Tool clamp special for aero-engine bearing chamber
By designing special tooling fixtures for the bearing chamber of the aircraft engine, the combination of positioning clamping discs, positioning bosses, strip pressing plates, mandrels and tightening mechanisms is used to solve the problem of bearing hole processing accuracy and inefficiency, and stable and efficient bearing hole processing is achieved.
Patent Information
- Application Number
- CN202421780865.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-25
- Publication Date
- 2025-04-29
- Estimated Expiration
- 2034-07-25
AI Technical Summary
When processing the bearing chamber of an aircraft engine, the prior art is difficult to achieve high precision and efficient processing of bearing holes, and the correcting is difficult, resulting in low production efficiency.
A special tool clamp for the bearing chamber of an aero engine is designed, including a positioning clamping disc, a positioning boss, a strip pressing plate, a mandrel and a tightening mechanism. Through the cooperation of these components, stable clamping and high-precision processing of the bearing chamber are achieved.
This tooling fixture can achieve stable clamping of bearing holes, improve processing accuracy and efficiency, and has repeatable positioning function, saves clamping time and is suitable for mass production.
Smart Images
Figure CN222806127U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of tooling fixtures, and in particular to a special tooling fixture for a bearing chamber of an aero-engine. Background Art
[0002] As the heart of the aircraft, the aircraft engine is known as the "crown jewel" of modern industry, and the bearing chamber, as the core part of the engine, provides a strong guarantee for the performance of the aircraft engine. The bearing chamber generally includes a central inner hole and bearing holes at both ends thereof. For the convenience of connection, flanges are generally provided at the ends of the bearing holes. Among them, the bearing holes have very high requirements for precision. At present, when processing the bearing holes at both ends of the bearing chamber, it is usually adopted to align the already processed bearing hole at one end to process the bearing hole at the other end. Because the alignment is difficult, it will take a lot of time to align, and it is impossible to achieve repeated positioning. In mass production, each part must be aligned, which greatly wastes time. Therefore, it is particularly important to design a special tooling fixture that can improve clamping stability, processing efficiency and precision. Utility Model Content
[0003] In view of the above-mentioned deficiencies in the prior art, the utility model provides a special tooling fixture for an aircraft engine bearing chamber, which solves the problem of low production efficiency caused by time-consuming and labor-intensive clamping and positioning of the bearing chamber.
[0004] In order to achieve the above purpose, the technical solution adopted by the utility model is:
[0005] A special tooling fixture for an aircraft engine bearing chamber is provided, which comprises a positioning clamping disc, one end of which is provided with a positioning boss for cooperating with a bearing hole, a plurality of strip pressure plates for pressing the bearing chamber onto the positioning clamping disc are arranged around the positioning boss, a core shaft is arranged on the positioning boss, and a tensioning mechanism for tensioning the central inner hole of the bearing chamber is arranged at the end of the core shaft away from the positioning boss.
[0006] Furthermore, the tensioning mechanism includes a tensioning threaded hole opened at the center of the end of the core shaft, and a plurality of open grooves are opened on the circumference of the core shaft to facilitate radial expansion of the core shaft, and the open grooves are connected to the tensioning threaded hole, and a flared conical surface is opened at the end of the tensioning threaded hole, and a tensioning bolt is matched on the tensioning threaded hole, and a frustum body matching the flared conical surface is arranged at the end of the tensioning bolt.
[0007] Furthermore, the radial dimension of the positioning boss matches the radial dimension of the bearing hole of the bearing chamber, and the radial dimension of the core shaft matches the radial dimension of the central inner hole of the bearing chamber.
[0008] Furthermore, a strip hole is arranged on the strip pressure plate, and a plurality of clamping threaded holes are arranged on the circumference of the positioning clamping disc. The strip pressure plate is fastened by clamping bolts passing through the strip holes and cooperating with the clamping threaded holes.
[0009] Furthermore, an annular boss is provided on the outer edge of the end of the positioning clamping disc, the axial dimension of the annular boss is the same as the axial dimension of the flange at the bearing hole port, and the strip pressure plate abuts against the annular boss and the flange at the bearing hole port at the same time.
[0010] Furthermore, the positioning clamping disc is clamped and fixed on the CNC lathe by a three-jaw chuck.
