A shot peening protection tool and method for aircraft engine turbine shafts

Abstract

This invention discloses a shot peening protection tool and method for aero-engine turbine shafts. The protection tool includes a support unit, a positioning unit mounted on the support unit, and a protection unit mounted on the positioning unit. The support unit includes a support base positioning plate and a support column, with the support base positioning plate connected to the support column. The positioning unit includes a positioning plate connected to the support column. The protection tool and method provided by this invention have a simple structure, low manufacturing and maintenance costs, and are applicable to shot peening strengthening of long-shaft thin-walled parts. It effectively solves the industry challenge of protecting key features such as serrations and threads during the shot peening strengthening process of aero-engine turbine shafts, significantly improving product quality and production efficiency, and providing a pathway for shot peening strengthening protection of long-shaft thin-walled parts.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine manufacturing technology, and particularly relates to a shot peening protection tool and method for aero-engine turbine shafts. Background Technology

[0002] The turbine shaft is a key component of an aero engine, such as... Figure 4 As shown, the turbine shaft has a complex structure, featuring features such as a waist-shaped bore, grating teeth, and threads. The turbine shaft operates for extended periods in extreme environments characterized by high temperatures, complex alternating stresses, and high-speed rotation. To improve the fatigue strength and lifespan of the turbine shaft, shot peening is commonly used to strengthen the surface of the part using high-speed shot. However, if the non-shot-peened areas such as the grating teeth and threads of the turbine shaft are impacted by the shot during the shot peening process, it will have a significant impact on the lifespan of the part and the rotor system.

[0003] Currently, before shot peening, aerospace-grade tape is typically applied to the non-shot-peened areas of the parts for protection. This method has several drawbacks: First, the application and removal of the aerospace-grade tape during non-shot-peened area protection is cumbersome and inefficient, hindering mass production. Second, the large end face of the turbine shaft contains multiple complex cavities, requiring protection of all cavities before shot peening. This consumes a large amount of aerospace-grade tape, which is non-reusable, leading to significant waste and increased product development costs. Finally, the turbine shaft is a long, thin-walled component requiring support during shot peening. Placing the entire component in the shot peening fixture results in a substantial weight, posing a significant safety risk during placement into the shot peening machine. Therefore, developing a tool that effectively protects the non-shot-peened areas of the turbine shaft from damage during shot peening is crucial.

[0004] Patent application CN116276684A discloses a shot peening fixture and method for hollow shaft parts with a large length-to-diameter ratio. It employs a protective fixture to hold the small end and an auxiliary support frame to support the upper end for clamping. Two shot guns move synchronously from bottom to top: the outer direct-spray gun treats the outer surface, while the top inner-diameter spear gun extends into the inner cavity to treat the inner surface. A shot venting system, combined with an air gun blowing system, removes accumulated shot particles in real time to prevent buildup. However, it does not address the protection of special areas of the machined parts. Summary of the Invention

[0005] To address the aforementioned technical problems, this invention provides a shot peening protection tool and method for aero-engine turbine shafts.

[0006] The present invention is achieved through the following technical solutions.

[0007] The present invention provides a shot peening protection tool for aero-engine turbine shaft, comprising a support unit, a positioning unit disposed on the support unit, and a protection unit disposed on the positioning unit; The support unit includes a support base positioning plate and a support column, wherein the support base positioning plate is connected to the support column; The positioning unit includes a positioning disk, which is connected to the support column.

[0008] Preferably, the support base positioning plate is provided with threaded holes for installing the support column, the support column is connected to the support base positioning plate through a support column positioning cover, and the support column positioning cover is connected and fastened to the support base positioning plate by screws.

[0009] Preferably, a base positioning pin is provided at the bottom of the support base positioning plate.

[0010] Preferably, a first connecting plate is provided on the support column, the support column is connected to the first connecting plate through a support column positioning cover, and the support column positioning cover is fastened to the first connecting plate by screws.

[0011] Preferably, a second connecting plate is provided on the support column, and the support column is connected to the second connecting plate through a support column positioning cover. The support column positioning cover is connected and fastened to the second connecting plate by screws.

[0012] Preferably, the second connecting disk is U-shaped.

[0013] Preferably, the positioning disc is connected to the top of the support column via a support column positioning cover. The positioning disc is U-shaped, and the support column positioning cover is fastened to the positioning disc with screws.

