Protective clamp and method for wet sand blasting of blisk of aero-engine

Abstract

The invention relates to the technical field of aero-engine blisk surface treatment, in particular to a protective clamp and method for wet sand blasting of an aero-engine blisk. The protective clamp comprises an upper disc body, a lower disc body, an upper annular cover, a lower annular cover and a rubber plug; the upper annular cover and the lower annular cover are both of an annular structure. The upper disc body and the lower disc body are used for being buckled to the middle positions of the upper side and the lower side of the blisk correspondingly, and the upper disc body and the lower disc body are connected through a first bolt. The upper annular cover and the lower annular cover are used for being buckled on the edges of the upper side and the lower side of the blisk correspondingly, and the upper annular cover and the lower annular cover jointly form an annular containing cavity used for containing blades of the blisk. The upper annular cover and the lower annular cover are connected through a second bolt; the peripheral surface of the upper disc body and the inner hole surface of the upper annular cover are arranged at an interval; the outer peripheral surface of the lower disc body and the inner hole surface of the lower annular cover are arranged at an interval; the rubber plug is used for being inserted into the through hole, close to the edge, of the blisk.

Description

Technical Field

[0001] The invention relates to the technical field of surface treatment of an aero-engine integral blade disk, and in particular to a protective fixture and method for wet sand blowing of an aero-engine integral blade disk. Background Art

[0002] like Figure 1 , Figure 2 As shown, the surface of the integral blade disk part of the aircraft engine needs to be wet sandblasted in the area where the multiple through holes are located near the blade position. Figure 2 The H1 and H2 areas shown in the figure are wet sandblasted to improve the surface finish and strength of the parts, and enhance the surface hardness, bonding strength and corrosion resistance. At present, for the sandblasting process of integral blade disk parts, under normal circumstances, it is necessary to protect the non-processed surfaces (disk body and blade shape, etc.) on the parts except for the H1 and H2 areas, and sandblasting is not allowed on the non-sandblasting surfaces; among them, the industry generally uses manual pasting of protective tape or other soft materials for shielding and protection, while the blade part is wrapped with pearl cotton. Although this protection method is simple to operate, the amount of tape used at a time is large, and the tape wrapping and pasting takes a long time, and the protection efficiency is low; in addition, during wet sandblasting, due to the high wind pressure, the viscosity of some tapes is reduced, which can easily cause the tape to fall off, resulting in damage to the non-sandblasting surface, which greatly affects the overall sandblasting quality of the parts and subsequent spraying operations. In addition, the existing protection method is easy to bump into the blades during the transportation of parts, causing blade damage, affecting the product qualification rate, and even causing parts to be scrapped. Summary of the invention

[0003] The main purpose of the present invention is to provide a protective fixture and method for wet sand blowing of an integral blade disk of an aero-engine, aiming to solve the above-mentioned technical problems.

[0004] To achieve the above-mentioned purpose, on the one hand, the present invention proposes a protective clamp for wet sand blowing of an integral blade disk of an aircraft engine, comprising an upper disk body, a lower disk body, an upper annular cover, a lower annular cover and a rubber plug; the upper annular cover and the lower annular cover are both annular structures; the upper disk body and the lower disk body are respectively used to buckle at the middle position of the upper and lower sides of the integral blade disk, and the upper disk body and the lower disk body are connected by a first bolt; the upper annular cover and the lower annular cover are respectively used to buckle at the edge positions of the upper and lower sides of the integral blade disk, and the upper annular cover and the lower annular cover together form an annular receiving cavity for accommodating the blades of the integral blade disk; the upper annular cover and the lower annular cover are connected by a second bolt; the outer peripheral surface of the upper disk body and the inner hole surface of the upper annular cover are spaced apart; the outer peripheral surface of the lower disk body and the inner hole surface of the lower annular cover are spaced apart; the rubber plug is used to be inserted into the through hole near the edge of the integral blade disk.

[0005] Preferably, a first boss is integrally formed at the center position of the upper disk body; a second boss is integrally formed at the center position of the lower disk body; the first boss is used to be inserted in the upper half of the center hole of the integral blade disk; the second boss is used to be inserted in the lower half of the center hole of the integral blade disk; the first boss and the second boss are connected by the first bolt.

[0006] Preferably, a first chamfer is provided at the edge of the outer peripheral surface of the upper disk body; and a second chamfer is provided at the edge of the outer peripheral surface of the lower disk body.

[0007] Preferably, the rubber stopper is in the shape of a truncated cone.

