CN112813431A - Laser repair process for rotor disc of gas turbine - Google Patents
Laser repair process for rotor disc of gas turbine Download PDFInfo
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- CN112813431A CN112813431A CN202011593371.7A CN202011593371A CN112813431A CN 112813431 A CN112813431 A CN 112813431A CN 202011593371 A CN202011593371 A CN 202011593371A CN 112813431 A CN112813431 A CN 112813431A
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
- C23C24/103—Coating with metallic material, i.e. metals or metal alloys, optionally comprising hard particles, e.g. oxides, carbides or nitrides
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Laser Beam Processing (AREA)
Abstract
The invention discloses a laser repair process for a rotor disc of a gas turbine, which comprises the following steps: the method comprises the steps of positioning, cleaning, detecting, polishing, secondary detecting, repairing and final detecting, wherein before repairing work begins, a rotor wheel disc needs to be fixed, the center of a rotor is enabled to be 1590mm away from the ground, then a repairing process flow is carried out, laser cladding powder is adopted in the repairing process to repair a damaged position, the proportioned cladding powder covers the damaged position, laser cladding is carried out, layer-by-layer cladding is adopted, after cladding, a surface oxide layer needs to be cleaned, next layer cladding is carried out after determining no defect, burning marks, undercut and overlap joint need to be controlled to be displayed in place in the cladding process, each section of overlap joint dislocation with the boundary is controlled within 1mm, and if the problems occur, re-cladding is needed. The invention fully detects and analyzes damage repair, and ensures that the hardness can reach the specified use requirement by matching metal powder close to the hardness of the base metal.
Description
Technical Field
The invention relates to the technical field of mechanical repair, in particular to a laser repair process for a rotor disc of a gas turbine.
Background
Along with the continuous development of the number of domestic gas turbines, the industries applying the gas turbines are more and more, the problems of defect and fault treatment are increased, and the phenomenon that a wheel disc of the gas turbine is damaged or corroded sometimes occurs.
After massive search, the prior art is found, the publication number is CN110482253A, and a sprocket disc repairing method is disclosed, and belongs to the field of machining. When the to-be-repaired chain wheel disc is repaired, the first repairing ring and the second repairing ring can be coaxially spot-welded on the inner wall of the cylinder body of the to-be-repaired chain wheel disc, the first repairing ring and the second repairing ring are located on two sides of the annular groove, the first repairing ring, the second repairing ring, the cylinder body and the sealing plate are welded, after the first repairing ring and the second repairing ring are welded on the cylinder body, the inner diameters of the first repairing ring and the second repairing ring are smaller than that of the cylinder body, and the repairing device can be applied to the environment where the to-be-repaired chain wheel disc needs to be used. The groove between the first repairing ring and the second repairing ring is welded to be full, the original annular groove on the inner wall of the cylinder body between the first repairing ring and the second repairing ring is welded to be full, and finally the repairing annular groove coaxial with the cylinder body is machined on the welding line between the first repairing ring and the second repairing ring, so that the inner diameter of the chain wheel disc to be repaired and the use requirement of the annular groove are met.
In conclusion, at present, the pit repairing work for the bottom of the dovetail groove of the wheel disc is lacked in China, the process difficulty is high, most of the pits are transported to foreign countries for maintenance when the pits need to be replaced, the transportation time is long, the maintenance cost is high, or the pits are directly replaced, the needed fund is high, and therefore the technology for repairing the wheel disc of the gas turbine is also deficient.
Disclosure of Invention
The invention aims to provide a laser repair process for a rotor disc of a gas turbine, which aims to solve the problems in the background technology.
In order to achieve the purpose, the invention provides the following technical scheme: a laser repair process for a gas turbine rotor disc comprises the following steps: the method comprises the following steps of positioning, cleaning, detecting, polishing, secondary detecting, repairing and final detecting, wherein before the repairing work is started, a rotor wheel disc needs to be fixed, the center of a rotor is 1590mm away from the ground, then the repairing process flow is carried out, and laser cladding powder is adopted in the repairing process to repair the damaged position.
Preferably, the rotor disc is packaged, lifted and positioned in the positioning stage, and the part which does not need to be repaired is covered, so that additional damage is avoided;
the rotor disc is positioned and kept stable, so that the subsequent repair operation is facilitated, and the influence on the actual operation due to shaking is avoided.
