CN114318064A - Nickel-based metal powder, and repair method and application of turbine blade - Google Patents
Nickel-based metal powder, and repair method and application of turbine blade Download PDFInfo
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- CN114318064A CN114318064A CN202111636069.XA CN202111636069A CN114318064A CN 114318064 A CN114318064 A CN 114318064A CN 202111636069 A CN202111636069 A CN 202111636069A CN 114318064 A CN114318064 A CN 114318064A
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Abstract
The invention relates to the field of metal additive repair, in particular to a repair method and application of nickel-based metal powder and a turbine blade. The nickel-based metal powder comprises the following components in parts by weight: 98-99 parts of metal pre-alloy powder, 0.5-2 parts of rare earth and 0.2-3 parts of modifier; the metal prealloyed powder comprises, in parts by weight: 15-17 parts of chromium, 10-11 parts of cobalt, 5-6 parts of tungsten, 2.5-3 parts of molybdenum, 2.5-3.5 parts of aluminum, 4.2-5 parts of titanium, 0.1-0.5 part of niobium, 0.15-0.25 part of trace elements and 53.75-60.55 parts of nickel; the rare earth comprises yttrium and/or yttrium oxide. The nickel-based metal powder has small harmful effect of impurity elements, and can reduce the crack rate and improve the service performance of the repaired turbine blade when used for laser additive repair of the turbine blade.
Description
Technical Field
The invention relates to the field of metal additive repair, in particular to a repair method and application of nickel-based metal powder and a turbine blade.
Background
The turbine blade is subjected to huge alternating tensile stress, torsional stress and abrasion in severe environments with high temperature, high pressure and dynamic load for a long time, and after being in service for a period of time, the turbine blade is inevitably damaged to a certain extent, such as defects of fatigue cracks, ablation, distortion, abrasion and the like. If new or old, the cost would be prohibitive, and therefore, repairs rather than replacements are often undertaken for damaged turbine blades. At present, the turbine blade repair technology is relatively laggard, most of the imported blades need to be returned to the import country for repair when the imported blades have defects, or well-known blade repair companies need to be entrusted to repair the imported blades, but the period is long, and the price is very expensive. Therefore, the research on the repair test of the turbine blade of the engine has very important practical significance and economic benefit for realizing the high-quality repair of the blade.
In view of the above, the present invention is particularly proposed.
Disclosure of Invention
One aspect of the invention relates to nickel-based metal powder which comprises the following components in parts by weight:
98-99 parts of metal pre-alloy powder, 0.5-2 parts of rare earth and 0.2-3 parts of modifier;
the metal prealloyed powder comprises, in parts by weight: 15-17 parts of chromium, 10-11 parts of cobalt, 5-6 parts of tungsten, 2.5-3 parts of molybdenum, 2.5-3.5 parts of aluminum, 4.2-5 parts of titanium, 0.1-0.5 part of niobium, 0.15-0.25 part of trace elements and 53.75-60.55 parts of nickel;
the rare earth comprises at least one of yttrium, scandium, lanthanum, yttrium oxide, scandium oxide, and lanthanum oxide.
The nickel-based metal powder has small harmful effect of impurity elements, can reduce the crack rate when used for laser additive repair of the turbine blade, and can improve the service performance of the repaired turbine blade.
According to another aspect of the invention, the invention also relates to a method for preparing a nickel-based metal powder, comprising the steps of:
mixing the above components.
The preparation method of the nickel-based metal powder is simple and easy to operate.
According to another aspect of the invention, the invention also relates to a method for repairing a turbine blade, comprising the steps of:
acquiring point cloud data of a turbine blade to be repaired, and performing first pretreatment on the point cloud data;
extracting a boundary curve of the section of the turbine blade to be repaired, establishing a characteristic section curve cluster, fitting a three-dimensional model of the turbine blade to be repaired and a repaired target model, and performing Boolean operation on the three-dimensional model and the target model to obtain the repaired target model;
taking the bottom surface of the repaired target model as a reference surface, amplifying free surfaces of the repaired target model except the bottom surface in equal proportion, dividing the amplified repaired target model, and performing laser material increase repair by adopting the nickel-based metal powder;
the first preprocessing includes an alignment processing and a denoising processing.
