CN114855106A - Device and method for local heat treatment after repair of large and complex aviation titanium alloy structural parts - Google Patents

Abstract

The invention discloses a local heat treatment device and a local heat treatment method for an aviation titanium alloy large-scale complex structural part after repair, wherein the local heat treatment device for the aviation titanium alloy large-scale complex structural part after repair comprises the following steps: the heater is used for attaching and heating the repair part of the large complex aviation titanium alloy structural part; the temperature sensor is used for detecting the temperature of the repair part of the large complex aviation titanium alloy structural part; and the temperature controller is respectively in communication connection with the heater and the temperature sensor. According to the scheme, the repair part of the large-scale complex aviation titanium alloy structural part can be effectively subjected to local heat treatment, the size of a heat treatment device can be greatly reduced, and the condition that the repair workpiece is deformed by heating to cause out-of-tolerance can be prevented.

Description

Device and method for local heat treatment after repair of large and complex aviation titanium alloy structural parts

technical field

The invention relates to the technical field of local heat treatment after repair of a large complex structure of aviation titanium alloy, in particular to a device and method of local heat treatment after repair of a large complex structure of aviation titanium alloy.

Background technique

The working environment of large and complex aviation titanium alloy structural parts such as casing and integral blisk is a high temperature and high pressure environment. During the service process, damage and failure such as cracks, corrosion and wear are inevitable. The use of high-energy beam repair processes such as laser additive repair and electron beam welding to achieve rapid repair of damaged parts has significant economic benefits for extending the life of damaged parts. The high-energy beam repair process has the characteristics of rapid melting, which makes the structure of the repaired parts metastable, and the repaired structural parts inevitably have large residual stress, which directly affects the mechanical properties of the repaired parts.

Heat treatment is the main technological means and necessary procedure for realizing residual stress elimination and microstructure regulation in the repair area of large and complex structural parts of aviation titanium alloys, thereby improving the mechanical properties of the repair parts. Aviation titanium alloy large and complex structural parts belong to large thin-walled parts. The overall heat treatment requires large-scale vacuum furnace equipment and complex heat treatment fixtures, and the stress release during the overall heat treatment of the workpiece is likely to cause new deformation out of tolerance.

SUMMARY OF THE INVENTION

In view of this, the present invention provides a local heat treatment device after repair of a large complex structure of aviation titanium alloy, which can effectively perform local heat treatment on the repaired part of a large complex structure of aviation titanium alloy, which can not only greatly reduce the size of the heat treatment device, but also It can prevent the repaired workpiece from being out of tolerance due to thermal deformation.

To achieve the above object, the present invention provides the following technical solutions:

A local heat treatment device for a large and complex structure of aviation titanium alloy, comprising:

A heater for fitting and heating the repaired parts of large and complex structural parts of aerospace titanium alloys;

A temperature sensor for detecting the temperature of the repaired part of the aviation titanium alloy large-scale complex structure;

a temperature controller connected in communication with the heater and the temperature sensor, respectively.

Preferably, the heater is a flexible heater.

Preferably, the flexible heater includes a crawler-type ceramic heater or a silicone rubber flexible heater.

Preferably, the temperature sensor includes:

A thermocouple installed on the surface of the repaired part of the aviation titanium alloy large-scale complex structure;

The heater is fitted and installed on the surface of the repair part of the aviation titanium alloy large-scale complex structure, and wraps the thermocouple.

Preferably, the number of the thermocouples is two, and they are temperature measurement thermocouples and temperature control thermocouples respectively;

The temperature-measuring thermocouple and the temperature-controlling thermocouple are installed on different surfaces of the repaired parts of the aviation titanium alloy large-scale complex structural parts, and are connected with the two different interfaces of the temperature controller in a one-to-one correspondence, so that the The detection value of the temperature-controlling thermocouple is greater than the detection value of the temperature-measuring thermocouple.

Preferably, it also includes:

The thermal insulation layer is used to wrap the repair part of the aviation titanium alloy large and complex structure and is located on the outer side of the heater.

Preferably, the thermal insulation layer includes an asbestos thermal insulation layer.

Preferably, it also includes:

An argon gas protective box for placing the large and complex structure of the aviation titanium alloy, and in which the heater and the temperature sensor are located.

