Method for repairing abrasion of inner and outer sealing runway rings of main drive of shield tunneling machine

Abstract

The invention provides a shield tunneling machine main drive inner and outer sealing runway ring abrasion repairing method. The method comprises the steps that a main drive inner sealing runway ring and an outer sealing runway ring are cleaned, and a corrosion layer and a fatigue layer are removed; the deformation conditions of the inner sealing runway ring and the outer sealing runway ring are checked, flaw detection is carried out, and the abrasion depths of the inner sealing runway ring and the outer sealing runway ring and the surface hardness of unabraded positions are measured; carrying out repair welding on the worn parts of the inner sealing runway ring and the outer sealing runway ring by adopting an argon arc welding repair welding process; and after the repair welding part is polished and quenched, detection and acceptance are conducted, and repair is completed. According to the repairing method, it is guaranteed that the hardness cannot be lower than HRC50-55 after repairing, no crack is generated through dye penetrant inspection, and the error between the repaired material and the original size is controlled within 0.05 mm.

Description

Technical Field

[0001] This application relates to the technical field of tunnel ring engineering construction equipment, and particularly to a method for repairing the wear of the inner and outer seal runway rings of the main drive of a shield machine. Background Art

[0002] At present, the main drive seal runway rings of shield machines are all of integral structure. During the tunneling process of the tunnel ring, there is rotational frictional contact between the runway ring and the seal. After long-term operation, the seal contact part of the runway ring wears, and it is necessary to repair the wear of the inner and outer seal runway rings of the main drive of the shield machine. The conventional method is to repair the worn surface by welding, but the current repair work has poor accuracy and is prone to crack damage. Summary of the Invention

[0003] This application aims to solve at least one of the technical problems in the related art to some extent. This application proposes a method for repairing the wear of the inner and outer seal runway rings of the main drive of a shield machine. After repair, the hardness shall not be lower than HRC50 - 55, the coloring flaw detection shall show no cracks, and the error from the original size after repair shall be controlled within 0.05 mm.

[0004] According to the embodiments of this application, a method for repairing the wear of the inner and outer seal runway rings of the main drive of a shield machine is proposed, including the following steps:

[0005] Clean the inner seal runway ring and the outer seal runway ring of the main drive respectively and remove the rust layer and fatigue layer;

[0006] Check the deformation of the inner seal runway ring and the outer seal runway ring and conduct flaw detection, and measure the wear depth and the surface hardness of the non-worn part of the inner seal runway ring and the outer seal runway ring;

[0007] Use the argon arc welding repair process to repair the worn parts of the inner seal runway ring and the outer seal runway ring; among them, the inner seal runway ring uses multi-layer argon arc welding, and the welding parameters of the backing layer are current 120 - 130 A and gas supply speed 8 - 12 L / min; the welding current of other welding layers is greater than that of the backing layer; the outer seal runway ring uses multi-layer argon arc welding, and the parameters of its backing layer are current 130 - 150 A and gas supply speed 8 - 12 L / min; the welding current of other welding layers is greater than that of the backing layer;

[0008] After grinding and quenching the repaired parts, conduct inspection and acceptance to complete the repair.

[0009] In some embodiments, use thousand-leaf blades to grind the worn and rusted parts of the inner seal runway ring and the outer seal runway ring to remove the rust layer and the fatigue layer and expose the metal itself;

[0010] And / or, the flaw detection is dye penetrant inspection, and the inner sealing runway ring and the outer sealing runway ring are polished until there are no dye penetrant inspection coloring points, and then the wear depth and the surface hardness of the unworn part are measured.

[0011] In some embodiments, the pre-welding area of the worn parts of the inner sealing runway ring and the outer sealing runway ring is preheated before welding, and the temperature is 70 - 80°C, and rust and dirt are removed.

[0012] In some embodiments, multi-layer and multi-pass circumferential symmetric welding is adopted for the worn parts of the inner sealing runway ring and the outer sealing runway ring;

[0013] And / or, immediately after one layer of welding is completed, the welding area is hammered for stress relief treatment and heat preservation is done with heat preservation cotton;

[0014] And / or, when welding the next circumferential weld, impurities on the surface of the adjacent weld layer are removed and the weld area is preheated;

[0015] And / or, the height of the weld layer is greater than the unworn parts of the inner sealing runway ring and the outer sealing runway ring.

[0016] In some embodiments, the worn parts of the inner sealing runway ring are welded with argon arc welding wire with a diameter of 1.6 mm;

[0017] And / or, the current of other welding layers except the backing layer is 130 - 150 A.

[0018] In some embodiments, the worn parts of the outer sealing runway ring are welded with argon arc welding wire with a diameter of 2 mm;

[0019] And / or, the current of other welding layers except the backing layer is 150 - 170 A.

[0020] In some embodiments, the repaired welding parts of the inner sealing runway ring and the outer sealing runway ring are ground in multiple steps of thick and thin to ensure the dimensions, roughness, and flatness of the repaired welding parts;

[0021] And / or, after the repaired welding parts are ground, they are heated with a blowtorch and then cooled with water to ensure that the surface hardness is quenched.

[0022] In some embodiments, wind prevention, dust prevention, and waterproofing work are done during welding to ensure that the repair site is clean.