The turbine blade repairing method can realize accurate repairing of the turbine blade, improve the service performance of the repaired turbine blade and reduce the crack rate.
According to another aspect of the invention, the invention also relates to a repaired turbine blade.
The repaired turbine blade has the advantages of reduced crack rate and improved service performance.
Compared with the prior art, the invention has the beneficial effects that:
(1) according to the nickel-based metal powder provided by the invention, the rare earth and the alterant are added, so that the harmful effect of impurity elements can be obviously reduced, the structure of the cladding layer is purified, the crack rate of the turbine blade is reduced, the nucleation rate of the cladding layer during solidification is greatly improved, the crystallization state of the cladding layer is changed, relatively fine isometric crystals are formed, the crystal grains are refined, the columnar crystals of the cladding layer are reduced, and the service performance of the repaired turbine blade is improved.
(2) The preparation method of the nickel-based metal powder provided by the invention is simple and easy to operate.
(3) According to the turbine blade repairing method, the point cloud data of the turbine blade to be repaired is taken as a basis, the point cloud data is aligned and denoised, a repaired target model is established, the precision of the fitting model is obviously improved, and efficient, high-quality and accurate-size laser additive repairing of the damaged turbine blade can be realized. The laser additive repair adopts nickel-based metal powder, so that the crack rate of the turbine blade can be reduced, and the service performance is improved. The repaired part of the turbine blade has compact tissue, fine crystal grains and small stress, the crack rate, the porosity and oxide inclusions of the repaired turbine blade are obviously reduced, and the service life of the repaired turbine blade is obviously prolonged.
(4) The repaired turbine blade provided by the invention has the advantages that the crack rate is reduced, and the service performance is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a microscopic structure picture of the K435 turbine blade prosthesis 2mm under the surface layer.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the following detailed description, but those skilled in the art will understand that the following described examples are some, not all, of the examples of the present invention, and are only used for illustrating the present invention, and should not be construed as limiting the scope of the present invention. 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. The examples, in which specific conditions are not specified, were conducted under conventional conditions or conditions recommended by the manufacturer. The reagents or instruments used are not indicated by the manufacturer, and are all conventional products available commercially.
One aspect of the invention relates to nickel-based metal powder which comprises the following components in parts by weight:
98-99 parts of metal pre-alloy powder, 0.5-2 parts of rare earth and 0.2-3 parts of modifier;
the metal prealloyed powder comprises, in parts by weight: 15-17 parts of chromium, 10-11 parts of cobalt, 5-6 parts of tungsten, 2.5-3 parts of molybdenum, 2.5-3.5 parts of aluminum, 4.2-5 parts of titanium, 0.1-0.5 part of niobium, 0.15-0.25 part of trace elements and 53.75-60.55 parts of nickel;
the rare earth comprises at least one of yttrium, scandium, lanthanum, yttrium oxide, scandium oxide, and lanthanum oxide.
Wherein, by weight, the metal prealloyed powder can be, for example, but not limited to, 98.1, 98.3, 98.5, 98.7, 98.9, or 99 parts; the rare earth can be, for example, but is not limited to, 0.5 parts, 0.8 parts, 1.0 parts, 1.2 parts, 1.5 parts, 1.7 parts, or 2 parts; the alterant can be, for example, but not limited to, 0.2 parts, 0.5 parts, 0.8 parts, 1.1 parts, 1.4 parts, 1.9 parts, 2.2 parts, 2.6 parts, 2.8 parts, or 3 parts.
