Modularized synchronous heat treatment method and device for single-crystal turbine blade

Abstract

The modularized synchronous heat treatment method comprises the following steps that the turbine blade is placed in a high-temperature space, and the high-temperature space is divided into a first temperature control area, a second temperature control area, a third temperature control area and a fourth temperature control area which are isolated from one another and correspond to the blade tip, the blade body, the blade root and the tenon of the turbine blade; and the four temperature control areas are synchronously subjected to heat treatment and cooling treatment, so that all the parts of the turbine blade are synchronously and respectively treated under different temperature control conditions. The invention further discloses a modularized synchronous heat treatment device of the single-crystal turbine blade and a treatment method of the single-crystal turbine blade. According to the method, the heat treatment efficiency can be effectively improved, the heat treatment temperature and the cooling rate of each region are accurate and controllable, so that the structure characteristics of each part of the blade are adjustable and controllable, and meanwhile, the formation of residual stress in the blade is controlled.

Description

Technical Field

[0001] The present invention belongs to the technical field of heat treatment of superalloys, and particularly relates to a modular synchronous heat treatment method and device for single crystal turbine blades. Background Technique

[0002] The turbine inlet temperature of an aeroengine is a core index to measure the performance of the engine, directly determining the thrust-to-weight ratio and fuel efficiency. "One generation of materials, one generation of engines", the key to increasing the turbine inlet temperature lies in developing turbine blade materials with higher temperature-bearing capabilities. Currently, the turbine blades of advanced model aeroengines mainly use nickel-based single crystal superalloys, which are jointly strengthened by a disordered FCC structure γ-phase matrix and an ordered γ'-precipitated phase. The morphology and distribution characteristics of the γ'-precipitated phase determine the high-temperature mechanical properties of the single crystal alloy. With the core goal of increasing the temperature-bearing capacity, the development of current single crystal alloys has entered the sixth generation. A typical representative is the TMS-238 alloy developed by the National Institute for Materials Science (NIMS) in Japan. Its temperature-bearing capacity under the condition of a 137 MPa / 1000 h creep life is as high as 1150 °C, which is about 150 °C higher than that of the first-generation single crystal superalloy, making it possible for the development of the next generation of high-thrust-to-weight-ratio and high-reliability aeroengines.

[0003] In practical engineering applications, turbine blades are subjected to complex temperature and stress conditions. The tip part of the blade is exposed to the high-temperature gas at the outlet of the combustion chamber and bears the highest service temperature but lower stress. The root and dovetail parts of the blade have low temperature but high stress. The service temperature and stress of the blade body are between those of the tip and the root. The complex temperature and stress conditions require the turbine blade material to have comprehensive service performance under different temperature and stress conditions. However, the traditional alloy design concept is difficult to meet this requirement, mainly due to the following reasons:

[0004] 1) The deformation of the γ-γ' two-phase structure in single crystal alloys is sensitive to temperature and stress conditions. Alloy designs aimed at improving the high-temperature performance of the tip part of the blade are difficult to take into account the low-temperature performance of parts such as the root and dovetail.

[0005] 2) Traditional turbine blades have a uniform and consistent organizational structure after heat treatment. Although the low-temperature performance of the root and dovetail parts can be improved by adjusting the heat treatment process, it inevitably sacrifices the high-temperature performance of the tip part, which is not conducive to the overall working efficiency and propulsion ratio of the engine.

[0006] Aiming at the key common problem that the high and low temperature properties of single crystal alloys do not match and affect the comprehensive performance of turbine blades under complex service environments, corresponding technical solutions have been disclosed in past patents (such as ZL 202210350200.4). By locally treating the tip, blade body, and root of the blade and adjusting the ratio of large and small γ′ phases in different regions, the performance of different parts of the blade can be matched. However, the previously disclosed technologies still have the following problems: The local treatments of the tip, blade body, and root of the blade need to be carried out step by step, resulting in low efficiency. The mutual influence between different heat treatment steps makes it difficult to accurately control the organizational structure of the corresponding regions, and it will also cause an increase in the residual stress of the blade, with limited engineering application value. Summary of the Invention

[0007] In view of the fact that the traditional strengthening design strategy of single crystal superalloys cannot meet the comprehensive service performance requirements of turbine blades under complex service environments, and the existing local treatment strategies for blades have technical problems such as low treatment efficiency, inability to accurately control the organizational structure, and increase in blade residual stress, the present invention proposes a modular synchronous heat treatment method and device for single crystal turbine blades through heat treatment process design and supporting device development. It can simultaneously carry out modular heat treatment of the tip, blade body, root, and tenon of the blade, and the organizational structure of each region is adjustable and controllable, which can effectively improve the comprehensive performance of turbine blades under complex service environments.

