Method and apparatus for forming cooling holes on turbine blades, computer readable medium

Abstract

The application provides a method and device for forming a cooling hole on a turbine blade, and a computer readable medium, which comprises the following steps: determining a to-be-removed part of the turbine blade corresponding to the cooling hole to be formed according to a target shape of the cooling hole to be formed and a target position of the cooling hole to be formed on the turbine blade; removing a rough machining part in the to-be-removed part of the turbine blade by using a first laser beam; and removing a remaining part in the to-be-removed part except the rough machining part by using a second laser beam to form the cooling hole, wherein the pulse width of the first laser beam is greater than a preset first pulse width threshold, the pulse width of the second laser beam is less than a preset second pulse width threshold, and the second pulse width threshold is less than the first pulse width threshold. The application provides a method and device for forming a cooling hole on a turbine blade, and a computer readable medium, which can process the cooling hole with less cracks faster.

Description

Technical Field

[0001] This invention relates to the field of numerical control technology, and in particular to a method and apparatus for forming cooling holes on turbine blades, and a computer-readable medium. Background Technology

[0002] Gas turbine blades operate at extremely high temperatures, and film cooling is a key cooling technology for turbine blades. Cooling holes for turbine blades are typically manufactured using laser drilling or electrical discharge machining (EDM), and a recast layer usually exists on the cooling holes. This recast layer contains numerous cracks, which reduce the fatigue life of the turbine blades. Minimizing cracks in the cooling holes has always been a goal in the manufacturing process.

[0003] In existing technology, cooling holes are drilled into turbine blades using electrical discharge machining (EDM). Because EDM introduces less heat into the turbine blades, it also results in a smaller recast layer, thus reducing the likelihood of cracks in the cooling holes. However, EDM is a relatively slow drilling method. Summary of the Invention

[0004] In order to solve the above and / or other technical problems, the present invention provides a method and apparatus for forming cooling holes on turbine blades, and a computer-readable medium, which can produce cooling holes with fewer cracks more quickly.

[0005] In a first aspect, embodiments of the present invention provide a method for forming cooling holes on turbine blades, the method comprising:

[0006] Based on the target shape of the cooling hole to be formed and the target position of the cooling hole to be formed on the turbine blade, determine the part of the turbine blade to be removed corresponding to the cooling hole to be formed.

[0007] The rough-machined portion of the turbine blade is removed using a first laser beam;

[0008] A second laser beam is used to remove the remaining portion of the part to be removed, excluding the rough-machined portion, to form cooling holes.

[0009] Wherein, the pulse width of the first laser beam is greater than a preset first pulse width threshold, the pulse width of the second laser beam is less than a preset second pulse width threshold, and the second pulse width threshold is less than the first pulse width threshold.

[0010] In the first possible implementation, in conjunction with the first aspect, the cooling hole to be formed has a target shape with a circular cross-section along the radial direction.

[0011] The rough-machined portion has a circular shape with a radial cross-section having the same center as the circular cross-section of the cooling hole to be formed, and a radius shorter than the radius of the circular cross-section of the cooling hole to be formed.

[0012] The remaining portion has a radially oriented cross-section with an inner diameter equal to the diameter of the circular cross-section of the rough-machined portion and an outer diameter equal to the diameter of the circular cross-section of the cooling hole to be formed, forming an annular shape.

[0013] In the second possible implementation, in conjunction with the first possible implementation of the first aspect, the step of removing the remaining portion of the portion to be removed using the second laser beam includes:

[0014] The remaining portion is irradiated with a second laser beam multiple times, thereby removing a portion of the remaining portion that has a radial cross-section identical to the annular cross-section of the remaining portion and an axial length that is determined according to the pulse width of the second laser beam and is smaller than the axial length of the remaining portion during each irradiation with the second laser beam.

[0015] In the third possible implementation, combined with the second possible implementation of the first aspect, the step of performing one second laser beam irradiation in the step of multiple second laser beam irradiations on the remaining portion includes:

[0016] A second laser beam, with a spot diameter equal to the outer diameter of the annular cross-section of the remaining portion, is used to irradiate the remaining portion of the turbine blade to remove a portion of the remaining portion.

[0017] In the fourth possible implementation, in conjunction with the first possible implementation of the first aspect, the difference between the outer diameter and the inner diameter of the annular cross-section of the remaining portion is in the range of greater than or equal to 0.1 mm and less than or equal to 0.2 mm.

