processing quality of the part; 5. The number of gas film holes is large, and the part deforms greatly after processing.

[0003] Figure 1 A cross-sectional structure diagram of a flame tube assembly for an aircraft engine is shown. The inner ring part 100 of the flame tube is an annular part with a wall thickness of 1.5mm. The cross-sectional structure includes a front mounting edge 1, a head flat and boss 2, a weld 3, an inner wall 4, and an annular groove 5. There are multiple gas film holes (not shown in the figure) on the head flat and boss 2 and the inner wall 4. The size requirements of the inner ring part 100 of the flame tube include parallelism of 0.05 and perpendicularity of 0.05, which means that the size precision of the inner ring part 100 of the flame tube is high. Due to the thin wall of the part, the need for welding and heat treatment process during processing, and the large number of gas film holes, the part reference surface is prone to deformation, which often causes a series of size deviations related to the reference surface. The existing processing process relies too much on the operation level of skilled personnel and the on-site processing environment, has great limitations, and is difficult to control the deformation and processing deviation of the part from the essence. SUMMARY

[0004] The present application provides an aircraft engine flame tube assembly processing method to solve the technical problem of easy deformation and size out of tolerance of the flame tube assembly during processing.

[0005] According to one aspect of the present application, an aircraft engine flame tube assembly processing method is provided, comprising the following steps:

[0006] S100, processing the gas film holes on the head ring of the flame tube assembly and the gas film holes on the bevel;

[0007] S200, welding the head ring and the inner wall of the flame tube assembly;

[0008] S300, the boss surface is processed to form the first supporting surface, the mounting edge is processed to form the second supporting surface, and the axial reference and center reference of the parts are converted to avoid deformation of the mounting edges and inner holes before and after welding.

[0009] The impact of part finishing;

[0010] S400, converting the angular datum of the blank and milling the boss, machining the angular hole on the mounting edge, and realizing the conversion from the angular datum of the blank to the angular datum of the machined part;

[0011] S500, based on the angle hole on the installation side, processes the lace on the installation side using wire cutting technology.

[0012] Manual edge forming lace;

[0013] S600, high-speed EDM machining of ring groove air film holes, using the second support fixture to support the second support surface,

[0014] The air film holes on the annular groove are processed to ensure the ventilation and heat dissipation function of the annular groove.

[0015] S700, spraying treatment on the inner wall: spraying thermal barrier coating on the inner wall surface, plasma spraying, material

[0016] It is aluminum silicon coating;

[0017] S800, laser processing of inner wall mixing holes: using the third support fixture, set the angle pin for the diagonal hole, support the second support surface, in order to find the center reference outer circle part, process the mixing holes of different sizes on the inner wall coating part.

[0018] mixed hole;

[0019] S900, laser processing of inner wall cooling holes: using a second support fixture, setting angle pins for the diagonal holes to support the mounting edge to align the outer circle of the mounting edge, and processing cooling holes of different sizes on the inner wall coating area, with the cooling holes and mixing holes staggered.

[0020] Optionally, in step S100, when processing the air film hole, the processing method is adjusted according to the position of the air film hole to avoid the influence of deformation caused by stress change of the part after the part material is removed on the benchmark.

[0021] Optionally, step S100 of processing the air film holes on the head ring and the air film holes on the bevel of the flame tube assembly includes the following steps:

[0022] S110, laser processing head plane gas film hole: find the head plane any large hole as the angular position, and process the gas film hole around the large hole to reduce the deformation of the part after material removal stress change caused by the influence of the reference.

[0023] S120, electric spark processing head plane gas film hole: find the head plane any large hole as the angular position, and process the gas film hole on the head plane.

[0024] Optionally, in step S120, the gas film hole to be processed is close to the mounting edge, and the outlet is the force bearing arc part, and electric spark processing is adopted to reduce the deformation of the part.