[0023] In some embodiments, after the repaired welding parts are ground and quenched, dye penetrant inspection is carried out to ensure that there are no cracks, no sand holes, no undercut, and no false welding in the repaired welding parts;

[0024] And / or, the dimensions, roughness, flatness, or roundness of the repaired welding parts are detected and accepted to complete the repair.

[0025] In some embodiments, the repaired welding part is smooth and flat, and its roughness is not lower than Ra3.2;

[0026] and / or, 100% dye penetrant inspection is adopted for the repaired welding part, and there are no cracks;

[0027] and / or, the hardness of the repaired welding part is not lower than HRC50 - 55;

[0028] and / or, the surface error between the repaired welding part and the adjacent original sealing runway ring is not greater than 0.05 mm.

[0029] Additional aspects and advantages of the present application will be given in part in the following description, will become apparent in part from the following description, or will be learned through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] The above and / or additional aspects and advantages of the present application will become apparent and easy to understand from the following description of embodiments in conjunction with the drawings, where:

[0031] Figure 1 is a schematic diagram of repairing the worn part of the inner sealing runway ring of the main drive of a shield machine provided in an embodiment of the present application;

[0032] Figure 2 is a schematic diagram of repairing the worn part of the outer sealing runway ring of the main drive of a shield machine provided in an embodiment of the present application. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0033] Embodiments of the present application will be described in detail below. Examples of the embodiments are shown in the drawings, where the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the drawings are exemplary only for explaining the present application and should not be construed as limiting the present application. On the contrary, the present application includes all variations, modifications, and equivalents falling within the spirit and scope of the appended claims.

[0034] The present application is improved based on the defects of the following related technologies. The main drive runway ring of a shield machine plays a crucial role in tunneling operations. First of all, it provides a stable power transmission channel ring to ensure that the shield machine can move forward smoothly and efficiently. Secondly, the design and optimization of the runway ring help to improve the tunneling speed and efficiency of the shield machine, thereby accelerating the construction progress of the tunnel ring. In addition, the main drive runway ring also undertakes the task of supporting the weight of the shield machine to ensure the stability and safety of the shield machine during tunneling.

[0035] Therefore, it is of great significance to repair the worn runway ring and formulate and implement the repair technology for the wear of the main drive runway ring of the shield machine. During the on-site tunneling process of the shield machine, the main reasons for the wear of the main drive runway ring are as follows:

[0036] Wear of the sealing lip: During use, the sealing lip of the main bearing and the sealing bushing rotate and rub against each other for a long time, and a fine groove about 3-5 mm wide will be worn out in the circumferential direction of the bushing (the depth of the groove depends on the running time and the pressure of the external soil bin on the sealing lip during tunneling). The existence of this groove gap will reduce the sealing performance, accelerate the wear of the sealing lip, cause the leakage of the gear oil in the main bearing chamber and the entry of muck, sediment and water, thus leading to the damage of the main bearing rollers, raceway rings and cages.

[0037] Improper adjustment of the sealing bushing: The outer circumferential surface of the sealing bushing contacts the lip of the main bearing seal. If the adjustment is improper, the clearance between the lip and the bushing will not meet the design and use requirements, and the sealing effect will not be ideal. To reduce this kind of wear, it is necessary to change the relative position of the sealing bushing and the lip seal to reduce the harm.

[0038] Insufficient lubrication: Although continuous filling of lubricating grease can reduce wear, when the wear reaches a certain level, it will still cause the leakage of the gear oil in the main bearing chamber and the entry of muck, sediment and water, thus leading to the damage of the main bearing rollers, raceway rings and cages. The conventional method is to repair the worn surface by welding, but the current repair work has poor accuracy and is prone to crack damage.

[0039] Based on this, the technical solution of the embodiment of the present application provides a method for repairing the wear of the inner and outer sealing runway rings of the main drive of the shield machine. The worn parts of the inner and outer first-ring sealing runway rings are welded by argon arc surfacing, polished after welding, and then quenched. After repair, the hardness is guaranteed to be not less than HRC50-55, and there are no cracks detected by dye penetrant inspection. The dimensional error after repair can be controlled within 0.05 mm.

[0040] The "range" disclosed in this application is defined in the form of a lower limit and an upper limit. A given range is defined by selecting a lower limit and an upper limit, and the selected lower limit and upper limit define the boundary of a specific range. The range defined in this way can include or exclude the end values, and can be combined arbitrarily, that is, any lower limit can be combined with any upper limit to form a range. For example, if ranges of 60 - 120 and 80 - 110 are listed for a specific parameter, ranges of 60 - 110 and 80 - 120 are also contemplated. In addition, if the minimum range values 1 and 2 are listed, and if the maximum range values 3, 4, and 5 are listed, then the following ranges are all contemplated: 1 - 3, 1 - 4, 1 - 5, 2 - 3, 2 - 4, and 2 - 5. In this application, unless otherwise stated, the numerical range "a - b" represents an abbreviated representation of any real number combination between a and b, where both a and b are real numbers. For example, the numerical range "0 - 5" means that all real numbers between "0 - 5" are fully listed herein, and "0 - 5" is only an abbreviated representation of these numerical combinations. Additionally, when stating that a certain parameter is an integer ≥ 2, it is equivalent to disclosing that the parameter is, for example, the integers 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, etc.

