Heating and curing equipment for thermal barrier coating of turbine blade of gas turbine

Abstract

The utility model discloses heating and curing equipment for a thermal barrier coating of a turbine blade of a gas turbine, which comprises a vacuum heat treatment furnace body and a furnace chamber, a central rod is rotatably erected in the furnace chamber through a support, a motor for driving the central rod to rotate is mounted outside the furnace chamber, and a mounting cylinder is connected outside the central rod. A ring frame is connected outside the mounting cylinder through a supporting rod, a plurality of profiling positioning grooves are formed in the ring frame in the axial direction and used for being matched with tenon structures of turbine blades, and a ring cover is detachably connected outside the ring frame. According to the utility model, when the plurality of blades are simultaneously heated and cured, the blades are assembled in the profiling positioning grooves of the ring frame and are uniformly distributed along the circumferential direction, and the distances between the plurality of blades and the inner wall of the furnace chamber are almost consistent, so that the heating uniformity of the blades in the furnace chamber is effectively improved, the temperature difference between the blades is favorably reduced, and the heating efficiency is improved. In addition, the annular frame can be driven by the center rod to slowly rotate and move, and the heating uniformity is further improved.

Description

Technical Field

[0001] This utility model relates to the technical field of coating post-treatment equipment, and in particular to a heating and curing equipment for thermal barrier coatings on gas turbine blades. Background Technology

[0002] Before applying a thermal barrier coating, gas turbine blades need to be coated with an MCrAlY bonding layer to provide good adhesion to the metal substrate and prevent substrate oxidation. After the MCrAlY bonding layer is applied, it needs to undergo high-temperature heat treatment to relieve stress and enhance adhesion. Since the MCrAlY bonding layer uses an active metal substrate, it is not suitable for coating curing in a traditional air furnace, as air furnaces can easily cause oxidation of the high-temperature alloy substrate. Therefore, a vacuum heat treatment furnace is often used. The vacuum heat treatment furnace uses a vacuum pump system to extract the air from the furnace, reducing the pressure inside the furnace to an extremely low level. This process eliminates active gases such as oxygen and water vapor, preventing the metal from undergoing adverse reactions such as oxidation and decarburization with these gases at high temperatures.

[0003] However, when heating and curing the coating on the surface of workpieces in existing vacuum heat treatment furnaces, the workpieces are often arranged in a matrix on the trays, with multiple workpieces on the same plane in the furnace cavity. This arrangement results in poor uniformity of temperature distribution, and the temperature difference between the blades at the edge and the center is large, which can easily cause blade deformation or coating cracking.

[0004] To address these issues, we propose a heating and curing device for thermal barrier coatings on gas turbine blades. Utility Model Content

[0005] The purpose of this invention is to provide a heating and curing device for thermal barrier coatings on gas turbine blades, so as to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, this utility model provides the following technical solution:

[0007] A heating and curing device for thermal barrier coating of gas turbine blades includes a vacuum heat treatment furnace body and a furnace cavity. A central rod is rotatably mounted inside the furnace cavity via a support, and a motor driving the central rod to rotate is installed outside the furnace cavity. An installation cylinder is connected to the outside of the central rod, and a ring frame is connected to the outside of the installation cylinder via a support rod. Several contoured positioning grooves are opened on the ring frame along the circumference to match the tenon structure of the turbine blade. A ring cover is detachably connected to the outside of the ring frame.

[0008] In a further embodiment, the ring frame is provided with multiple rings at equal intervals along the axial direction of the mounting cylinder.

[0009] In a further embodiment, the mounting cylinder and the center rod are slidably connected, the inner wall of the mounting cylinder is provided with a protrusion, and the outer wall of the center rod is provided with a groove that matches the protrusion.

[0010] In a further embodiment, the mounting cylinder, the ring frame, and the ring cover are all provided with slots, and the width of the slots is greater than the width of the bracket.

[0011] In a further embodiment, a pair of clamps are installed on the outer wall of the central rod near the outer end of the mounting cylinder by bolts and nuts.