Wherein, the chromium can be, but not limited to, 15 parts, 15.5 parts, 16 parts, 16.5 parts or 17 parts by weight; cobalt can be, for example, but is not limited to, 10 parts, 10.2 parts, 10.4 parts, 10.6 parts, 10.8 parts, or 11 parts; tungsten can be, for example, but is not limited to, 5 parts, 5.2 parts, 5.4 parts, 5.6 parts, 5.8 parts, or 6 parts; molybdenum may be, for example, but is not limited to, 2.5 parts, 2.6 parts, 2.7 parts, 2.8 parts, 2.9 parts, or 3 parts; aluminum may be, for example, but is not limited to, 2.5 parts, 2.7 parts, 2.9 parts, 3.1 parts, 3.3 parts, or 3.5 parts; titanium may be, for example, but is not limited to, 4.2 parts, 4.4 parts, 4.6 parts, 4.8 parts, or 5 parts; niobium may be, for example, but is not limited to, 0.1 parts, 0.2 parts, 0.3 parts, 0.4 parts, or 0.5 parts; the trace elements may be, for example, but are not limited to, 0.15 parts, 0.17 parts, 0.19 parts, 0.21 parts, 0.23 parts, or 0.25 parts; the nickel may be, for example, but is not limited to, 53.75 parts, 54.75 parts, 55.75 parts, 56.75 parts, 58.75 parts, or 60.55 parts.
According to the nickel-based metal powder provided by the invention, the rare earth and the alterant are added, so that the harmful effects of impurity elements can be obviously reduced, the structure of the cladding layer is purified, the crack rate of the turbine blade is reduced, the nucleation rate of the cladding layer during solidification is greatly improved, the crystalline state of the cladding layer is changed, the crystal grains are refined, the columnar crystals of the cladding layer are reduced, and the service performance of the repaired turbine blade is improved.
According to the invention, yttrium or yttrium oxide is added into the nickel-based metal powder, the yttrium oxide can be decomposed at high temperature to generate yttrium ions with higher activity, the yttrium ions have strong affinity with impurity elements in the nickel-based metal powder, and the impurity elements in the nickel-based metal powder can be separated out and float to the surface layer of a laser cladding molten pool under the action of the yttrium ions, so that the harmful effect of the impurity elements is obviously reduced, the cladding layer tissue is purified, and the crack rate is reduced.
According to the invention, the composite modifier is added into the nickel-based metal powder to form a large amount of heterogeneous nucleation cores, so that the nucleation rate of the solidified cladding layer is greatly improved, the crystallization state of the cladding layer is changed, relatively fine isometric crystals are formed, the crystal grains are refined, the columnar crystals of the cladding layer are reduced, and the service performance of the repaired turbine blade is improved.
Preferably, the alterant includes at least two of Si, Na, and K.
Preferably, the trace elements comprise 88-95 parts of iron, 2-4 parts of magnesium, 3-5 parts of boron and 3-5 parts of zirconium.
Wherein, by weight, the iron can be, but is not limited to, 88 parts, 89 parts, 90 parts, 92 parts, 93 parts, 94 parts or 95 parts; magnesium may be, for example, but is not limited to, 2 parts, 2.5 parts, 3 parts, 3.5 parts, or 4 parts; boron, for example, may be, but is not limited to, 3 parts, 3.4 parts, 3.6 parts, 3.9 parts, 4.2 parts, 4.4 parts, 4.8 parts, or 5 parts; zirconium may be, for example, but is not limited to, 3 parts, 3.4 parts, 3.6 parts, 3.9 parts, 4.2 parts, 4.4 parts, 4.8 parts, or 5 parts.
According to another aspect of the invention, the invention also relates to a method for preparing a nickel-based metal powder, comprising the steps of:
the components are mixed.
The preparation method of the nickel-based metal powder is simple and convenient to operate.
Preferably, the mixing time is 1-5 h (e.g., 1h, 2h, 3h, 4h, or 5 h).
