Machining tooling for turbine casings for aeroengines and method thereof

Abstract

The application provides a machining tool for a turbine casing of an aero-engine and a method thereof, comprising a base, a first support block, an inner pressing plate, a first screw, an arc-shaped sliding block, an arc-shaped rubber pad, a center pressing bolt, a stand, a ring pressing plate, a support ring, a positioning pin, a bracket, a support shaft and a ring frame; the bracket and the T-shaped shaft can replace the inner pressing plate and the center bolt, the bracket and the T-shaped shaft are coaxial with the base, the T-shaped shaft is inserted into the base, the bracket is supported by the T-shaped shaft, and the bracket is used for coaxially supporting the turbine casing, the bracket has a plurality of positioning holes which are distributed in a ring shape and are matched with the positioning pin, and the bracket is used for positioning the bottom flange of the turbine casing. The application realizes clamp loading and unloading, quick replacement and flexible machining, avoids repeated clamp loading and unloading, reduces the error of clamp loading, reduces the time of clamp alignment, only needs to clamp the part three times to ensure the machining precision of the part, improves the machining efficiency, reduces the manufacturing cost of the tool, is convenient for production management, reduces the deformation of the part, improves the machining precision of the part, effectively ensures the machining quality of the part, uses one set of clamp to complete the finish machining of the part, improves the machining efficiency and precision, and the vibration reduction device for turning can be replaced and adjusted according to the size of the outer diameter and has a universal type.

Description

Technical Field

[0001] This invention relates to the field of aero-engines, and more specifically to a method for processing a turbine casing for an aero-engine. Background Technology

[0002] The turbine casing is a typical large-sized, thin-walled casing component in aero-engines. It has relatively low overall rigidity, is made of high-temperature alloys, and is a crucial high-temperature load-bearing component with relatively high precision requirements. As an assembly base for other parts, the machining quality of this component not only affects the operational quality of the individual part but also directly impacts the stability of the entire mechanical system, playing a pivotal role in the overall system. The component's low overall rigidity, susceptibility to deformation during machining, low surface roughness, poor machinability of the high-temperature alloy material, and the difficulty in machining high-precision positioning holes result in low machining efficiency and yield. Summary of the Invention

[0003] The purpose of this invention

[0004] The purpose of this invention is to provide a machining process for turbine casings, which reduces part deformation, improves part surface quality and positioning hole accuracy, and achieves stable machining.

[0005] The technical solution of this invention is:

[0006] The present invention provides a machining fixture for a turbine casing for an aero-engine, comprising: a base 1, a first support block 2, an inner pressure plate 3, a first screw 4, an arc-shaped slider 5, an arc-shaped rubber pad 6, a central clamping bolt 7, a column 8, a circumferential pressure plate 11, a support ring 12, a positioning pin 13, a bracket 14, a support shaft 16, and a ring frame 17.

[0007] The base is coaxial with the turbine casing parts, and multiple columns 8 are circumferentially distributed and fixed on the base plane with the center point of the base as the center; the ring frame 17 is parallel to the base, and the upper ends of the multiple columns are fixedly connected to the ring frame 17.

[0008] Multiple arc-shaped sliders 5 are circumferentially distributed on the inner ring of the ring frame 17. A radial guide rod is formed on the inner ring of the ring frame 17. The arc-shaped sliders 5 slide with the ring frame through the radial guide rod. Multiple first screws 4 are radially threaded with the ring frame, and the end of each first screw is correspondingly and fixedly connected to an arc-shaped slider 5. Rotating the first screw can drive the arc-shaped slider 5 to move radially.

[0009] Multiple first support blocks 2 are arranged in a ring on the base 1. Each first support block 2 is radially slidably engaged with the base, and a locking pin is provided on the first support block 2. The locking pin can lock the first support block 2 to the base.