[0025] Optionally, step S300 includes the following steps,

[0026] S310, determining the axial reference of the part: coloring the inner wall end face, supporting and pressing the coloring point, processing the boss surface to process the first supporting surface, and the inner wall end face is the axial reference before welding, and the first supporting surface is the axial reference after welding, so as to realize the conversion from the axial reference before welding to the axial reference after welding, and avoid the influence of the deformation of the front and rear end faces on the processing of the part.

[0027]

[0028] S320, converting the axial reference and turning the ring groove: using the first supporting clamp to support the first supporting surface, pressing the part through the screw rod passing through the head hole, aligning the inner hole circle of the inner wall, processing the mounting edge and the ring groove to process the second supporting surface and the center reference, and the second supporting surface is the design axial reference, so as to realize the conversion from the axial reference in processing to the axial reference in design.

[0029] Optionally, step S400 includes the following steps,

[0030] Using the second supporting clamp, supporting the second supporting surface, aligning the mounting edge outer circle, and aligning the uniformly distributed boss to coarsely determine the angle;

[0031] After setting the workpiece coordinate system, pre-programming the milling cutter processing program to mill 0.3mm depth on several uniformly distributed boss holes on the head, then checking whether the pre-milling center hole of each boss is in the center of the boss, if there is deviation, adjusting the workpiece coordinate system and repeating the above steps until the pre-milling center hole of each boss is in the center of the boss.

[0032] Milling the angular hole on the mounting edge and milling the boss surface, and the several uniformly distributed bosses of the blank are the angular reference of the blank, and the angular hole on the mounting edge is the angular reference of the machined part, so as to realize the conversion from the angular reference of the blank to the angular reference of the machined part.

[0033] ​Optionally, in step S600, when the second supporting surface is supported by the second supporting clamp, an angular pin is arranged on the second supporting clamp corresponding to the angular hole to find the outer circle of the mounting edge.

[0034] Optionally, before step S700, a step of polishing the part is further included to remove burrs and flash generated by machining to avoid the excess of the gas film hole and the annular groove.

[0035] Optionally, before step S700, a step of fluorescent inspection is further included to perform fluorescent inspection on the mounting edge and the gas film hole to eliminate crack defects.

[0036] Optionally, after step S900, the following steps are further included,

[0037] Remove the gas film hole splashes and burrs: remove the gas film hole splashes and burrs, use water as a medium, pressurize the cooling hole, and perform light transmission inspection on all holes to remove the excess that may exist in the hole.

[0038] In summary, the present application includes at least one of the following beneficial technical effects:

[0039] 1. By the steps of converting the axial reference and the center reference before and after welding, the part avoids deformation caused by stress concentration during welding, and ensures that each mounting edge and the inner hole maintains stable precision during finishing;

[0040] 2. By the steps of supporting the part by using a special clamp and using a screw to punch and press during machining, the rigidity of the part during machining is significantly enhanced, the tool marks and size deviations caused by unstable clamping or vibration are prevented, and the accuracy and surface quality of the key parts of the part are ensured;

[0041] 3. By the steps of pre-milling and checking the center position of the boss when converting the angular reference of the blank, the angular reference of the blank and the angular reference of the machined part are accurately converted, the machining allowance is avoided or machining error is avoided, and the accuracy requirements of the subsequent angular hole and mounting edge are ensured.

[0042] In addition to the purposes, features and advantages described above, the present application has other purposes, features and advantages. The present application will be further described below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0043] The accompanying drawings, which form a part of this application, are included to provide a further understanding of the application, illustrate preferred embodiments of the application, and assist in the explanation of the application. In the drawings:

[0044] Figure 1 The first supporting clamp for the aero-engine flame tube assembly machining method of the present application is shown schematically.

[0045] Figure 2 The second supporting fixture for the aero-engine flame tube assembly machining method of the application is schematically shown in the figure;

[0046] Figure 3 The third supporting fixture for the aero-engine flame tube assembly machining method of the application is schematically shown in the figure.

[0047] Legend:

[0048] 1. first supporting fixture; 2. second supporting fixture; 3. third supporting fixture. DETAILED DESCRIPTION

[0049] The embodiments of the application are described in detail below with reference to the accompanying drawings, but the application can be implemented in various different ways as defined and covered by the following.