Preferably, the method of preparing the metal prealloyed powder includes the steps of:
uniformly mixing all components of the metal pre-alloy powder, and then carrying out first smelting to obtain a pre-alloy blank;
carrying out second smelting on the pre-alloy blank to obtain molten metal;
and carrying out casting and atomization on the molten metal after heat preservation to obtain the metal prealloy powder.
Preferably, the first melting is vacuum pulse arc melting.
Preferably, the first melting is performed 3 to 6 times.
Preferably, a turn-over is included between each first shot.
Preferably, the second melting adopts vacuum induction melting.
Preferably, the temperature of the heat preservation is 1490-1600 ℃ (such as 1490 ℃, 1520 ℃, 1550 ℃, 1580 ℃ or 1600 ℃), and the time of the heat preservation is 5-10 min (such as 5min, 7min, 9min or 10 min).
Preferably, the size of the pre-alloyed round bar obtained by casting is
Preferably, the metal pre-alloy powder further comprises a fourth cleaning and drying before the components are uniformly mixed.
Preferably, the atomization is carried out by a consumable inert gas atomization method.
According to another aspect of the invention, the invention also relates to a method for repairing a turbine blade, comprising the steps of:
acquiring point cloud data of a turbine blade to be repaired, and performing first pretreatment on the point cloud data;
extracting a boundary curve of the section of the turbine blade to be repaired, establishing a characteristic section curve cluster, fitting a three-dimensional model of the turbine blade to be repaired and a repaired target model, and performing Boolean operation on the three-dimensional model and the target model to obtain the repaired target model;
taking the bottom surface of the repaired target model as a reference surface, amplifying free surfaces of the repaired target model except the bottom surface in equal proportion, dividing the amplified repaired target model, and performing laser material increase repair by adopting the nickel-based metal powder;
the first preprocessing includes an alignment processing and a denoising processing.
According to the turbine blade repairing method, the point cloud data of the turbine blade to be repaired is taken as the basis, the point cloud data is aligned and denoised, a repaired target model is established, the precision of a fitting model is remarkably improved, and the turbine blade can be accurately repaired. The laser additive repair adopts nickel-based metal powder to repair the damaged part of the turbine blade layer by layer, so that the crack rate of the turbine blade can be reduced, and the service performance of the repaired turbine blade is improved.
Preferably, the point cloud data of the turbine blade to be repaired is acquired in a non-contact mode.
Preferably, the turbine blades comprise high temperature alloy turbine blades.
Preferably, the superalloy turbine blade comprises a K435 turbine blade.
Preferably, the laser power of the laser additive repair is 0.3-3.8 kW (e.g., 0.3kW, 0.6kW, 0.9kW, 1.2kW, 1.5kW, 2kW, 2.5kW, 3kW, 3.5kW, or 3.8 kW);
and/or the diameter of the laser additive repair light spot is 0.5-3 mm (such as 0.5mm, 1mm, 1.5mm, 2mm, 2.5mm or 3 mm);
and/or the laser scanning speed of the laser additive repair is 2.5-8 mm/s (such as 2.5mm/s, 3.5mm/s, 4.5mm/s, 5.5mm/s, 6.5mm/s, 7.5mm/s or 8 mm/s);
and/or the powder feeding rate of the laser additive repair is 5-20 g/min (such as 5g/min, 10g/min, 15g/min or 20 g/min);
and/or the defocusing amount of the laser additive repair is 5-10 mm (such as 5mm, 7mm, 8mm, 9mm or 10 mm);
and/or the ultrasonic vibration frequency of the laser additive repair is 10-30 kHz (such as 10kHz, 15kHz, 20kHz, 25kHz or 30 kHz).
