A solidification mold for aircraft engine blades

Abstract

This utility model relates to a solidification mold for aero-engine blades, comprising a blade shell membrane, a base plate, a pouring head, a sprue, a runner, and a heat insulation plate. The heat insulation plate includes an inner heat insulation plate and an outer heat insulation plate. The outer edge of the inner heat insulation plate has multiple evenly distributed notches (I). The outer heat insulation plate has a fan-shaped structure with notches (II) on its inner side. Notches (I) and (II) form a channel with the same cross-section as the blade shell membrane. The outer heat insulation plate is detachably installed on the outside of the inner heat insulation plate. This utility model, through the combined design of the inner and outer heat insulation plates and the ingenious cooperation of notches (I) and (II), forms a channel that perfectly fits the cross-section of the blade shell membrane. This design significantly reduces the gap between the blade shell membrane and the heat insulation plate, improves the heat insulation effect, effectively prevents heat exchange at the gap, and achieves a higher and more stable temperature gradient. The detachable connection between the inner and outer heat insulation plates provides convenience for the placement and removal of the blade shell membrane.

Description

Technical Field

[0001] This utility model relates to the technical field of aero-engine blade production equipment, specifically to an aero-engine blade solidification mold. Background Technology

[0002] Turbine single-crystal blades are key components in power equipment such as aero-engines. Due to their single-grain structure, uniform internal structure, and absence of weak points such as grain boundaries, they possess excellent fatigue resistance and resistance to hot corrosion, enabling them to maintain stable performance and extend service life under complex operating environments.

[0003] Turbine single-crystal blades are typically produced using directional solidification precision casting technology. This technology uses specific equipment and processes to create a stable temperature gradient in a specific direction during solidification, usually from one end of the blade to the other. This allows the liquid metal to solidify from the lower temperature end to the higher temperature end, with the solidification mold playing a crucial role.

[0004] Chinese patent CN116079034A discloses a device for optimizing the temperature gradient distribution of single-crystal blades in a directional solidification casting furnace. The device includes a mold, a first heat-insulating baffle, a second telescopic device, a heat-insulating baffle, and a cooling device. The mold is located between the first and second heat-insulating baffles. The first telescopic device is positioned below the second telescopic device. The second telescopic device is connected to both the heat-insulating baffle and the second heat-insulating baffle. The first telescopic device is connected above the cooling device. This invention reduces the probability of impurity crystals, improves the quality of single-crystal blades, and increases the forming rate. This device is used to cast single-crystal blades for aero-engines. It is simple to operate and can optimize the temperature gradient distribution of the blade during directional solidification, reducing the probability of defects and impurities. It also improves blade quality and production efficiency. However, the gaps between the first and second heat insulation baffles and the blade shell are large, resulting in poor heat insulation. Heat exchange will occur between the heating and cooling zones at this point, making the temperature gradient unstable. The second heat insulation baffle on the inner side is removable, but the first heat insulation baffle on the outer side is not removable, which makes it inconvenient to pick up and put down the blade shell. Utility Model Content

[0005] The purpose of this invention is to overcome the defects in the prior art and provide a solidification mold for aero-engine blades.

[0006] To achieve the above objectives, this utility model adopts the following technical solution: a solidification mold for an aero-engine blade, comprising a blade shell membrane, a base plate, a pouring head, a sprue, a runner, and a heat insulation plate. The heat insulation plate includes an inner heat insulation plate and an outer heat insulation plate. The outer edge of the inner heat insulation plate is uniformly provided with multiple notches I. The outer heat insulation plate has a fan-shaped structure with notches II on its inner side. The notches I and II form a channel with the same cross-section as the blade shell membrane. The outer heat insulation plate is detachably installed on the outside of the inner heat insulation plate. The sprue is located at the center of the base plate. The base plate has multiple runners inside, which connect the sprue and the inner cavity of the blade shell membrane. The pouring head is located at the top of the sprue.

[0007] Furthermore, the inner wall of the outer heat insulation plate is provided with a connecting post, and the outer wall of the inner heat insulation plate is provided with a connecting groove, and the connecting post is inserted into the connecting groove.

[0008] Furthermore, a limiting groove is provided at the end of the connecting column away from the external heat insulation plate, and a receiving groove is provided in the connecting groove. A limiting block is movably provided inside the receiving groove, and the bottom surface of the limiting block is inclined.

[0009] Furthermore, the bottom of the receiving groove is provided with an anti-detachment frame, and the top of the limiting block is provided with a stop block. The diameter of the stop block is greater than the width of the anti-detachment frame and less than the diameter of the receiving groove.

[0010] Furthermore, an annular heat insulation plate is provided on the outer side of the outer heat insulation plate, and the outer heat insulation plate overlaps on the annular heat insulation plate.

[0011] Furthermore, the bottom of the annular heat insulation plate is provided with a telescopic device, and a support plate is connected to the bottom of the telescopic device. The bottom plate is installed on the support plate.