[0018] In the fifth possible implementation, in combination with the first aspect, the first possible implementation of the first aspect, the second possible implementation of the first aspect, the third possible implementation of the first aspect, or the fourth possible implementation of the first aspect, the first pulse width threshold is equal to 1 millisecond, and the second pulse width threshold is equal to 500 nanoseconds.

[0019] In a second aspect, embodiments of the present invention provide an apparatus for forming cooling holes on turbine blades, the apparatus comprising: a determining module, a first processing module, and a second processing module;

[0020] The determining module is used to determine the part of the turbine blade to be removed corresponding to the cooling hole to be formed, based on the target shape of the cooling hole to be formed and the target position of the cooling hole to be formed on the turbine blade.

[0021] The first processing module is used to remove the rough-machined portion of the turbine blade from the part to be removed using a first laser beam;

[0022] The second processing module is used to remove the remaining portion of the part to be removed, excluding the rough-processed portion, using a second laser beam to form cooling holes.

[0023] Wherein, the pulse width of the first laser beam is greater than a preset first pulse width threshold, the pulse width of the second laser beam is less than a preset second pulse width threshold, and the second pulse width threshold is less than the first pulse width threshold.

[0024] In the first possible implementation, in conjunction with the second aspect, the cooling hole to be formed has a target shape with a circular cross-section along the radial direction.

[0025] The rough-machined portion has a circular shape with a radial cross-section having the same center as the circular cross-section of the cooling hole to be formed, and a radius shorter than the radius of the circular cross-section of the cooling hole to be formed.

[0026] The remaining portion has a radially oriented cross-section with an inner diameter equal to the diameter of the circular cross-section of the rough-machined portion and an outer diameter equal to the diameter of the circular cross-section of the cooling hole to be formed, forming an annular shape.

[0027] In a second possible implementation, in conjunction with the first possible implementation of the second aspect, the second processing module is used to irradiate the remaining portion multiple times with a second laser beam, thereby removing a portion of the remaining portion having a shape with a radial cross-section identical to the annular cross-section of the remaining portion and an axial length determined according to the pulse width of the second laser beam and smaller than the axial length of the remaining portion during each second laser beam irradiation.

[0028] In a third possible implementation, combined with the second possible implementation of the second aspect, the second processing module is used to irradiate the remaining part of the turbine blade with a second laser beam whose diameter is equal to the outer diameter of the annular cross-section of the remaining part, so as to remove a portion of the remaining part.

[0029] In the fourth possible implementation, in conjunction with the first possible implementation of the second aspect, the difference between the outer diameter and the inner diameter of the annular cross-section of the remaining portion is in the range of greater than or equal to 0.1 mm and less than or equal to 0.2 mm.

[0030] In the fifth possible implementation, in combination with the second aspect, the first possible implementation of the second aspect, the second possible implementation of the second aspect, the third possible implementation of the second aspect, or the fourth possible implementation of the second aspect, the first pulse width threshold is equal to 1 millisecond, and the second pulse width threshold is equal to 500 nanoseconds.

[0031] Thirdly, embodiments of the present invention provide an apparatus for forming cooling holes on turbine blades, the apparatus comprising: at least one memory and at least one processor;

[0032] The at least one memory is used to store a machine-readable program;

[0033] The at least one processor is configured to invoke the machine-readable program to execute any of the methods described in the first aspect.

[0034] Fourthly, embodiments of the present invention provide a computer-readable medium storing computer instructions, which, when executed by a processor, cause the processor to perform any of the methods described in the first aspect.

[0035] Fifthly, embodiments of the present invention provide an apparatus for forming cooling holes on turbine blades, the apparatus comprising: a first laser and a second laser;

[0036] The first laser is used to remove the rough-machined portion of the part to be removed corresponding to the cooling hole to be formed on the turbine blade using a first laser beam, wherein the part to be removed is the part of the turbine blade corresponding to the cooling hole to be formed, determined according to the target shape of the cooling hole to be formed and the target position of the cooling hole to be formed on the turbine blade.

[0037] The second laser is used to remove any remaining portion of the part to be removed, excluding the rough-machined portion, using a second laser beam to form cooling holes.

[0038] Wherein, the pulse width of the first laser beam is greater than a preset first pulse width threshold, the pulse width of the second laser beam is less than a preset second pulse width threshold, and the second pulse width threshold is less than the first pulse width threshold.

[0039] In a first possible implementation, in conjunction with the fifth aspect, the second laser is used to irradiate the remaining portion multiple times with a second laser beam, thereby removing a portion of the remaining portion having a shape with a radial cross-section identical to the annular cross-section of the remaining portion and an axial length determined according to the pulse width of the second laser beam and smaller than the axial length of the remaining portion during each second laser beam irradiation.