Preferably, the alignment process specifically includes the steps of:
selecting any X-Y direction section of the non-damaged area of the turbine blade to be repaired; calculating the chord lengths of the two farthest points of the point cloud in the section in the X-Y direction; calculating the geometric center point of the three-dimensional model of the turbine blade to be repaired;
taking the geometric center as a rotation center point, passing through the rotation center point and taking a straight line parallel to the X axis as a rotation axis, and rotating positively and negatively within an angle range of-0.8 degrees to make the chord lengths of two points at the farthest point of the point cloud in the section in the X-Y direction shortest, and aligning point cloud data relative to the X axis;
and (3) positively and negatively rotating within an angle range of-0.8 to 0.8 degrees by taking the geometric center as a rotation center point and a straight line parallel to the Y axis as a rotation axis to ensure that the chord lengths of two points at the farthest point of the point cloud in the section in the X-Y direction are shortest, and performing point cloud data to positively align the Y axis.
Preferably, the denoising process employs a gaussian filter algorithm and/or an adaptive bilateral filter algorithm.
Denoising point cloud data of a smooth area with small curvature by adopting a Gaussian filtering algorithm; and denoising the point cloud data of the large curvature area by adopting a self-adaptive bilateral filtering algorithm.
Preferably, the scale-up ratio is 2% to 5% (e.g., 2%, 3%, 4%, or 5%).
Preferably, the laser additive repair is further followed by detection and subtractive processing.
And (3) detecting the K435 turbine blade subjected to laser additive repair by adopting a nondestructive detection method, and determining whether the turbine blade has defects such as cracks, air holes and inclusions. And (3) carrying out self-adaptive material reduction processing on the turbine blade to be detected, so that the size of the repaired part of the turbine blade reaches the original design target size, and completing the repair of the turbine blade to be repaired.
Preferably, a second preprocessing is further included before the point cloud data of the turbine blade to be repaired is acquired.
Preferably, the second pre-treatment comprises in particular grinding and washing.
Preferably, the washing includes a first washing, a second washing, and a third washing.
Preferably, the first cleaning is acetone cleaning.
Preferably, the second washing is washing with distilled water.
Preferably, the third wash uses an alcohol scrub.
And exposing the metal luster on the damaged part of the turbine blade to be repaired after polishing and scrubbing.
According to another aspect of the invention, the invention also relates to a repaired turbine blade.
The turbine blade repaired by the method has the advantages of reduced crack rate and improved service performance.
The present invention will be further explained with reference to specific examples and comparative examples.
Example 1
The nickel-based metal powder provided by the embodiment comprises the following components in parts by weight:
98 parts of metal prealloying powder, 0.5 part of yttrium, 0.1 part of Si and 0.1 part of Na;
the metal prealloyed powder includes: 15 parts of chromium, 10 parts of cobalt, 5 parts of tungsten, 2.5 parts of molybdenum, 2.5 parts of aluminum, 4.2 parts of titanium, 0.1 part of niobium, 0.15 part of trace element and 60.55 parts of nickel;
the trace elements comprise 88 parts of iron, 2 parts of magnesium, 3 parts of boron and 3 parts of zirconium.
Example 2
The nickel-based metal powder provided by the embodiment comprises the following components in parts by weight:
99 parts of metal prealloy powder, 2 parts of yttrium oxide, 1 part of Si, 1 part of Na and 1 part of K;
the metal prealloyed powder includes: 17 parts of chromium, 11 parts of cobalt, 6 parts of tungsten, 3 parts of molybdenum, 3.5 parts of aluminum, 5 parts of titanium, 0.5 part of niobium, 0.25 part of trace element and 53.75 parts of nickel;
the trace elements comprise 88 parts of iron, 2 parts of magnesium, 3 parts of boron and 3 parts of zirconium.
Example 3
The nickel-based metal powder provided by the embodiment comprises the following components in parts by weight:
98.5 parts of metal prealloying powder, 0.5 part of yttrium oxide, 1 part of Na and 78 parts of K1;
the metal prealloyed powder includes: 16 parts of chromium, 10.5 parts of cobalt, 5.5 parts of tungsten, 2.7 parts of molybdenum, 3 parts of aluminum, 4.6 parts of titanium, 0.3 part of niobium, 0.2 part of trace elements and 55.2 parts of nickel;
the trace elements comprise 90 parts of iron, 3 parts of magnesium, 4 parts of boron and 4 parts of zirconium.
