An aero-engine blade sizing tool

Abstract

The utility model discloses an aero-engine blade shaping frock relates to aero-engine blade production technical field, aims at solving the problem that the blade production process in the prior art, the blade crown angle often exceeds the drawing requirement range because of deformation, lacks the shaping frock and adjusts, and its technical scheme main points are including clamping seat, the first clamping groove is reserved to one end of clamping seat outside, the inside of clamping seat is seted up with the screw hole and the clamping groove, the other end of clamping seat outside reserves the installation groove, the outside of clamping seat is provided with the clamping block, the outside of clamping block reserves the second clamping groove, the outside fixedly connected with the clamping block of clamping block has the clamping block, the inside of clamping block is seted up with the countersunk hole, and the inside of countersunk hole is inserted with the bolt. Reach the effect that the convenient adjustment uses.

Description

Technical Field

[0001] This utility model relates to the field of aero-engine blade manufacturing technology, and in particular to an aero-engine blade shaping tooling. Background Technology

[0002] Compared to equiaxed blades, oriented stranded blades for aero engines have only a few grain boundaries in a direction approximately parallel to the blade's working axis (i.e., the Z-axis). Because the transverse grain boundaries are eliminated, the service life and performance of oriented stranded blades are improved to a certain extent, and they have been widely used in the field of aero engines. When manufacturing oriented stranded blades, the blade crown angle must be controlled according to the acceptance standards to ensure their later use.

[0003] The existing technical solutions mentioned above have the following drawbacks: In the current blade production process, the blade crown angle often exceeds the range required by the drawings due to deformation, and there is a lack of standardized tooling for adjustment. Utility Model Content

[0004] The purpose of this invention is to provide a tooling for shaping aero-engine blades.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] A blade shaping fixture for aero-engines includes a clamping seat, one end of which has a first clamping groove, the interior of which has a slot and a threaded hole, the other end of which has an installation groove, a clamping block on the outside of the clamping seat, a second clamping groove on the outside of the clamping block, a locking block fixedly connected to the outside of the clamping block, and a countersunk hole inside the clamping block into which a bolt is inserted.

[0007] By adopting the above technical solution, a clamping structure is added to the bottom of the blade. The blade can be clamped and fixed by the cooperation between the clamping seat and the clamping block, and by locking the two parts with bolts. At the same time, the overall structure is simple and easy to adjust and use.

[0008] Furthermore, an adjustment block is provided on the outer side of the clamping seat, and a handle is fixedly connected to the outer side of the adjustment block. A groove is opened inside the adjustment block, and a blade body is installed between the first clamping groove and the second clamping groove.

[0009] By adopting the above technical solution, an adjustment device for the blade is added to the outside. The groove inside the adjustment block can be installed with one end of the blade. By manually rotating the adjustment block, the angle of the blade can be adjusted to shape the casting.

[0010] Furthermore, the first clamping groove and the second clamping groove are the same size and have the same specifications. There are two of each of the slot and the block. The block and the slot are engaged. The clamping block and the mounting groove are engaged. There are two of each of the threaded hole, the countersunk hole and the bolt. The bolt passes through the countersunk hole and extends into the threaded hole, and is threadedly connected to the threaded hole.

[0011] By adopting the above technical solution, the clamping seat and clamping block can be better matched and used.

[0012] Furthermore, the inner sides of both the first and second clamping grooves are in contact with the outer side of the blade body, and one end of the outer side of the blade body is inserted into the inside of the groove.

[0013] By adopting the above technical solution, the blades are shaped using adjusting blocks.

[0014] In summary, the beneficial technical effects of this utility model are as follows:

[0015] The system employs a clamping seat, clamping block, bolts, and adjusting block. The bolts control the locking and fixing between the clamping block and the clamping seat, allowing one end of the blade inside the clamping groove to be clamped. At the same time, the adjusting block engages with the other end of the blade. Rotating the adjusting block begins to shape the blade, adjusting the angle to the appropriate position. Then, the casting angle is checked, and the above operations are repeated until it meets the requirements of the machining drawings, resulting in a convenient adjustment and use effect. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0017] Figure 2 This is a schematic diagram of the disassembled structure of this utility model;

[0018] Figure 3 This is a three-dimensional structural diagram of the clamping base of this utility model;

[0019] Figure 4 This is a schematic diagram of the three-dimensional structure of the clamping block of this utility model;

[0020] Figure 5 This is a three-dimensional structural diagram of the adjusting block of this utility model;

[0021] Figure 6 This is a schematic diagram showing the dimensional requirements of the leaf crown angle of this utility model.

[0022] In the figure, 1 is the clamping seat; 2 is the first clamping groove; 3 is the slot; 4 is the threaded hole; 5 is the mounting groove; 6 is the clamping block; 7 is the second clamping groove; 8 is the slot; 9 is the countersunk hole; 10 is the bolt; 11 is the adjusting block; 12 is the handle; 13 is the groove; and 14 is the blade body. Detailed Implementation

[0023] The present invention will be further described in detail below with reference to the accompanying drawings.