[0008] Preferably, there is a first rubber ring between the outer ring of the upper disc body and the upper surface of the integral blade disc; and a second rubber ring between the outer ring of the lower disc body and the lower surface of the integral blade disc.

[0009] Preferably, the upper disk body, the lower disk body, the upper annular cover and the lower annular cover are all made of nylon.

[0010] Preferably, an upper edge plate is integrally formed on the outer circumferential surface of the upper annular cover; a lower edge plate is integrally formed on the outer circumferential surface of the lower annular cover; a plurality of bolt holes are evenly distributed in an annular pattern on the upper edge plate and the lower edge plate, and the positions of the bolt holes of the upper edge plate and the lower edge plate correspond to each other; the second bolt is installed on the bolt holes of the upper edge plate and the lower edge plate.

[0011] Preferably, the rubber plugs are arranged in pairs, and two rubber plugs are arranged on each through hole near the edge of the integral blade disk.

[0012] On the other hand, the present invention also provides a method for wet sand blowing of an integral blade disk of an aero-engine, using the above-mentioned protective fixture, comprising the following steps:

[0013] S1. Buckle the upper plate body and the lower plate body at the middle position of the upper and lower sides of the integral blade disk respectively, and connect the upper plate body and the lower plate body with the first bolt;

[0014] S2. Buckle the upper annular cover and the lower annular cover at the upper and lower edge positions of the integral blade disk respectively, so that the blades of the integral blade disk are located in the annular receiving cavity formed by the upper annular cover and the lower annular cover; and the upper annular cover and the lower annular cover are connected by a second bolt;

[0015] S3, inserting rubber plugs into the through holes near the edge of the integral blade disk, with a rubber plug being inserted into each of the upper and lower ends of each through hole;

[0016] S4. The outer circumferential surface of the upper disk body and the inner hole surface of the upper annular cover are spaced apart to form an exposed first sand blasting area; the outer circumferential surface of the lower disk body and the inner hole surface of the lower annular cover are spaced apart to form an exposed first sand blasting area, and sand is blasted on the first sand blasting area respectively.

[0017] Preferably, when assembling the upper disc body and the lower disc body, a first rubber ring is arranged between the outer ring of the upper disc body and the upper surface of the integral blade disc; and a second rubber ring is arranged between the outer ring of the lower disc body and the lower surface of the integral blade disc.

[0018] Due to the adoption of the above technical solution, the beneficial effects of the present invention are as follows:

[0019] (1) By using the protective fixture provided by the present invention, the sandblasting protective fixture replaces the inefficient manual application of protective tape or other soft materials, which greatly reduces the protection time and significantly improves the processing efficiency.

[0020] (2) Protective clamps are used instead of manually applying protective tape, which overcomes the problem of large amount of tape used and high cost in manual application of protective tape. In addition, protective clamps can be reused, effectively reducing the cost of parts processing.

[0021] (3) By using the protective fixture and sand blasting method provided by the present invention, the protective fixture can be quickly positioned, clamped and disassembled, and the operation is simple, which effectively ensures the sand blasting protection quality of the parts and greatly improves the production efficiency.

[0022] (4) The sandblasting protection fixture is made of nylon material, which is light, rust-resistant, highly reusable and easy to use. After clamping, the fixture is integrated with the part and can be quickly flipped over to effectively protect the non-sandblasting surface of the part, thereby achieving the purpose of improving the spray protection efficiency, reducing costs and improving the coating quality of the integral blade disk parts of the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0024] Figure 1 This is a schematic diagram of the structure of an aero-engine integral blade disk part;

[0025] Figure 2 for Figure 1 Sectional view of AA in the middle;

[0026] Figure 3A cross-sectional view of the protective fixture provided by the present invention after being matched with the integral blade disk component;

[0027] Figure 4 An exploded view of the protective fixture and the integral blade disk parts provided by the present invention;

[0028] Figure 5 It is a schematic diagram of the structure of the upper plate body and the lower plate body in the present invention;

[0029] Figure 6 It is a schematic diagram of the structure of the upper annular cover and the lower annular cover in the present invention;

[0030] Figure 7 It is a schematic diagram of the structure of the first bolt or the second bolt in the present invention;

[0031] Figure 8 It is a schematic diagram of the structure of the rubber plug in the present invention;

[0032] Fig. 9 This is an overall structural diagram of the protective clamp provided by the present invention after being matched with the integral blade disk parts.