[0050] The embodiments of the application are described in detail below with reference to the accompanying drawings, but the application can be implemented in various different ways as defined and covered by the following. Figures 1-3 The application is further described in detail.

[0051] The embodiments of the application disclose an aero-engine flame tube assembly machining method, comprising the following steps:

[0052] The embodiments of the application disclose an aero-engine flame tube assembly machining method, comprising the following steps:

[0053] S100, machining the gas film holes on the head ring of the flame tube assembly and the gas film holes on the bevel;

[0054] S200, welding the head ring and the inner wall of the flame tube assembly;

[0055] S300, machining the boss surface to form a first supporting surface, machining the mounting edge to form a second supporting surface, and converting the axial reference and the central reference of the part to avoid the influence of the deformation of each mounting edge and each inner hole before and after welding on the machining of the part;

[0056] the machining of the part;

[0057] S400, converting the angular reference of the blank and milling the boss, machining the angular hole on the mounting edge, and realizing the conversion from the angular reference of the blank to the angular reference of the machined part;

[0058] S500, taking the angular hole on the mounting edge as the reference to machine the mounting edge lace, and using the wire cutting process to form the lace on the mounting edge;

[0059] S500, taking the angular hole on the mounting edge as the reference to machine the mounting edge lace, and using the wire cutting process to form the lace on the mounting edge;

[0060] S600, high-speed electric spark machining the annular groove gas film hole, using the second supporting fixture to support the second supporting surface,

[0061] The gas film hole on the annular groove is processed to ensure the ventilation and heat dissipation function of the annular groove.

[0062] S700, spraying treatment is performed on the inner wall: the inner wall profile is sprayed with a thermal barrier coating, plasma spraying is performed, and the material

[0063] is an aluminum-silicon coating;

[0064] S800, laser processing of the inner wall mixing hole: a third supporting clamp is used, an angular pin is arranged on the angular hole, the second supporting surface is supported to find the center reference outer circle position, and the inner wall coating part is processed into mixing holes of different sizes.

[0065] The mixing hole is processed.

[0066] S900, laser processing of the inner wall cooling hole: a second supporting clamp is used, an angular pin is arranged on the angular hole, and the installation edge is supported to find the installation edge outer circle position, and the inner wall coating part is processed into cooling holes of different sizes. The cooling holes are distributed in a staggered manner with the mixing holes.

[0067] In step S100, when the gas film hole is processed, the processing method is adjusted according to the position of the gas film hole to avoid the influence of the deformation of the part caused by the stress change of the part material after material removal on the reference.

[0068] The processing method will affect the heat input and cooling process of the part material. Laser processing is a local heat source processing, which has a small heat affected zone and can accurately remove material, but the heat generated in the local area may cause thermal expansion and stress concentration of the material. Especially for large-area or flat-hole processing, the heat effect of laser processing is small and controllable, which is suitable for such processing. Electric spark machining is a kind of discharge machining, which does not directly act on the material surface through grinding removal, but ablates the material through local discharge. The heat affected zone generated by electric spark machining is relatively small, so it is more suitable for use near the installation edge or in complex-shaped parts. Especially when the part shape is complex or the wall is thin, this processing method can reduce the local stress concentration caused by heat accumulation and avoid deformation caused by thermal expansion. Adjusting the processing method can select the appropriate processing heat source to avoid excessive thermal stress during material removal and maintain the stability of the part shape.

[0069] Specifically, step S100 processes the gas film holes on the head ring of the flame tube assembly and the gas film holes on the bevel includes the following steps:

[0070] S110, laser processing of the head plane gas film hole: the head plane any large hole is found as an angular position, and the gas film holes around the large hole periphery are processed to reduce the influence of the deformation of the part caused by the stress change of the part material after material removal on the reference.

[0071] S120, the electric spark machining head slope air film hole: find the head plane any large hole as the angular position, the air film hole on the head slope is processed.