[0012] In a further embodiment, the inner ring of the ring cover is provided with a plurality of connecting ears corresponding one-to-one with the support rod, and the connecting ears and the support rod are locked together by bolts.

[0013] In a further embodiment, a bevel gear is connected to the output shaft of the motor, and a bevel gear ring is meshed with the upper edge of the bevel gear, and the bevel gear ring is coaxially connected to a section of the central rod that extends out of the furnace cavity.

[0014] Compared with the prior art, the beneficial effects of this utility model are:

[0015] This invention, by setting multiple blades to be heated and cured simultaneously, assembles the blades into the contour positioning groove of the ring frame, so that they are arranged in a circumferentially uniform manner. The distance between the multiple blades after circumferential arrangement and the inner wall of the furnace cavity is almost the same, thereby effectively improving the uniformity of heating of the blades in the furnace cavity, which helps to reduce the temperature difference between the blades and thus prevents blade deformation or coating cracking. In addition, the ring frame can also slowly rotate and move under the drive of the central rod, further improving the uniformity of heating. Attached Figure Description

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

[0017] Figure 2 This is a schematic diagram of the internal cross-sectional structure of this utility model;

[0018] Figure 3 This is a three-dimensional structural diagram of the ring frame and central rod installation of this utility model;

[0019] Figure 4 This is a side view of the installation structure of the ring frame and the central rod of this utility model.

[0020] In the diagram: 1. Vacuum heat treatment furnace body; 2. Furnace cavity; 3. Center rod; 31. Groove; 4. Support; 5. Motor; 51. Bevel gear; 52. Bevel gear ring; 6. Mounting cylinder; 61. Raised bar; 7. Support rod; 8. Ring frame; 81. Contour positioning groove; 9. Ring cover; 91. Connecting ear; 10. Clamp. Detailed Implementation

[0021] In the description of this utility model, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. In the description of this utility model, unless otherwise stated, "a plurality of" means two or more.

[0022] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0023] 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. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0024] Please see Figure 1-4A heating and curing device for thermal barrier coating of gas turbine blades includes a vacuum heat treatment furnace body 1 and a furnace cavity 2. The furnace cavity 2 is located inside the vacuum heat treatment furnace body 1. Specifically, heating elements are evenly distributed circumferentially on the inner wall of the furnace cavity 2, while the outer shell of the furnace cavity 2 is a ceramic fiber-supported heat insulation layer. A central rod 3 is rotatably mounted inside the furnace cavity 2 via a bracket 4. The axis of the central rod 3 coincides with the axis of the furnace cavity 2. A motor 5 is installed outside the furnace cavity 2 to drive the rotation of the central rod 3. Specifically, a bevel gear 51 is connected to the output shaft of the motor 5. A bevel gear ring 52 is meshed with the upper edge of the bevel gear 51, and the bevel gear ring 52 is coaxially connected to a section of the central rod 3 that extends out of the furnace cavity 2. The motor 5 is isolated outside the furnace cavity 2. When the furnace cavity 2 is heated, the motor is heated. 5. The working environment has little impact. The center rod 3 is connected to the mounting cylinder 6, and the mounting cylinder 6 is connected to the ring frame 8 through the support rod 7. The ring frame 8 has several contour positioning grooves 81 along the circumference. The contour positioning grooves 81 are used to match the tenon structure of the turbine blade. One side of the contour positioning groove 81 is open and the other side is closed, so that the tenon of the turbine blade can be inserted into the contour positioning groove 81, thereby assembling the turbine blade on the ring frame 8. The ring frame 8 is detachably connected to the ring cover 9. Specifically, the inner ring of the ring cover 9 has several connecting ears 91 that correspond one-to-one with the support rod 7, and the connecting ears 91 are locked to the support rod 7 by bolts. The ring cover 9 is used to close the contour positioning groove 81 on the open side to prevent the assembled turbine blade from falling out.

[0025] To improve the efficiency of the curing process, three ring frames 8 are provided at equal intervals along the axial direction of the mounting cylinder 6, so that a larger number of turbine blades can be assembled and cured at one time.

