General tooling for combined machining of two-component space engine and method of using same

Abstract

This invention provides a universal tooling fixture for machining dual-component aerospace engines and its usage method. The fixture includes a fixed base, a tool setting module, a fine-tuning bolt, a head connecting block, and a measuring mandrel. The tool setting module is detachably mounted on the fixed base, and the fine-tuning bolt is movably mounted on the reverse side of the fixed base. The tool setting module and the fine-tuning bolt cooperate to adjust the angle of the fixed base. The head connecting block is securely mounted on the fixed base. The engine includes an engine head and an engine exhaust nozzle. The head connecting block is securely connected to the engine head. The measuring mandrel is inserted into the engine exhaust nozzle and is used to measure the axial position of the engine. This invention fixes the engine on the machine tool using the head connecting block and the fixed base. By tightening the fine-tuning nut, the clamping position and angle of the engine can be precisely adjusted, ensuring that the axial lines of the engine head and the engine exhaust nozzle are aligned. This facilitates assembly and disassembly, is convenient to use, allows for easy tool setting, and increases work efficiency.

Description

Technical Field

[0001] This invention relates to the field of aerospace engine technology, specifically to a general-purpose tooling for the assembly and processing of bi-component aerospace engines and its usage method. Background Technology

[0002] Because dual-element aerospace engines have complex structures and high precision requirements, and contain many components, they will deform due to heat during the welding and assembly process. In order to ensure the precision requirements of the aerospace engine, a combination machining process is added after the overall assembly is completed. The flange end face and outer circle of the engine head are machined to ensure that the axis of the engine head and the body are in a straight line.

[0003] Chinese Patent CN114227111A discloses a conical workpiece clamping fixture and its usage method, and a conical workpiece welding system. The system includes: an operating table; a bottom mold fixedly mounted on the operating table and having a frustum-shaped structure corresponding to the conical workpiece; a weld positioning assembly located on one side of the bottom mold, having a movable abutment block that can move closer to or further away from the peripheral outer wall of the bottom mold, so that when the conical workpiece is placed on the bottom mold, the abutment block can abut against at least one edge of the weld gap of the conical workpiece; and a clamping assembly including multiple clamping blocks spaced apart on the periphery of the bottom mold, each clamping block being movable, and each clamping block connected to a first driving member, the clamping block being movable via the driving member to abut against and clamp the conical workpiece on the bottom mold.

[0004] Currently, there is no universal tooling for the assembly and machining of aerospace engines. Due to the significant size differences between different engine models, different clamping methods must be considered and specially designed tooling must be used during assembly and machining. This not only results in high machining costs, long clamping times, and lengthy tool setting times, but also fails to guarantee the machining accuracy of the engine, seriously affecting production efficiency and quality. Summary of the Invention

[0005] To address the shortcomings of existing technologies, the purpose of this invention is to provide a universal tooling for the assembly and machining of dual-component aerospace engines and its usage method.

[0006] According to the present invention, a universal tooling for machining a dual-component aerospace engine assembly includes: a fixed base, a tool setting module, a fine-tuning bolt, a head connecting block, and a measuring mandrel. The tool setting module is detachably mounted on the fixed base, and the fine-tuning bolt is movably mounted on the reverse side of the fixed base. The tool setting module and the fine-tuning bolt cooperate to adjust the angle of the fixed base.

[0007] The head connecting block is fastened to the fixed base. The engine includes an engine head and an engine tail nozzle. The head connecting block is fastened to the engine head. The measuring mandrel is inserted into the engine tail nozzle and is used to measure the axial position of the engine.

[0008] Preferably, the fixing base is circular, and a circular boss is provided on the side of the fixing base near the head connecting block, and a circular groove corresponding to the circular boss is provided on the end of the head connecting block near the fixing base.

[0009] The fixed base is provided with a plurality of threaded holes evenly distributed along the circumference, and the head connecting block is provided with a plurality of through holes.

[0010] Preferably, the head connecting block has a square groove at one end near the engine head, and the protruding structure of the engine head is inserted into the square groove without contacting the groove wall.

[0011] The engine head is provided with a plurality of engine head through holes evenly arranged circumferentially, and the end of the head connecting block near the engine head is provided with a fixing threaded hole corresponding to the engine head through holes.