[0010] The inner pressure plate is coaxial with the base and can be penetrated and screwed onto the base by the central clamping bolt 7, for pressing it onto the base inside the turbine casing;

[0011] The bracket 14 and the support shaft 16 can replace the inner pressure plate and the center bolt 7. The bracket 14 and the support shaft 16 are both coaxial with the base. The support shaft 16 is inserted into the base. The bracket is supported by the support shaft 16 for coaxial support of the turbine casing. The bracket 14 has a plurality of positioning holes distributed in a ring and cooperates with the positioning pin 13 for positioning the bottom flange of the turbine casing.

[0012] The support ring 12 can replace the ring frame 17, and multiple circumferential pressure plates 11 are distributed on the support ring. The circumferential pressure plates 11 are detachably connected to the support ring and are used to press and fix the upper flange of the turbine casing.

[0013] Furthermore, it also includes a plurality of second screws 15, each of which is threaded into the support shaft, and the end of the second screw 15 passes through the support shaft and abuts against the base. Rotating the second screw 15 can adjust the horizontal height and levelness of the support shaft.

[0014] Furthermore, it also includes an arc-shaped rubber pad 6, which is adapted to the front end of the arc-shaped slider. This pad is used for contact with the turbine casing, providing support and cushioning.

[0015] Furthermore, the arc-shaped slider 5 includes a large size and a small size, corresponding to the wide outer diameter and narrow outer diameter of the turbine casing, respectively; the arc-shaped rubber pad 6 includes a large size and a small size, corresponding to the large and small arc-shaped sliders 5.

[0016] This invention provides a method for machining a turbine casing for an aero-engine.

[0017] Step 1: Place the turbine casing with the wide outer diameter end facing upwards on the base plane, adjust the multiple arc-shaped sliders 5 so that the multiple arc-shaped sliders 5 radially abut against the outer wall of the wide outer diameter of the turbine casing, rotate the center clamping bolt so that the inner pressure plate presses the turbine casing tightly inside the turbine casing; adjust the first support block 2 so that the first support block 2 abuts against the outer wall of the narrow outer diameter of the turbine casing.

[0018] Step 2: Perform precision machining on the wide outer diameter section of the turbine casing;

[0019] Step 3: Remove the inner pressure plate, the center clamping bolt, and the turbine casing from the base. Place the narrow outer diameter end of the turbine casing upwards onto the base plane. Adjust the multiple arc-shaped sliders 5 so that they radially abut against the outer wall of the narrow outer diameter of the turbine casing. Adjust the first support block 2 so that it abuts against the outer wall of the wide outer diameter of the turbine casing.

[0020] Step 4: Perform precision machining on the narrow outer diameter section of the turbine casing;

[0021] Step 5: Remove the ring frame 17 and the first support block 2 from the base, install and fix the bracket 14 and the support shaft 16 coaxially to the base, fasten the wide outer diameter end of the turbine casing upward onto the bracket 14, fix the circumferential pressure plate 11 to the support ring, and press and fix the upper flange of the turbine casing.

[0022] Step 6: Perform precision machining on the wide outer diameter portion of the turbine casing.

[0023] Furthermore, in step 2, the turbine casing is stress-relieved before finishing.

[0024] Furthermore, the finishing process includes boring, initial drilling, and threading.

[0025] Furthermore, precision boring employs a boring-then-reaming machining method. Boring ensures the hole diameter position, while reaming ensures the dimensions. During boring, a single-sided allowance is retained for the hole diameter, followed by reaming. By selecting appropriate coated tools, machining parameters, and machining strategies, the challenging machining of high-temperature alloy materials is overcome. Even further, threaded hole machining utilizes a thread milling cutter for thread milling. The threaded hole is milled in stages, with new values ​​continuously assigned via macro programming statements to achieve layered milling.