[0072] In step S110, first, a larger hole on the head plane is accurately positioned and aligned by a measuring device, serving as an angular reference. The role of the angular reference is to ensure that the processing position of all air film holes during processing is determined relative to the center of this large hole. Once the angular position of the large hole is determined, the processing positions of other air film holes around the large hole are also accurately positioned based on this reference. This ensures the consistency of the position accuracy of each air film hole in the relative angular direction. Laser technology is used to process the air film holes around the large hole. Laser processing is a high-precision, low-heat-affected processing method suitable for thin-walled structure parts. The laser beam melts the material through high-energy focusing, forming a hole. During laser processing, the material removal amount can be accurately controlled by adjusting the focal length and power of the laser, thereby avoiding excessive heat input and reducing the impact of local thermal stress concentration on the material. By gradually processing the air film holes around the large hole, uniform stress on the material during processing can be ensured, and deformation of the part caused by excessive release of local stress can be avoided.

[0073] In step S120, first, a larger hole on the head plane is aligned as an angular reference. Through the position of this large hole, the air film holes on the slope can maintain accurate relative positions in the angular direction. After aligning the large hole as the processing reference, it is ensured that the positions of the air film holes on the head slope relative to the large hole do not deviate during the entire processing process, ensuring the processing accuracy of the air film holes.

[0074] The air film hole to be processed is close to the mounting edge, and the outlet is a force-bearing arc part. Electric spark machining is used to reduce deformation of the part. The area close to the mounting edge is usually less rigid, and the part is prone to deformation at this location. Using electric spark machining, this non-contact processing method can effectively avoid mechanical impact on thin-walled or weakly rigid parts during processing, thereby reducing the likelihood of deformation at this location.

[0075] In step S200, strict alignment and fixation are required before welding to ensure accurate positioning of the head ring and the inner wall. Through clamps or support devices, it is ensured that the two parts remain stable during welding to avoid position deviation affecting accuracy during welding. Through electron beam welding, the focused electron beam melts the joint area of the head ring and the inner wall, forming a precise weld. This process can achieve high-strength welding on thin-walled parts while maintaining the shape stability of the part.

[0076] Step S300 includes the following steps:

[0077] S310, determining a part axial reference: coloring the inner wall end face, supporting and pressing the colored point, processing the boss face, processing the first supporting surface, the inner wall end face being the pre-welding axial reference, the first supporting surface being the post-welding axial reference, so as to realize the conversion from the pre-welding axial reference to the post-welding axial reference, and avoid the influence of the deformation of each end face before and after welding on the processing of the part;

[0078] The welding process may cause thermal deformation of the part, resulting in the loss of precision of the selected reference surface before welding. By reprocessing a new axial reference (the first supporting surface) after welding, the influence of welding deformation on subsequent finishing can be effectively avoided, and the size and precision requirements of the final product can be ensured; through reference conversion, it is ensured that the part always has an accurate and reliable reference surface at different processing stages, especially after welding, the new reference surface can ensure the processing precision of each part, avoid the accumulation of dimensional errors, and thus improve the overall processing quality and stability of the part; the conversion of the axial reference provides a new positioning reference for the subsequent process, and the new reference surface can ensure the dimensional precision of the part in subsequent machining such as turning and milling, especially when machining important parts such as the mounting edge and the annular groove, the precision transmission and interchangeability of the part in the entire machining chain are ensured.

[0079] S320, converting the axial reference and turning the ring groove: using the first supporting clamp to color and support the first supporting surface, pressing the part through the screw rod passing through the head hole, aligning the inner hole circle of the inner wall, machining the mounting edge and the annular groove, and processing the second supporting surface and the center reference, the second supporting surface being the design axial reference, so as to realize the conversion from the axial reference in processing to the design axial reference. Through the conversion of the axial reference, the temporary reference (the first supporting surface) in welding and processing is converted to the final design reference (the second supporting surface), ensuring that the processing of the part is always based on an accurate and stable reference surface. Especially in the machining of the ring groove and the mounting edge, this conversion helps to improve the concentricity, parallelism and surface quality of the part; the conversion of the reference surface ensures the precision transmission of the axial reference in the machining process, avoids the influence of the deformation of the part in welding and initial machining on the consistency of the final size and shape, especially for thin-walled and complex-shaped parts, the reference conversion can minimize the error in the machining process; by accurately machining the mounting edge and the ring groove and ensuring the consistency of the second supporting surface with the design reference, the part can meet the high-precision matching requirements in the final assembly. The precision of the ring groove and the mounting edge is directly related to the sealing, pressure resistance and working performance of the part.

