Elastic clamping tool for inertia friction of aero-engine compressor drum

Abstract

The elastic clamping tool for inertia friction of the aero-engine gas compressor drum comprises an elastic clamping sleeve and a taper sleeve, a workpiece to be welded is installed in an inner cavity of the elastic clamping sleeve, the elastic clamping sleeve is installed in an inner cavity of an inner ring of the taper sleeve, then the inner ring is installed in an inner cavity of an outer ring of the taper sleeve, the workpiece to be welded is clamped through the elastic clamping sleeve, and then the workpiece to be welded is clamped through the taper sleeve. The problem of workpiece abrasion caused by rigid clamping is avoided; meanwhile, the taper sleeve is a rigid sleeve, elastic uniform centripetal clamping is provided for the elastic rubber sleeve, it is guaranteed that vibration caused by inertia friction welding is released to a certain degree under the large upsetting force, the large inertia and the high rotating speed, and therefore high-precision welding is achieved, and the requirements for high coaxiality and radial run-out of inertia friction welding of the aero-engine compressor drum are met.

Description

Technical Field

[0001] The utility model relates to the technical field of inertia friction welding, in particular to an elastic clamping tool for inertia friction of a compressor drum of an aero-engine. Background Art

[0002] Inertia friction welding is a solid-state connection method that can meet all technical and economic requirements of aircraft engine rotor drums and is an ideal and reliable connection method. In order to establish independent inertia friction welding capabilities, our company introduced 560 tons of high-precision domestic inertia friction welding equipment for aviation, with the goal of completing the inertia friction welding of a certain type of gas turbine and aircraft engine compressor drum; the compressor drum is the core component of the "two machines", its operating temperature is about 400℃, and the speed can reach 14000r / m. In order to avoid surge during operation, the welding requirements are extremely high, and the coaxiality of the 5 discs after welding is no more than 0.15mm. However, the main material of the compressor drum is high-temperature alloy, and its yield strength at 650℃ can reach more than 1000MPa, and the inertia requirements are relatively high during inertia friction welding; under the welding upsetting force of up to hundreds of tons, the welding specimen takes only a few seconds from more than 100 revolutions per minute to parking and completing the welding, which will generate a huge torque, and it is extremely difficult to control the coaxiality of the compressor disc.

[0003] For example, the patent with publication number CN115889970A is a tooling for inertia friction welding that our company is using. For example, the elastic jacket for inertia friction welding of compressor drum disc shown in the patent with publication number CN218745505U is a tooling fixture that our company is using. By placing the elastic jacket between the compressor drum disc and the welding tooling during inertia friction welding, it can rely on the deformation of the through holes and shrinkage seams set on the elastic jacket to provide buffering in the case of large top forging force, large inertia, high speed, rapid stop rotation, and vibration caused by inertia friction welding. However, the clamping force provided by the elastic jacket currently in use cannot meet the increased torque required by the new equipment.

[0004] In the prior art, if one wants to increase the clamping force, the welded parts are usually clamped based on rigid constraints. However, during the inertial friction welding of the compressor drum, a large upsetting force and rotation speed are used. The rigid constraint will cause a large deformation of the disc center, which will cause the disc to wear due to the rigid constraint. Summary of the invention

[0005] In order to solve the problem that the tooling and fixture of inertia friction welding currently in use cannot meet the new torque requirement, the utility model provides an elastic clamping tooling for inertia friction of aircraft engine compressor drum, which can meet the increased clamping torque requirement, and at the same time, ensure that the vibration generated during the welding process is released to a certain extent and ensure the welding accuracy.

[0006] The structure of the utility model is as follows: an elastic clamping tool for inertial friction of an aircraft engine compressor drum, comprising: an elastic jacket; characterized in that it also comprises: a cone sleeve;

[0007] The cone sleeve comprises: an inner ring, an outer ring and a cone sleeve shrinkage seam;

[0008] The outer wall of the inner ring is in the shape of a truncated cone with one end narrow and the other end wide; the inner cavity of the outer ring is in the shape of a truncated cone with one end narrow and the other end wide, and the inner cavity size of the outer ring is adapted to the outer wall of the inner ring, and the two are interference fit; the outer wall of the outer ring is in the shape of a cylindrical cone; the inner cavity of the inner ring is in the shape of a cylindrical cone;

[0009] The inner ring body is provided with a locking screw hole perpendicular to the ring surface; the cone sleeve contraction seams are evenly arranged on the outer ring and the inner ring along the radial direction; in the cone sleeve contraction seams on the same ring structure, the opening ends of two adjacent cone sleeve contraction seams are in different directions;

[0010] The inner ring is arranged in the inner cavity of the outer ring, and the outer ring is placed in the inner cavity of the test ring;

[0011] The elastic jacket is in the shape of a circular ring, and its outer diameter is adapted to the inner cavity diameter of the inner ring; the inner cavity diameter of the elastic jacket is adapted to the diameter of the workpiece to be welded.