[0012] Preferably, a weight-reducing through hole is provided in the middle of the head connecting block, and the head connecting block includes a large head connecting block or a small head connecting block. The large head connecting block is a cylindrical shaft with a flange, and the connecting through hole is provided on the flange of the large head connecting block.

[0013] The small head connector is a flangeless cylindrical shaft, and the connecting through hole is located in the square groove of the small head connector.

[0014] Preferably, when the outer diameter of the engine head is greater than or equal to 80 mm, the engine is connected to the large connecting block of the engine head;

[0015] When the outer diameter of the engine head is less than or equal to 80mm, the engine is connected to the small connecting block of the head.

[0016] Preferably, the tool setting module includes a detachably connected tool setting connector and a tool setting block. The tool setting block is disc-shaped, the end of the tool setting connector is a threaded shaft, and the middle of the fixed base is provided with a threaded through hole. The threaded shaft is threadedly engaged with the threaded through hole.

[0017] Preferably, a plurality of fine-tuning bolts are evenly installed around the outer ring of the fixed base in the circumferential direction. The fine-tuning bolts include hexagonal bolts, with the head of the fine-tuning bolt located on the back of the fixed base and the nut located on the front of the fixed base.

[0018] Preferably, the measuring mandrel includes a large conical shaft, a small conical shaft, and a spring. The small conical shaft has a stepped shaft structure. The large conical shaft has two optical shafts at both ends and a conical disk in the middle. The shaft at the tail of the small conical shaft is inserted into the shaft hole at the head of the large conical shaft. The spring is sleeved on the shaft, and the two ends of the spring abut against the small conical shaft and the large conical shaft, respectively. Both the small conical shaft and the large conical shaft can move along their axial direction.

[0019] Preferably, the tail end of the large conical shaft is provided with two measuring dial indicators, and the line connecting the two measuring dial indicators is parallel to the axis of the large conical shaft.

[0020] A method for using a universal tooling fixture for assembling and machining a dual-component aerospace engine according to the present invention includes the following steps:

[0021] Step S1, tool setting: First, evenly distribute and install multiple fine-tuning bolts on the fixed base. Then, fix the fixed base on the machine tool using a four-jaw chuck. Next, install the tool setting module on the fixed base. Rotate the fine-tuning bolts so that the end face of the fine-tuning bolts contacts the four-jaw chuck. Adjust the angle of the fixed base so that the fixed base is parallel to the machine tool.

[0022] Step S2: After the tool setting is completed, disassemble the tool setting module and install the head connecting block and the engine;

[0023] Step S3: Position the small conical shaft of the measuring mandrel to the throat of the engine exhaust nozzle, and clamp the large conical shaft of the measuring mandrel to the tail of the engine exhaust nozzle;

[0024] Step S4: Measure the axis using a dial indicator, rotate the fine-tuning bolt, adjust the position of the four jaws of the four-jaw chuck, change the clamping angle and position of the engine, so that the axis of the engine head and the engine exhaust nozzle are in a straight line, and the clamping is completed.

[0025] Compared with the prior art, the present invention has the following beneficial effects:

[0026] 1. This invention fixes the engine on the machine tool by connecting the head and fixing the base. The clamping position and angle of the engine can be precisely adjusted by turning the fine-tuning nut, ensuring that the axis of the engine head and the engine tail nozzle are in a straight line. This makes it easy to disassemble and assemble, convenient to use, easy to set the tool, and more efficient to work, effectively reducing labor costs.

[0027] 2. By using head connecting blocks of different sizes, when processing aerospace engines of different models and sizes, it is only necessary to change the head connecting blocks according to the outer diameter of the engine head to be processed. It is not necessary to disassemble all tooling parts, which reduces tooling costs, reduces the clamping time of parts, and improves the convenience and stability of repeated disassembly and assembly of the product. Attached Figure Description

[0028] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0029] Figure 1 This is a schematic diagram illustrating the structure of a general-purpose tooling for the assembly and processing of dual-component aerospace engines, which is the main feature of this invention.

[0030] Figure 2 This is a cross-sectional view of a general-purpose tooling for the assembly and machining of dual-component aerospace engines, which is the main feature of this invention.