[0080] Step S400 includes the following steps:

[0081] The second supporting clamp is used to support the second supporting surface, align the mounting edge outer circle, and align the uniformly distributed boss to coarsely determine the angular direction;

[0082] After setting the workpiece coordinate system, the pre-milling cutter machining program is used to mill 0.3mm deep on several evenly distributed boss circular holes on the head, and then each boss pre-milling center hole is checked to see if it is in the center of the boss. If there is deviation, adjust the workpiece coordinate system and repeat the above steps until each boss pre-milling center hole is in the center of the boss.

[0083] An angular hole is machined on the mounting edge, and the boss surface is milled. The several evenly distributed bosses of the blank part are the angular reference of the blank part, and the angular hole on the mounting edge is the angular reference of the machined part, so as to realize the conversion from the angular reference of the blank part to the angular reference of the machined part.

[0084] The main function of step S400 is to convert the angular reference of the part, ensuring that the angular accuracy of the part can be effectively controlled from the blank part to the finished part. The specific operation includes using the second supporting clamp to support the second supporting surface, and preliminarily determining the angular position of the part by aligning the outer circle of the mounting edge and the evenly distributed bosses. After setting the workpiece coordinate system, the pre-milling is carried out, and each boss circular hole is checked to see if it is in the center position, and the deviation is eliminated by adjusting the coordinate system. This process ensures the consistency of the geometric center of each boss and the machining reference, avoiding the accumulation of machining errors. Further angular reference conversion is realized by machining an angular hole on the mounting edge. Through accurate positioning and milling, it is ensured that the evenly distributed bosses of the blank part (blank reference) are converted to the angular hole of the machined part (machining reference). The core function of this step is to improve the assembly accuracy of the part, especially for the aviation engine parts with high installation and assembly requirements. The accuracy of the angular reference is crucial. Through this reference conversion, angular errors can be reduced, ensuring that the part has good symmetry and accuracy in subsequent assembly, thereby improving the performance and reliability of the entire product

[0085] In step S600, when the second supporting surface is supported by the second supporting clamp, an angular pin is arranged on the corresponding angular hole of the second supporting clamp to align the outer circle of the mounting edge. When the second supporting surface is supported by the second supporting clamp, the angular pin is arranged on the clamp to align the outer circle of the mounting edge, which ensures that the part can be accurately positioned during machining, thereby ensuring the machining accuracy of the angular hole and the mounting edge. The arrangement of the angular pin can make the position of the part in the clamp more stable, and through the accurate alignment with the outer circle of the mounting edge, the angular error caused by the position deviation of the part during machining can be avoided. The accurate alignment of this process is crucial for high-precision parts such as aircraft engines, especially for parts that need to maintain symmetry and high-precision assembly. Through the auxiliary positioning of the angular pin, it is ensured that each hole position of the part during the machining of the ring groove gas film hole on the machine tool is consistent with the angular reference, preventing deviation or error accumulation after machining. In addition, the combination of the supporting clamp and the angular pin can also effectively prevent the slight deviation caused by the vibration or stress generated during machining, thereby ensuring the assembly accuracy, functionality and durability of the final part. This precise positioning system improves the stability and overall accuracy of the machining process, which helps to ensure the machining quality of high-requirement parts.

[0086] Before step S700, a step of polishing the part is also included to remove burrs and flash generated during machining, thereby avoiding excess material of the gas film hole and the annular groove.