[0012] It is further characterized by:

[0013] The inner and outer cone angles of the outer ring and the inner ring bracket are designed to be 29°;

[0014] One end of the cone sleeve contraction seam is open, and the cone sleeve contraction seam passes through the cone sleeve in the thickness direction, and the length of the cone sleeve contraction seam is smaller than the width of the annular structure where the cone sleeve contraction seam is located;

[0015] When the inner ring is installed, the narrower end thereof faces the bottom of the installation cavity in which it is located;

[0016] The inner cavity of the elastic jacket is provided with a 15° chamfer;

[0017] The outer diameter of the outer ring is adapted to the inner diameter of the sleeve on the welding tool.

[0018] The present application provides an elastic clamping tool for inertial friction of an aircraft engine compressor drum, which includes an elastic sleeve and a tapered sleeve. The workpiece to be welded is installed in the inner cavity of the elastic sleeve, the elastic sleeve is installed in the inner cavity of the inner ring of the tapered sleeve, and then the inner ring is installed in the inner cavity of the outer ring of the tapered sleeve. The workpiece to be welded is clamped by the elastic sleeve, thereby avoiding the problem of workpiece wear caused by rigid clamping. At the same time, the tapered sleeve is a rigid sleeve, which provides elastic and uniform centripetal clamping for the elastic rubber sleeve, ensuring that the vibration caused by inertial friction welding is released to a certain extent under large top forging force, large inertia and high rotation speed, thereby achieving high-precision welding and meeting the requirements of high coaxiality and radial runout of inertial friction welding of aircraft engine compressor drums. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a schematic diagram of the structure of the elastic clamping tool of the present application;

[0020] Figure 2 This is a 3D schematic diagram of the outer ring of the cone sleeve;

[0021] Figure 3 This is a 3D schematic diagram of the inner ring of the cone sleeve;

[0022] Figure 4 It is a structural schematic diagram of the cone sleeve;

[0023] Figure 5 Schematic diagram of the elastic jacket. DETAILED DESCRIPTION

[0024] like Figure 1 As shown, the utility model includes an elastic clamping tool for inertial friction of an aircraft engine compressor drum, which includes: a cone sleeve 1 and an elastic jacket 2. The outer diameter of the outer ring 11 is adapted to the inner diameter of the sleeve on the welding tool. When installing, the following are coaxially installed from the inside to the outside: a workpiece to be welded (not marked in the figure), an elastic jacket 2, an inner ring 12, an outer ring 11 and a welding tool (not marked in the figure).

[0025] During inertia friction welding of the compressor drum, a relatively large upsetting force and rotation speed are used. Direct use of rigid constraints may cause large deformation of the disc core. The present application designs a cone sleeve 1 based on the elastic sleeve 2 in the prior art. The cone sleeve 1 is used in conjunction with the elastic sleeve 2 to flexibly clamp the disc core of each stage during welding, thereby providing a uniform centripetal clamping force, ensuring that the vibration generated during the welding process is released to a certain extent, and ensuring welding accuracy.

[0026] like Figure 2 and Figure 3As shown, the cone sleeve 1 includes: an outer ring 11 and an inner ring 12, the outer wall of the inner ring 12 is a truncated cone shape with one end narrow and the other end wide; the inner cavity of the outer ring 11 is a truncated cone shape with one end narrow and the other end wide, and the inner cavity size of the outer ring is adapted to the outer wall of the inner ring 12, and the two are interference fit; the outer wall of the outer ring 11 is a cylindrical cone shape; the inner cavity of the inner ring 12 is a cylindrical cone shape. The inner ring 12 is arranged in the inner cavity of the outer ring 11, and the outer ring 11 is placed in the installation cavity of the welding tool. When installing, the narrower end of the inner ring 12 faces the bottom of the installation cavity where it is located.

