A tooling fixture for repairing aircraft engine blades

Abstract

This utility model discloses a tooling fixture for repairing aircraft engine blades, including a base plate and a pressure plate. The base plate has a repair side and a mounting side, and also has at least one mounting hole connecting the repair side and the mounting side. The mounting hole is used to connect the tenon of the engine blade, with the bottom surface of the tenon facing the side where the repair side is located. The pressure plate is detachably connected to the base plate and covers the repair side. The pressure plate has several repair holes that correspond one-to-one with the mounting holes, and the shape and size of the repair holes match the bottom surface of the tenon. Compared with the prior art, this tooling fixture installs and fixes the tenon of the blade through the mounting holes on the base plate, and then uses the pressure plate to press and fix the tenon, while only the bottom surface of the tenon, i.e., the repair surface, is exposed, while other parts are covered. This tooling fixture can fix the position and attitude of the engine blade, ensuring that the distance and angle between the spray gun and the repair surface remain stable, so that different blades have good consistency after repair.

Description

Technical Field

[0001] This utility model relates to the field of aircraft engine blade repair technology, specifically to a tooling fixture for aircraft engine blade repair. Background Technology

[0002] Aircraft engines are the core power unit of an aircraft, and their reliability is of paramount importance. Engine blades operate in harsh environments, enduring multiple complex conditions such as high-speed airflow impact, centrifugal force, high-temperature and high-pressure gas scouring, and vibration caused by airflow changes. Common blades use a tenon-mortise and tenon joint with a pin connection. Under complex stress and wear, the connection is prone to fretting wear, abrasive wear, and fatigue wear. This leads to increased clearance between the tenon base and the mortise and tenon, decreased blade positioning accuracy, affects overall engine performance, and can even cause serious malfunctions.

[0003] Common methods for addressing wear at aircraft engine fan blade joints include adding shims, welding repair, laser cladding repair, and thermal spraying. Adding shims adjusts the gap at the joint by filling the voids created by wear to maintain a tight connection. However, a drawback is the difficulty in precisely matching the shim material and thickness, leading to uneven stress distribution, increased localized wear, and potential deformation and displacement under long-term vibration, affecting fan blade installation accuracy and increasing maintenance costs. Welding repair fills the worn area by high-temperature fusion of wear-resistant materials. The principle is to restore the component's dimensions and enhance wear resistance through the weld layer. However, the high temperatures during welding alter the properties of the base material, causing grain coarsening, reduced strength, and potential defects such as porosity and cracks. The repaired component exhibits lower fatigue performance than its original state, resulting in insufficient reliability. Laser cladding repair technology uses a high-energy laser beam to melt wear-resistant alloy powder, forming a metallurgical bonding layer on the worn surface. The principle is to restore dimensions and improve wear resistance through material accumulation. However, its drawbacks include the fact that high temperatures can still cause localized thermal effects on the substrate, potentially leading to structural deformation, and the process parameters are strictly controlled, resulting in high costs. Thermal spraying technology (such as plasma spraying) heats wear-resistant materials like ceramics to a molten state and then sprays them onto the bonding surface to form a coating. The principle is to use the high hardness of the coating to resist wear. However, its disadvantages include the fact that high-temperature spraying can cause the substrate to anneal and soften, the coating and substrate are mainly mechanically bonded with low bonding strength, high internal porosity, and the coating is prone to peeling.

[0004] Compared with the methods mentioned above, cold spraying technology has significant advantages: its principle is to spray powder particles onto the substrate surface through a high-speed airflow at low temperature (below the material's melting point), relying on the plastic deformation of the particles to achieve mechanical interlocking and metallurgical bonding, forming a highly dense coating. Since the spraying process is not affected by high temperatures, it does not change the microstructure and properties of the substrate material, avoiding thermal stress damage and phase transformation problems.