A method for local heat treatment after repair of a large-scale complex structure of aviation titanium alloy, which adopts the above-mentioned local heat treatment device after repair of a large-scale complex structure of aviation titanium alloy to perform local heat treatment, and the method includes the following steps:

S1. According to the determined heat treatment system of large-scale complex structural parts of aviation titanium alloy, the temperature rise time, heat preservation temperature, heat preservation time and cooling time of each stage of local heat treatment are set by the temperature controller;

S2. Control the operation of the heater through a temperature controller according to the temperature rise time, holding temperature and holding time of each stage of the local heat treatment set in step S1.

Preferably, in step S1, the heat treatment system for the aviation titanium alloy large-scale complex structure includes:

The temperature was evenly heated to 600° C. in multiple stages according to the preset heating rate, and the temperature was maintained for 4 h; wherein, the temperature was maintained for 5 min when the temperature was raised to the corresponding preset temperature in each stage.

It can be seen from the above technical solutions that the local heat treatment device provided by the present invention can effectively perform local heat treatment on the repaired parts of the large and complex aviation titanium alloy structural parts, which can not only greatly reduce the size of the heat treatment device The size of the repaired workpiece can also be prevented from being out of tolerance due to thermal deformation of the repaired workpiece.

Description of drawings

In order to explain the embodiments of the present invention or the technical solutions in the prior art more clearly, the following briefly introduces the accompanying drawings that need to be used in the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description are only These are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can also be obtained according to these drawings without creative efforts.

1 is a schematic structural diagram of a local heat treatment device after repair of a certain aviation titanium alloy large-scale complex structural component provided by an embodiment of the present invention;

2 is a schematic diagram of the installation of a heating device in a heat treatment area after repair of a large-scale complex structure of an aviation titanium alloy provided by an embodiment of the present invention;

FIG. 3 is a schematic diagram of the installation of a flexible heater and an asbestos thermal insulation layer provided by an embodiment of the present invention.

Among them, 1 is an argon protective box; 2 is a thermocouple; 3 is a flexible heater; 4 is a large complex structure of aviation titanium alloy; 5 is a temperature controller; 6 is a repair area; 7 is an asbestos insulation layer.

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described below 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, but not all of 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.

The local heat treatment device after repair of a large complex structure of aviation titanium alloy provided by the embodiment of the present invention, as shown in FIG. 1 , includes:

A heater used to fit and heat the repaired part of the large complex structure 4 of aviation titanium alloy;

A temperature sensor used to detect the temperature of the repaired part of the large and complex structure of aviation titanium alloy 4;

The temperature controller 5 is respectively connected to the heater and the temperature sensor in communication.

It should be noted that the heating temperature of the heater can be fed back through the temperature sensor; of course, the temperature controller 5 will control the operation of the heater according to the detection value of the temperature sensor. For example, when the aviation titanium alloy large-scale complex structure 4 is heated to the corresponding preset temperature at a certain stage, the temperature controller 5 will control the heater to enter the heat preservation state according to the feedback of the temperature sensor. That is to say, the temperature controller 5 of this solution realizes precise regulation of the heating temperature of the heater according to the detection feedback of the temperature sensor. In addition, the local heat treatment device provided by this scheme is suitable for large and complex structural parts of aviation titanium alloy such as engine casing and integral blisk, as well as for spacecraft titanium alloy shell and fuel tank. In addition, the large complex structure 4 of aviation titanium alloy in FIG. 1 is the engine casing.

It can be seen from the above technical solutions that the local heat treatment device for the repaired large-scale complex structure of aviation titanium alloy provided by the embodiment of the present invention can effectively perform local heat treatment on the repaired part of the large-scale complex structure of aviation titanium alloy, which can not only greatly reduce the size of the The size of the heat treatment device can avoid the design and manufacture of heat treatment fixtures with complex structures, and can also prevent the repaired workpiece from being out of tolerance due to thermal deformation.

In this solution, as shown in FIG. 2 , the heater is a flexible heater 3 . That is to say, the heater of this solution adopts the flexible heater 3, so as to facilitate the fitting and flexible heating according to the structural characteristics of the repaired part of the repaired workpiece, which can help to improve the local heat treatment effect of the repaired workpiece, so that the repaired part of the repaired workpiece can be heated. The heat affected zone is small and the deformation is small.

Specifically, the flexible heater 3 includes a crawler-type ceramic heater or a silicone rubber flexible heater. Among them, the flexible heater 3 of this solution adopts a crawler-type ceramic heater, which can be spliced, bent or wound and heated according to the structural characteristics of the repaired part of the repaired workpiece, so as to achieve adaptive contact heating for the repaired part of the repaired workpiece. Therefore, a simple and effective heating method can be provided for repairing the complex structure of the repairing area of the workpiece.