[0014] Preferably, the protection unit includes a shielding cover and a protective ring from top to bottom, with the shielding cover positioned above the positioning plate and below the protective ring.

[0015] Preferably, the shielding cover and protective ring are made of nylon.

[0016] A method for using a shot peening protection tool for an aircraft engine turbine shaft includes the following steps: S1. Residual Material Removal: Remove residual materials from the positioning holes of the rotary platform of the shot peening machine, the surface of the turbine shaft, and the surface of the shot peening protection tools; S2. Insert parts into the support unit: Insert the base positioning pin into the positioning hole of the rotating platform of the shot blasting machine, so that the protective tool is installed on the rotating platform of the shot blasting machine. Remove the protective cover and put the turbine shaft into the support unit, ensuring that the inner cavity of the turbine shaft teeth matches the positioning plate. S3 Non-Shot Peening Area Protection: Install the shielding cover on the positioning plate so that the shielding cover fits tightly against the large end face of the turbine shaft and the surface of the positioning plate. Fix the turbine shaft to the positioning plate with screws, and then install the protective ring on the turbine shaft tubular body. S4. Shot peening: After checking that the non-shot-peened area of ​​the turbine shaft is completely covered and protected by the protective cover and protective ring, the shot peening machine performs a test shot peening on the turbine shaft in trial operation mode. After the trial operation is successful, the shot peening machine is then controlled to release shot to perform shot peening on the turbine shaft. S5. Remove the protective unit: After the turbine shaft has passed the shot peening test, clean the shot particles from its surface and the protective tool, remove the shielding cover and protective ring, and take the turbine shaft out of the protective tool.

[0017] The beneficial effects of this invention are as follows: 1. Reliable protection accuracy: Through the structural design of "support unit + positioning unit + protection unit", the turbine shaft parts are precisely protected by the grating teeth and outer circle. A safety cover with excellent protection is tailored for the turbine shaft parts, effectively blocking the impact of shot on the turbine shaft grating teeth.

[0018] 2. Simple operation and economical and practical: The installation and disassembly of this protective tool is simple and quick. Before shot peening, the turbine shaft part only needs to be placed into the protective tool through the opening and the end face of the part is pressed with the protective cover to achieve shielding protection of the non-shot peening area of ​​the part. This eliminates the need for frequent cutting, pasting and removal of aviation special tape, shortens the shot peening processing cycle of the part, and is conducive to the mass production of parts.

[0019] 3. Stable structure: The bottom of the support base positioning plate of the protective tool is equipped with a positioning pin. The positioning pin and the positioning hole in the rotating platform of the shot peening machine form a basic hole system fit, realize the positioning of the parts during the shot peening process, and ensure the safety of the turbine shaft parts during the processing.

[0020] 4. Pollution-free and reusable: This protective tool avoids the waste of aviation-grade tape and eliminates the risk of adhesive residue after application. While ensuring the cleanliness of turbine shaft parts, it avoids the waste of aviation-grade tape resources and reduces development costs.

[0021] 5. Versatility and practicality: The protective tools and methods provided by this invention have a simple structure and low manufacturing and maintenance costs. They can be applied to shot peening strengthening of long-shaft thin-walled parts, effectively solving the industry difficulties in protecting key features such as serrations and threads during the shot peening strengthening of aero-engine turbine shafts, significantly improving product quality and production efficiency, and providing a path for shot peening strengthening protection of long-shaft thin-walled parts. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the structure of the present invention; Figure 2 yes Figure 1 Schematic diagram of the structure of region A; Figure 3 yes Figure 1 Schematic diagram of the structure of region B; Figure 4 It is an isometric view of the turbine shaft of an aircraft engine placed in protective equipment; Figure 5 This is a schematic diagram showing the placement of an aircraft engine turbine shaft within protective equipment. Figure 6 This is a schematic diagram of the turbine shaft structure; In the diagram: 1-positioning disc, 2-support column, 3-support column positioning cover, 4-first connecting disc, 5-screw, 6-base positioning pin, 7-support seat positioning disc, 8-shielding protective cover, 9-protective ring, 10-second connecting disc, 100-turbine shaft, 110-turbine shaft teeth, 120-turbine shaft tubular body. Detailed Implementation

[0023] The technical solution of the present invention is further described below, but the scope of protection is not limited to what is described.