[0008] The technical solution adopted by the present invention to solve its technical problems is: A modular synchronous heat treatment method for single crystal turbine blades, comprising the following steps:

[0009] Place the turbine blade in a high-temperature space, and the high-temperature space is divided into mutually isolated first temperature control zone, second temperature control zone, third temperature control zone, and fourth temperature control zone corresponding to the tip, blade body, root, and tenon of the turbine blade;

[0010] Simultaneously carry out heat treatment on the first temperature control zone, second temperature control zone, third temperature control zone, and fourth temperature control zone, and simultaneously carry out cooling treatment, so that the tip, blade body, root, and tenon of the turbine blade are simultaneously treated under different temperature control conditions.

[0011] Further, the temperature of the first temperature control zone is 1080 - 1100 °C, the cooling rate ≤ 100 °C / s, and the structure includes a γ-phase matrix and primary γ′ phases with a size of 200 - 350 nm;

[0012] The temperature of the second temperature control zone is 1100 - 1120 °C, the cooling rate ≤ 100 °C / s, and the structure includes a γ-phase matrix and primary γ′ phases with a size of 300 - 400 nm;

[0013] The temperature of the third temperature control zone is 1100 - 1120 °C, the cooling rate is ≥ 300 °C / s, and the structure includes a γ-phase matrix, primary γ'-phase with a size of 300 - 400 nm, and secondary γ'-phase with a size of 10 nm - 50 nm;

[0014] The temperature of the fourth temperature control zone is 1120 - 1150 °C, the cooling rate is ≥ 1000 °C / s, and the structure includes a γ-phase matrix, primary γ'-phase with a size of 350 - 500 nm, and secondary γ'-phase with a size of 10 nm - 50 nm.

[0015] The present invention also discloses a processing method for a single-crystal turbine blade, including the following steps:

[0016] High-temperature solution treatment: The whole turbine blade is kept at a temperature in the range of 1300 - 1350 °C for 10 hours, and then air-cooled;

[0017] Medium-temperature aging treatment: Treat by the method described in any one of claims 1 - 2;

[0018] Low-temperature aging treatment: The turbine blade that has undergone high-temperature solution treatment and medium-temperature aging treatment is kept at a temperature in the range of 850 - 890 °C for 16 hours, and then air-cooled.

[0019] The present invention also discloses a modular synchronous heat treatment device for a single-crystal turbine blade, including:

[0020] A heat insulation cavity, which is hollow inside for placing the turbine blade. Its side wall is sequentially provided with an inner heat insulation layer, a heating layer, and an outer heat insulation layer from the inside to the outside. The heating layer includes a plurality of heating elements arranged adjacent to each other from top to bottom;

[0021] A partition member, which is arranged in the heat insulation cavity and is used to isolate the hollow part inside the heat insulation cavity from each other, so that the tip of the turbine blade is located in the first temperature control zone, the blade body is located in the second temperature control zone, the blade root is located in the third temperature control zone, and the tenon head is located in the fourth temperature control zone;

[0022] A cooling medium supply unit, which includes a plurality of cooling medium delivery channels, and they respectively extend into the first temperature control zone, the second temperature control zone, the third temperature control zone, and the fourth temperature control zone for delivering cooling medium to the inside.

[0023] Furthermore, the heating element is a high-frequency induction coil group.

[0024] Furthermore, the temperature of the first temperature control zone is 1080 - 1100 °C, the temperature of the second temperature control zone is 1100 - 1120 °C, the temperature of the third temperature control zone is 1100 - 1120 °C, and the temperature of the fourth temperature control zone is 1120 - 1150 °C.

[0025] Furthermore, it also includes an infrared temperature measurement unit, which is used to monitor the real-time temperatures of the first temperature control zone, the second temperature control zone, the third temperature control zone, and the fourth temperature control zone respectively.