Example 4
The repair method for the turbine blade provided by the embodiment comprises the following steps:
(1) sequentially polishing, acetone cleaning, distilled water cleaning and alcohol scrubbing the damaged part of the K435 turbine blade to be repaired to expose the metal luster of the damaged part;
(2) acquiring point cloud data of K435 turbine blades to be repaired by a non-contact method, and performing alignment processing and denoising on the point cloud data;
(3) extracting a boundary curve of the section of the K435 turbine blade to be repaired, establishing a characteristic section curve cluster of the K435 turbine blade to be repaired, fitting a target model of the repaired K435 turbine blade to be repaired and a three-dimensional model of the repaired K435 turbine blade, and performing Boolean operation on the repaired target model of the K435 turbine blade to be repaired and the three-dimensional model of the repaired K435 turbine blade to obtain a repaired target model of the K435 turbine blade to be repaired;
(4) the method comprises the steps of taking the bottom surface of a repair target model of the K435 turbine blade to be repaired as a reference surface, amplifying other free surfaces of the repair target model of the K435 turbine blade to be repaired by 2% -5% in an equal proportion, then carrying out segmentation treatment on the K435 turbine blade to be repaired after the equal proportion is amplified, and carrying out laser material increase repair layer by layer on the damaged part of the K435 turbine blade by selecting the nickel-based metal powder in the embodiment 1 to obtain a K435 turbine blade prosthesis; when the damaged part of the K435 turbine blade is subjected to layer-by-layer laser additive repair, 10kHz ultrasonic vibration is applied to the K435 turbine blade;
(5) detecting the K435 turbine blade restoration by adopting a nondestructive detection method, and determining whether the K435 turbine blade restoration has defects such as cracks, air holes, inclusions and the like;
(6) and (5) carrying out self-adaptive material reduction processing on the K435 turbine blade restoration detected in the step (5), so that the size of the repaired part of the K435 turbine blade restoration reaches the original design size, and completing the repair of the K435 turbine blade to be repaired.
Example 5
The method for repairing a turbine blade according to the present embodiment differs from embodiment 4 only in that:
layer-by-layer laser additive repair the nickel-based metal powder of example 2 was used, and ultrasonic vibration of 30kHz was applied.
Example 6
The method for repairing a turbine blade according to the present embodiment differs from embodiment 4 only in that:
layer-by-layer laser additive repair the nickel-based metal powder of example 3 was used, and 20kHz ultrasonic vibration was applied.
Comparative example 1
Compared with example 4, the repair method of the turbine blade provided by the comparative example only has the following difference:
and step 2, the point cloud data is not subjected to data preprocessing.
Comparative example 2
Compared with example 4, the repair method of the turbine blade provided by the comparative example only has the following difference:
the nickel-based metal powder used for the layer-by-layer laser additive repair does not contain yttrium, and the rest is the same as that of the nickel-based metal powder used in the example 1.
Comparative example 3
Compared with example 4, the repair method of the turbine blade provided by the comparative example only has the following difference:
the nickel-based metal powder adopted for the layer-by-layer laser additive repair does not contain Si and Na, and the rest is the same as that of the nickel-based metal powder in the example 1.
Examples of the experiments
Table 1 shows the results of the height of the K435 turbine blade prosthesis of example 4 and comparative examples 1-3 above the original design size, the residual stress 2mm below the surface of the prosthesis, fluorescence detection and X-ray detection. The detection of the residual stress 2mm below the repair surface layer is carried out according to the standard of the national standard GB/T31310-2014 drilling strain method for measuring the residual stress of metal materials.