Further, as shown in Figure 2, the temperature sensor includes:

The thermocouple 2 installed on the surface of the repaired part of the large complex structure 4 of aviation titanium alloy;

The heater is fitted and installed on the surface of the repaired part of the large complex structure 4 of aviation titanium alloy, and wraps the thermocouple 2 . That is to say, as shown in FIG. 2 , the heater fits and wraps the surface of the repaired part of the large complex structure 4 of aviation titanium alloy, and the thermocouple 2 is installed inside the heater. This solution is designed so that the temperature detection of the thermocouple 2 is more accurate, thereby helping to improve the accuracy of the local heat treatment of the device.

Further, as shown in Figure 2, the number of thermocouples 2 is two, and they are respectively temperature measurement thermocouples and temperature control thermocouples; of course, the heater wraps temperature measurement thermocouples and temperature control thermocouples;

The temperature-measuring thermocouple and the temperature-controlling thermocouple are installed on the different surfaces of the repaired parts of the aviation titanium alloy large-scale complex structure 4, and are connected to the two different interfaces of the temperature controller 5 in a one-to-one correspondence, so that the temperature-controlling thermocouple can detect The value is greater than the detection value of the temperature-measuring thermocouple, that is, to ensure that the temperature value of the temperature-controlling thermocouple at the same repair site is not lower than the temperature value of the temperature-measuring thermocouple, so as to ensure the precise regulation of the heating temperature.

Further, the temperature controller 5 is provided with 6 interfaces, which are respectively No. 1, 2, 3, 4, 5, and No. 6 interfaces; wherein, No. 1, 2, and No. 3 interfaces are used to communicate with the temperature-controlling thermocouple respectively. , No. 4, 5, and No. 6 interfaces are used to communicate with temperature measuring thermocouples respectively, and the temperature controller 5 can display the value of each thermocouple 2 connected to it, so that the two thermocouples 2 in the heat treatment position of the workpiece are repaired. The temperature value is visible. In addition, before the heat treatment, the temperature of the temperature-controlling thermocouple and the temperature-measuring thermocouple is detected by preheating the heat treatment part:

Taking the first temperature-controlling thermocouple (which communicates with the No. 1 interface) and the first temperature-measuring thermocouple (which is communicatively connected with the No. 4 interface) as an example, if the temperature of the first temperature-controlling thermocouple is greater than that of the first measuring The temperature of the thermocouple can ensure that the temperature of the heating area reaches the temperature set by the heat treatment; if the temperature of the first temperature-controlling thermocouple is lower than the temperature of the first temperature-measuring thermocouple, connect the power supply of the No. The lines are switched so that the temperature of the first temperature-controlling thermocouple is greater than the temperature of the first temperature-measuring thermocouple. That is to say, if the temperature of the temperature-controlling thermocouple is not guaranteed to be greater than that of the temperature-measuring thermocouple, the temperature of the heat treatment area may not reach the set value.

That is to say, this scheme is based on the optimal arrangement of multi-point thermocouples and real-time temperature measurement, automatically adjusts the heating power of the heater, ensures the accessibility of local heating temperature, ensures the reliability of the required heat treatment system, and can achieve multiple types of damage. Adaptive local heat treatment of repaired structures.

In this solution, in order to improve the heat preservation effect of the repaired workpiece in the local heat treatment; accordingly, the local heat treatment device after repairing the large and complex structure of aviation titanium alloy provided by the embodiment of the present invention further includes:

It is used to wrap the repair part of the aviation titanium alloy large and complex structure 4 and is located on the outer side of the heater. That is to say, as shown in Figures 2 and 3, the heater first wraps and fixes the thermocouple in the heat treatment area (repair part, that is, the repair area 6 of the large and complex structure of aviation titanium alloy), The thermal insulation layer then wraps the outer layer of the heater to fix it. In this way, in order to obtain better thermal insulation effect and temperature control effect.

Specifically, as shown in FIG. 3 , the thermal insulation layer includes an asbestos thermal insulation layer 7 . Among them, the asbestos thermal insulation layer 7 has the characteristics of good thermal insulation effect, convenient installation and long service life.

In order to further optimize the above technical solution, as shown in FIG. 1 , the local heat treatment device for a large-scale complex structure of aviation titanium alloy provided by the embodiment of the present invention also includes:

Argon gas protective box 1 for placing large and complex aviation titanium alloy structural parts 4, in which heaters and temperature sensors are located. That is to say, in this solution, by providing an argon gas protective box 1, it is convenient to provide a heat treatment environment with low water oxygen and argon gas protection for the local heat treatment of the repaired workpiece; wherein, the water and oxygen content in the box can be lower than 50PPM after purification. , so as to effectively prevent the high-temperature oxidation of the repaired workpiece during local heat treatment.