[0041] In the description of the embodiments of this application, the term "and / or" is merely a description of the association relationship of associated objects, indicating that three relationships can exist. For example, A and / or B can represent: A exists alone, A and B exist simultaneously, and B exists alone. Additionally, in this document, the character " / " generally indicates that the associated objects before and after are in an "or" relationship.

[0042] To achieve the above object, according to the embodiments of this application, a method for repairing the wear of the inner and outer sealing runway rings of the main drive of a shield machine is proposed, including the following steps:

[0043] S1: Clean the inner and outer sealing runway rings of the main drive respectively and remove the rust layer and fatigue layer;

[0044] S2: Check the deformation of the inner and outer sealing runway rings and perform flaw detection, and measure the wear depth of the inner and outer sealing runway rings and the surface hardness of the non-worn parts;

[0045] S3: Use the argon arc welding repair process to repair the worn parts of the inner seal runway ring and the outer seal runway ring; for the inner seal runway ring, use multi-layer argon arc welding. The welding parameters for the backing layer are a current of 120 - 130 A and a gas supply speed of 8 - 12 L / min; the welding current of other welding layers is greater than that of the backing layer. For the outer seal runway ring, use multi-layer argon arc welding. The parameters for the backing layer are a current of 130 - 150 A and a gas supply speed of 8 - 12 L / min; the welding current of other welding layers is greater than that of the backing layer.

[0046] S4: After grinding and quenching the repaired parts, conduct inspection and acceptance to complete the repair.

[0047] In S1, prepare the tools, machinery and materials required for the repair process. Clean the main drive inner seal runway ring and the outer seal runway ring, wipe off impurities such as oil stains on the surface, and use abrasive discs to grind the worn and rusted parts of the main drive inner seal runway ring and the outer seal runway ring respectively to remove the rust layer and fatigue layer, revealing the luster of the metal itself.

[0048] In S2, check whether the main drive inner seal runway ring and the outer seal runway ring are deformed and conduct flaw detection; for the main drive inner seal runway ring and the outer seal runway ring, use penetrant flaw detection, and after grinding the inner seal runway ring and the outer seal runway ring until there are no flaw detection coloring points, measure the wear depth and the surface hardness of the non-worn parts.

[0049] In S3, first do a good job in wind prevention, dust prevention and waterproofing to ensure that the repair site is clean; preheat the pre-welding area of the worn parts of the inner seal runway ring and the outer seal runway ring before welding, with a temperature of 70 - 80 °C, and remove rust and dirt. For example, use a cleaning agent to remove rust and dirt, and then wipe it clean with a clean piece of cloth to achieve rust and dirt removal of the pre-welding area.

[0050] For the worn parts of the inner seal runway ring and the outer seal runway ring respectively, adopt multi-layer and multi-pass circumferential symmetric welding. For example, the method of multi-layer and multi-pass circumferential symmetric welding for the worn parts of the inner seal runway ring is as follows: use an argon arc welding wire with a diameter of 1.6 mm for the worn parts of the inner seal runway ring. The argon arc welding wire is 42CrMo, and use the welding parameters of current: 120 - 130 A; gas supply speed: 8 - 12 L / min to complete the backing layer welding. After the backing layer welding is completed, immediately hammer the welding area for stress relief treatment and use heat preservation cotton for heat preservation. When conducting the next circumferential welding, remove the impurities on the surface of the backing layer weld and preheat the weld area; and use an argon arc welding wire with a diameter of 1.6 mm. The argon arc welding wire is 42CrMo, and use a current greater than that of the backing layer welding, for example, a current of 130 - 150 A, and a gas supply speed of 8 - 12 L / min to complete the second layer welding, and then complete the surfacing according to the method of the second layer welding. The height of the weld layer is greater than that of the non-worn part of the inner seal runway ring, such asFigure 1 As shown, where Figure A is a state diagram of the worn part of the inner seal runway ring without repair, and Figure B is a state diagram of the worn part of the inner seal runway ring after repair.

[0051] For example, the method of symmetrically welding multiple layers and multiple passes on the worn part of the outer seal runway ring is as follows: For the worn part of the outer seal runway ring, use an argon arc welding wire with a diameter of 2 mm. The argon arc welding wire is 42CrMo. Use the welding parameters of current: 130 - 150 A; gas supply speed: 8 - 12 L / min to complete the root pass welding. After the root pass welding is completed, immediately hammer the welding area for stress relief treatment and use heat preservation cotton for heat preservation. When performing the next pass of welding, remove the impurities on the surface of the root pass weld layer and preheat the weld area; and use an argon arc welding wire with a diameter of 2 mm. The argon arc welding wire is 42CrMo. Use a current greater than that of the root pass welding, for example, a current of 150 - 170 A, and a gas supply speed: 8 - 12 L / min to complete the second layer of welding, and then complete the surfacing welding in the same way as the second layer of welding. The height of the weld layer is greater than the non-worn part of the outer seal runway ring, as Figure 2 As shown, where Figure A is a state diagram of the worn part of the outer seal runway ring without repair, and Figure B is a state diagram of the worn part of the outer seal runway ring after repair.