[0005] However, the lack of specialized fixtures for cold spraying makes it difficult to precisely control the coating thickness and uniformity when using cold spraying to repair damaged blades, as the distance and angle between the spray gun and the repair surface can easily vary slightly. Utility Model Content

[0006] The purpose of this invention is to overcome the above-mentioned technical deficiencies and propose a tooling fixture for repairing aircraft engine blades, which solves the technical problem of the lack of special fixtures for cold spraying in the prior art, making it difficult to accurately control the coating thickness and uniformity.

[0007] To achieve the above-mentioned technical objectives, the present invention adopts the following technical solution:

[0008] This utility model provides a tooling fixture for repairing aircraft engine blades, including a base plate and a pressure plate.

[0009] The substrate has a repair side and a mounting side, and the substrate also has at least one mounting hole communicating with the repair side and the mounting side. The mounting hole is used to connect a tenon of an engine blade, and the bottom surface of the tenon faces the side where the repair side is located.

[0010] The pressure plate is detachably connected to the base plate and covers the repair side arrangement. The pressure plate has a plurality of repair holes that correspond one-to-one with the mounting holes. The shape and size of the repair holes match the bottom surface of the tenon.

[0011] In some embodiments, the mounting hole is a trapezoidal hole that is reduced in the direction from the repair side to the mounting side.

[0012] In some embodiments, the mounting hole is a polygonal hole, and the substrate also has a plurality of protective holes, which are respectively connected to each corner of the mounting hole.

[0013] In some embodiments, the mounting hole is a parallelogram.

[0014] In some embodiments, the substrate and the pressure plate are respectively formed with corresponding first connecting holes and second connecting holes. The tooling fixture for repairing aircraft engine blades also includes a connector, which includes a connecting rod, a first clamping part and a second clamping part. The connecting rod is arranged through the first connecting hole and the second connecting hole. The first clamping part is detachably connected to the connecting rod. The second clamping part is fixedly connected to or detachably connected to the connecting rod. The first clamping part and the second clamping part cooperate to clamp and fix the substrate and the pressure plate.

[0015] In some embodiments, the connecting rod has an external thread, the first clamping part has a corresponding threaded hole, and the first clamping part is connected to the connecting rod by thread engagement.

[0016] In some embodiments, one of the substrate and the pressure plate has at least two connection holes, and the other has a corresponding connection post, wherein the connection holes and the connection post are detachably plugged in.

[0017] In some embodiments, the substrate includes a plurality of detachably connected sub-boards, and the mounting hole is formed by two of the sub-boards.

[0018] In some embodiments, the substrate includes a first sub-board and two second sub-boards. The first sub-board has an I-shaped structure, and the two second sub-boards are detachably connected to the two sides of the waist of the first sub-board. Each second sub-board and the first sub-board together form at least one mounting hole.

[0019] In some embodiments, the substrate and the pressure plate are respectively formed with corresponding first fixing holes and second fixing holes, through which the tooling fixture for repairing the aircraft engine blades can be installed onto the repair equipment.

[0020] Compared with the prior art, the tooling fixture for repairing aircraft engine blades provided by this utility model installs and fixes the tenon of the blade through the mounting holes on the base plate, and then uses the pressure plate to press and fix the tenon, while only the bottom surface of the tenon, i.e. the repair surface, is exposed, and the other parts are covered. This tooling fixture can fix the position and attitude of the engine blade, and ensure that the distance and angle between the spray gun and the repair surface remain stable, so that different blades have good consistency after repair. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the structure of an aircraft engine blade;

[0022] Figure 2 This is a schematic diagram of the mounting side of the tooling fixture for repairing aircraft engine blades provided in this embodiment of the utility model;

[0023] Figure 3 This is a front view of the repair side of the tooling fixture for repairing aircraft engine blades provided in this embodiment of the utility model;

[0024] Figure 4 This is an exploded view of the tooling fixture for repairing aircraft engine blades provided in this embodiment of the utility model. Detailed Implementation

[0025] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present utility model and are not intended to limit the present utility model.