The embodiment of the present invention also provides a method for local heat treatment after repair of a large-scale complex structure of aviation titanium alloy, using the above-mentioned local heat treatment device after repair of a large-scale complex structure of aviation titanium alloy to perform local heat treatment, and the method includes the following steps:

S1. According to the determined post-repair heat treatment system for aviation titanium alloy large and complex structural parts, the temperature rise time, heat preservation temperature, heat preservation time and cooling time of each stage of local heat treatment are set by the temperature controller;

S2. Control the operation of the heater through a temperature controller according to the temperature rise time, holding temperature and holding time of each stage of the local heat treatment set in step S1.

It should be noted that, the time of the different processes in each stage can be set by a temperature controller, so that precise control of the time of the different processes in each stage can be realized. In addition, the heater (flexible heater) of this scheme is heated with a high frequency of 20-80 kHz to ensure the local heat treatment effect of the repaired workpiece; in addition, the current of the heater is adjusted by a temperature controller to control its output power. At the same time, since this solution adopts the above-mentioned local heat treatment device for local heat treatment after repairing a large complex structure of aviation titanium alloy, it also has corresponding beneficial effects.

In this solution, in order to obtain a better local heat treatment effect for the repaired workpiece; accordingly, in step S1, the post-repair heat treatment system for the large-scale complex structure of aviation titanium alloy includes:

The temperature was evenly heated to 600° C. in multiple stages according to the preset heating rate, and the temperature was maintained for 4 h; wherein, the temperature was maintained for 5 min when the temperature was raised to the corresponding preset temperature in each stage. Further, the preset heating rate may be 100°C/10min.

Below in conjunction with specific embodiment, this scheme is further introduced:

The present invention adopts flexible heating for local heat treatment, which can effectively solve the problems in the background technology, and the flexible heating only heats the repaired part, and the heating speed, temperature and range are controllable. The adaptability of the flexible heater and the accuracy of the regulation of the heat treatment regime directly determine the effects of stress release and tissue regulation. Therefore, how to accurately control the design of flexible heaters and the regulation of heat treatment regimes according to the structural characteristics of the repaired parts of large and complex aviation titanium alloy structural parts is the key to flexible local heat treatment.

The purpose of the present invention is to provide a local heat treatment method after repairing a large and complex structure of aviation titanium alloy, which can accurately treat large and complex aviation titanium alloy under the premise of preventing high-temperature oxidation during local heat treatment and repairing the workpiece's thermal deformation out of tolerance. Local heat treatment is performed on the repaired parts of the structural parts to reduce residual stress and improve microstructure and mechanical properties.

A method for local heat treatment after repair of a large-scale complex structure of aviation titanium alloy, the method comprises: an argon gas protective box and an intelligent temperature controller, and is characterized in that: the argon gas protective box is placed inside the protective box with flexible heating for local heat treatment Structure, the flexible heating local heat treatment structure includes an asbestos insulation layer, a crawler-type ceramic heater is installed inside the asbestos insulation layer, and a flexible thermocouple is installed inside the installed crawler-type ceramic heater, and the thermocouple passes through The transmission line is connected to the intelligent temperature controller outside the inert gas protection box. The crawler-type ceramic heater wraps and fixes the flexible thermocouple in the heat treatment area of a large complex structure of aviation titanium alloy. The outer layer of the ceramic heater is wrapped and fixed, the argon gas protective box has its own purification system, and an argon gas inlet pipe is installed on the side.

The method for local heat treatment after repairing a large-scale complex structure of aviation titanium alloy includes the following steps:

1. Flexible heater design. The flexible heater used in the present invention is a crawler-type ceramic heater, and a matching flexible heater is designed according to the structural characteristics of the repair part of the large-scale complex structural parts of aviation titanium alloy, combined with the structural characteristics of the elongated repair area and its annular repair area; For a long repair area (as shown in Figure 2), the length of the flexible heater should be 0.5-1 cm larger than the length of the entire repair area, and the overall width of the flexible heater should be 3-5 cm larger than the width of the repair area, so that Ensure the heating area of the repair area; for the annular repair area, the overall length of the flexible heater should be equal to the perimeter of the annular repair area, and the width of the flexible heater The overall width of the flexible heater is also 3-5 cm larger than the width of the repair area. This design scheme achieves precise control of the heating area on the premise of ensuring the adaptability of the flexible heater;