[0052] It should be noted that when using the argon arc welding repair process to repair the worn parts of the inner seal runway ring and the outer seal runway ring, pay attention to preheating before welding and heat preservation after welding to prevent the generation of welding crack defects and ensure the fusion of the surfacing metal and the original base material. The argon arc welding wire is 42CrMo. Using other argon arc welding wires with too low or too high strength, after surfacing with a wire with too low strength, it is difficult to reach the required strength even after quenching treatment, and it is not easy to perform surfacing with a wire with too high strength

[0053] In some embodiments, the repaired parts of the inner seal runway ring and the outer seal runway ring are polished in multiple rough and fine passes to ensure the size, roughness, and flatness of the repaired parts; after the repaired parts are polished, they are heated with a blowtorch and then cooled with water to ensure the surface hardness and complete the quenching treatment.

[0054] Among them, for the repaired parts of the inner seal runway ring and the outer seal runway ring, they are polished manually in multiple rough and fine passes to ensure the size, roughness, and flatness of the repaired parts of the inner seal runway ring and the outer seal runway ring. After the repaired parts are polished, use a mobile trolley to slowly move the blowtorch for heating, and then cool with water to ensure the surface hardness. After the repaired parts are polished and quenched, perform penetrant inspection to ensure that there are no cracks, no sand holes, no undercut, and no false welding in the repaired parts; at the same time, inspect and accept the size, roughness, flatness, or roundness of the repaired parts to complete the repair. In addition, if the repaired parts are not quenched, it is easy to cause low strength of the parts, and it is easy to cause wear of the inner and outer seal runway rings of the main drive of the shield machine during use.

[0055] In some embodiments, the repaired welding part is smooth and flat, and the roughness is not less than Ra3.2; 100% dye penetrant inspection is adopted for the repaired welding part, without cracks, and the hardness of the repaired welding part is not less than HRC50-55; the surface error between the repaired welding part and the adjacent original sealing runway ring is not greater than 0.05 mm, realizing the wear repair of the inner sealing runway ring and the outer sealing runway ring of the main drive of the shield machine.

[0056] This application uses the metal surface additive repair technology, and applies the surfacing method to butt-weld the worn parts of the inner and outer runway rings of the main drive of the shield machine. And non-destructive testing technology, using a roughness meter to detect the surface finish, using dye penetrant inspection to detect the butt-welding quality, and using a portable hardness tester to detect the surface hardness, etc. It not only has low cost, only material cost and labor cost, but also is low-carbon and environmentally friendly, with high safety.

[0057] To facilitate a further understanding of this application, the solutions of this application will be further described below in conjunction with embodiments. Those skilled in the art will understand that only some examples are described in this application, and any other suitable specific examples are within the scope of this application.

[0058] The following embodiments all take the repair of the inner and outer sealing runway rings of the main drive of the shield machine in the following case as an example: Prepare the tools and materials required for the repair process, clean the inner sealing runway ring and the outer sealing runway ring of the main drive, wipe off the oil stains and other impurities on the surface, and use abrasive discs to polish the worn and rusted parts of the inner sealing runway ring and the outer sealing runway ring of the main drive respectively, removing the rust layer and fatigue layer to expose the luster of the metal itself. Check whether the inner sealing runway ring and the outer sealing runway ring of the main drive are deformed, and use dye penetrant inspection. After grinding the inner sealing runway ring and the outer sealing runway ring until there are no dye penetrant coloring points, then measure the wear depth and the surface hardness of the non-worn part. It is found that the first ring (HBW) of the inner sealing runway ring of the main drive is severely worn, with an average wear depth of 0.60 mm, greater than the allowable depth of 0.5 mm, and an average width wear of 2.6 mm. The first ring (HBW) of the outer sealing runway ring is severely worn, with an average wear depth of 0.66 mm, greater than the allowable depth of 0.5 mm, and an average width wear of 3 mm.

[0059] Embodiment 1

[0060] Do a good job in wind prevention, dust prevention and waterproofing to ensure that the repair site is clean; preheat the pre-welding area at 80 °C with a cleaning agent to remove rust before welding the worn parts of the inner sealing runway ring and the outer sealing runway ring, and then wipe it clean with a clean rag.

[0061] For the worn part of the inner sealed runway ring, 42CrMo with a diameter of 1.6 mm is used. The welding parameters for the backing pass welding are: current 130 A; gas supply speed 8 L / min. Immediately after the backing pass welding is completed, the welding area is hammered to relieve stress and insulated with heat preservation cotton. When proceeding with the next ring welding, the impurities on the surface of the backing pass weld layer are removed and the weld area is preheated. Then, 42CrMo with a diameter of 1.6 mm is used, and the welding parameters for the second layer welding are: current 150 A, gas supply speed 8 L / min. The surfacing is completed in the same way as the second layer welding, and the height of the weld layer is greater than the non-worn part of the inner sealed runway ring. The repaired welding area is ground in multiple steps, both thick and thin, to ensure the size, roughness, and flatness of the repaired welding area. After grinding the repaired welding area, it is heated with a blowtorch and then cooled with water to complete the quenching treatment to ensure the surface hardness. During repair welding, pay attention to preheating before welding and heat preservation after welding to prevent the generation of welding crack defects, ensure the fusion of the surfacing metal and the original base metal, make the repaired welding area smooth and flat, with a roughness not lower than Ra3.2; the repaired welding area is inspected by 100% dye penetrant inspection, without cracks, and the hardness of the repaired welding area is not lower than HRC50 - 55; the surface error between the repaired welding area and the adjacent original sealed runway ring is not greater than 0.05 mm.