[0026] To address the current technical problem of lacking dedicated fixtures for cold spraying and making it difficult to precisely control the coating thickness and uniformity, this invention provides a tooling fixture for repairing aircraft engine blades. This fixture can fix the position and orientation of the engine blades, ensuring that the distance and angle between the spray gun and the repair surface remain stable, resulting in good consistency between different blades after repair.

[0027] Please see Figure 1 , Figure 1 This is a structural schematic diagram of engine blade 1. Engine blade 1 includes a tenon 11 and a fan blade 12 that are fixedly connected, and is mounted on the engine via the tenon 11. During repair, the lower surface of the tenon 11 is repaired to increase its thickness and compensate for wear in that area.

[0028] Please see Figures 2 to 4 , Figure 2 This is a schematic diagram of the mounting side of the tooling fixture for repairing aircraft engine blades in one embodiment of the present invention. Figure 3 This is a front view of the repaired side of the tooling fixture. Figure 4 This is an exploded view of the tooling fixture.

[0029] The tooling fixture for repairing the engine blades of this aircraft includes a base plate 2 and a pressure plate 3.

[0030] The substrate 2 has a repair side 2A and a mounting side 2B. The substrate 1 also has at least one mounting hole 21 that connects the repair side 2A and the mounting side 2B. The shape of the mounting hole 21 matches the shape of the tenon 11 for connecting the tenon 11 of the engine blade 1. The bottom surface of the tenon 11, i.e. the repair surface, faces the side where the repair side 2A is located.

[0031] The pressure plate 3 is detachably connected to the base plate 2 and covers the repair side 2A. The pressure plate 3 has a number of repair holes 31 that correspond one-to-one with the mounting holes 21. The shape and size of the repair holes 31 match the bottom surface of the tenon 11.

[0032] The pressure plate 3 exposes only the bottom surface of the tenon 11 through the repair hole 31, while concealing the other parts. At the same time, it cooperates with the base plate 2 to clamp and fix the tenon 11, fix the position and orientation of the engine blade, and ensure that the distance and angle between the spray gun and the repair surface remain stable, so that different blades have good consistency after repair.

[0033] In some embodiments, the mounting hole 21 is a trapezoidal hole, the width of which decreases from the repair side 2A to the mounting side 2B.

[0034] In some embodiments, the mounting hole 21 is a polygonal hole, and the substrate 2 also has a plurality of protective holes 22, which are respectively connected to each corner of the mounting hole 21. When the tenon 11 is inserted into the mounting hole 21, the corner of the tenon 11 will not contact the inner wall of the mounting hole 21, but will be located in the protective hole 22, so as to protect the corner of the tenon 11 from being damaged by bumps.

[0035] In this embodiment, the mounting hole 21 is a parallelogram.

[0036] In some embodiments, the substrate 2 includes multiple detachably connected sub-plates, and the mounting hole 21 is formed by two sub-plates enclosing each other. The sub-plates can be detachably connected by bolts or other means. This split substrate 2 makes it easier to install and remove the tenon 11.

[0037] In this embodiment, the substrate 2 includes a first sub-board 23A and two second sub-boards 23B. The first sub-board 23A has an I-shaped structure. The two second sub-boards 23B are detachably connected to the two sides of the waist of the first sub-board 23A respectively. Each second sub-board 23B and the first sub-board 23A together form at least one mounting hole 21.

[0038] In some embodiments, the substrate 2 and the pressure plate 3 are respectively provided with corresponding first connecting holes 24 and second connecting holes 32. This tooling fixture also includes a connector 4, which comprises a connecting rod 41, a first clamping portion 42, and a second clamping portion 43. The connecting rod 41 passes through the first connecting hole 24 and the second connecting hole 32. The first clamping portion 42 is detachably connected to the connecting rod 41, and the second clamping portion 43 is either fixedly connected to or detachably connected to the connecting rod 41. The first clamping portion 42 and the second clamping portion 43 cooperate to clamp and fix the substrate 2 and the pressure plate 3.

[0039] In some embodiments, the connecting rod 41 has an external thread, and the first clamping part 42 has a corresponding threaded hole. The first clamping part 42 and the connecting rod 43 are connected by threaded engagement. The substrate 2 and the pressure plate 3 are clamped by screwing the first clamping part 42.