Preferably, the cleaning stage is used for cleaning the damaged position, cleaning oil dirt and other dirt at the damaged position until the metal luster is exposed, and marking the repaired part;
and in the cleaning stage, a brush and a detergent are adopted, the detergent is soaked in advance, after the soaking is carried out for 15min, workers brush the damaged position by using the brush until the metal presents the color, and mark the damaged position by using a mark pen.
Preferably, the detection stage is used for carrying out coloring nondestructive detection, material detection and hardness detection on the dovetail groove;
in the coloring nondestructive testing, the coloring agent is smeared at the damaged position, the position is kept stand for 2 hours, the smeared position is washed, the coloring agent is washed away, the developer is smeared at the damaged position after the water stain is completely eliminated, the gap penetrated by the coloring agent can be visually observed, and the visualization is more realized;
the material quality detection adopts a spectrum analyzer to carry out proportion of wood metal and nonmetal elements of a raw material worker so as to prepare cladding powder in a repair stage;
and the hardness detection adopts a hardness detector to detect the hardness of the material at the damaged position.
And in the polishing stage, the damage position confirmed by the mark is manually polished, the fatigue layer is removed until the root, the polishing surface is kept smooth in the polishing process, and other positions are protected to avoid causing additional damage.
Preferably, after the polishing stage is completed in the secondary detection stage, the damage position is detected again by adopting coloring detection and hardness detection, and whether the polishing depth reaches the root of the damaged gap can be judged;
and detecting and recording the processed size of the damaged part so as to control the thickness of the repair layer.
Preferably, in the repairing stage, metal powder with hardness close to that of the base metal is configured according to the ratio of the original base metal to the nonmetal elements measured in the detecting stage, and meanwhile, wear-resistant and high-temperature-resistant materials are added, the proportioned metal powder needs to be tested, and the test result meets the hardness requirement measured in the detecting stage;
covering the proportioned cladding powder at the damaged position, carrying out laser cladding, adopting layer-by-layer cladding, cleaning a surface oxide layer after cladding, carrying out next-layer cladding after determining no defect, controlling the appearance of burning marks, undercut and lap joints in the cladding process, controlling the overlap joint dislocation of each section and the boundary within 1mm, and carrying out re-cladding if the problems occur;
the height of laser cladding needs to be 0.5-0.8 mm higher than the surface of the matrix, the machining allowance is ensured, polishing is carried out until the surface has reflection, and dimension detection and dye check detection are carried out.
Preferably, if the cladding defect exists, the cladding layer needs to be completely cleaned, the cladding layer is completely worn away, the cladding layer is cleaned again for flaw detection, and the cladding repair operation is carried out again after the cladding layer is free of defects.
And in the final detection stage, red lead side view is carried out on the damage position after cladding and grinding are finished, high points are finely ground on the ground oilstone, and repeated operation is carried out until the red lead test eliminates the high points, so that the polished repair surface, the maintenance surface and the undamaged surface are kept parallel.
Compared with the prior art, the invention has the beneficial effects that: the invention appoints a perfect repair scheme aiming at the particularity of the rotor wheel disc, comprehensively detects the damaged part, can intuitively know the depth and the degree of the damage through coloring detection, hardness detection and material detection, can facilitate the configuration of cladding powder through the material detection and the hardness detection, reduces the difference between the components and the hardness of the cladding powder and the base material quality, improves the degree of fit, ensures the subsequent normal use and fills the gap of the domestic technology.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front", "rear", "both ends", "one end", "the other end", and the like indicate orientations or positional relationships only for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "connected," and the like are to be construed broadly, such as "connected," which may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The invention provides two embodiments:
the first embodiment is as follows:
a laser repair process for a gas turbine rotor disc comprises the following steps: the method comprises the following steps of positioning, cleaning, detecting, polishing, secondary detecting, repairing and final detecting, wherein before the repairing work is started, a rotor wheel disc needs to be fixed, the center distance of a rotor is 1590mm from the ground, then the repairing process flow is carried out, laser cladding powder is adopted in the repairing process, and the damaged position is repaired.
In the positioning stage, the rotor wheel disc is packaged, lifted and positioned, and the part which does not need to be repaired is covered, so that additional damage is avoided;
the rotor disc is positioned and kept stable, so that the subsequent repair operation is facilitated, and the influence on the actual operation due to shaking is avoided.