[0062] For the worn part of the outer sealed runway ring, argon arc welding wire with a diameter of 2 mm is used, and the argon arc welding wire is 42CrMo. The welding parameters for the backing pass welding are: current 130 A; gas supply speed 12 L / min. Immediately after the backing pass welding is completed, the welding area is hammered to relieve stress and insulated with heat preservation cotton. When proceeding with the next ring welding, the impurities on the surface of the backing pass weld layer are removed and the weld area is preheated. Then, argon arc welding wire with a diameter of 2 mm, where the argon arc welding wire is 42CrMo, and with a current greater than that of the backing pass welding, for example, current 150 A, gas supply speed 12 L / min, is used to complete the second layer welding. Then, the surfacing is completed in the same way as the second layer welding, and the height of the weld layer is greater than the non-worn part of the outer sealed runway ring. The repaired welding area is ground in multiple steps, both thick and thin, to ensure the size, roughness, and flatness of the repaired welding area. After grinding the repaired welding area, it is heated with a blowtorch and then cooled with water to complete the quenching treatment to ensure the surface hardness. During repair welding, pay attention to preheating before welding and heat preservation after welding to prevent the generation of welding crack defects, ensure the fusion of the surfacing metal and the original base metal, make the repaired welding area smooth and flat, with a roughness not lower than Ra3.2; the repaired welding area is inspected by 100% dye penetrant inspection, without cracks, and the hardness of the repaired welding area is not lower than HRC50 - 55; the surface error between the repaired welding area and the adjacent original sealed runway ring is not greater than 0.05 mm.

[0063] Example 2

[0064] Do a good job in wind prevention, dust prevention and waterproofing to ensure the cleanliness of the repair site; preheat the pre-welding area at 80°C, remove rust with a cleaning agent, and then wipe it clean with a clean rag at the worn parts of the inner and outer sealed runway rings before welding.

[0065] For the worn parts of the inner sealed runway ring, use 42CrMo with a diameter of 1.6mm, adopt the welding parameters of current: 125A; gas supply speed: 12L / min to complete the root pass welding. Immediately after the root pass welding is completed, hammer the welding area for stress relief treatment and use heat preservation cotton for heat preservation. When performing the next ring welding, remove the impurities on the surface of the root pass weld layer and preheat the weld seam; and use 42CrMo with a diameter of 1.6mm, adopt a current of 140A, and a gas supply speed of 12L / min for welding parameters to complete the second layer welding, and then complete the surfacing welding in the same way as the second layer welding. The height of the weld layer is greater than the non-worn part of the inner sealed runway ring. The repaired welding area is ground in multiple steps of thick and thin to ensure the size, roughness and flatness of the repaired welding area; after grinding the repaired welding area, heat it with a torch and then cool it with water to ensure the surface hardness to complete the quenching treatment. Pay attention to preheating before welding and heat preservation after welding during repair welding to prevent the generation of welding crack defects, ensure the fusion of the surfacing metal and the original base metal, the repaired welding area is smooth and flat, and the roughness is not less than Ra3.2; the repaired welding area is inspected by 100% dye penetrant inspection, without cracks, the hardness of the repaired welding area is not less than HRC50-55; the surface error between the repaired welding area and the adjacent original sealed runway ring is not more than 0.05mm.

[0066] For the worn parts of the outer sealed runway ring, use an argon arc welding wire with a diameter of 2mm, and the argon arc welding wire is 42CrMo. Adopt the welding parameters of current: 130A; gas supply speed: 9L / min to complete the root pass welding. Immediately after the root pass welding is completed, hammer the welding area for stress relief treatment and use heat preservation cotton for heat preservation. When performing the next ring welding, remove the impurities on the surface of the root pass weld layer and preheat the weld seam; and use an argon arc welding wire with a diameter of 2mm, and the argon arc welding wire is 42CrMo. Adopt a current greater than the current of the root pass welding, for example, a current of 170A, and a gas supply speed of 10L / min for welding parameters to complete the second layer welding, and then complete the surfacing welding in the same way as the second layer welding. The height of the weld layer is greater than the non-worn part of the outer sealed runway ring. The repaired welding area is ground in multiple steps of thick and thin to ensure the size, roughness and flatness of the repaired welding area; after grinding the repaired welding area, heat it with a torch and then cool it with water to ensure the surface hardness to complete the quenching treatment. Pay attention to preheating before welding and heat preservation after welding during repair welding to prevent the generation of welding crack defects, ensure the fusion of the surfacing metal and the original base metal, the repaired welding area is smooth and flat, and the roughness is not less than Ra3.2; the repaired welding area is inspected by 100% dye penetrant inspection, without cracks, the hardness of the repaired welding area is not less than HRC50-55; the surface error between the repaired welding area and the adjacent original sealed runway ring is not more than 0.05mm.

[0067] Example 3

[0068] Do a good job in wind prevention, dust prevention and waterproofing to ensure the cleanliness of the repair site; preheat the pre-welding area at a temperature of 80°C and remove rust with a cleaning agent before welding the worn parts of the inner sealing runway ring and the outer sealing runway ring, and then wipe it clean with a clean rag.