[0027] A locking screw hole 13 is provided on the ring body of the inner ring 12 perpendicular to the ring surface. When installing the tapered sleeve, the narrower end of the inner ring 12 is inserted into the inner cavity of the outer ring 11, and then the inner ring 12 is gradually pressed into the inner cavity of the outer ring 11 based on the locking bolt passing through the locking screw hole 13 and the bolt holes distributed in the installation cavity in sequence, and finally fixed in the installation cavity. In the process of screwing in the locking bolt 13, the outer wall of the inner ring 12 gradually enters the inner cavity of the outer ring 11 based on the frustum shape. Because the two are interference fit, the outer diameter of the outer ring 11 will be gradually expanded to ensure that the tapered sleeve is fixed in the installation cavity of the welding tool; the inner diameter of the inner ring 12 will be gradually compressed, and the elastic jacket 2 placed in the inner ring will be clamped by the inner ring, and then the workpiece to be welded inside the elastic jacket 2 will be clamped.

[0028] Specific as Figure 4 The cone sleeve 1 shown is a structural example of a rotating end elastic cone sleeve 3, which includes an outer ring 11 and an inner ring 12. The inner ring 12 is evenly provided with locking screw holes 13, and the fitting surface between the outer ring 11 and the inner ring 12 is an inclined surface 14. When the inner ring 12 is gradually pressed into the inner cavity of the outer ring 11, the two are pressed against each other based on the interference fit of the inclined surface 14.

[0029] The outer ring 11 is placed in the installation cavity of the welding fixture, and the cone sleeve is fixed to the welding fixture by passing bolts through the bolt holes 13. At the same time, tightening the elastic cone sleeve by bolts can ensure the restraint effect, and the elastic cone sleeve can be loosened after welding, which makes it convenient to take out the cone sleeve and the workpiece to be welded, reducing the difficulty of rigid assembly.

[0030] The inner and outer cone angles of the outer ring 11 and the inner ring 12 brackets, that is, the angle between the inclined surface 14 and the axis, are designed to be 29°, ensuring sufficient supporting force to clamp the outer ring and the inner ring together.

[0031] The cone sleeve 1 also includes a cone sleeve contraction slit 15, one end of which is open. The cone sleeve contraction slit 15 penetrates the annular structure in the thickness direction, and the length is less than the width of the annular structure. The cone sleeve contraction slit 15 is evenly arranged on the outer ring 11 and the inner ring 12 along the radial direction; in the cone sleeve contraction slit 15 on the same device, the opening ends of two adjacent cone sleeve contraction slits 15 are in different directions, and the setting of the cone sleeve contraction slit ensures that the outer ring and the inner ring maintain elastic margin.

[0032] The elastic jacket 2 is annular, and its outer diameter is adapted to the inner diameter of the inner ring 12; the inner diameter of the elastic jacket 2 is adapted to the diameter of the workpiece to be welded. The inner cavity of the elastic jacket 2 is provided with a 15° chamfer to prevent the surface of the workpiece from being damaged when the workpiece to be welded is clamped. The specific structure of the elastic jacket 2 can be realized based on the elastic jacket structure in the prior art. For example Figure 5 In the structure shown, a through hole 22 and a jacket shrinkage slit 23 perpendicular to the annular surface are provided on a jacket body 21 on the elastic jacket 2, each through hole 22 is connected to one end of the jacket shrinkage slit 23, and the jacket shrinkage slit 23 extends along the radial direction of the elastic jacket 2.

[0033] The specific processing of the cone sleeve and the elastic sleeve of the present application is realized based on the following steps.

[0034] Step 1, 42CrMo blank size re-inspection: measure the size of the annular blank, ensure that there is a margin on each processing surface, and check the surface quality of the blank without defects. In order to ensure the strength of the elastic tooling, the parts are all made of 42CrMo low-alloy material, which has higher tensile strength and yield strength after quenching and tempering.

[0035] Step 2: Rough turn the blanks of the taper sleeve and elastic jacket, remove most of the blank machining allowance, and reserve allowance for stress relief heat treatment and fine machining. In order to ensure the accuracy of the elastic tooling parts, the process method is adopted. The blank allowance is removed and stress relief heat treatment is performed before fine machining to ensure that there will be no excessive deformation after fine machining.

[0036] Step 3: Stress relief heat treatment.

[0037] Step 4: Finish the cone sleeve and elastic jacket. The cone sleeve outer diameter is consistent with the sleeve of the inertia friction welding equipment, and the inner diameter is consistent with the outer diameter of the elastic jacket. The inner diameter of the elastic jacket is consistent with the diameter between the compressor discs, and the dimensional tolerance meets the matching requirements. Finish the elastic tooling parts. The cone sleeve outer diameter is consistent with the equipment sleeve, the inner and outer cone angles are designed to be 29°, the inner diameter of the elastic jacket is consistent with the outer diameter of the drum disc, the outer diameter of the elastic jacket is consistent with the inner diameter of the rigid sleeve, and the inner side is chamfered at 15° to facilitate the installation of the disc.