2. The large and complex structural parts of aviation titanium alloy are placed in the argon protective box;

3. The heat treatment system is determined. The material of aviation titanium alloy large and complex structural parts is titanium alloy, and the repair method usually adopts electron beam welding, laser additive repair and other processes; after the repair of aviation titanium alloy large and complex structural parts, the residual stress in the repair area is relatively large; For the characteristics of the structure, the stress relief annealing heat treatment process is adopted; the heat treatment system of the stress relief annealing of titanium alloy is 600 °C, and the temperature is kept for 4 hours; , heat preservation for 4h; after the end of the heat preservation time, the argon gas protective box is cooled naturally;

4. Thermocouple clamping and temperature monitoring. Choose a suitable length and an upright hot-spot couple, install 2 thermocouples at each repair area and do not loosen them. The functions are temperature control and temperature measurement respectively; The temperature rise time is 5min, adjust the current to control the output power, and check the temperature of the thermocouple in the temperature control area and the thermocouple in the temperature measurement area after the temperature rise time is reached. If the temperature value of the temperature control thermocouple is not lower than that of the temperature measurement thermocouple, then Do not adjust the connection. If the temperature value of the temperature-controlled thermocouple is lower than the temperature value of the temperature-measurement thermocouple, adjust the connection of the two thermocouples to ensure that the temperature value of the thermocouple used for temperature control in the same repair area is not lower than that of the temperature-measurement thermocouple. The temperature value of the thermocouple can ensure the precise control of the heating temperature; after the installation and commissioning of the thermocouple, the designed flexible heater is covered with the thermocouple and adjusted and positioned at the repaired part;

5. Purify the atmosphere in the argon protective box; pass argon gas to the heat treatment protective box, so that the oxygen content in the box is lower than 100PPM; the protective box is circulated and purified, so that the oxygen content of the water in the box is lower than 50PPM after purification, which is Local heat treatment of large and complex structural parts of aerospace titanium alloys provides a processing environment with low water oxygen and argon protection.

6. The flexible heating device is used for local heat treatment of the repair area of large and complex structural parts of aviation titanium alloys. The invention adopts a high-frequency heating source with a frequency of 20-80 kHz, adjusts the oscillating current of the heating source through an intelligent temperature controller, controls the output power, and heats up through a flexible heater to generate a local high-temperature temperature field, thereby realizing large-scale complex aviation titanium alloys. Heat treatment of local repair parts of structural parts; set the determined temperature rise time, heat preservation temperature, heat preservation time and cooling time of each stage of local heat treatment through the intelligent temperature control box. Local heat treatment in the area.

The present invention has the following advantages:

1. The flexible heater mainly adopts crawler type ceramic heater, which can be spliced, bent and wound according to the structural characteristics of the repaired workpiece and the repaired part, and is closely attached to the surface of the repair area of the large and complex structural parts of aviation titanium alloy for contact heating, which can be simple and convenient. Effectively achieve heating of complex structures in the repair area.

2. Based on the optimal arrangement of multi-point thermocouples and real-time temperature measurement, the heating power can be automatically adjusted to ensure the accessibility of local heating temperature, to ensure the reliability of the required heat treatment system, and to achieve adaptive local heat treatment of multi-type damage repair structures. .

3. The oscillating current of the high-frequency heating source (frequency 20-80kHz) is adjusted by the intelligent temperature controller to control the heating temperature to achieve precise control of the local heat treatment temperature.

4. The argon protective box is used to perform local heat treatment under the overall argon protective state for large and complex aviation titanium alloy structural parts. After purification, the water and oxygen content in the box can be lower than 50PPM to prevent high temperature oxidation during local heat treatment.

5. The use of a flexible heating device can perform local heat treatment on the repair area of large and complex aviation titanium alloy structural parts, with a small heat-affected zone and small deformation.

More specifically, as shown in FIG. 1 , a local heat treatment device after repair of a large complex structure of aviation titanium alloy, including a protective gas box, a thermocouple 2, a flexible heater 3, and an intelligent temperature controller, described in the present invention. The protective gas box, thermocouple 2, flexible heater 3, and intelligent temperature controller can be purchased commercially, or prepared according to methods disclosed in the prior art, and those skilled in the art can select and set them according to the prior art. The thermocouple 2 is installed at the part repairing part and is connected with the intelligent temperature controller, and the corresponding flexible heater 3 is designed and manufactured according to the shape feature of the parts repairing area and is closely attached to the surface of the large and complex aerospace parts repairing area. The thermocouple 2 is wrapped and connected to the intelligent temperature controller, and the large and complex structure of aviation titanium alloy is placed in the argon gas protective box 2.