[0069] For the worn part of the inner sealing runway ring, 42CrMo with a diameter of 1.6 mm is used, and the welding parameters of current: 130 A; gas supply speed: 12 L / min are adopted to complete the root pass welding. After the root pass welding is completed, immediately hammer the welding area for stress relief treatment and use heat preservation cotton for heat preservation. When performing the next ring welding, remove the impurities on the surface of the root pass weld layer and preheat the weld seam; and adopt 42CrMo with a diameter of 1.6 mm, with a current of 150 A and a gas supply speed of 11 L / min to complete the second layer welding, and then complete the surfacing welding in the same way as the second layer welding. The height of the weld layer is greater than the non-worn part of the inner sealing runway ring. The repaired welding part is polished in multiple times of thick and thin to ensure the size, roughness and flatness of the repaired welding part; after the repaired welding part is polished, it is heated with a blowtorch and then cooled with water to ensure the surface hardness to complete the quenching treatment. Pay attention to preheating before welding and heat preservation after welding during repair welding to prevent the generation of welding crack defects, ensure the fusion of the surfacing metal and the original base metal, the repaired welding part is smooth and flat, and the roughness is not less than Ra3.2; the repaired welding part is inspected by 100% dye penetrant inspection, without cracks, the hardness of the repaired welding part is not less than HRC50-55; the surface error between the repaired welding part and the adjacent original sealing runway ring is not greater than 0.05 mm.

[0070] For the worn part of the outer seal runway ring, an argon arc welding wire with a diameter of 2 mm is used. The argon arc welding wire is 42CrMo. The root pass welding is completed with the welding parameters of current: 140 A; gas supply speed: 11 L / min. Immediately after the root pass welding, the welding area is hammered for stress relief treatment and insulated with heat preservation cotton. When performing the next ring welding, the impurities on the surface of the root pass weld layer are removed and the weld seam is preheated. And an argon arc welding wire with a diameter of 2 mm is used. The argon arc welding wire is 42CrMo. The current is greater than that of the root pass welding, for example, the current is 160 A, and the gas supply speed: 12 L / min. The second layer welding is completed with these welding parameters, and then the surfacing is completed in the same way as the second layer welding. The height of the weld layer is greater than the non-worn part of the outer seal runway ring. The repaired welding area is ground in multiple times with different fineness to ensure the dimensions, roughness and flatness of the repaired welding area. After grinding the repaired welding area, it is heated with a blowtorch and then cooled with water to ensure the surface hardness and complete the quenching treatment. During the repair welding, pay attention to preheating before welding and heat preservation after welding to prevent the generation of welding crack defects, ensure the fusion of the surfacing metal and the original base metal, the repaired welding area is smooth and flat, and the roughness is not less than Ra3.2; the repaired welding area is inspected by 100% dye penetrant inspection, without cracks, and the hardness of the repaired welding area is not less than HRC50-55; the surface error between the repaired welding area and the adjacent original seal runway ring is not more than 0.05 mm.

[0071] Example 4

[0072] Do a good job in wind prevention, dust prevention and waterproofing to ensure the cleanliness of the repair site; before welding the worn parts of the inner seal runway ring and the outer seal runway ring, preheat the pre-welding area to a temperature of 80 °C, remove rust with a cleaning agent, and then wipe it clean with a clean piece of cloth.

[0073] For the worn part of the inner sealed runway ring, 42CrMo with a diameter of 1.6 mm is used. The root pass welding is completed with the welding parameters of current: 120 A; gas supply speed: 12 L / min. Immediately after the root pass welding is completed, the welding area is hammered for stress relief treatment and heat preservation is done with heat preservation cotton. When proceeding with the next ring welding, the impurities on the surface of the root pass weld layer are removed and the weld seam is preheated; and 42CrMo with a diameter of 1.6 mm is used. The second layer welding is completed with the welding parameters of current: 150 A, gas supply speed: 12 L / min, and then surfacing is completed in the same way as the second layer welding. The height of the weld layer is greater than the non-worn part of the inner sealed runway ring. The repaired welding part is ground in multiple steps, thick and thin, to ensure the dimensions, roughness, and flatness of the repaired welding part; after the repaired welding part is ground, it is heated with a torch and then cooled with water to ensure the surface hardness for quenching treatment. During repair welding, pay attention to preheating before welding and heat preservation after welding to prevent the generation of welding crack defects, ensure the fusion of the surfacing metal and the original base metal, the repaired welding part is smooth and flat, and the roughness is not less than Ra3.2; the repaired welding part is inspected by 100% dye penetrant inspection, without cracks, the hardness of the repaired welding part is not less than HRC50 - 55; the surface error between the repaired welding part and the adjacent original sealed runway ring is not more than 0.05 mm.

[0074] For the worn part of the outer sealed runway ring, an argon arc welding wire with a diameter of 2 mm is used, and the argon arc welding wire is 42CrMo. The root pass welding is completed with the welding parameters of current: 145 A; gas supply speed: 12 L / min. Immediately after the root pass welding is completed, the welding area is hammered for stress relief treatment and heat preservation is done with heat preservation cotton. When proceeding with the next ring welding, the impurities on the surface of the root pass weld layer are removed and the weld seam is preheated; and an argon arc welding wire with a diameter of 2 mm is used, and the argon arc welding wire is 42CrMo. The second layer welding is completed with the welding parameters of current greater than that of the root pass welding, for example, current: 165 A, gas supply speed: 11 L / min, and then surfacing is completed in the same way as the second layer welding. The height of the weld layer is greater than the non-worn part of the outer sealed runway ring. The repaired welding part is ground in multiple steps, thick and thin, to ensure the dimensions, roughness, and flatness of the repaired welding part; after the repaired welding part is ground, it is heated with a torch and then cooled with water to ensure the surface hardness for quenching treatment. During repair welding, pay attention to preheating before welding and heat preservation after welding to prevent the generation of welding crack defects, ensure the fusion of the surfacing metal and the original base metal, the repaired welding part is smooth and flat, and the roughness is not less than Ra3.2; the repaired welding part is inspected by 100% dye penetrant inspection, without cracks, the hardness of the repaired welding part is not less than HRC50 - 55; the surface error between the repaired welding part and the adjacent original sealed runway ring is not more than 0.05 mm.