[0024] Example: like Figures 1 to 6 As shown, a shot peening protection tool for an aero-engine turbine shaft includes a support unit, a positioning unit disposed on the support unit, and a protection unit disposed on the positioning unit. The support unit includes a support base positioning plate 7 and a support column 2. The support base positioning plate 7 is connected to the support column 2, and the support column 2 is a hollow tube, which reduces the overall weight of the protective tool. The positioning unit includes a positioning disk 1, which is connected to the support column 2.

[0025] The support base positioning plate 7 is provided with threaded holes for installing the support column 2. The support column 2 is connected to the support base positioning plate 7 through the support column positioning cover 3, and the support column positioning cover 3 is connected and fastened to the support base positioning plate 7 by screws 5. The support base positioning plate 7 is made of high-strength steel plate and has sufficient rigidity and stability.

[0026] The bottom of the support base positioning plate 7 is provided with a base positioning pin 6.

[0027] The support column 2 is provided with a first connecting plate 4. The support column 2 is connected to the first connecting plate 4 through a support column positioning cover 3. The support column positioning cover 3 is connected and fastened to the first connecting plate 4 by screws 5.

[0028] The support column 2 is provided with a second connecting plate 10. The support column 2 is connected to the second connecting plate 10 through a support column positioning cover 3. The support column positioning cover 3 is connected and fastened to the second connecting plate 10 by screws 5.

[0029] The second connecting plate 10 is U-shaped, which facilitates the placement and removal of the turbine shaft 100.

[0030] The positioning disk 1 is connected to the top of the support column 2 via the support column positioning cover 3. The positioning disk 1 is U-shaped, which makes the positioning disk 1 have an open notch. The inner side of the positioning disk 1 forms a receiving cavity. The center of the positioning disk 1 is a part receiving cavity for placing the rod of the turbine shaft 100. The support column positioning cover 3 is connected and fastened to the positioning disk 1 by screws 5.

[0031] Screw 5 mentioned above is an internal hexagon screw.

[0032] The protection unit includes a shielding cover 8 and a protective ring 9 from top to bottom. The shielding cover 8 is located above the positioning plate 1 and below the protective ring 9. The shielding cover 8 is connected and fastened to the positioning plate 1 by screws 5.

[0033] The protective shield 8 and protective ring 9 are made of nylon. Nylon effectively protects the parts while also offering durability and economy. Its relatively soft texture allows it to fit snugly against the parts, preventing indentations or unnecessary secondary reinforcement during clamping. Its excellent wear resistance and energy absorption capacity not only withstand long-term impacts from high-speed projectiles but also reduce rebound interference, extending the service life of the protective tool. Furthermore, nylon is chemically stable, rust-resistant, and prevents contamination of the parts. Its lightweight nature and ease of processing result in low costs, significantly improving operational convenience and overall efficiency while ensuring process quality. The protective shield 8 and protective ring 9 prevent parts from tipping over, increasing safety during shot peening.

[0034] The non-shot-peened area of ​​the aircraft engine turbine shaft 100 includes the turbine shaft grating 110 and the turbine shaft tubular body 120 on one side of the large end of the turbine shaft 100.

[0035] A method for using a shot peening protection tool for an aircraft engine turbine shaft includes the following steps: S1. Removal of Excess Material: Use compressed air to remove excess material from the positioning holes of the rotating platform of the shot peening machine, the surface of the turbine shaft, and the surface of the shot peening protective tools; S2. Insert parts into the support unit: Insert the base positioning pin 6 into the positioning hole of the rotating platform of the shot blasting machine, so that the protective tool is installed on the rotating platform of the shot blasting machine. Remove the protective cover 8, put the turbine shaft 100 into the support unit, and ensure that the inner cavity of the turbine shaft grate 110 matches the positioning plate 1. S3 Non-shot peening area protection: Install the shielding cover 8 on the positioning plate 1 so that the shielding cover 8 is in close contact with the large end face of the turbine shaft 100 and the surface of the positioning plate 1. Fix the turbine shaft 100 on the positioning plate 1 by using hexagon socket screws, and then install the protective ring 9 on the turbine shaft tubular body 120. S4. Shot peening: After checking that the non-shot peening area of ​​the turbine shaft 100 is completely covered and protected by the protective cover 8 and the protective ring 9, the shot peening machine performs a test shot peening on the turbine shaft 100 in the trial operation mode. After the trial operation is successful, the shot peening machine is then controlled to release shot to perform shot peening on the turbine shaft 100. S5. Remove the protective unit: After the turbine shaft 100 has passed the shot peening test, use compressed air to clean the shot particles on its surface and the protective tool, remove the shielding cover 8 and the protective ring 9, and take the turbine shaft 100 out of the protective tool.