[0026] Furthermore, the cooling medium of the cooling medium supply unit is liquid nitrogen and / or high-pressure inert gas and / or air.

[0027] Furthermore, the cooling medium transported by the cooling medium supply unit to the first temperature control zone and the second temperature control zone is air, and its cooling rate is ≤100℃ / s; the cooling medium transported by the cooling medium supply unit to the third temperature control zone is high-pressure inert gas, and its cooling rate is ≥300℃ / s; the cooling medium transported by the cooling medium supply unit to the fourth temperature control zone is liquid nitrogen, and its cooling rate is ≥1000℃ / s.

[0028] The single-crystal turbine blades of the present invention are primarily produced through vacuum precision casting. After conventional solution and aging treatments, the blades exhibit a uniform, consistent microstructure from tip to tenon, characterized by a cubic primary γ′ phase, sized 200-400 nm, uniformly distributed within a γ matrix. By adjusting the aging temperature and time, and altering the size and content of the γ′ phase, the high- and low-temperature properties of the turbine blade material can be adjusted to a certain extent. However, improving low-temperature performance using this method inevitably results in a decrease in high-temperature performance. Rapid cooling after aging allows for the precipitation of a large amount of secondary γ′ phase, sized 10-50 nm, improving the low-temperature performance of the blade material while minimizing its impact on high-temperature performance. Previously, this technique was applied to localized treatment of turbine blades to overcome the mismatch between high- and low-temperature properties of turbine blade materials. However, its engineering application value was limited due to issues such as low processing efficiency, the inability to precisely control the microstructure, and increased residual stress in the blades. The modular, simultaneous heat treatment of single-crystal turbine blades in this invention allows for simultaneous localized heat treatment of the blade tip, blade body, blade root, and tenon in a single device. The treatment temperature and cooling rate of each region can be independently controlled, enabling the microstructure characteristics of each region to be adjusted and controlled. This technology enables the targeted design of the microstructure of each region of the blade material based on the actual service environment of the turbine blade.

[0029] The present invention adopts a unified solution treatment for the overall investment-cast turbine blade, ensuring that each region of the blade has consistent precipitation tissue characteristics. Subsequently, age hardening heat treatment with different temperatures and cooling rates is carried out on the tip, blade body, root, and tenon parts based on the modular synchronous heat treatment method and modular synchronous heat treatment device: the treatment temperature of the tip part is the lowest (1080 - 1100 °C) and air cooling is used (cooling rate ≤ 100 °C / s), which can form a single-mode distribution of primary γ' phase with a smaller size (200 - 350 nm), and can improve the resistance of the tip part to the deformation dominated by γ-phase dislocation slip at high temperatures; the blade body part adopts a medium aging temperature (1100 - 1120 °C) and air cooling, and also forms a single-mode distribution of primary γ' phase, but the size of the γ' phase slightly increases (300 - 400 nm), which can improve the resistance of the blade body part to the deformation dominated by super-dislocation shear of γ' phase at medium temperatures; the root part has the same aging temperature as the blade body, but high-pressure inert gas cooling (cooling rate ≥ 300 °C / s) can cause the precipitation of secondary γ' phase with a size of 10 nm - 50 nm in this region, improving the resistance of the root part to the deformation dominated by complex stacking fault zone shear at low temperatures; the aging temperature of the tenon part is the highest (1120 - 1150 °C), and at this temperature, the size of the primary γ' phase further increases (350 - 500 nm), and the partially redissolved γ' phase increases the supersaturation of the γ phase, and a large amount of precipitation occurs in the form of secondary γ' phase under the action of liquid nitrogen spray cooling (cooling rate ≥ 1000 °C / s), which can effectively improve the high-cycle fatigue performance of the tenon part.

[0030] The beneficial effect of the present invention is that modular heat treatment is carried out synchronously on the tip, blade body, root, and tenon parts in a modular synchronous heat treatment device for a set of single-crystal turbine blades. Combining with the heating system composed of a high-frequency induction coil group and an infrared temperature measurement unit, the heat treatment efficiency can be effectively improved, and the heat treatment temperature and cooling rate of each region are accurately controllable, so as to realize the adjustable and controllable tissue characteristics of each part of the blade and control the formation of residual stress in the blade at the same time. In addition, the present invention does not need to change the composition and preparation process of the existing single-crystal blade, and has high engineering application value. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 It is the front view of the turbine blade in the present invention.