[0075] Comparative Example 1

[0076] Do a good job in wind prevention, dust prevention and waterproofing to ensure the cleanliness of the repair site; preheat the pre-welding area at 80°C, remove rust with a cleaning agent, and then wipe it clean with a clean rag at the worn parts of the inner sealing runway ring and the outer sealing runway ring before welding.

[0077] For the worn parts of the inner sealing runway ring, use ER80S-D2 with a diameter of 1.6 mm, and complete the root pass welding with the welding parameters of current: 130 A; gas supply speed: 10 L / min. Immediately after the root pass welding is completed, hammer the welding area for stress relief treatment and use heat preservation cotton for heat preservation. When performing the next ring welding, remove the impurities on the surface of the root pass weld layer and preheat the weld seam; and use ER80S-D2 with a diameter of 1.6 mm, with a current of 130 A and a gas supply speed of 12 L / min to complete the second layer welding, and then complete the surfacing welding in the same way as the second layer welding. The height of the weld layer is greater than the non-worn part of the inner sealing runway ring. The repaired welding area is polished in multiple steps, thick and thin, to ensure the size, roughness and flatness of the repaired welding area; after the repaired welding area is polished, it is heated with a torch and then cooled with water to ensure the surface hardness and complete the quenching treatment. Pay attention to preheating before welding and heat preservation after welding during repair welding to prevent the generation of welding crack defects, ensure the fusion of the surfacing metal and the original base metal, the repaired welding area is smooth and flat, and the roughness is not less than Ra3.2; the repaired welding area is inspected by 100% dye penetrant inspection, without cracks, and the hardness of the repaired welding area is not less than HRC50-55; the surface error between the repaired welding area and the adjacent original sealing runway ring is not greater than 0.05 mm.

[0078] For the worn parts of the outer sealing runway ring, use an argon arc welding wire with a diameter of 2 mm, where the argon arc welding wire is ER80S-D2, and complete the root pass welding with the welding parameters of current: 140 A; gas supply speed: 11 L / min. Immediately after the root pass welding is completed, hammer the welding area for stress relief treatment and use heat preservation cotton for heat preservation. When performing the next ring welding, remove the impurities on the surface of the root pass weld layer and preheat the weld seam; and use an argon arc welding wire with a diameter of 2 mm, where the argon arc welding wire is ER80S-D2, with a current greater than that of the root pass welding, for example, the current is 155 A and the gas supply speed is 12 L / min to complete the second layer welding, and then complete the surfacing welding in the same way as the second layer welding. The height of the weld layer is greater than the non-worn part of the outer sealing runway ring. The repaired welding area is polished in multiple steps, thick and thin, to ensure the size, roughness and flatness of the repaired welding area; after the repaired welding area is polished, it is heated with a torch and then cooled with water to ensure the surface hardness and complete the quenching treatment. However, in this comparative example, the strength of the outer sealing runway ring and the inner sealing runway ring after welding is relatively low, and even after quenching, the strength is still low and the wear is relatively fast during on-site use.

[0079] Comparative Example 2

[0080] Do a good job in wind prevention, dust prevention and waterproofing to ensure the cleanliness of the repair site; preheat the pre-welding area of the worn parts of the inner sealing runway ring and the outer sealing runway ring before welding, with a temperature of 80°C, remove rust with a cleaning agent, and then wipe it clean with a clean rag.

[0081] For the worn parts of the inner sealing runway ring, use 42CrMo with a diameter of 1.6 mm, and complete the root pass welding with welding parameters of current: 125 A; gas supply speed: 9 L / min. Immediately after the root pass welding is completed, hammer the welding area for stress relief treatment and use heat preservation cotton for heat preservation. When performing the next ring welding, remove the impurities on the surface of the root pass weld layer and preheat the weld seam; and use 42CrMo with a diameter of 1.6 mm, with a current of 135 A and a gas supply speed of 8 L / min to complete the second layer welding, and then complete the surfacing welding in the same way as the second layer welding, with the weld layer height greater than the non-worn part of the inner sealing runway ring. The repaired welding area is polished in multiple steps, thick and thin, to ensure the dimensions, roughness and flatness of the repaired welding area; after the repaired welding area is polished, it is heated with a blowtorch and then cooled with water to ensure the surface hardness and complete the quenching treatment. Pay attention to preheating before welding and heat preservation after welding during repair welding to prevent the generation of welding crack defects, ensure the fusion of the surfacing metal and the original base metal, the repaired welding area is smooth and flat, and the roughness is not less than Ra3.2; the repaired welding area is inspected by 100% penetrant testing, without cracks, and the hardness of the repaired welding area is not less than HRC50-55; the surface error between the repaired welding area and the adjacent original sealing runway ring is not more than 0.05 mm.