Claims

1. A shot peening protection tool for an aircraft engine turbine shaft, characterized in that: Includes a support unit, a positioning unit disposed on the support unit, and a protection unit disposed on the positioning unit; The support unit includes a support base positioning plate (7) and a support column (2), wherein the support base positioning plate (7) is connected to the support column (2); The positioning unit includes a positioning disk (1) which is connected to a support column (2).

2. The shot peening protection tool for an aero-engine turbine shaft as described in claim 1, characterized in that: The support base positioning plate (7) is provided with threaded holes for the support column (2). The support column (2) is connected to the support base positioning plate (7) through the support column positioning cover (3). The support column positioning cover (3) is connected and fastened to the support base positioning plate (7) by screws (5).

3. The shot peening protection tool for an aero-engine turbine shaft as described in claim 1, characterized in that: The bottom of the support base positioning plate (7) is provided with a base positioning pin (6).

4. The shot peening protection tool for an aero-engine turbine shaft as described in claim 1, characterized in that: The first connecting plate (4) is provided on the support column (2). The support column (2) is connected to the first connecting plate (4) through the support column positioning cover (3). The support column positioning cover (3) is connected and fastened to the first connecting plate (4) by screws (5).

5. The shot peening protection tool for an aero-engine turbine shaft as described in claim 1, characterized in that: The second connecting plate (10) is provided on the support column (2). The support column (2) is connected to the second connecting plate (10) through the support column positioning cover (3). The support column positioning cover (3) is connected and fastened to the second connecting plate (10) by screws (5).

6. The shot peening protection tool for an aero-engine turbine shaft as described in claim 5, characterized in that: The second connecting plate (10) is U-shaped.

7. The shot peening protection tool for an aero-engine turbine shaft as described in claim 1, characterized in that: The positioning plate (1) is connected to the top of the support column (2) through the support column positioning cover (3). The positioning plate (1) is U-shaped, and the support column positioning cover (3) is connected and fastened to the positioning plate (1) by screws (5).

8. The shot peening protection tool for an aero-engine turbine shaft as described in claim 1, characterized in that: The protection unit includes a shielding cover (8) and a protective ring (9) from top to bottom. The shielding cover (8) is located above the positioning plate (1) and below the protective ring (9).

9. The shot peening protection tool for an aero-engine turbine shaft as described in claim 8, characterized in that: The shielding cover (8) and the protective ring (9) are made of nylon.

10. A method of using the shot peening protection tool for an aero-engine turbine shaft as described in any one of claims 1-9, characterized in that, Includes the following steps: S1. Residual Material Removal: Remove residual materials from the positioning holes of the rotary platform of the shot peening machine, the surface of the turbine shaft, and the surface of the shot peening protection tools; S2. Insert parts into the support unit: Insert the base positioning pin (6) into the positioning hole of the rotating platform of the shot blasting machine, so that the protective tool is installed on the rotating platform of the shot blasting machine. Remove the protective cover (8), put the turbine shaft (100) into the support unit, and ensure that the inner cavity of the turbine shaft grate (110) matches the positioning plate (1). S3 Non-shot peening area protection: Install the shielding cover (8) on the positioning plate (1) so that the shielding cover (8) is in close contact with the large end face of the turbine shaft (100) and the surface of the positioning plate (1). Fix the turbine shaft (100) on the positioning plate (1) by using screws, and then install the protective ring (9) on the turbine shaft tubular body (120). S4. Shot peening: After checking that the non-shot peening area of ​​the turbine shaft (100) is completely covered and protected by the shield (8) and the protective ring (9), the shot peening machine performs a test shot peening on the turbine shaft (100) in the trial operation mode. After the trial operation is successful, the shot peening machine is controlled to release the shot to perform shot peening on the turbine shaft (100). S5. Remove the protective unit: After the turbine shaft (100) has passed the shot peening test, clean the surface of the turbine shaft (100) and the shot on the protective tool, remove the shielding cover (8) and the protective ring (9), and take the turbine shaft (100) out of the protective tool.

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