[0032] Figure 2 It is a three-dimensional schematic diagram of the modular synchronous heat treatment device adopted in the present invention, and the turbine blade is placed in the heat insulation cavity.

[0033] Figure 3 It is a front view schematic diagram of the modular synchronous heat treatment device adopted in the present invention, and the turbine blade is placed in the heat insulation cavity.

[0034] Figure 4This is the top view of the modular synchronous heat treatment device used in the present invention, with the turbine blade placed in the heat insulation chamber.

[0035] Figure 5 This is the microstructure morphology diagram of the blade tip, blade body, blade root, and tenon head parts after modular synchronous heat treatment of the blade in Example 1 of the present invention.

[0036] Figure 6 This is the microstructure morphology diagram of the blade tip, blade body, blade root, and tenon head parts after modular synchronous heat treatment of the blade in Example 2 of the present invention.

[0037] Figure 7 This is the microstructure morphology diagram of the blade tip, blade body, blade root, and tenon head parts of the comparative example blade after traditional homogeneous heat treatment. Detailed implementation manners

[0038] In order to enable those skilled in the art to better understand the solution of the present invention, the following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0039] The turbine blades prepared from the well-known nickel-based single-crystal superalloy are used in the embodiments and comparative examples of the present invention, and the chemical compositions of the alloy are shown in Table 1.

[0040] Table 1 Chemical compositions of the single-crystal superalloy in the embodiments and comparative examples of the present invention (weight percentage wt.%)

[0041] Element Chromium Cobalt Tungsten Molybdenum Rhenium Tantalum Aluminum Ruthenium Niobium Hafnium Carbon Yttrium wt.% 2.8 6.6 5.5 3.2 4.8 6.2 6.0 2.1 0.1 0.05 0.02 0.005

[0042] Specific preparation method:

[0043] In the embodiments and comparative examples of the present invention, the blades all adopt a three-step treatment process of high-temperature solution treatment, medium-temperature aging treatment, and low-temperature aging treatment. Among them, the high-temperature solution treatment and low-temperature aging treatment processes are the same, specifically:

[0044] (1) High-temperature solution treatment: The as-cast blade is kept at a temperature in the range of 1300 - 1350 °C for 10 hours, and then air-cooled;

[0045] (2) Low-temperature aging treatment: The blade that has undergone high-temperature solution treatment and medium-temperature aging treatment is kept at a temperature in the range of 850 - 890 °C for 16 hours, and then air-cooled.

[0046] In the embodiments and comparative examples of the present invention, different medium-temperature aging treatment processes are adopted. The comparative example adopts a traditional homogenization treatment process: the whole solution-treated blade is kept at 1100 °C for 4 hours and then air-cooled. Embodiments 1-2 adopt a modular synchronous heat treatment process: the solution-treated blade is loaded into a modular synchronous heat treatment device and processed independently in 4 zones (tip, blade body, root, and tenon), with the same heat treatment time for each zone, but different temperatures and cooling rates, as follows:

[0047] (1) The first temperature control zone (tip zone): 1080-1100 °C, 4 hours, air-cooled (cooling rate ≤ 100 °C / s);

[0048] (2) The second temperature control zone (blade body zone): 1100-1120 °C, 4 hours, air-cooled (cooling rate ≤ 100 °C / s);

[0049] (3) The third temperature control zone (root zone): 1100-1120 °C, 4 hours, cooled by high-pressure inert gas (cooling rate ≥ 300 °C / s);

[0050] (4) The fourth temperature control zone (tenon zone): 1120-1150 °C, 4 hours, cooled by liquid nitrogen spraying (cooling rate ≥ 1000 °C / s).

[0051] The specific temperatures of the modular synchronous heat treatment in Embodiments 1-2 of the present invention are shown in Table 2 and have the following characteristics: 1) The treatment temperatures from the tip to the tenon in Embodiment 1 are different, having a positive temperature gradient; 2) In Embodiment 2, the same treatment temperatures are adopted for the tip and the blade body, and the root and the tenon respectively.