[0011] The beneficial effects of the utility model are:
[0012] 1. This scheme can realize stable clamping of the bearing holes at both ends of the bearing chamber during the processing, improve the processing accuracy and surface roughness of the bearing holes, and has a repeatable positioning function, without the need for alignment, which greatly saves clamping time and thus improves processing efficiency; wherein, by pressing the flange at the end of the bearing hole through a number of strip pressure plates, the entire bearing chamber is pressed and fixed on the positioning clamping disc; through the close cooperation between the positioning boss and the bearing hole of the bearing chamber, the shape and position tolerance requirements of the bearing holes at both ends of the bearing chamber are effectively guaranteed; the core shaft is radially expanded by the tensioning bolts, so that the core shaft is tightened in the central inner hole of the bearing chamber, thereby playing a positioning and supporting role in the processing of the bearing hole at the other end of the bearing chamber, thereby improving the processing accuracy and the stability and reliability of the processing.
[0013] 2. This solution has simple loading and unloading process for the clamping process of the bearing chamber, convenient and quick operation, strong versatility, high repeatability and positioning accuracy, and is suitable for mass production of bearing chambers. BRIEF DESCRIPTION OF THE DRAWINGS
[0014] Figure 1 This is a schematic diagram of the structure of the special tooling fixture for the bearing chamber of an aircraft engine.
[0015] Figure 2 This is a schematic diagram of the structure of this solution and the bearing chamber clamping.
[0016] Figure 3 for Figure 2 sectional view of .
[0017] Among them, 1. positioning clamping disc, 2. positioning boss, 3. strip pressure plate, 4. core shaft, 5. tightening threaded hole, 6. opening groove, 7. flared cone, 8. tightening bolt, 9. truncated cone body, 10. strip hole, 11. tightening bolt, 12. annular boss, 13. bearing chamber, 14. bearing hole, 15. flange. DETAILED DESCRIPTION
[0018] The specific implementation methods of the utility model are described below to facilitate technical personnel in this technical field to understand the utility model, but it should be clear that the utility model is not limited to the scope of the specific implementation methods. For ordinary technical personnel in this technical field, as long as various changes are within the spirit and scope of the utility model defined and determined by the attached claims, these changes are obvious, and all utility model creations using the concept of the utility model are protected.
[0019] like Figures 1 to 3 As shown, the special tooling fixture for the aircraft engine bearing chamber 13 of the present scheme includes a positioning clamping disc 1, a positioning boss 2 is provided at one end of the positioning clamping disc 1, and the radial dimension of the positioning boss 2 is matched with the radial dimension of the bearing hole 14 of the bearing chamber 13; three strip pressure plates 3 are provided around the positioning boss 2, and strip holes 10 are provided on the strip pressure plates 3, and three clamping threaded holes are provided on the circumference of the positioning clamping disc 1, and the strip pressure plates 3 are fastened by clamping bolts 11 passing through the strip holes 10 and cooperating with the clamping threaded holes.
[0020] An annular boss 12 is provided on the outer edge of the end of the positioning and clamping disc 1, and the axial dimension of the annular boss 12 is the same as the axial dimension of the flange 15 at the end of the bearing hole 14. The strip pressure plate 3 is simultaneously in contact with the annular boss 12 and the flange 15 at the end of the bearing hole 14. In this scheme, the flange 15 at the end of the bearing hole 14 is pressed by three strip pressure plates 3 to realize the pressing and fixing of the entire bearing chamber 13 on the positioning and clamping disc 1. At the same time, the strip pressure plate 3 can be adjusted in radial direction through the strip hole 10 to facilitate the pressing of flanges 15 of different sizes.
[0021] A core shaft 4 is arranged on the positioning boss 2, and the radial dimension of the core shaft 4 is matched with the radial dimension of the central inner hole of the bearing chamber 13; a tensioning mechanism for tightening the central inner hole of the bearing chamber 13 is arranged at one end of the core shaft 4 away from the positioning boss 2, and the tensioning mechanism includes a tensioning threaded hole 5 opened at the center of the end of the core shaft 4, and four opening grooves 6 are opened on the circumference of the core shaft 4 to facilitate the radial expansion of the core shaft 4, and the four opening grooves 6 are arranged in a cross on the core shaft 4, and the opening grooves 6 are connected with the tensioning threaded hole 5; a flared conical surface 7 is opened at the end of the tensioning threaded hole 5, and a tensioning bolt 8 is matched on the tensioning threaded hole 5, and a truncated cone body 9 matching the flared conical surface 7 is arranged at the end of the tensioning bolt 8.