[0033] Explanation of the accompanying drawings: 1. Upper disk body; 1a. First boss; 1b. First chamfer; 2. Lower disk body; 2a. Second boss; 2b. Second chamfer; 3. Upper annular cover; 3a. Upper edge plate; 4. Lower annular cover; 4a. Lower edge plate; 5. Integral blade; 5a. Blade; 6. Annular receiving cavity; 7. First bolt; 8. Second bolt; 9. Rubber plug; 10. Rubber ring. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0036] In addition, the descriptions of "first", "second", etc. in the present invention are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the technical solutions between the various embodiments can be combined with each other, but they must be based on the ability of ordinary technicians in the field to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0037] Combination Figure 2 , Figure 3 As shown, on the one hand, this embodiment provides a protective fixture for wet sand blowing of an aircraft engine integral blade disk, comprising an upper disk body 1, a lower disk body 2, an upper annular cover 3, a lower annular cover 4 and a rubber plug 9; the upper annular cover 3 and the lower annular cover 4 are both annular structures; the upper disk body 1 and the lower disk body 2 are respectively used to buckle at the middle position of the upper and lower sides of the integral blade disk 5, and the upper disk body 1 and the lower disk body 2 are connected by a first bolt 7; the upper annular cover 3 and the lower annular cover 4 are respectively used to buckle at the edge positions of the upper and lower sides of the integral blade disk 5, and the upper annular cover 3 and the lower annular cover 4 jointly form an annular receiving cavity 6 for accommodating the blades 5a of the integral blade disk 5; the upper annular cover 3 and the lower annular cover 4 are connected by a second bolt 8; the outer peripheral surface of the upper disk body 1 and the inner hole surface of the upper annular cover 3 are spaced apart; the outer peripheral surface of the lower disk body 2 and the inner hole surface of the lower annular cover 4 are spaced apart; the rubber plug 9 is used to be inserted into the through hole near the edge of the integral blade disk 5.

[0038] The upper disk body 1 and the lower disk body 2 are mainly used to cooperate with and protect the inner annular surfaces of the upper and lower ends of the blade disk. The main function of the upper annular cover 3 and the lower annular cover 4 is to jointly protect the outer annular surfaces of the upper and lower ends of the integral blade disk 5 and the blades 5a to prevent sand from entering the area where the blades 5a are located. The upper annular cover 3 and the lower annular cover 4 have the same shape. The upper annular cover 3 and the lower annular cover 4 together form an annular receiving cavity 6 with a height higher than the blade 5a to prevent the cover plate from scratching the blade, thereby achieving the purpose of protecting the blade.

[0039] Combination Figure 2 As shown, a first boss 1a is integrally formed at the center of the upper disk body 1; a second boss 2a is integrally formed at the center of the lower disk body 2; the first boss 1a is used to be inserted in the upper half of the center hole of the integral blade disk 5; the second boss 2a is used to be inserted in the lower half of the center hole of the integral blade disk 5; the first boss 1a and the second boss 2a are connected by the first bolt 7. When the upper disk body 1 and the lower disk body 2 are assembled to the integral blade disk 5, there is no need to adjust and align them significantly, and only the first boss 1a and the second boss 2a need to be aligned and inserted in the center hole of the integral blade disk 5.

[0040] Combination Figure 5 As shown, a first chamfer 1b is provided at the edge of the outer peripheral surface of the upper disk body 1; a second chamfer 2b is provided at the edge of the outer peripheral surface of the lower disk body 2. By providing chamfers on the upper disk body 1 and the lower disk body 2, overlapping of the edges of the sand blowing surface can be effectively avoided, making it easier to perform sand blowing operations on the sand blowing surface of the integral blade disk.

[0041] Combination Figure 8 As shown, the rubber plug 9 is in the shape of a truncated cone, which facilitates the rubber plug 9 to be sealed on the through hole near the edge of the integral blade disk 5.

[0042] Combination Figure 2 , Figure 3 As shown, there is a first rubber ring 10 between the outer ring of the upper disc body 1 and the upper surface of the integral blade disc 5; and a second rubber ring 11 between the outer ring of the lower disc body 2 and the lower surface of the integral blade disc 5. The inner ring surface of the blade disc is an irregular concave surface. When the upper disc body 1 and the lower disc body 2 are used to cooperate and fix with the inner ring surface of the blade disc, there is a gap left at the concave surface and it cannot be completely protected. When sand is blown, sand particles may pass through the gap and blow the non-sand blowing surface, and it is easy to cause the cover plate edge to collide with the inner ring surface of the blade disc. Therefore, the first rubber ring 10 and the second rubber ring 11 are set to achieve the purpose of protecting parts and improving the quality of sand blowing protection. Under the action of the first bolt 7, the upper disc body 1 and the lower disc body 2 respectively form an extrusion force on the first rubber ring 10 and the second rubber ring 11, so that the rubber ring fits tightly with the concave ring surface in the blade disc, playing a seamless protection role.