Example two:
the repair process flow is as follows:
cleaning the damaged position in a cleaning stage, cleaning oil dirt and other dirt at the damaged position until the metal luster is exposed, and marking the repaired part;
and in the cleaning stage, a brush and a detergent are adopted, the detergent is soaked in advance, after soaking for 15min, workers brush the damaged position by using the brush until the color of the metal is presented, and mark the damaged position by using a mark pen.
In the detection stage, the dovetail groove is subjected to coloring nondestructive detection, material detection and hardness detection;
in the coloring nondestructive testing, the coloring agent is smeared at the damaged position, the position is kept stand for 2h, the smeared position is washed, the coloring agent is washed away, the developer is smeared at the damaged position after the water stain is completely eliminated, the gap penetrated by the coloring agent can be visually observed, and the visualization is more realized;
the material quality detection adopts a spectrum analyzer to compare the wood metal and nonmetal elements of the raw material workers so as to prepare the cladding powder in the repair stage;
and the hardness detection adopts a hardness detector to detect the hardness of the material at the damaged position.
And in the polishing stage, the damage position confirmed by the mark is manually polished, the fatigue layer is removed until the root, the polishing surface is kept smooth in the polishing process, and other positions are protected to avoid causing additional damage.
In the secondary detection stage, after the polishing stage is finished, the damage position is detected again by adopting coloring detection and hardness detection, and whether the polishing depth reaches the root of the damaged gap can be judged;
and detecting and recording the processed size of the damaged part so as to control the thickness of the repair layer.
In the repairing stage, metal powder with hardness close to that of the base metal is prepared according to the ratio of the original base metal to the nonmetal elements measured in the detecting stage, meanwhile, wear-resistant and high-temperature-resistant materials are added, the proportioned metal powder needs to be tested, and the test result meets the hardness requirement measured in the detecting stage;
covering the proportioned cladding powder at the damaged position, carrying out laser cladding, adopting layer-by-layer cladding, cleaning a surface oxide layer after cladding, carrying out next-layer cladding after determining no defect, controlling the appearance of burning marks, undercut and lap joints in the cladding process, controlling the overlap joint dislocation of each section and the boundary within 1mm, and carrying out re-cladding if the problems occur;
the height of laser cladding needs to be 0.5-0.8 mm higher than the surface of the matrix, the machining allowance is ensured, polishing is carried out until the surface has reflection, and dimension detection and dye check detection are carried out.
If the cladding defect exists, the cladding layer needs to be completely cleaned, the cladding layer is completely worn away, the cladding layer is cleaned again for flaw detection, and the cladding repair operation is carried out again after the cladding layer is free of defects.
And in the final detection stage, red lead side view is carried out on the damaged position after cladding and grinding are finished, high points are finely ground on the ground oilstone, and repeated operation is carried out until the red lead test eliminates the high points, so that the polished repair surface, the maintenance surface and the undamaged surface are kept parallel.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.
Claims (8)
1. A laser repair process for a gas turbine rotor disc is characterized by comprising the following steps: the repair process flow comprises the following steps: the method comprises the following steps of positioning, cleaning, detecting, polishing, secondary detecting, repairing and final detecting, wherein before the repairing work is started, a rotor wheel disc needs to be fixed, the center of a rotor is 1590mm away from the ground, then the repairing process flow is carried out, and laser cladding powder is adopted in the repairing process to repair the damaged position.
2. The laser repair process for a gas turbine rotor disk according to claim 1, wherein: in the positioning stage, the rotor wheel disc is packaged, lifted and positioned, and the part which does not need to be repaired is covered, so that additional damage is avoided;
the rotor disc is positioned and kept stable, so that the subsequent repair operation is facilitated, and the influence on the actual operation due to shaking is avoided.
3. The laser repair process for a gas turbine rotor disk according to claim 1, wherein: in the cleaning stage, the damaged position is cleaned, oil dirt and other dirt at the damaged position are cleaned until the metallic luster is exposed, and the repaired part is marked;
and in the cleaning stage, a brush and a detergent are adopted, the detergent is soaked in advance, after the soaking is carried out for 15min, workers brush the damaged position by using the brush until the metal presents the color, and mark the damaged position by using a mark pen.