Thermocouple 2, flexible heater 3, and intelligent temperature controller form a flexible heating local heat treatment system. The surface temperature of the workpiece repair area is detected by the thermocouple 2, and the current is adjusted by the intelligent temperature controller to realize the local heating of the casing repair area and the regulation of the heating temperature.

According to the established flexible heating local heat treatment system, thermocouple 2 is used to detect the temperature of the repaired part, and the oscillating current is adjusted by the intelligent temperature controller to control the heating speed, the holding temperature, the holding time and the cooling time.

The various embodiments in this specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments, and the same and similar parts between the various embodiments can be referred to each other.

The above description of the disclosed embodiments enables any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims (10)

1. The utility model provides a local heat treatment device after large-scale complicated structure spare of aviation titanium alloy is restoreed which characterized in that includes:

the heater is used for heating the repair part of the large-scale complex aviation titanium alloy structural part (4) in a fitting manner;

the temperature sensor is used for detecting the temperature of the repair part of the large-scale complex aviation titanium alloy structural part (4);

and the temperature controller (5) is in communication connection with the heater and the temperature sensor respectively.

2. The post-repair local heat treatment device for large-scale complex aviation titanium alloy structural parts according to claim 1, wherein the heater is a flexible heater (3).

3. The post-repair local heat treatment device for large-scale complex aviation titanium alloy structural components according to claim 2, wherein the flexible heater (3) comprises a crawler-type ceramic heater or a silicon rubber flexible heater.

4. The post-repair local heat treatment device for large-scale complex aviation titanium alloy structural members according to claim 1, wherein the temperature sensor comprises:

the thermocouple (2) is arranged on the surface of the repair part of the large-scale complex aviation titanium alloy structural part (4);

the heater is attached to the surface of the repair part of the large-scale complex aviation titanium alloy structural part (4) and wraps the thermocouple (2).

5. The post-repair local heat treatment device for the large-scale complex aviation titanium alloy structural part according to claim 4, wherein the number of the thermocouples (2) is two, and the thermocouples are a temperature measuring thermocouple and a temperature control thermocouple;

the temperature thermocouple and the temperature thermocouple are arranged on different surfaces of the repaired part of the large complex aviation titanium alloy structural part (4) and are in one-to-one corresponding communication connection with two different interfaces of the temperature controller (5), so that the detection value of the temperature thermocouple is larger than that of the temperature thermocouple.

6. The post-repair local heat treatment device for large-scale complex aviation titanium alloy structural members according to claim 1, further comprising:

and the heat insulation layer is used for wrapping the repair part of the large-scale complex aviation titanium alloy structural part (4) and is positioned on the outer side of the heater.

7. The post-repair local heat treatment device for large-scale complex aviation titanium alloy structural members according to claim 6, wherein the heat-insulating layer comprises an asbestos heat-insulating layer (7).

8. The post-repair local heat treatment device for large-scale complex aviation titanium alloy structural members according to claim 1, further comprising:

and the argon protection box (1) is used for placing the large-scale complex structural part (4) of the aviation titanium alloy, and the heater and the temperature sensor are both positioned in the argon protection box.

9. A local heat treatment method after repairing an aviation titanium alloy large-scale complex structural part is characterized in that the local heat treatment device is adopted for local heat treatment after repairing the aviation titanium alloy large-scale complex structural part according to any one of claims 1 to 8, and the method comprises the following steps:

s1, setting temperature rise time, heat preservation temperature, heat preservation time and cooling time of each stage of local heat treatment through a temperature controller according to the determined heat treatment system after repairing the large-scale complex aviation titanium alloy structural part;

and S2, controlling the operation of the heater through a temperature controller according to the temperature rise time, the heat preservation temperature and the heat preservation time of each stage of the local heat treatment set in the step S1.

10. The method for locally heat treating the repaired large-scale complex aviation titanium alloy structural component according to claim 9, wherein in step S1, the heat treatment schedule for the repaired large-scale complex aviation titanium alloy structural component comprises:

uniformly heating to 600 ℃ in multiple stages according to a preset heating speed, and keeping the temperature for 4 hours; and keeping the temperature for 5min when the temperature is increased to the corresponding preset temperature in each stage.

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