[0031] Figure 3 This is a schematic diagram illustrating the structure of the tool setting module, which is the main feature of this invention.

[0032] Figure 4 This is a cross-sectional view of the small connecting block at the head, which is the main feature of this invention.

[0033] As shown in the figure:

[0034] Four-jaw chuck 1 Fixed base 2 Tool setting module 3

[0035] 4. Head large connecting block; 5. Fine-tuning bolt; 6. Engine

[0036] 7 Measuring mandrel; 8 Measuring dial indicator; 9 Head connecting block

[0037] Threaded through hole 21; Tool setting connector 31; Tool setting block 32

[0038] Threaded shaft 311, engine head 61, engine tail nozzle 62

[0039] Engine head through hole 63, small tapered shaft 81, spring 82

[0040] Large conical shaft 83 Detailed Implementation

[0041] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0042] Example 1

[0043] like Figure 1-4 As shown, a universal tooling for machining a dual-component aerospace engine assembly according to the present invention includes: a fixed base 2, a tool setting module 3, a fine-tuning bolt 5, a head connecting block, and a measuring mandrel 7. The tool setting module 3 is detachably mounted on the fixed base 2, and the fine-tuning bolt 5 is movably mounted on the reverse side of the fixed base 2. The tool setting module 3 and the fine-tuning bolt 5 cooperate to adjust the angle of the fixed base 2. The head connecting block is fastened to the fixed base 2. The engine 6 includes an engine head 61 and an engine exhaust nozzle 62. The head connecting block is fastened to the engine head 61. The measuring mandrel 7 is inserted into the engine exhaust nozzle 62 and is used to measure the axial position of the engine 6.

[0044] The fine-tuning bolt 5 is connected to the reverse side of the fixed chassis 2 and is used to fine-tune the angle of the engine 6; the head connecting block is connected to the fixed chassis 2 and is used to fix the engine 6; the measuring mandrel 7 is installed on the engine 6 to measure the position of the engine axis; the tool setting module 3 is installed on the fixed chassis 2 and is used for tool setting before machining.

[0045] The fixed base 2 is circular. A circular boss is provided on one side of the fixed base 2 near the head connecting block, and a circular groove corresponding to the circular boss is provided on one end of the head connecting block near the fixed base 2. Multiple threaded holes are evenly distributed along the circumference of the fixed base 2, and multiple through holes are correspondingly provided on the head connecting block. Preferably, the outer circumference of the fixed base 2 has eight threaded holes and eight fan-shaped grooves staggered, the inner circumference has a circular boss and two threaded holes, and a larger threaded through hole 21 is designed in the center.

[0046] The head connecting block has a square groove at one end near the engine head 61. The protruding structure of the engine head 61 is inserted into the square groove and does not contact the groove wall. The engine head 61 has a plurality of engine head through holes 63 evenly arranged in the circumferential direction. The head connecting block has a fixing threaded hole corresponding to the engine head through hole 63 at one end near the engine head 61.

[0047] A weight-reducing through hole is provided in the middle of the head connecting block. The head connecting block includes a large head connecting block 4 or a small head connecting block 9. The large head connecting block 4 is a cylindrical shaft with a flange, and the connecting through hole is provided on the flange of the large head connecting block 4. The small head connecting block 9 is a cylindrical shaft without a flange, and the connecting through hole is provided in the square groove of the small head connecting block 9.

[0048] The head connecting blocks are designed in two sizes to accommodate the needs of engines 6 of different sizes. The large head connecting block 4 is designed as a flanged cylindrical shaft with four through holes evenly distributed around the flange. One end face has a square groove and four fixing threaded holes, the other end has a circular groove, and a weight-reducing through hole in the middle. The small head connecting block 9 is a flangeless cylindrical shaft, and the through hole for connecting with the fixed base 2 is located in the square groove.

[0049] When the outer diameter of the engine head 61 is greater than or equal to 80mm, the engine 6 is connected to the large connecting block 4 of the head; when the outer diameter of the engine head 61 is less than or equal to 80mm, the engine 6 is connected to the small connecting block 9 of the head.