[0043] In this embodiment, the upper plate body 1, the lower plate body 2, the upper annular cover 3, and the lower annular cover 4 are all made of nylon, which has the characteristics of light weight, corrosion resistance, high reusability, and easy use.

[0044] Combination Figure 6 As shown, an upper edge plate 3a is integrally formed on the outer circumference of the upper annular cover 3; a lower edge plate 4a is integrally formed on the outer circumference of the lower annular cover 4; multiple bolt holes are evenly distributed in annular patterns on the upper edge plate 3a and the lower edge plate 4a, and the bolt holes of the upper edge plate 3a and the lower edge plate 4a are located in corresponding positions; the second bolts 8 are installed on the bolt holes of the upper edge plate 3a and the lower edge plate 4a. Bolt connection is adopted for easy disassembly, effectively avoiding relative sliding or rotation between the upper annular cover 3 and the lower annular cover 4, and playing an anti-rotation and fixing role.

[0045] Combination Figure 2 , Figure 3As shown, the rubber plugs 9 are arranged in pairs, and two rubber plugs 9 are arranged on each through hole near the edge of the integral blade disk 5. The rubber plugs 9 are used to plug the holes in the integral blade disk. The holes are located on the sand blowing surface, but sand blowing is not allowed in the holes, so the rubber plugs 9 are used to block them, so that the holes can be sealed to prevent sand particles from entering the holes, which plays a protective role.

[0046] On the other hand, this embodiment also provides a method for wet sand blowing of an integral blade disk of an aircraft engine, using the above-mentioned protective fixture, comprising the following steps:

[0047] S1. Buckle the upper plate body 1 and the lower plate body 2 at the middle positions of the upper and lower sides of the integral blade disk 5 respectively, and connect the upper plate body 1 and the lower plate body 2 with the first bolt 7;

[0048] S2. The upper annular cover 3 and the lower annular cover 4 are buckled onto the upper and lower edges of the integral blade disk 5, respectively, so that the blades 5a of the integral blade disk 5 are located in the annular receiving cavity 6 formed by the upper annular cover 3 and the lower annular cover 4; and the upper annular cover 3 and the lower annular cover 4 are connected by a second bolt 8;

[0049] S3, inserting the rubber plugs 9 into the through holes near the edge of the blisk 5, with a rubber plug 9 inserted into each of the upper and lower ends of each through hole;

[0050] S4. The outer circumferential surface of the upper disk body 1 and the inner hole surface of the upper annular cover 3 are spaced apart to form an exposed first sand blasting area H1; the outer circumferential surface of the lower disk body 2 and the inner hole surface of the lower annular cover 4 are spaced apart to form an exposed first sand blasting area H2, and sand is blasted on the first sand blasting area H1 respectively.

[0051] Furthermore, in step S1 , when assembling the upper disc body 1 and the lower disc body 2 , a first rubber ring 10 is arranged between the outer ring of the upper disc body 1 and the upper surface of the integral blade disc 5 ; and a second rubber ring 11 is arranged between the outer ring of the lower disc body 2 and the lower surface of the integral blade disc 5 .

[0052] The above description is only a preferred embodiment of the present invention, and does not limit the patent scope of the present invention. All equivalent structural changes made by using the contents of the present invention specification and drawings under the inventive concept of the present invention, or directly / indirectly applied in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. A protective fixture for wet sand blowing of an integral blade disk of an aircraft engine, characterized in that: The invention comprises an upper disk body (1), a lower disk body (2), an upper annular cover (3), a lower annular cover (4) and a rubber plug (9); the upper annular cover (3) and the lower annular cover (4) are both annular structures; the upper disk body (1) and the lower disk body (2) are respectively used to buckle at the middle position of the upper and lower sides of the integral blade disk (5); the upper disk body (1) and the lower disk body (2) are connected by a first bolt (7); the upper annular cover (3) and the lower annular cover (4) are respectively used to buckle at the upper and lower sides of the integral blade disk (5) At the edge position, the upper annular cover (3) and the lower annular cover (4) jointly form an annular accommodation cavity (6) for accommodating the blades (5a) of the integral blade disk (5); the upper annular cover (3) and the lower annular cover (4) are connected by a second bolt (8); the outer peripheral surface of the upper disk body (1) and the inner hole surface of the upper annular cover (3) are arranged at intervals; the outer peripheral surface of the lower disk body (2) and the inner hole surface of the lower annular cover (4) are arranged at intervals; and the rubber plug (9) is used to be inserted into the through hole near the edge of the integral blade disk (5).