TABLE 1K 435 turbine blade prosthesis test results
FIG. 1 shows the microstructure 2mm below the surface layer of the K435 turbine blade prosthesis of example 4 and comparative example 3.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. The nickel-based metal powder is characterized by comprising the following components in parts by weight:
98-99 parts of metal pre-alloy powder, 0.5-2 parts of rare earth and 0.2-3 parts of modifier;
the metal prealloyed powder comprises, in parts by weight: 15-17 parts of chromium, 10-11 parts of cobalt, 5-6 parts of tungsten, 2.5-3 parts of molybdenum, 2.5-3.5 parts of aluminum, 4.2-5 parts of titanium, 0.1-0.5 part of niobium, 0.15-0.25 part of trace elements and 53.75-60.55 parts of nickel;
the rare earth comprises at least one of yttrium, scandium, lanthanum, yttrium oxide, scandium oxide, and lanthanum oxide.
2. The nickel-based metal powder of claim 1, wherein the alterant includes at least two of Si, Na, and K;
preferably, the trace elements comprise 88-95 parts of iron, 2-4 parts of magnesium, 3-5 parts of boron and 3-5 parts of zirconium.
3. The method for the preparation of nickel-based metal powder according to claim 1 or 2, comprising the steps of:
mixing the above components.
4. A method of repairing a turbine blade, comprising the steps of:
acquiring point cloud data of a turbine blade to be repaired, and performing first pretreatment on the point cloud data;
extracting a boundary curve of the section of the turbine blade to be repaired, establishing a characteristic section curve cluster, fitting a three-dimensional model of the turbine blade to be repaired and a repaired target model, and performing Boolean operation on the three-dimensional model and the target model to obtain the repaired target model;
taking the bottom surface of the repaired target model as a reference surface, amplifying free surfaces of the repaired target model except the bottom surface in equal proportion, dividing the amplified repaired target model, and performing laser additive repair by using the nickel-based metal powder of claim 1 or 2;
the first preprocessing includes an alignment processing and a denoising processing.
5. The method for repairing a turbine blade of claim 4, wherein the laser power of the laser additive repair is 0.3-3.8 kW;
and/or the diameter of a light spot of the laser material increase repair is 0.5-3 mm;
and/or the laser scanning speed of the laser material increase repair is 2.5-8 mm/s;
and/or the powder feeding rate of the laser additive repair is 5-20 g/min;
and/or the defocusing amount of the laser additive repair is 5-10 mm;
and/or the ultrasonic vibration frequency of the laser additive repair is 10-30 kHz.
6. The method for repairing a turbine blade according to claim 4, wherein the alignment process comprises the steps of:
selecting any X-Y direction section of the non-damaged area of the turbine blade to be repaired; calculating the chord lengths of the two farthest points of the point cloud in the section in the X-Y direction; calculating the geometric center point of the three-dimensional model of the turbine blade to be repaired;
taking the geometric center as a rotation center point, passing through the rotation center point and taking a straight line parallel to the X axis as a rotation axis, and rotating positively and negatively within an angle range of-0.8 degrees to make the chord lengths of two points at the farthest point of the point cloud in the section in the X-Y direction shortest, and aligning point cloud data relative to the X axis;
and (3) positively and negatively rotating within an angle range of-0.8 to 0.8 degrees by taking the geometric center as a rotation center point and a straight line parallel to the Y axis as a rotation axis to ensure that the chord lengths of two points at the farthest point of the point cloud in the section in the X-Y direction are shortest, and performing point cloud data to positively align the Y axis.
7. The method for repairing a turbine blade of claim 4, wherein said de-noising process employs a Gaussian filter algorithm and/or an adaptive bilateral filter algorithm;
preferably, the scale-up ratio is 2% to 5%.
8. The method of repairing a turbine blade of claim 4, further comprising inspecting and subtractive machining after said laser additive repair.
9. The method for repairing the turbine blade of claim 4, wherein a second preprocessing is further included before the point cloud data of the turbine blade to be repaired is acquired;
preferably, the second pre-treatment comprises in particular grinding and washing.
10. The method for repairing a turbine blade according to any one of claims 4 to 9, wherein the turbine blade is repaired.
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