[0050] The tool setting module 3 includes a detachably connected tool setting connector 31 and a tool setting block 32. The tool setting block 32 is disc-shaped with three countersunk holes in the middle. One end of the tool setting connector 31 is a threaded shaft 311, and the other end is a stepped shaft with three threaded holes on its end face for fixing the tool setting block 32. The fixed base 2 has a threaded through hole 21 in the middle, and the threaded shaft 311 is threadedly connected to the threaded through hole 21.

[0051] Multiple fine-tuning bolts 5 are evenly installed around the outer ring of the fixed base 2. The fine-tuning bolts 5 include extended hexagonal bolts, which are installed on four threaded holes around the fixed base 2. The heads of the fine-tuning bolts 5 are located on the back of the fixed base 2, and the nuts are located on the front of the fixed base 2.

[0052] The measuring mandrel 7 includes a large conical shaft 83, a small conical shaft 81, and a spring 82. The small conical shaft 81 has a smaller overall size and is a stepped shaft structure. The large conical shaft 83 has smooth shafts at both ends and a large conical disc in the middle. The shaft at the tail of the small conical shaft 81 is inserted into the shaft hole at the head of the large conical shaft 83. The spring 82 is sleeved on the shaft, and the two ends of the spring 82 abut against the small conical shaft 81 and the large conical shaft 83 respectively. Both the small conical shaft 81 and the large conical shaft 83 can move along their axial direction. That is, the tail of the small conical shaft 81 can move back and forth when inserted into the head of the large conical shaft 83. The two are limited by the spring 82.

[0053] Two dial gauges 8 are installed at the tail of the large conical shaft 83, and the line connecting the two dial gauges 8 is parallel to the axis of the large conical shaft 83.

[0054] Before assembling the engine, a tool setting operation is required to ensure machining accuracy.

[0055] During tool setting, first, evenly distribute the four fine-adjusting bolts 5 on the four threaded holes on the outer ring of the fixed base 2, and then fix the fixed base 2 to the machine tool using the four-jaw chuck 1. One end of the tool setting connector 31 is designed as a threaded shaft 311, which connects to the threaded through hole 21 in the middle of the fixed base 2. For easy disassembly and assembly, the tool setting connector 31 has a hexagonal structure in the middle. The tool setting block 32 is specially machined to have high precision in its outer circle and end face. It is fixed to the tool setting connector 31 with three screws for easy replacement after wear. After installation, the fine-adjusting bolts 5 need to be rotated so that the end face of the fine-adjusting bolts 5 contacts the four-jaw chuck 1. Unlike the automatic centering function of the three-jaw chuck, the four-jaw chuck 1 is more flexible, and the position of the four jaws is controllable, which can better ensure clamping accuracy. By rotating the fine-adjusting bolts 5, the distance between the fixed base 2 and the four-jaw chuck 1 in four directions is finely adjusted, thereby adjusting the angle of the fixed base 2 so that the fixed base 2 is parallel to the machine tool and ensures machining accuracy.

[0056] After tool setting, there is no need to disassemble the fixed base 2 and the fine-tuning bolt 5. Simply rotate the tool setting connector 31 to remove the tool setting module 3, and then install the head connector block and the engine 6. For machining the engine 6 with a head outer diameter greater than 80mm, a large head connector block 4 is used. One end of the large head connector block 4 has a circular groove that mates with the circular boss on the end face of the fixed base 2, serving a positioning and guiding function. The head connector block is then installed on the fixed base 2 using bolts. The fixed base 2 has eight threaded holes on its outer ring, four for installing the fine-tuning bolt 5 and four for fixing the head connector block. Four small threaded holes are located on the other end face of the head connector block, which mate with the four engine head through holes 63 on the head of the engine 6. The engine 6 is then installed on the head connector block using bolts. Simultaneously, because the engine head 61 has a protruding structure, to prevent interference between the protruding structure and the head connector block during machining, a square groove is designed on the end face of the head connector block after dimensional calculations to avoid the protruding structure.

[0057] When machining an engine 6 with a head outer diameter less than 80mm, a small head connecting block 9 is used. The small head connecting block 9 has a small overall size, and its through-hole for connecting to the fixed base 2 is located in a square groove that mates with the threaded hole on the fixed base 2. Similar to the installation method of the large head connecting block 4, the groove at one end of the small head connecting block 9 mates with the boss on the fixed base 2, and then it is bolted to the fixed base 2. The engine 6 is mounted on the small head connecting block 9 through the mounting hole on the head for assembly machining.