[0012] The beneficial effects of this invention are as follows: By employing a combination design of inner and outer heat insulation plates, and through the ingenious cooperation of notch one and notch two, a channel is formed that perfectly fits the cross-section of the blade shell membrane. This design significantly reduces the gap between the blade shell membrane and the heat insulation plate, thereby improving the heat insulation effect, effectively preventing heat exchange at the gap, reducing the width of the mushy zone in the casting, and achieving a higher and more stable temperature gradient. This is of great significance for improving the production qualification rate of single-crystal blades. Simultaneously, the detachable connection between the inner and outer heat insulation plates greatly facilitates the placement and removal of the blade shell membrane. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the structure of a solidification mold for an aero-engine blade according to the present invention;

[0014] Figure 2 This is a schematic diagram of the exploded structure of the heat insulation panel;

[0015] Figure 3This is a perspective view of the inner insulation panel;

[0016] Figure 4 yes Figure 3 Enlarged view of section A;

[0017] Figure 5 This is a schematic diagram of the longitudinal section structure of a solidification mold for aero-engine blades according to this utility model;

[0018] Figure 6 This is a schematic diagram of the limit block structure;

[0019] Figure 7 This is a structural diagram of the anti-detachment frame.

[0020] 1. Blade shell membrane; 2. Base plate; 3. Pour head; 4. Sprue; 5. Runner; 6. Insulation plate; 7. Inner insulation plate; 8. Outer insulation plate; 9. Notch 1; 10. Notch 2; 11. Channel; 12. Connecting column; 13. Connecting groove; 14. Receiving groove; 15. Limiting block; 16. Limiting groove; 17. Anti-detachment frame; 18. Stop block; 19. Annular insulation plate; 20. Telescopic device; 21. Support plate. Detailed Implementation

[0021] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model are within the protection scope of the present utility model.

[0022] Embodiments of this utility model: such as Figure 1 , 2 As shown in Figure 5, a solidification mold for an aero-engine blade includes a blade shell 1, a base plate 2, a pouring head 3, a sprue 4, a runner 5, and a heat insulation plate 6. The heat insulation plate 6 includes an inner heat insulation plate 7 and an outer heat insulation plate 8. The outer edge of the inner heat insulation plate 7 is uniformly provided with multiple notches 9. The outer heat insulation plate 8 has a fan-shaped structure with a second notch 10 on its inner side. The first notch 9 and the second notch 10 form a channel 11 with the same cross-section as the blade shell 1. The outer heat insulation plate 8 is detachably installed on the outside of the inner heat insulation plate 7. The sprue 4 is located at the center of the base plate 2. The base plate 2 has multiple runners 5 inside, which connect the sprue 4 and the inner cavity of the blade shell 1. The pouring head 3 is located on top of the sprue 4.

[0023] It is worth noting that the area above the heat insulation plate 6 is the heating zone, and the area below is the cooling zone. The inner heat insulation plate 7 has through holes corresponding to the sprue 4, which facilitates the installation of the inner heat insulation plate 7. The pouring head 3 and the sprue 5 are detachably connected, which also facilitates the installation of the inner heat insulation plate 7.

[0024] Through the above structure, the cooperation of notch 19 and notch 20 forms a channel 11 that perfectly fits the cross-section of the blade shell membrane 1. During the cooling process, the blade shell membrane 1 slides in the channel 11, effectively separating the heating zone and the cooling zone, effectively blocking heat exchange, achieving a higher and more stable temperature gradient, reducing the width of the mushy area of ​​the casting, and improving the production qualification rate of single crystal blades; the inner heat insulation plate 7 and the outer heat insulation plate 8 can be disassembled to facilitate the removal and placement of the blade shell membrane 1.

[0025] like Figure 2 As shown, the inner wall of the outer heat insulation plate 8 is provided with a connecting post 12, and the outer wall of the inner heat insulation plate 7 is provided with a connecting groove 13, and the connecting post 12 is inserted into the connecting groove 13.

[0026] like Figure 2 , 3 As shown in Figure 4, the end of the connecting column 12 away from the outer heat insulation plate 8 is provided with a limiting groove 16, and a corresponding receiving groove 14 is provided in the connecting groove 13. A limiting block 15 is movably provided inside the receiving groove 14, and the bottom surface of the limiting block 15 is an inclined surface.

[0027] like Figure 3 , 4 As shown in Figures 6 and 7, the bottom of the receiving groove 14 is provided with an anti-detachment frame 17, and the top of the limiting block 15 is provided with a stop block 18. The diameter of the stop block 18 is greater than the width of the anti-detachment frame 17 and less than the diameter of the receiving groove 14.

[0028] With the above structure, when installing the external heat insulation plate 8, align the connecting post 12 with the connecting groove 13 and insert it into it. When the connecting post 12 releases the inclined surface of the limiting block 15, push the limiting block 15 upward. After the connecting post 12 is inserted into the position, align the bottom of the limiting block 15 with the limiting groove 16 and insert it into the limiting groove 16. When disassembling the external heat insulation plate 8, flip it up and down. Under the action of gravity, the limiting block 15 retracts into the receiving groove 14, and the external heat insulation plate 8 can be pulled out.