2. A protective fixture for wet sand blowing of an aircraft engine integral blade disk as claimed in claim 1, characterized in that: A first boss (1a) is integrally formed at the center of the upper disk body (1); A second boss (2a) is integrally formed at the center of the lower plate (2); The first boss (1a) is used for being inserted into the upper half of the central hole of the integral blade disk (5); The second boss (2a) is used for being inserted into the lower half of the central hole of the integral blade disk (5); The first boss (1a) and the second boss (2a) are connected via the first bolt (7).

3. The protective fixture for wet sand blowing of an aircraft engine integral blade disk according to claim 1, characterized in that: A first chamfer (1b) is provided at the edge of the outer peripheral surface of the upper plate body (1); and a second chamfer (2b) is provided at the edge of the outer peripheral surface of the lower plate body (2).

4. The protective fixture for wet sand blowing of an aircraft engine integral blade disk according to claim 1, characterized in that: The rubber stopper (9) is in the shape of a truncated cone.

5. The protective fixture for wet sand blowing of an aircraft engine integral blade disk according to claim 1, characterized in that: A first rubber ring (10) is provided between the outer ring of the upper disk body (1) and the upper surface of the integral blade disk (5); and a second rubber ring (11) is provided between the outer ring of the lower disk body (2) and the lower surface of the integral blade disk (5).

6. The protective fixture for wet sand blowing of an aircraft engine integral blade disk according to claim 1, characterized in that: The upper disk body (1), the lower disk body (2), the upper annular cover (3) and the lower annular cover (4) are all made of nylon.

7. The protective fixture for wet sand blowing of an aircraft engine integral blade disk according to claim 1, characterized in that: An upper edge plate (3a) is integrally formed on the outer circumferential surface of the upper annular cover (3); a lower edge plate (4a) is integrally formed on the outer circumferential surface of the lower annular cover (4); a plurality of bolt holes are evenly distributed in an annular pattern on the upper edge plate (3a) and the lower edge plate (4a), and the positions of the bolt holes on the upper edge plate (3a) and the lower edge plate (4a) correspond to each other; and the second bolts (8) are installed on the bolt holes on the upper edge plate (3a) and the lower edge plate (4a).

8. The protective fixture for wet sand blowing of an aircraft engine integral blade disk according to claim 1, characterized in that: The rubber plugs (9) are arranged in pairs, and two rubber plugs (9) are arranged on each through hole near the edge of the integral blade disk (5).

9. A method for wet sand blowing of an integral blade disk of an aircraft engine, characterized in that: The protective clamp according to any one of claims 1 to 8 comprises the following steps: S1. The upper disk body (1) and the lower disk body (2) are respectively buckled at the middle positions of the upper and lower sides of the integral blade disk (5), and the upper disk body (1) and the lower disk body (2) are connected by a first bolt (7); S2. The upper annular cover (3) and the lower annular cover (4) are buckled onto the upper and lower edge positions of the integral blade disk (5) respectively, and the blades (5a) of the integral blade disk (5) are located in the annular receiving cavity (6) formed by the upper annular cover (3) and the lower annular cover (4); and the upper annular cover (3) and the lower annular cover (4) are connected by a second bolt (8); S3, inserting a rubber plug (9) into a through hole near the edge of the integral blade disk (5), wherein a rubber plug (9) is inserted into each of the upper and lower ends of each through hole; S4, the outer circumferential surface of the upper disk body (1) and the inner hole surface of the upper annular cover (3) are spaced apart to form an exposed first sand blasting area (H1); the outer circumferential surface of the lower disk body (2) and the inner hole surface of the lower annular cover (4) are spaced apart to form an exposed first sand blasting area (H2), and sand blasting is performed on the first sand blasting area (H1) respectively.

10. A method for wet sand blowing of an aircraft engine integral blade disk as claimed in claim 9, characterized in that: In the step S1, when assembling the upper disc body (1) and the lower disc body (2), a first rubber ring (10) is arranged between the outer ring of the upper disc body (1) and the upper surface of the integral blade disc (5); and a second rubber ring (11) is arranged between the outer ring of the lower disc body (2) and the lower surface of the integral blade disc (5).

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