[0087] Before step S700, a step of fluorescent inspection is also included to perform fluorescent inspection on the mounting edge and the gas film hole to eliminate crack defects.

[0088] After step S900, the following steps are also included to remove gas film hole splashes and burrs: remove gas film hole splashes and burrs, use water as a medium, pressurize the cooling hole, and perform light transmission inspection on all holes to remove possible excess material in the hole.

[0089] A specific embodiment of the present embodiment includes the following steps:

[0090] Step A, laser machining head plane gas film hole: align any large hole on the head plane as an angular position, and process the gas film holes around the periphery of the large hole, a total of 644 gas film holes of different sizes are processed to reduce the influence of stress changes caused by material removal on the part after the part is deformed.

[0091] Step B, electric spark machining head plane gas film hole: align any large hole on the head plane as an angular position, and process the gas film holes on the head plane, a total of 294 gas film holes are processed. The gas film holes at this position are close to the mounting edge, and the outlet is a force- bearing arc part. Electric spark machining is used instead of laser machining to reduce the heat generated by electric machining and the deformation of the part.

[0092] Step C, welding head ring and inner wall: arrange electron beam welding process, welding head ring and inner wall at the weld, and after welding, stress relief treatment, X-ray inspection and fluorescent inspection are carried out to ensure the quality of the weld;

[0093] Step D, determining the axial reference of the part after welding: coloring the inner wall end face, supporting and pressing the colored point, machining the first supporting surface on the boss surface, so as to realize the conversion from the axial reference before welding (i.e. the inner wall end face) to the axial reference after welding (i.e. the boss surface), avoiding the influence of the deformation of each end face before and after welding on the machining of the part;

[0094] Step E, converting the axial reference and turning the ring groove: providing a first supporting fixture, supporting the first supporting surface machined in step D, pressing the part through the head hole with a screw rod, aligning the inner hole of the inner wall, machining the installation edge and the ring groove, and machining the axial reference (i.e. the second supporting surface) and the center reference, so as to realize the conversion from the axial reference in machining (i.e. the boss end face) to the designed axial reference (i.e. the installation edge);

[0095] Step F, converting the blank angular reference and milling the boss: providing a second supporting fixture, supporting the second supporting surface machined in step E (optionally coloring the second supporting surface), aligning the installation edge outer circle, and aligning the evenly distributed bosses at the boss to coarsely determine the angular reference, setting the workpiece coordinate system, pre-programming the milling cutter processing program to mill 0.3mm deep on several evenly distributed boss hole on the head, then checking whether the pre-milling center hole of each boss is in the center of the boss (the judgment basis is to ensure the subsequent machining allowance), if there is deviation, adjust the workpiece coordinate system and repeat the above steps until the pre-milling center hole of each boss is in the center of the boss, finally machining several holes and angular holes on the installation edge, and milling the boss surface, so as to realize the conversion from the angular reference of the blank (i.e. the several evenly distributed bosses of the blank) to the angular reference of the machined part (i.e. the angular hole on the installation edge);

[0096] Step G, cutting the lace of the installation edge: providing a third supporting fixture, setting an angular pin on the angular hole machined in step F, aligning the center reference circle, and machining the installation edge by wire cutting process to ensure the angular and wall thickness requirements of the lace of the part;

[0097] Step H, high-speed electric spark machining of ring groove air film hole: providing a second supporting fixture, supporting the second supporting surface machined in step E, setting an angular pin on the angular hole machined in step F, aligning the installation edge outer circle, and machining the air film hole on the ring groove to ensure the air circulation and heat dissipation function of the ring groove;

[0098] Step I, polishing the parts: arrange the content of the fitter, remove the burrs and flash generated by the above process of machine, so as to avoid the excess of the gas film hole and the annular groove;

[0099] Step J, fluorescent inspection: arrange the content of the fluorescent inspection, and carry out fluorescent inspection on the installation edge and the gas film hole to eliminate crack defects;

[0100] Step K, spraying treatment on the inner wall: arrange the spraying process, spray the thermal barrier coating on the inner wall profile, and carry out plasma spraying, the material is aluminum silicon coating. In order to reduce the influence of cold and hot fatigue, gas oxidation corrosion and wear on the flame cylinder, and increase the service life of the flame cylinder.