4. The laser repair process for a gas turbine rotor disk according to claim 1, wherein: in the detection stage, the dovetail groove is subjected to coloring nondestructive detection, material detection and hardness detection;
in the coloring nondestructive testing, the coloring agent is smeared at the damaged position, the position is kept stand for 2 hours, the smeared position is washed, the coloring agent is washed away, the developer is smeared at the damaged position after the water stain is completely eliminated, the gap penetrated by the coloring agent can be visually observed, and the visualization is more realized;
the material quality detection adopts a spectrum analyzer to carry out proportion of wood metal and nonmetal elements of a raw material worker so as to prepare cladding powder in a repair stage;
and the hardness detection adopts a hardness detector to detect the hardness of the material at the damaged position.
5. The laser repair process for a gas turbine rotor disk according to claim 1, wherein: and in the polishing stage, the damage position confirmed by the mark is manually polished, the fatigue layer is removed until the root, the polishing surface is kept smooth in the polishing process, and other positions are protected to avoid causing additional damage.
6. The laser repair process for a gas turbine rotor disk according to claim 1, wherein: after the polishing stage is finished in the secondary detection stage, the damage position is detected again by adopting coloring detection and hardness detection, and whether the polishing depth reaches the root of the damaged gap can be judged;
and detecting and recording the processed size of the damaged part so as to control the thickness of the repair layer.
7. The laser repair process for a gas turbine rotor disk according to claim 1, wherein: in the repairing stage, metal powder with hardness close to that of the base metal is configured according to the ratio of the original base metal to the nonmetal elements measured in the detecting stage, meanwhile, wear-resistant and high-temperature-resistant materials are added, the proportioned metal powder needs to be tested, and the test result needs to meet the hardness requirement measured in the detecting stage;
covering the proportioned cladding powder at the damaged position, carrying out laser cladding, adopting layer-by-layer cladding, cleaning a surface oxide layer after cladding, carrying out next-layer cladding after determining no defect, controlling the appearance of burning marks, undercut and lap joints in the cladding process, controlling the overlap joint dislocation of each section and the boundary within 1mm, and carrying out re-cladding if the problems occur;
the height of laser cladding needs to be 0.5-0.8 mm higher than the surface of the matrix, the machining allowance is ensured, polishing is carried out until the surface has reflection, and dimension detection and dye check detection are carried out.
If the cladding defect exists, the cladding layer needs to be completely cleaned, the cladding layer is completely worn away, the cladding layer is cleaned again for flaw detection, and the cladding repair operation is carried out again after the cladding layer is free of defects.
8. The laser repair process for a gas turbine rotor disk according to claim 1, wherein: and in the final detection stage, red lead side view is carried out on the damage position after cladding and grinding are finished, high points are finely ground on the ground oilstone, and repeated operation is carried out until the red lead test eliminates the high points, so that the polished repair surface, the maintenance surface and the undamaged surface are kept parallel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011593371.7A CN112813431A (en) | 2020-12-29 | 2020-12-29 | Laser repair process for rotor disc of gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011593371.7A CN112813431A (en) | 2020-12-29 | 2020-12-29 | Laser repair process for rotor disc of gas turbine |
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| CN112813431A true CN112813431A (en) | 2021-05-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011593371.7A Pending CN112813431A (en) | 2020-12-29 | 2020-12-29 | Laser repair process for rotor disc of gas turbine |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101629289A (en) * | 2009-07-22 | 2010-01-20 | 岳阳大陆激光技术有限公司 | Laser anti-corrosion and wear-resistant process for trunnion of movable guide vanes of turbines |
| CN102127762A (en) * | 2011-01-12 | 2011-07-20 | 唐山瑞兆激光技术机械修复有限公司 | Laser repair method for damaged blade of coal gas turbo expander |
| CN104532233A (en) * | 2015-01-28 | 2015-04-22 | 河北瑞兆激光电机修复有限公司 | Motor rotor shaft position laser cladding repair method |
-
2020
- 2020-12-29 CN CN202011593371.7A patent/CN112813431A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101629289A (en) * | 2009-07-22 | 2010-01-20 | 岳阳大陆激光技术有限公司 | Laser anti-corrosion and wear-resistant process for trunnion of movable guide vanes of turbines |
| CN102127762A (en) * | 2011-01-12 | 2011-07-20 | 唐山瑞兆激光技术机械修复有限公司 | Laser repair method for damaged blade of coal gas turbo expander |
| CN104532233A (en) * | 2015-01-28 | 2015-04-22 | 河北瑞兆激光电机修复有限公司 | Motor rotor shaft position laser cladding repair method |
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Application publication date: 20210518 |
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