[0038] Step 5: After the tooling parts are processed, they are nitrided to a depth of 0.5 mm, and the hardness reaches HB350 or above. In order to ensure the surface hardness of the elastic tooling parts and ensure sufficient wear resistance, the surface of the parts is nitrided to a depth of 0.5 mm, and the hardness needs to reach HB350 or above.

[0039] Step 6: Perform three-coordinate inspection on the tooling, and the key dimensions must meet the requirements of the drawing.

[0040] Step 7: Perform pre-welding assembly, install the compressor drum disc into the moving end and rotating end of the equipment, install the elastic clamp on the aircraft engine compressor drum disc, install a cone sleeve on the outside of the elastic clamp, tighten the bolts, and press the elastic clamp inward to press the compressor drum disc.

[0041] Step 8: Perform pre-welding inspection to ensure static coaxiality.

[0042] Step 9: Perform inertia friction welding and check after welding. The welding deformation of the drum disc is within the error range, and the elastic clamping fixture is not deformed after use, which meets the requirements for repeated use.

[0043] When welding compressor drum discs, elastic clamping fixtures are used step by step. During the welding process, the weldment is given uniform centripetal elastic clamping to ensure that the vibration stress during welding is released and the radial runout accuracy is within the required range after welding is completed.

[0044] After using the technical solution of the utility model, when the compressor drum disc is welded step by step, it is clamped between the compressor disc and the rigid sleeve, providing elastic and uniform centripetal clamping, ensuring that under large top forging force, large inertia and high speed, the vibration caused by inertia friction welding is released to a certain extent, thereby realizing high-precision welding and meeting the requirements of high coaxiality and radial runout of inertia friction welding of aircraft engine compressor drum.

Claims

1. An elastic clamping tool for inertial friction of an aircraft engine compressor drum, comprising: The elastic jacket is characterized in that it also includes: a cone sleeve; The cone sleeve comprises: an inner ring, an outer ring and a cone sleeve shrinkage seam; The outer wall of the inner ring is in the shape of a truncated cone with one end narrow and the other end wide; the inner cavity of the outer ring is in the shape of a truncated cone with one end narrow and the other end wide, and the inner cavity size of the outer ring is adapted to the outer wall of the inner ring, and the two are interference fit; the outer wall of the outer ring is in the shape of a cylindrical cone; the inner cavity of the inner ring is in the shape of a cylindrical cone; The inner ring body is provided with a locking screw hole perpendicular to the ring surface; the cone sleeve contraction seams are evenly arranged on the outer ring and the inner ring along the radial direction; in the cone sleeve contraction seams on the same ring structure, the opening ends of two adjacent cone sleeve contraction seams are in different directions; The inner ring is arranged in the inner cavity of the outer ring, and the outer ring is placed in the inner cavity of the test ring; The elastic jacket is in the shape of a circular ring, and its outer diameter is adapted to the inner cavity diameter of the inner ring; the inner cavity diameter of the elastic jacket is adapted to the diameter of the workpiece to be welded.

2. The elastic clamping fixture for inertial friction of an aircraft engine compressor drum according to claim 1, characterized in that: The inner and outer cone angles of the outer ring and the inner ring bracket are designed to be 29°.

3. The elastic clamping fixture for inertial friction of an aircraft engine compressor drum according to claim 1, characterized in that: One end of the cone sleeve contraction seam is open, and the cone sleeve contraction seam passes through the cone sleeve in the thickness direction, and the length of the cone sleeve contraction seam is smaller than the width of the annular structure where the cone sleeve contraction seam is located.

4. The elastic clamping fixture for inertial friction of an aircraft engine compressor drum according to claim 1, characterized in that: When the inner ring is installed, the narrower end faces the bottom of the installation cavity where the inner ring is located.

5. The elastic clamping tool for inertial friction of an aircraft engine compressor drum according to claim 1, characterized in that: The inner cavity of the elastic jacket is provided with a 15° chamfer.

6. The elastic clamping fixture for inertial friction of an aircraft engine compressor drum according to claim 1, characterized in that: The outer diameter of the outer ring is adapted to the inner diameter of the sleeve on the welding tool.

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