[0026] Advantages of the present invention

[0027] This invention enables quick-change and flexible fixture loading and unloading, avoiding repeated fixture loading and unloading, reducing fixture clamping errors, and shortening fixture alignment time. Only three clamping operations are required to ensure part machining accuracy, thus improving machining efficiency, reducing tooling manufacturing costs, and facilitating production management. The device reduces part deformation and improves machining accuracy, effectively guaranteeing part machining quality. A single set of fixtures is used to complete the finishing of the part, improving both machining efficiency and precision. The turning and shearing vibration reduction device can be changed and adjusted according to the outer diameter, making it a universal design. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the structure of the present invention;

[0029] Figure 2 This is a partial structural view of the turbine casing;

[0030] Figure 3 This is a schematic diagram of step 1;

[0031] Figure 4 This is a schematic diagram of step 3;

[0032] Figure 5 This is a schematic diagram of an arc-shaped slider;

[0033] Figure 6 and 7 This is a schematic diagram of step 5;

[0034] Figure 8 This is a schematic diagram of the base plate;

[0035] Figure 9 This is a schematic diagram of the support ring structure;

[0036] The components include: base 1, first support block 2, inner pressure plate 3, first screw 4, arc-shaped slider 5 (large size), arc-shaped rubber pad 6 (large size), center clamping bolt 7, column 8, arc-shaped slider 9 (small size), arc-shaped rubber pad 10 (small size), circumferential pressure plate 11, support ring 12, positioning pin 13, bracket 14, support shaft 16, and ring frame 17. Detailed Implementation

[0037] The disclosed examples will be described more fully with reference to the accompanying drawings, in which some (but not all) of the disclosed examples are shown. In fact, many different examples may be described, and these examples should not be construed as limited to those set forth herein. These examples are described so that this disclosure will be thorough and complete, and will fully convey the scope of this disclosure to those skilled in the art.

[0038] A machining fixture for a turbine casing for an aero-engine is provided, comprising: a base 1, a first support block 2, an inner pressure plate 3, a first screw 4, an arc-shaped slider 5, an arc-shaped rubber pad 6, a central clamping bolt 7, a column 8, a circumferential pressure plate 11, a support ring 12, a positioning pin 13, a bracket 14, a support shaft 16, and a ring frame 17.

[0039] The base is coaxial with the turbine casing parts, and multiple columns 8 are circumferentially distributed and fixed on the base plane with the center point of the base as the center; the ring frame 17 is parallel to the base, and the upper ends of the multiple columns are fixedly connected to the ring frame 17.

[0040] Multiple arc-shaped sliders 5 are circumferentially distributed on the inner ring of the ring frame 17. A radial guide rod is formed on the inner ring of the ring frame 17. The arc-shaped sliders 5 slide with the ring frame through the radial guide rod. Multiple first screws 4 are radially threaded with the ring frame, and the end of each first screw is correspondingly and fixedly connected to an arc-shaped slider 5. Rotating the first screw can drive the arc-shaped slider 5 to move radially.

[0041] Multiple first support blocks 2 are arranged in a ring on the base 1. Each first support block 2 is radially slidably engaged with the base, and a locking pin is provided on the first support block 2. The locking pin can lock the first support block 2 to the base.

[0042] The inner pressure plate is coaxial with the base and can be penetrated and screwed onto the base by the central clamping bolt 7, for pressing it onto the base inside the turbine casing;

[0043] The bracket 14 and the support shaft 16 can replace the inner pressure plate and the center bolt 7. The bracket 14 and the support shaft 16 are both coaxial with the base. The support shaft 16 is inserted into the base. The bracket is supported by the support shaft 16 for coaxial support of the turbine casing. The bracket 14 has a plurality of positioning holes distributed in a ring and cooperates with the positioning pin 13 for positioning the bottom flange of the turbine casing.

[0044] The support ring 12 can replace the ring frame 17, and multiple circumferential pressure plates 11 are distributed on the support ring. The circumferential pressure plates 11 are detachably connected to the support ring and are used to press and fix the upper flange of the turbine casing.

[0045] It also includes a plurality of second screws 15, each of which is threaded into the support shaft, and the end of the second screw 15 passes through the support shaft and abuts against the base. Rotating the second screw 15 can adjust the horizontal height and levelness of the support shaft.