[0052] Table 2 Temperatures of the modular synchronous heat treatment in Embodiments 1-2 (°C)

[0053] Sample Tip Blade Root Tenon Example 1 1080 1100 1120 1150 Example 2 1100 1100 1120 1120

[0054] Figures 1 - 4 Figure is a schematic structural diagram of the 4-zone modular synchronous heat treatment process device adopted in Embodiments 1 and 2, Figure 5 、 Figure 6 are respectively the microstructural morphology diagrams of the tip, blade body, root, and tenon parts after the modular synchronous heat treatment in Embodiment 1 and Embodiment 2. After the modular synchronous heat treatment, the turbine blade forms a gradient tissue feature, among which:

[0055] (1) The first temperature control zone (tip zone): composed of a γ-phase matrix and primary γ'-phase with a size of 200-350 nm, and the γ'-phase has a single-mode distribution;

[0056] (2) The second temperature control zone (blade body zone): composed of a γ-phase matrix and primary γ'-phase with a size of 300-400 nm, and the γ'-phase has a single-mode distribution;

[0057] (3) The third temperature control zone (blade root zone): It is composed of a γ-phase matrix, primary γ'-phase with a size of 300 - 400 nm, and secondary γ'-phase with a size of 10 - 50 nm, showing a bimodal distribution of the γ'-phase.

[0058] (4) The fourth temperature control zone (tenon zone): It is composed of a γ-phase matrix, primary γ'-phase with a size of 350 - 500 nm, and secondary γ'-phase with a size of 10 - 50 nm, showing a bimodal distribution of the γ'-phase.

[0059] Figure 7 This is the microstructure morphology diagram of the blade tip, blade body, blade root, and tenon parts of the comparative example blade of the present invention after traditional homogeneous heat treatment. The blade tip, blade body, blade root, and tenon parts are all composed of a γ-phase matrix and primary γ'-phase with a size of about 300 nm, showing a unimodal distribution of the γ'-phase.

[0060] Table 3 gives the quantitative data of the primary γ'-phase size in the blade tip, blade body, blade root, and tenon parts of Example 1, Example 2, and the comparative example. In Example 1, as the treatment temperature of the blade tip, blade body, blade root, and tenon parts increases continuously, the primary γ'-phase size also increases continuously, and the gradient tissue characteristics are more obvious. In Example 2, the treatment temperatures of the blade tip and blade body, blade root and tenon are the same, and the primary γ'-phase sizes in the corresponding regions are close. However, due to the higher cooling rate adopted in the tenon part, the content of the secondary γ'-phase increases slightly, specifically about 2.5 ± 1% in the blade root and about 4.7 ± 1% in the tenon. In the comparative example, due to the adoption of the traditional homogeneous heat treatment method, the γ'-phase sizes in the blade tip, blade body, blade root, and tenon parts are the same.

[0061] Table 3 Size of γ'-phase after modular synchronous heat treatment in Examples 1 - 2 (nm)

[0062] Sample Tip Blade Root Tenon Example 1 254±10 302±10 377±10 460±10 Example 2 313±10 311±10 362±10 369±10 Comparative Example 309±10 315±10 318±10 311±10

[0063] The above results fully demonstrate that the modular synchronous heat treatment method and device in the present invention can achieve precise control of the organizational structures of the tip, blade body, root, and tenon of a turbine blade by changing the treatment conditions of different modules. Compared with traditional, homogeneous-structure blades, the modular synchronous heat treatment in the present invention can customize the organizational structures of the tip, blade body, root, and tenon with reference to the actual service environment of the turbine blade, and can improve the comprehensive performance of the blade under complex environments. The advantages of the present invention are as follows: 1) The prior art forms non-uniform organizational structures in different regions of the blade through step-by-step heat treatment. The present invention can simultaneously process the tip, blade body, root, tenon, etc. of the blade in a set of devices, with higher efficiency; 2) In the prior art, due to the blade experiencing thermal cycling in different regions during different treatment steps, large residual stresses are likely to be generated. The present invention realizes synchronous treatment of different regions through a modular heating device, and the residual stress will be greatly reduced; 3) Due to the use of a multi-step treatment process in the prior art, effective isolation of the tip, blade body, root, tenon, etc. cannot be achieved, and the local heat treatment of different regions inevitably affects the surrounding tissues, making it difficult to achieve precise control of the blade's organizational structure. The present invention realizes adjustable and controllable organizational structures of the tip, blade body, root, and tenon through modular synchronous treatment.