[0022] This solution effectively ensures the form and position tolerance requirements of the bearing holes 14 at both ends of the bearing chamber 13 through the close fit between the positioning boss 2 and the bearing hole 14 of the bearing chamber 13; the core shaft 4 is radially expanded by the tightening bolt 8, so that the core shaft 4 is tightened in the central inner hole of the bearing chamber 13, thereby playing a positioning and supporting role in the processing of the bearing hole 14 at the other end of the bearing chamber 13, thereby improving the processing accuracy and the stability and reliability of the processing.
[0023] During processing of this scheme, the positioning clamping disc 1 can be clamped and fixed on the CNC lathe by a three-jaw chuck, and the bearing chamber 13 can be processed once on the CNC lathe; during specific implementation, the bearing hole 14 that has been processed at one end of the bearing chamber 13 is first tightly matched and positioned with the positioning boss 2, and then the bearing chamber 13 is fixed on the positioning clamping disc 1 through the cooperation of the clamping bolt 11 and the strip pressure plate 3; thereafter, the tensioning bolt 8 is tightened so that the truncated cone body 9 at the end of the tensioning bolt 8 is tightly fitted with the expanded conical surface 7 at the end of the tensioning threaded hole 5, so that the core shaft 4 tightens the central inner hole of the bearing chamber 13; at this time, the bearing hole 14 at the other end of the bearing chamber 13 can be processed on the CNC machine tool; after the processing is completed, the tensioning bolt 8 and the clamping bolt 11 are loosened, and the next bearing chamber 13 is replaced for processing without alignment, thereby realizing efficient and stable mass production.
[0024] In summary, this solution can achieve stable clamping of the bearing holes 14 at both ends of the bearing chamber 13 during processing, improve the processing accuracy and surface roughness of the bearing holes 14, and have a repeatable positioning function, which greatly saves clamping time and thus improves processing efficiency.
Claims
1. A special fixture for an aircraft engine bearing chamber, characterized in that: It includes a positioning clamping disc, one end of which is provided with a positioning boss for cooperating with the bearing hole, a plurality of strip pressure plates for pressing the bearing chamber onto the positioning clamping disc are arranged around the positioning boss, a core shaft is arranged on the positioning boss, and a tensioning mechanism for tightening the central inner hole of the bearing chamber is arranged at the end of the core shaft away from the positioning boss.
2. The special fixture for the bearing chamber of an aircraft engine according to claim 1, characterized in that: The tensioning mechanism includes a tensioning threaded hole opened at the center of the end of the core shaft, a plurality of open grooves are opened on the circumference of the core shaft to facilitate the radial expansion of the core shaft, and the open grooves are connected to the tensioning threaded hole, a flared conical surface is opened at the end of the tensioning threaded hole, a tensioning bolt is matched on the tensioning threaded hole, and a frustum body matching the flared conical surface is arranged at the end of the tensioning bolt.
3. The special fixture for the bearing chamber of an aircraft engine according to claim 2, characterized in that: The radial dimension of the positioning boss matches the radial dimension of the bearing hole of the bearing chamber, and the radial dimension of the core shaft matches the radial dimension of the central inner hole of the bearing chamber.
4. The special fixture for the bearing chamber of an aircraft engine according to claim 1, characterized in that: The strip pressure plate is provided with a strip hole, and the positioning clamping disc is provided with a plurality of clamping threaded holes on its circumference. The strip pressure plate is fastened by clamping bolts passing through the strip holes and cooperating with the clamping threaded holes.
5. The special fixture for the bearing chamber of an aircraft engine according to claim 4, characterized in that: An annular boss is arranged on the outer edge of the end of the positioning clamping disc, the axial dimension of the annular boss is the same as the axial dimension of the flange at the end of the bearing hole, and the strip pressure plate abuts against the annular boss and the flange at the end of the bearing hole at the same time.
6. The special fixture for the bearing chamber of an aircraft engine according to claim 1, characterized in that: The positioning clamping disc is clamped and fixed on the CNC lathe by a three-jaw chuck.