[0058] After installation, the position of engine 6 needs further adjustment to ensure that the axes of engine head 61 and engine exhaust nozzle 62 are aligned. This requires the use of a dial indicator 8 and a measuring mandrel 7. First, position the small conical shaft 81 of the measuring mandrel 7 at the throat of the engine exhaust nozzle 62. Then, use a compression spring 82 to hold the conical disc of the large conical shaft 83 at the tail of the engine exhaust nozzle 62. At this point, the axis of the measuring mandrel 7 coincides with the axis of the engine exhaust nozzle 62. It is only necessary to ensure that the axes of engine head 61 and measuring mandrel 7 are aligned. Next, use the dial indicator 8 to measure the diameter at two points on the optical axis at the tail of the measuring mandrel 7. Then, by rotating the fine-tuning bolt 5 and adjusting the position of the four jaws of the four-jaw chuck 1, the clamping angle and position of engine 6 are changed. If the difference between the data measured by the dial indicator 8 at the front and rear ends of the measuring mandrel 7 does not exceed 0.01, it is confirmed that the axes of engine head 61 and engine exhaust nozzle 62 are aligned, indicating that the clamping is complete.

[0059] The general-purpose tooling for aerospace engine assembly machining of this application fixes the engine 6 on the machine tool through the head connecting block and the fixed base 2, and the clamping position and angle of the engine 6 can be finely adjusted by turning the fine adjustment nut 5 to ensure that the axis of the engine head 61 and the engine tail nozzle 62 are on a straight line. This tooling is easy to use, convenient for tool setting, and more efficient. It can be completed by only one person.

[0060] Furthermore, when using this application to process aerospace engines of different models and sizes, it is only necessary to change the two types of head connecting blocks according to the outer diameter of the engine head 61 to be processed. It is not necessary to disassemble all tooling parts, which reduces tooling costs, reduces the clamping time of parts, and improves the convenience and stability of repeated disassembly and assembly of the product.

[0061] Example 2

[0062] Based on Embodiment 1, the method for using a universal tooling for the assembly and machining of a dual-component aerospace engine according to the present invention includes the following steps:

[0063] Step S1, tool setting: First, evenly distribute and install multiple fine adjustment bolts 5 on the fixed base 2. Then, fix the fixed base 2 on the machine tool using the four-jaw chuck 1. Then, install the tool setting module 3 on the fixed base 2. Rotate the fine adjustment bolts 5 so that the end face of the fine adjustment bolts 5 contacts the four-jaw chuck 1. Adjust the angle of the fixed base 2 so that the fixed base 2 is parallel to the machine tool.

[0064] Step S2: After tool setting is completed, disassemble tool setting module 3 and install head connecting block and engine 6;

[0065] Step S3: Position the small conical shaft 81 of the measuring mandrel 7 to the throat of the engine exhaust nozzle 62, and clamp the large conical shaft 83 of the measuring mandrel 7 to the tail of the engine exhaust nozzle 62.

[0066] Step S4: Measure the axis by measuring the dial indicator 8, rotate the fine adjustment bolt 5, adjust the position of the four jaws of the four-jaw chuck 1, change the clamping angle and position of the engine 6, so that the axis of the engine head 61 and the engine tail nozzle 62 are on a straight line, and the clamping is completed.