[0029] like Figure 1 , 2 As shown in Figures 5 and 6, an annular heat insulation plate 19 is also provided on the outer side of the outer heat insulation plate 8, and the outer heat insulation plate 8 overlaps on the annular heat insulation plate 19.

[0030] It is worth noting that: the annular heat insulation plate 19 is provided with a groove, the outer heat insulation plate 8 overlaps in the groove, and the annular heat insulation plate 19 is fixed to the bottom of the heating zone.

[0031] like Figure 1 , 5 As shown, the bottom of the annular heat insulation plate 19 is provided with a telescopic device 20, and the bottom of the telescopic device 20 is connected to a support plate 21. The bottom plate 2 is placed or fixed on the support plate 21.

[0032] It is worth noting that the telescopic device is an electric telescopic rod or other telescopic structure.

[0033] The telescopic device 20 facilitates the pulling and lowering of the solidification mold for aero-engine blades, achieving uniform speed transfer and cooling.

[0034] In this specific implementation, the notch 9 of the inner heat insulation plate 7 is aligned with the blade shell membrane 1. The sprue 4 passes through the middle of the inner heat plate 7 and moves downward. Then, the connecting post 12 on the outer heat insulation plate 8 is aligned with the connecting groove 13 and pushed inward. The connecting post 12 is inserted into the connecting groove 13 to connect the inner and outer heat insulation plates. The solidification mold is placed in the heating zone, so that the outer heat insulation plate 8 overlaps on the annular heat insulation plate 19. The bottom plate 2 is installed on the support plate 21. During the operation, the blade shell membrane 1 is driven to move from the heating zone to the cooling zone at a uniform speed through the telescopic device 20 to realize the directional solidification process of the single crystal blade casting. During this process, the heat exchange between the heating zone and the cooling zone is blocked by the combination of the inner and outer heat insulation plates, thereby optimizing the temperature gradient of the entire blade casting during the directional solidification process and significantly improving the casting quality of the single crystal blade.

[0035] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0036] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

[0037] The present invention and its embodiments have been described above. This description is not restrictive, and the accompanying drawings are only one embodiment of the present invention; the actual structure is not limited thereto. In conclusion, if those skilled in the art are inspired by this description and design similar structures and embodiments without departing from the inventive spirit of the present invention, such designs should fall within the protection scope of the present invention.

Claims

1. A solidification mold for an aero-engine blade, comprising a blade shell (1), a base plate (2), a pouring head (3), a sprue (4), a runner (5), and a heat insulation plate (6), characterized in that: The heat insulation plate (6) includes an inner heat insulation plate (7) and an outer heat insulation plate (8). The outer edge of the inner heat insulation plate (7) is uniformly provided with multiple notches (9). The outer heat insulation plate (8) is a fan-shaped structure with a notch (10) on its inner side. The notch (9) and the notch (10) form a channel (11) with the same cross-section as the blade shell membrane (1). The outer heat insulation plate (8) is detachably installed on the outside of the inner heat insulation plate (7). The sprue (4) is located at the center of the base plate (2). The base plate (2) is provided with multiple horizontal sprues (5). The horizontal sprues (5) connect the sprue (4) and the inner cavity of the blade shell membrane (1). The pouring head (3) is located at the top of the sprue (4).

2. The solidification mold for an aero-engine blade according to claim 1, characterized in that: The outer heat insulation plate (8) has a connecting column (12) on its inner side wall and a connecting groove (13) on its outer side wall. The connecting column (12) is inserted into the connecting groove (13).

3. The solidification mold for an aero-engine blade according to claim 2, characterized in that: The connecting column (12) is provided with a limiting groove (16) at one end away from the outer heat insulation plate (8), and a corresponding receiving groove (14) is provided in the connecting groove (13). A limiting block (15) is movably provided inside the receiving groove (14), and the bottom surface of the limiting block (15) is an inclined surface.

4. The solidification mold for an aero-engine blade according to claim 3, characterized in that: The bottom of the receiving groove (14) is provided with an anti-detachment frame (17), and the top of the limiting block (15) is provided with a stop block (18). The diameter of the stop block (18) is greater than the width of the anti-detachment frame (17) and less than the diameter of the receiving groove (14).

5. The solidification mold for an aero-engine blade according to claim 1, characterized in that: The outer heat insulation plate (8) is also provided with an annular heat insulation plate (19) on the outside, and the outer heat insulation plate (8) overlaps on the annular heat insulation plate (19).

6. The solidification mold for an aero-engine blade according to claim 5, characterized in that: The bottom of the annular heat insulation plate (19) is provided with a telescopic device (20), and the bottom of the telescopic device (20) is connected to a support plate (21). The bottom plate (2) is installed on the support plate (21).

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