[0024] Reference Figure 1-6 A blade shaping fixture for aero-engines includes a clamping base 1. One end of the clamping base 1 has a first clamping groove 2. The clamping base 1 has a slot 3 and a threaded hole 4 inside. The other end of the clamping base 1 has an installation groove 5. A clamping block 6 is provided on the outer side of the clamping base 1. A second clamping groove 7 is provided on the outer side of the clamping block 6. A retaining block 8 is fixedly connected to the outer side of the clamping block 6. A countersunk hole 9 is provided inside the clamping block 6, and a bolt 10 is inserted into the countersunk hole 9. An adjusting block 11 is provided on the outer side of the clamping base 1, and a handle 12 is fixedly connected to the outer side of the adjusting block 11. The segment 11 has a groove 13 inside. The blade body 14 is installed between the first clamping groove 2 and the second clamping groove 7. A clamping structure is added to the bottom of the blade. The blade can be clamped and fixed by the cooperation between the clamping seat 1 and the clamping block 6 and by locking the two parts with bolts 10. The overall structure is simple and easy to adjust and use. An adjustment device for the blade is added to the outside. The groove 13 inside the adjustment block 11 can be installed with one end of the blade. The angle of the blade can be adjusted by manually rotating the adjustment block 11 to shape the casting.

[0025] like Figure 1-6 As shown, the first clamping groove 2 and the second clamping groove 7 are the same size and have the same specifications. There are two slots 3 and two blocks 8 respectively. The blocks 8 and the slots 3 are engaged and connected. The clamping block 6 and the mounting groove 5 are engaged and connected. There are two threaded holes 4, countersunk holes 9 and two bolts 10 respectively. The bolts 10 pass through the countersunk holes 9 and extend into the inside of the threaded holes 4 and are threadedly connected to the threaded holes 4. The inner sides of the first clamping groove 2 and the second clamping groove 7 are in contact with the outer side of the blade body 14. One end of the outer side of the blade body 14 is inserted into the inside of the groove 13.

[0026] The implementation principle of this embodiment is as follows: one end of the blade is placed between the first clamping groove 2 and the second clamping groove 7 on the outside of the clamping seat 1 and the clamping block 6. Then, the bolt 10 is tightened to lock and fix the clamping block 6 and the clamping seat 1. At the same time, the locking block 8 is engaged in the middle of the locking groove 3, which can make the structure after the clamping block 6 is clamped more stable. Then, the groove 13 inside the adjusting block 11 is engaged with the other end of the blade. The handle 12 is manually gripped and rotated to start shaping the blade. The angle is checked while shaping until it meets the requirements.

[0027] The embodiments described herein are preferred embodiments of this utility model and are not intended to limit the scope of protection of this utility model. Therefore, all equivalent changes made to the structure, shape, and principle of this utility model should be included within the scope of protection of this utility model.

Claims

1. A blade shaping fixture for aero-engines, comprising a clamping seat (1), characterized in that: The clamping seat (1) has a first clamping groove (2) reserved at one end of its outer side. The clamping seat (1) has a slot (3) and a threaded hole (4) inside. The clamping seat (1) has an installation groove (5) reserved at the other end of its outer side. The clamping seat (1) has a clamping block (6) on its outer side. The clamping block (6) has a second clamping groove (7) reserved on its outer side. The clamping block (6) has a fixed connection to a locking block (8) on its outer side. The clamping block (6) has a countersunk hole (9) inside. The countersunk hole (9) has a bolt (10) inserted inside.

2. The aero-engine blade shaping fixture according to claim 1, characterized in that: An adjustment block (11) is provided on the outside of the clamping seat (1), and a handle (12) is fixedly connected to the outside of the adjustment block (11). A groove (13) is provided inside the adjustment block (11), and a blade body (14) is installed between the first clamping groove (2) and the second clamping groove (7).

3. The aero-engine blade shaping fixture according to claim 1, characterized in that: The first clamping groove (2) and the second clamping groove (7) are the same size and have the same specifications. There are two of each of the slot (3) and the block (8). The block (8) and the slot (3) are engaged. The clamping block (6) and the mounting groove (5) are engaged. There are two of each of the threaded hole (4), the countersunk hole (9) and the bolt (10). The bolt (10) passes through the countersunk hole (9) and extends into the threaded hole (4), and is threadedly connected to the threaded hole (4).

4. The aero-engine blade shaping fixture according to claim 2, characterized in that: The inner sides of the first clamping groove (2) and the second clamping groove (7) are in contact with the outer side of the blade body (14), and one end of the outer side of the blade body (14) is inserted into the inside of the groove (13).

Images