[0064] As Figures 1 - 4 shown, a modular synchronous heat treatment device for a single-crystal turbine blade includes a heat insulation cavity 1, a partition 2, a cooling medium supply unit 3, and an infrared temperature measurement unit. The interior of the heat insulation cavity 1 is hollow and can be used to place the turbine blade 4. The side wall of the heat insulation cavity 1 is sequentially provided with an inner heat insulation layer 11, a heating layer 12, and an outer heat insulation layer 13 from the inside to the outside. The heating layer 12 includes a plurality of heating elements 121 arranged adjacent to each other from top to bottom. In this embodiment, the heating element 121 is a high-frequency induction coil group.

[0065] The partition 2 is detachably connected inside the heat insulation cavity 1 and is used to isolate the hollow part inside the heat insulation cavity 1 from each other. Specifically, a plurality of partitions 2 are respectively located between the tip 41 and the blade body 42 of the turbine blade 4, between the blade body 42 and the root 43, and between the root 43 and the tenon 44, so that the tip 41 of the turbine blade 4 is located in the first temperature control zone 14, the blade body 42 is located in the second temperature control zone 15, the root 43 is located in the third temperature control zone 16, and the tenon 44 is located in the fourth temperature control zone 17. The above-mentioned first temperature control zone 14, second temperature control zone 15, third temperature control zone 16, and fourth temperature control zone 17 are isolated from each other, that is, the treatment temperatures between them are independently controllable and will not be affected.

[0066] The temperature controlled by the high-frequency induction coil group in the first temperature control zone 14 (tip region) is 1080 - 1100 °C, the temperature controlled by the high-frequency induction coil group in the second temperature control zone 15 (blade body region) is 1100 - 1120 °C, the temperature controlled by the high-frequency induction coil group in the third temperature control zone 16 (root region) is 1100 - 1120 °C, and the temperature controlled by the high-frequency induction coil group in the fourth temperature control zone 17 (tenon region) is 1120 - 1150 °C. Since the whole turbine blade is placed in the heat insulation cavity, the treatment of different regions is carried out synchronously, but the temperature of each region is independently controllable.

[0067] The cooling medium supply unit 3 includes a plurality of cooling medium delivery channels 31, which respectively extend into the first temperature control zone 14 (tip region), the second temperature control zone 15 (blade body region), the third temperature control zone 16 (root region), and the fourth temperature control zone 17 (tenon region) to deliver the cooling medium into each region. The cooling medium can be liquid nitrogen, high-pressure inert gas, or air, and the cooling medium delivery channels 31 pass through the side wall of the heat insulation cavity 1 and enter its hollow interior.

[0068] Specifically, the cooling medium delivered by the cooling medium supply unit 3 to the first temperature control zone 14 (tip region) and the second temperature control zone 15 (blade body region) is air, and its cooling rate ≤ 100 °C / s; the cooling medium delivered by the cooling medium supply unit 3 to the third temperature control zone 16 (root region) is high-pressure inert gas, and its cooling rate ≥ 300 °C / s; the cooling medium delivered by the cooling medium supply unit 3 to the fourth temperature control zone 17 (tenon region) is liquid nitrogen, and its cooling rate ≥ 1000 °C / s.

[0069] The infrared temperature measurement unit is used to monitor the temperature in the first temperature control zone 14 (tip region), the second temperature control zone 15 (blade body region), the third temperature control zone 16 (root region), and the fourth temperature control zone 17 (tenon region) in real time respectively, so as to facilitate timely adjustment. Thus, the purpose of adjustable and controllable tissue characteristics of each part of the tip 41, blade body 42, root 43, and tenon 44 of the turbine blade 4 is achieved.

[0070] The above specific embodiments are used to explain and illustrate the present invention, rather than to limit the present invention. Any modification and change made to the present invention within the spirit and scope of the protection of the claims of the present invention fall within the protection scope of the present invention.