[0046] It also includes an arc-shaped rubber pad 6, which is adapted to the front end of the arc-shaped slider. This pad is used for contact with the turbine casing, providing support and cushioning.

[0047] The arc-shaped slider 5 includes a large size and a small size, which correspond to the wide outer diameter and narrow outer diameter of the turbine casing, respectively; the arc-shaped rubber pad 6 includes a large size and a small size, which correspond to the large and small sizes of the arc-shaped slider 5.

[0048] This invention provides a method for machining a turbine casing for an aero-engine.

[0049] Step 1: Place the turbine casing with the wide outer diameter end facing upwards on the base plane, adjust the multiple arc-shaped sliders 5 so that the multiple arc-shaped sliders 5 radially abut against the outer wall of the wide outer diameter of the turbine casing, rotate the center clamping bolt so that the inner pressure plate presses the turbine casing tightly inside the turbine casing; adjust the first support block 2 so that the first support block 2 abuts against the outer wall of the narrow outer diameter of the turbine casing.

[0050] Step 2: Perform precision machining on the wide outer diameter section of the turbine casing;

[0051] Step 3: Remove the inner pressure plate, the center clamping bolt, and the turbine casing from the base. Place the narrow outer diameter end of the turbine casing upwards onto the base plane. Adjust the multiple arc-shaped sliders 5 so that they radially abut against the outer wall of the narrow outer diameter of the turbine casing. Adjust the first support block 2 so that it abuts against the outer wall of the wide outer diameter of the turbine casing.

[0052] Step 4: Perform precision machining on the narrow outer diameter section of the turbine casing;

[0053] Step 5: Remove the ring frame 17 and the first support block 2 from the base, install and fix the bracket 14 and the support shaft 16 coaxially to the base, fasten the wide outer diameter end of the turbine casing upward onto the bracket 14, fix the circumferential pressure plate 11 to the support ring, and press and fix the upper flange of the turbine casing.

[0054] Step 6: Perform precision machining on the wide outer diameter portion of the turbine casing.

[0055] In step 2, stress is relieved on the turbine casing before finishing.

[0056] The finishing process includes boring, initial drilling, and threading.

[0057] Descriptions of various advantageous arrangements have been shown for illustrative and descriptive purposes, but such descriptions are not intended to be exclusive or limited to the disclosed forms. Many modifications and variations will be apparent to those skilled in the art. Furthermore, different advantageous examples may describe different advantages compared to other advantageous examples. One or more examples have been selected and described in order to best illustrate the principles and practical application of the examples, and to enable those skilled in the art to understand that this disclosure contains various examples with various modifications suitable for the particular intended use.

Claims

1. A machining fixture for a turbine casing of an aircraft engine, characterized in that: Base 1, first support block (2), inner pressure plate (3), first screw (4), arc-shaped slider (5), arc-shaped rubber pad (6), center clamping bolt (7), column (8), circumferential pressure plate (11), support ring (12), positioning pin (13), bracket (14), support shaft (16) and ring frame (17); The base is coaxial with the turbine casing parts, and multiple columns (8) are circumferentially distributed and fixed on the base plane with the center point of the base as the center; the ring frame (17) is parallel to the base, and the upper ends of the multiple columns are fixedly connected to the ring frame. Multiple arc-shaped sliders (5) are distributed circumferentially in the inner ring of the ring frame (17). A radial guide rod is formed in the inner ring of the ring frame (17). The arc-shaped sliders (5) slide with the ring frame through the radial guide rod. Multiple first screws (4) are radially threaded with the ring frame, and the end of each first screw is correspondingly and fixedly connected to an arc-shaped slider (5). Rotating the first screw can drive the arc-shaped slider (5) to move radially. The base (1) has a plurality of first support blocks (2) arranged in a ring. Each first support block is radially slidably fitted with the base, and a locking pin is provided on the first support block (2). The locking pin can lock the first support block to the base. The inner pressure plate is coaxial with the base and can be penetrated and spirally pressed onto the base by the central clamping bolt, for pressing it onto the base inside the turbine casing; The bracket (14) and support shaft (16) can replace the inner pressure plate and the center clamping bolt. The bracket and support shaft (16) are coaxial with the base. The support shaft is inserted into the base. The bracket is supported by the support shaft and is used to coaxially support the turbine casing. The bracket has multiple positioning holes distributed in a ring and cooperates with the positioning pin (13) for positioning the bottom flange of the turbine casing. The support ring (12) can replace the ring frame (17), and multiple circumferential pressure plates are distributed on the support ring. The circumferential pressure plates (11) are detachably connected to the support ring and are used for pressing and fixing the upper flange of the turbine casing.