[0067] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0068] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A universal tooling fixture for assembling and machining bi-component aerospace engines, characterized in that, include: The tool setting module (3), the fine adjustment bolt (5), the head connecting block and the measuring mandrel (7) are detachably installed on the fixed base (2). The fine adjustment bolt (5) is movably installed on the back of the fixed base (2). The tool setting module (3) and the fine adjustment bolt (5) cooperate to adjust the angle of the fixed base (2). The head connecting block is fastened to the fixed base (2). The engine (6) includes an engine head (61) and an engine tail nozzle (62). The head connecting block is fastened to the engine head (61). The measuring spindle (7) is inserted into the engine tail nozzle (62). The measuring spindle (7) is used to measure the axial position of the engine (6). The tool setting module (3) includes a detachably connected tool setting connector (31) and a tool setting block (32). The tool setting block (32) is in the shape of a disc. The end of the tool setting connector (31) is a threaded shaft (311). The middle part of the fixed base (2) is provided with a threaded through hole (21). The threaded shaft (311) is threadedly connected to the threaded through hole (21). The outer ring of the fixed base (2) is uniformly equipped with a plurality of fine-tuning bolts (5) along the circumferential direction. The fine-tuning bolts (5) include hexagonal bolts. The head of the fine-tuning bolts (5) is located on the back of the fixed base (2), and the nut is located on the front of the fixed base (2). The measuring mandrel (7) includes a large conical shaft (83), a small conical shaft (81), and a spring (82). The small conical shaft (81) has a stepped shaft structure. The large conical shaft (83) has smooth shafts at both ends and a conical disc in the middle. The shaft at the tail of the small conical shaft (81) is inserted into the shaft hole at the head of the large conical shaft (83). The spring (82) is sleeved on the shaft, and the two ends of the spring (82) abut against the small conical shaft (81) and the large conical shaft (83) respectively. Both the small conical shaft (81) and the large conical shaft (83) can move along their axial direction. Two dial gauges (8) are provided at the tail of the large conical shaft (83), and the line connecting the two dial gauges (8) is parallel to the axis of the large conical shaft (83).

2. The universal tooling for machining dual-component aerospace engines as described in claim 1, characterized in that, The fixed base (2) is circular. A circular boss is provided on the side of the fixed base (2) near the head connecting block. A circular groove corresponding to the circular boss is provided on the end of the head connecting block near the fixed base (2). The fixed base (2) is provided with a plurality of threaded holes evenly arranged along the circumference, and the head connecting block is provided with a plurality of through holes.

3. The universal tooling for machining dual-component aerospace engines as described in claim 2, characterized in that, The head connecting block is provided with a square groove at one end near the engine head (61), and the protruding structure of the engine head (61) is inserted into the square groove and does not contact the groove wall of the square groove. The engine head (61) is provided with a plurality of engine head through holes (63) evenly arranged in the circumferential direction, and the end of the head connecting block near the engine head (61) is provided with a fixing thread hole corresponding to the engine head through hole (63).

4. The universal tooling for machining dual-component aerospace engines as described in claim 3, characterized in that, The head connecting block is provided with a weight reduction through hole in the middle. The head connecting block includes a large head connecting block (4) or a small head connecting block (9). The large head connecting block (4) is a cylindrical shaft with a flange. The connecting through hole is provided on the flange of the large head connecting block (4). The head small connecting block (9) is a flangeless cylindrical shaft, and the connecting through hole is set in the square groove of the head small connecting block (9).

5. The universal tooling for machining dual-component aerospace engines as described in claim 4, characterized in that, When the outer diameter of the engine head (61) is greater than or equal to 80 mm, the engine (6) is connected to the head large connecting block (4); When the outer diameter of the engine head (61) is less than or equal to 80 mm, the engine (6) is connected to the head small connecting block (9).

6. A method of using a universal tooling fixture for assembling and machining bi-component aerospace engines as described in any one of claims 1-5, characterized in that, Includes the following steps: Step S1, tool setting: First, evenly distribute and install multiple fine adjustment bolts (5) on the fixed base (2), then fix the fixed base (2) on the machine tool using a four-jaw chuck (1), then install the tool setting module (3) on the fixed base (2), rotate the fine adjustment bolts (5) so that the end face of the fine adjustment bolts (5) contacts the four-jaw chuck (1), adjust the angle of the fixed base (2) so that the fixed base (2) and the machine tool are parallel; Step S2: After the tool setting is completed, disassemble the tool setting module (3) and install the head connecting block and the engine (6). Step S3: Position the small conical shaft (81) of the measuring mandrel (7) to the throat of the engine tail nozzle (62), and clamp the large conical shaft (83) of the measuring mandrel (7) at the tail of the engine tail nozzle (62); Step S4: Measure the axis by measuring the dial indicator (8), rotate the fine adjustment bolt (5), adjust the position of the four jaws of the four-jaw chuck (1), change the clamping angle and position of the engine (6), so that the axis of the engine head (61) and the engine tail nozzle (62) are on a straight line, and the clamping is completed.

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