[0026] To facilitate the assembly of turbine blades on the ring frame 8, a sliding connection is provided between the mounting cylinder 6 and the central rod 3. The diameter of one section of the central rod 3 near the motor 5 is larger than that of the other section, so as to form a baffle to limit the mounting cylinder 6. The outer wall of the smaller diameter section of the central rod 3 has a groove 31 parallel to the axial direction, and the inner wall of the mounting cylinder 6 has a protrusion 61 parallel to the axial direction. The protrusion 61 slides into the groove 31, so that the mounting cylinder 6 can slide out relative to the central rod 3, so as to remove the furnace cavity 2, thereby driving the ring frame 8 out of the furnace cavity 2.

[0027] Furthermore, the mounting cylinder 6, the ring frame 8, and the ring cover 9 are all provided with slots, and the width of the slots is greater than the width of the bracket 4, so that when the mounting cylinder 6 is pulled out, the slots of the mounting cylinder 6, the ring frame 8, and the ring cover 9 can pass over the bracket 4 without being blocked by the bracket 4.

[0028] Considering that the mounting cylinder 6 can slide and is prone to displacement during rotation, a pair of clamps 10 are installed on the outer wall of the central rod 3 near the outer end of the mounting cylinder 6 by bolts and nuts. After the clamps 10 clamp the central rod 3, they form a retaining ring on the central rod 3, thereby closely adhering to the outer end face of the mounting cylinder 6 and limiting its movement to prevent it from slipping out during operation.

[0029] It will be apparent to those skilled in the art that this invention is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or essential characteristics of this invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within this invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0030] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A heating and curing device for thermal barrier coatings on gas turbine blades, comprising a vacuum heat treatment furnace body (1) and a furnace chamber (2), characterized in that: The furnace cavity (2) is equipped with a central rod (3) which is rotatably mounted on a bracket (4), and a motor (5) that drives the central rod (3) to rotate is installed outside the furnace cavity (2). The central rod (3) is connected to an installation cylinder (6), and the installation cylinder (6) is connected to a ring frame (8) through a support rod (7). The ring frame (8) has several contoured positioning grooves (81) along the circumferential direction for matching the tenon structure of the turbine blade. The ring frame (8) is detachably connected to a ring cover (9).

2. The heating and curing equipment for thermal barrier coating of gas turbine blades according to claim 1, characterized in that: The ring frame (8) is provided with multiple rings at equal intervals along the axial direction of the mounting cylinder (6).

3. The heating and curing equipment for thermal barrier coating of gas turbine blades according to claim 1, characterized in that: The mounting cylinder (6) and the center rod (3) are slidably connected. The inner wall of the mounting cylinder (6) is provided with a protrusion (61), and the outer wall of the center rod (3) is provided with a groove (31) that matches the protrusion (61).

4. The heating and curing equipment for thermal barrier coating of gas turbine blades according to claim 1, characterized in that: The mounting cylinder (6), ring frame (8) and ring cover (9) are all provided with slots, and the width of the slots is greater than the width of the bracket (4).

5. The heating and curing equipment for thermal barrier coating of gas turbine blades according to claim 1, characterized in that: A pair of clamps (10) are installed on the outer wall of the central rod (3) near the outer end of the mounting cylinder (6) by bolts and nuts.

6. The heating and curing equipment for thermal barrier coating of gas turbine blades according to claim 1, characterized in that: The inner ring of the ring cover (9) is provided with a number of connecting ears (91) corresponding to the support rod (7), and the connecting ears (91) and the support rod (7) are locked together by bolts.

7. The heating and curing equipment for thermal barrier coating of gas turbine blades according to claim 1, characterized in that: A bevel gear (51) is connected to the output shaft of the motor (5). A bevel gear ring (52) is meshed with the upper edge of the bevel gear (51), and the bevel gear ring (52) is coaxially connected to a section of the central rod (3) that extends out of the furnace cavity (2).

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