[0082] For the worn parts of the outer sealing runway ring, use an argon arc welding wire with a diameter of 2 mm, and the argon arc welding wire is 42CrMo. Complete the root pass welding with welding parameters of current: 140 A; gas supply speed: 11 L / min. Immediately after the root pass welding is completed, hammer the welding area for stress relief treatment and use heat preservation cotton for heat preservation. When performing the next ring welding, remove the impurities on the surface of the root pass weld layer and preheat the weld seam; and use an argon arc welding wire with a diameter of 2 mm, and the argon arc welding wire is 42CrMo, with a current greater than that of the root pass welding, for example, the current is 160 A and the gas supply speed is 9 L / min to complete the second layer welding, and then complete the surfacing welding in the same way as the second layer welding, with the weld layer height greater than the non-worn part of the outer sealing runway ring. The repaired welding area is polished in multiple steps, thick and thin, to ensure the dimensions, roughness and flatness of the repaired welding area; after the repaired welding area is polished, it is cooled with water to ensure the surface hardness and complete the quenching treatment. However, in this comparative example, the strength of the outer sealing runway ring and the inner sealing runway ring is relatively low after welding, and even the strength is still low after quenching, and the wear is relatively fast during on-site use.

[0083] In the description of this specification, the description with reference to terms such as "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of this application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0084] Although the embodiments of this application have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting this application. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of this application.

Claims

1. Method for repairing wear of inner and outer sealing runway rings of main drive of shield machine, characterized in that, The steps are as follows: Clean the main drive inner seal runway ring and the outer seal runway ring respectively, and remove the rust layer and fatigue layer; Check the deformation of the inner seal runway ring and the outer seal runway ring and perform flaw detection, and measure the wear depth of the inner seal runway ring and the outer seal runway ring and the surface hardness of the non-worn part; Use the argon arc welding repair process to repair the worn parts of the inner seal runway ring and the outer seal runway ring; among them, the inner seal runway ring is welded by multi-layer argon arc welding, and the welding parameters of the backing layer are current 120-130A, gas supply speed 8-12L / min; the welding current of other welding layers is greater than that of the backing layer; the outer seal runway ring is welded by multi-layer argon arc welding, and the parameters of its backing layer are current 130-150A, gas supply speed 8-12L / min; the welding current of other welding layers is greater than that of the backing layer; After grinding and quenching the repaired part, conduct inspection and acceptance to complete the repair.

2. The repair method according to claim 1, wherein Use a thousand-leaf blade to grind the worn and rusted parts of the inner seal runway ring and the outer seal runway ring to remove the rust layer and the fatigue layer and expose the metal itself; And / or, the flaw detection is dye penetrant inspection, and the inner seal runway ring and the outer seal runway ring are ground until there is no dye penetrant coloring point, and then the wear depth and the surface hardness of the non-worn part are measured.

3. The repair method according to claim 1, wherein Preheat the pre-welding area of the worn parts of the inner seal runway ring and the outer seal runway ring before welding, the temperature is 70-80°C and remove rust and dirt.

4. The repair method according to any one of claims 1 to 3, characterized in that The worn parts of the inner seal runway ring and the outer seal runway ring adopt multi-layer and multi-pass ring symmetric welding; And / or, immediately hammer the welded area after one layer of welding to perform stress relief treatment and use heat preservation cotton for heat preservation; And / or, remove the impurities on the surface of the adjacent weld layer and preheat the weld area when welding the next ring; And / or, the height of the weld layer is greater than the non-worn parts of the inner seal runway ring and the outer seal runway ring.

5. The repair method according to claim 4, characterized in that, The worn parts of the inner seal runway ring adopt an argon arc welding wire with a diameter of 1.6mm for welding; And / or, the current of other welding layers except the backing layer is 130-150A.

6. The repair method according to claim 4, characterized in that, The worn parts of the outer seal runway ring adopt an argon arc welding wire with a diameter of 2mm for welding; And / or, the current of other welding layers except the backing layer is 150-170A.

7. The repair method according to claim 4, characterized in that The repaired parts of the inner seal runway ring and the outer seal runway ring are ground in multiple times with different fineness to ensure the size, roughness and flatness of the repaired parts; And / or, after grinding the repaired part, heat it with a blowtorch and then cool it with water to ensure the surface hardness to complete the quenching treatment.

8. The repair method according to claim 4, wherein Do a good job in wind prevention, dust prevention and waterproofing during welding to ensure that the repair site is clean.

9. The repair method according to claim 4, characterized in that After grinding and quenching the repaired part, perform dye penetrant inspection to ensure that there are no cracks, no sand holes, no undercut and no false welding in the repaired part; And / or, conduct inspection and acceptance on the size, roughness, flatness or roundness of the repaired part to complete the repair.

10. The repair method according to claim 4, characterized in that, The repaired part is smooth and flat, and the roughness is not less than Ra3.2; And / or, the repaired part adopts 100% dye penetrant inspection and has no cracks; And / or, the hardness of the repaired welding area is not less than HRC50 - 55; And / or, the surface error between the repaired welding area and the adjacent original sealing runway ring is not greater than 0.05 mm.

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