2. The machining fixture for the turbine casing of an aero-engine as described in claim 1, characterized in that: It also includes multiple second screws, each second screw (15) being threaded into the support shaft, and the end of the second screw (15) passing through the support shaft and abutting against the base. Rotating the second screw can adjust the horizontal height and level of the support shaft.

3. The machining fixture for the turbine casing of an aero-engine as described in claim 1, characterized in that: It also includes an arc-shaped rubber pad 6, which is adapted to the front end of the arc-shaped slider; Used for contact with the turbine casing, providing support and cushioning.

4. The machining fixture for the turbine casing of an aero-engine as described in claim 3, characterized in that: The arc-shaped slider (5) includes a large size and a small size, which correspond to the wide outer diameter and narrow outer diameter of the turbine casing, respectively; the arc-shaped rubber pad (6) includes a large size and a small size, which correspond to the large size and the small size of the arc-shaped slider.

5. A machining method for a turbine casing for an aircraft engine according to any one of claims 1-4, comprising the following steps: Step 1: Place the wide outer diameter end of the turbine casing upwards on the base plane, adjust multiple arc-shaped sliders (5) so that the multiple arc-shaped sliders radially abut against the outer wall of the wide outer diameter of the turbine casing, rotate the central clamping bolt so that the inner pressure plate presses the turbine casing inside the turbine casing; adjust the first support block (2) so that the first support block abuts against the outer wall of the narrow outer diameter of the turbine casing. Step 2: Perform precision machining on the wide outer diameter section of the turbine casing; Step 3: Remove the inner pressure plate, the center clamping bolt, and the turbine casing from the base. Place the narrow outer diameter end of the turbine casing upwards onto the base plane. Adjust the multiple arc-shaped sliders so that they radially abut against the outer wall of the narrow outer diameter of the turbine casing. Adjust the first support block so that it abuts against the outer wall of the wide outer diameter of the turbine casing. Step 4: Perform precision machining on the narrow outer diameter section of the turbine casing; Step 5: Remove the ring frame (17) and the first support block from the base, install and fix the bracket and support shaft coaxially to the base, fasten the wide outer diameter end of the turbine casing upwards onto the bracket, fix the circumferential pressure plate to the support ring, and press and fix the upper flange of the turbine casing. Step 6: Perform precision machining on the wide outer diameter portion of the turbine casing.

6. The machining method for the machining fixture of the turbine casing for an aero-engine as described in claim 5, characterized in that: In step 2, stress is relieved on the turbine casing before finishing.

7. The machining method for the machining fixture of the turbine casing for an aero-engine as described in claim 5, characterized in that: The finishing process includes boring, initial drilling, and threading.

8. The machining method of the machining fixture for the turbine casing of an aero-engine as described in claim 7, characterized in that: Precision boring adopts a machining method of boring first and then reaming; boring can ensure the hole diameter position, and reaming can ensure the size.

9. The machining method of the machining fixture for the turbine casing of an aero-engine as described in claim 7, characterized in that: Threaded hole machining uses a thread milling cutter to mill the threaded hole in stages, and the layered milling process is achieved by continuously assigning new values ​​through macro program statements.

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