[0101] Step L, laser processing of the inner wall mixing hole: provide a third support clamp, set the angular pin of the angular hole processed in step F, support the second support surface processed in step E, find the center reference outer circle part, and process mixing holes of different sizes in the inner wall coating part.

[0102] Step M, laser processing of the inner wall cooling hole: provide a second support clamp, set the angular pin of the angular hole processed in step F, support the installation edge, find the installation edge outer circle part, and process 12 rows of cooling holes of different sizes in the inner wall coating part. The cooling holes and the mixing holes are distributed in a staggered manner, which enhances the cooling effect of the combustion chamber.

[0103] Step N, remove the gas film hole splashes and burrs: remove the gas film hole splashes and burrs, use water as medium, pressurize and flush the cooling hole, and carry out light transmission inspection on all holes, so as to remove the possible excess in the hole.

[0104] The main problems and methods solved by the processing method are as follows:

[0105] 1. By steps A and B, the gas film holes on the head ring and the gas film holes on the bevel are processed respectively, and the processing method is adjusted according to the position of the gas film hole to avoid the influence of the deformation of the part after the material removal on the reference caused by the stress change; 2. After welding, steps D and E are arranged to convert the axial reference and the center reference of the part respectively, to avoid the influence of the deformation of each mounting edge and each hole on the part finishing before and after welding; 3. By the screw hole pressing method of the second supporting fixture in step E, the rigidity of the part is increased by the supporting and pressing part, and the clamping deformation caused by the pressing plate pressing the arc surface is avoided, so as to finally ensure the size and roughness requirements of the mounting edge reference and the annular groove; 4. By adjusting the processing method according to whether the convex boss is in the center of the convex boss after pre-milling of the milling cutter, the angular orientation is roughly determined by the several evenly distributed convex bosses, to avoid the conversion error between the angular reference of the blank and the angular reference of the machined part, so as to prevent the problem of insufficient convex boss machining allowance; 5. By arranging steps F and G to process the mounting edge angular hole and the mounting edge lace respectively, the deformation of the mounting edge caused by numerical milling is avoided, and finally the angular position of the angular hole and the lace wall thickness requirement are ensured.

[0106] Since most of the machining processes have special fixtures to constrain the machining parts, the interchangeability in the part machining process is good, the dependence on the operation level of skilled personnel is reduced, and there are special deburring and cleaning steps to prevent the phenomenon of gas film hole attachment of redundant materials, the precision size quality of the part is stable, and the qualified rate is high.

[0107] The above only describes the preferred embodiments of the present application and is not used to limit the present application. For those skilled in the art, the present application can have various changes and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the protection scope of the present application.

Claims

1. A method of processing an aircraft engine flame tube assembly, characterized by, It comprises the following steps: S100, machining the film holes on the head ring of the flame tube assembly and the film holes on the bevel; S200, welding the head ring and the inner wall of the flame tube assembly; S300, machining the first supporting surface on the boss surface, machining the second supporting surface on the mounting edge, and converting the axial reference and the center reference of the part to avoid the influence of the deformation of each mounting edge and each inner hole before and after welding on the finishing of the part; S400, converting the angular reference of the blank and milling the boss, machining the angular hole on the mounting edge to realize the conversion from the angular reference of the blank to the angular reference of the machined part; S500, taking the angular hole on the mounting edge as the reference to machine the mounting edge lace, and using wire cutting process to machine the mounting edge to form the lace; S600, high-speed electric spark machining of the ring groove film hole, using the second supporting fixture to support the second supporting surface, and machining the film hole on the ring groove to ensure the air ventilation and heat dissipation function of the ring groove; S700, spraying treatment of the inner wall: spraying thermal barrier coating on the inner wall profile, and performing plasma spraying with aluminum silicon coating; S800, laser processing of the inner wall mixing hole: using the third supporting fixture, setting the angular pin on the angular hole, supporting the second supporting surface to find the center reference outer circle position, and machining mixing holes of different sizes on the inner wall coating part; S900, laser processing of the inner wall cooling hole: using the second supporting fixture, setting the angular pin on the angular hole, supporting the mounting edge to find the mounting edge outer circle position, and machining cooling holes of different sizes on the inner wall coating part, with the cooling holes and the mixing holes distributed in a staggered manner.