[0040] In other embodiments, other connection and fixing methods may also be adopted. For example, one of the substrate 2 and the pressure plate 3 is formed with at least two connection holes, and the other is formed with a corresponding connection post, and the connection holes and the connection post are detachably plugged in.

[0041] In some embodiments, the substrate 2 and the pressure plate 3 are respectively formed with corresponding first fixing holes 25 and second fixing holes 33, through which the tooling fixture for repairing the aircraft engine blade can be installed onto the repair equipment.

[0042] In use, first disassemble the base plate 2, insert the tenon of the blade into the mounting hole 21, then assemble the first sub-plate 23A and the second sub-plate 23B together, and then install the pressure plate 3 through the connector 4 to complete the fixation of the blade. Finally, install this fixture onto the repair equipment, so that the repair side 2A faces the spray gun, and the repair can be performed.

[0043] The specific embodiments of this utility model described above do not constitute a limitation on the scope of protection of this utility model. Any other corresponding changes and modifications made based on the technical concept of this utility model should be included within the scope of protection of the claims of this utility model.

Claims

1. A tooling fixture for repairing aircraft engine blades, characterized in that, include: A substrate having a repair side and a mounting side, the substrate also having at least one mounting hole communicating with the repair side and the mounting side, the mounting hole being used to connect a tenon of an engine blade, the bottom surface of the tenon facing the side where the repair side is located. A pressure plate, which is detachably connected to the base plate and covers the repair side arrangement, has a plurality of repair holes corresponding one-to-one with the mounting holes, and the shape and size of the repair holes match the bottom surface of the tenon.

2. The tooling fixture for repairing aircraft engine blades according to claim 1, characterized in that, The mounting hole is a trapezoidal hole, tapering from the repair side towards the mounting side.

3. The tooling fixture for repairing aircraft engine blades according to claim 1, characterized in that, The mounting hole is a polygonal hole, and the substrate also has multiple protective holes, which are respectively connected to each corner of the mounting hole.

4. The tooling fixture for repairing aircraft engine blades according to claim 3, characterized in that, The mounting hole is a parallelogram.

5. The tooling fixture for repairing aircraft engine blades according to claim 1, characterized in that, The substrate and the pressure plate are respectively formed with corresponding first connecting holes and second connecting holes. The tooling fixture for repairing aircraft engine blades also includes a connector. The connector includes a connecting rod, a first clamping part and a second clamping part. The connecting rod is arranged through the first connecting hole and the second connecting hole. The first clamping part is detachably connected to the connecting rod. The second clamping part is fixedly connected to or detachably connected to the connecting rod. The first clamping part and the second clamping part cooperate to clamp and fix the substrate and the pressure plate.

6. The tooling fixture for repairing aircraft engine blades according to claim 5, characterized in that, The connecting rod has an external thread, and the first clamping part has a corresponding threaded hole. The first clamping part and the connecting rod are connected by thread engagement.

7. The tooling fixture for repairing aircraft engine blades according to claim 1, characterized in that, One of the substrate and the pressure plate has at least two connection holes, and the other has a corresponding connection post. The connection holes and the connection post are detachably plugged in.

8. The tooling fixture for repairing aircraft engine blades according to claim 1, characterized in that, The substrate includes multiple detachably connected sub-boards, and the mounting hole is formed by two of the sub-boards.

9. The tooling fixture for repairing aircraft engine blades according to claim 8, characterized in that, The substrate includes a first sub-board and two second sub-boards. The first sub-board has an I-shaped structure. The two second sub-boards are detachably connected to the two sides of the waist of the first sub-board. Each second sub-board and the first sub-board together form at least one mounting hole.

10. The tooling fixture for repairing aircraft engine blades according to claim 1, characterized in that, The substrate and the pressure plate are respectively formed with corresponding first fixing holes and second fixing holes, through which the tooling fixture for repairing the aircraft engine blades can be installed onto the repair equipment.

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