Claims

1. A modular synchronous heat treatment method for single crystal turbine blades, characterized in that, Including the following steps: Place the turbine blade in a high-temperature space, which is divided into mutually isolated first temperature control zone, second temperature control zone, third temperature control zone, and fourth temperature control zone corresponding to the tip, blade body, root, and tenon of the turbine blade; Simultaneously perform heat treatment and cooling treatment on the first temperature control zone, second temperature control zone, third temperature control zone, and fourth temperature control zone, so that the tip, blade body, root, and tenon of the turbine blade are simultaneously treated separately under different temperature control conditions.

2. The heat treatment method according to claim 1, wherein: The temperature of the first temperature control zone is 1080 - 1100 °C, the cooling rate ≤ 100 °C / s, and the structure contains a γ-phase matrix and primary γ'-phase with a size of 200 - 350 nm; The temperature of the second temperature control zone is 1100 - 1120 °C, the cooling rate ≤ 100 °C / s, and the structure contains a γ-phase matrix and primary γ'-phase with a size of 300 - 400 nm; The temperature of the third temperature control zone is 1100 - 1120 °C, the cooling rate ≥ 300 °C / s, and the structure contains a γ-phase matrix, primary γ'-phase with a size of 300 - 400 nm, and secondary γ'-phase with a size of 10 nm - 50 nm; The temperature of the fourth temperature control zone is 1120 - 1150 °C, the cooling rate ≥ 1000 °C / s, and the structure contains a γ-phase matrix, primary γ'-phase with a size of 350 - 500 nm, and secondary γ'-phase with a size of 10 nm - 50 nm.

3. A processing method for a single crystal turbine blade, characterized in that, Including the following steps: High-temperature solution treatment, keep the whole turbine blade at a temperature in the range of 1300 - 1350 °C for 10 hours, and then air-cool; Medium-temperature aging treatment, treat by the method as described in any one of claims 1 - 2; Low-temperature aging treatment: Keep the turbine blade after high-temperature solution treatment and medium-temperature aging treatment at a temperature in the range of 850 - 890 °C for 16 hours, and then air-cool.

4. A modular synchronous heat treatment device for single crystal turbine blades, characterized in that, Including: Insulation cavity, which is hollow inside for placing the turbine blade, and its side wall is sequentially provided with an inner insulation layer, a heating layer, and an outer insulation layer from the inside to the outside. The heating layer includes a plurality of heating elements arranged adjacent to each other from top to bottom; Partition member, arranged in the insulation cavity, used to isolate the hollow part inside the insulation cavity from each other, so that the tip of the turbine blade is located in the first temperature control zone, the blade body is located in the second temperature control zone, the root is located in the third temperature control zone, and the tenon is located in the fourth temperature control zone; Cooling medium supply unit, including a plurality of cooling medium delivery channels, which respectively extend into the first temperature control zone, second temperature control zone, third temperature control zone, and fourth temperature control zone for delivering cooling medium to the inside.

5. The heat treatment apparatus according to claim 4, wherein: The heating element is a high-frequency induction coil group.

6. The heat treatment apparatus according to claim 4, characterized in that: The temperature of the first temperature control zone is 1080 - 1100 °C, the temperature of the second temperature control zone is 1100 - 1120 °C, the temperature of the third temperature control zone is 1100 - 1120 °C, and the temperature of the fourth temperature control zone is 1120 - 1150 °C.

7. The heat treatment apparatus according to claim 4, wherein: It further includes an infrared temperature measurement unit, which is used to respectively monitor the real-time temperature of the first temperature control zone, second temperature control zone, third temperature control zone, and fourth temperature control zone.

8. The heat treatment apparatus according to claim 4, wherein: The cooling medium of the cooling medium supply unit is liquid nitrogen and / or high-pressure inert gas and / or air.

9. The heat treatment apparatus according to claim 8, wherein: The cooling medium supplied by the cooling medium supply unit to the first temperature control zone and the second temperature control zone is air, and its cooling rate is ≤ 100 °C / s; the cooling medium supplied by the cooling medium supply unit to the third temperature control zone is high-pressure inert gas, and its cooling rate is ≥ 300 °C / s; the cooling medium supplied by the cooling medium supply unit to the fourth temperature control zone is liquid nitrogen, and its cooling rate is ≥ 1000 °C / s.

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