2. The machining method of the aircraft engine flame tube assembly according to claim 1, wherein: In step S100, when machining the film holes, the machining method is adjusted according to the position of the film holes to avoid the influence of the deformation of the part after removing the material on the reference due to the stress change.

3. The machining method of the aircraft engine flame tube assembly according to claim 2, wherein: Step S100 of machining the film holes on the head ring of the flame tube assembly and the film holes on the bevel comprises the following steps, S110, laser processing of the head plane film hole: finding the angular position of any large hole on the head plane, and machining the film holes around the large hole to reduce the influence of the deformation of the part after removing the material on the reference due to the stress change, S120, electric spark machining of the head bevel film hole: finding the angular position of any large hole on the head plane, and machining the film holes on the head bevel.

4. The machining method of the aircraft engine flame tube assembly according to claim 3, wherein: In step S120, the film hole to be machined is close to the mounting edge, and the outlet is a force circle arc part, and electric spark machining is used to reduce the deformation of the part.

5. The machining method of the aircraft engine flame tube assembly according to claim 4, wherein: Step S300 comprises the following steps, S310, determining the axial reference of the part: coloring the inner wall end face, supporting and pressing the colored point, machining the boss face to form the first supporting surface, the inner wall end face being the axial reference before welding, the first supporting surface being the axial reference after welding, so as to realize the conversion from the axial reference before welding to the axial reference after welding and avoid the influence of the deformation of each end face before and after welding on the machining of the part; S320, converting the axial reference and turning the ring groove: using the first supporting clamp to support the first supporting surface, pressing the part through the screw rod passing through the head hole, aligning the inner hole circle of the inner wall, machining the mounting edge and the ring groove to form the second supporting surface and the center reference, the second supporting surface being the design axial reference, so as to realize the conversion from the axial reference in machining to the axial reference in design.

6. The method of claim 5, wherein: Step S400 comprises the following steps, A second supporting clamp is used to support the second supporting surface, align the mounting edge outer circle, and align the uniformly distributed bosses on the boss to coarsely determine the angular direction; After setting the workpiece coordinate system, a pre-milling machining program is pre-programmed to mill 0.3mm deep on several uniformly distributed boss holes on the head, and then each pre-milled center hole of each boss is checked to see if it is in the center of the boss. If there is deviation, adjust the workpiece coordinate system and repeat the above steps until each pre-milled center hole of each boss is in the center of the boss. The angular holes are machined on the mounting edge, and the boss surface is milled. The several uniformly distributed bosses of the blank are the angular reference of the blank, and the angular holes on the mounting edge are the angular reference of the machined part, so as to realize the conversion from the angular reference of the blank to the angular reference of the machined part.

7. The method of claim 6, wherein: In step S600, when the second supporting clamp supports the second supporting surface, an angular pin is arranged on the second supporting clamp corresponding to the angular hole to align the mounting edge outer circle.

8. The aircraft engine flame tube assembly machining method of claim 7, wherein: Before step S700, a step of polishing the part is further included to remove burrs and flash generated during machining, so as to avoid the excess of the film holes and the ring groove.

9. The method of claim 8, wherein: Before step S700, a step of fluorescent inspection is further included to perform fluorescent inspection on the mounting edge and the film holes to eliminate crack defects.

10. The method of claim 1, wherein: After step S900, the following steps are further included, Removing film hole splashes and burrs: removing film hole splashes and burrs, using water as a medium, pressurizing the cooling hole, and performing light transmission inspection on all holes to remove possible excess in the holes.

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