[0040] In the second possible implementation, combined with the first possible implementation of the fifth aspect, the second laser is used to irradiate the remaining portion of the turbine blade with a second laser beam whose diameter is equal to the outer diameter of the annular cross-section of the remaining portion, so as to remove a portion of the remaining portion.

[0041] In the third possible implementation, in combination with the fifth aspect, the first possible implementation of the fifth aspect, or the second possible implementation of the fifth aspect, the pulse width of the first laser beam output by the first laser is greater than 1 millisecond;

[0042] The pulse width of the second laser beam output by the second laser is less than 500 nanoseconds.

[0043] In this embodiment of the invention, a first laser beam with a larger pulse width is used to drill holes in the turbine blade, removing the rough-machined portion of the part to be removed. Then, a second laser beam with a smaller pulse width is used to process the remaining portion, forming the desired cooling hole. The larger pulse width of the first laser beam allows for rapid drilling of holes in the turbine blade. The second laser beam removes the cracks formed by the rough-machined portion removed by the first laser beam, and because the pulse width of the second laser beam is smaller, fewer cracks are generated during the removal of the remaining portion. The second laser beam does not need to process the entire cooling hole, only the remaining portion, resulting in less workload and less time consumption. Therefore, in this embodiment of the invention, combining the first and second laser beams enables the faster production of cooling holes with fewer cracks. Attached Figure Description

[0044] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0045] Figure 1 This is a flowchart of a method for forming cooling holes on turbine blades according to an embodiment of the present invention;

[0046] Figure 2 This is a flowchart of another method for forming cooling holes on turbine blades according to an embodiment of the present invention;

[0047] Figure 3 This is a schematic diagram of an apparatus for forming cooling holes on turbine blades according to an embodiment of the present invention;

[0048] Figure 4 This is a schematic diagram of another device for forming cooling holes on turbine blades according to an embodiment of the present invention.

[0049] List of reference numerals in the attached diagram:

[0050] 301: Determining Module; 302: First Processing Module; 303: Second Processing Module

[0051] 401: First laser; 402: Second laser Detailed Implementation

[0052] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0053] When metal materials are hot-worked, the area to be worked on must first be melted or vaporized, producing slag. After removing the slag, the outermost layer cools and resolidifies, forming a recast layer, which often contains numerous cracks. Similarly, when creating cooling holes on turbine blades, the drilling area needs to be melted or vaporized, forming a recast layer on the inner wall of the resulting cooling hole. This recast layer also contains many cracks. To more quickly create cooling holes with fewer cracks on turbine blades, such as... Figure 1 As shown, an embodiment of the present invention provides a method for forming cooling holes on turbine blades, comprising:

[0054] Step 101: Based on the target shape of the cooling hole to be formed and the target position of the cooling hole to be formed on the turbine blade, determine the part of the turbine blade to be removed corresponding to the cooling hole to be formed.

[0055] Step 102: Use the first laser beam to remove the rough-machined portion of the turbine blade in the part to be removed;

[0056] Step 103: Use a second laser beam to remove the remaining portion of the part to be removed, excluding the rough-machined portion, to form cooling holes.

[0057] Wherein, the pulse width of the first laser beam is greater than a preset first pulse width threshold, the pulse width of the second laser beam is less than a preset second pulse width threshold, and the second pulse width threshold is less than the first pulse width threshold.

[0058] In this embodiment of the invention, a first laser beam with a larger pulse width is used to drill holes in the turbine blade, removing the rough-machined portion of the part to be removed. Then, a second laser beam with a smaller pulse width is used to process the remaining portion, forming the desired cooling hole. The larger pulse width of the first laser beam allows for rapid drilling of holes in the turbine blade. The second laser beam removes the cracks formed by the rough-machined portion removed by the first laser beam, and because the pulse width of the second laser beam is smaller, fewer cracks are generated during the removal of the remaining portion. The second laser beam does not need to process the entire cooling hole, only the remaining portion, resulting in less workload and less time consumption. Therefore, in this embodiment of the invention, combining the first and second laser beams enables the faster production of cooling holes with fewer cracks.

[0059] In one embodiment of the present invention, the cooling hole to be formed has a target shape with a circular cross-section along the radial direction.

[0060] The rough-machined portion has a circular shape with a radial cross-section having the same center as the circular cross-section of the cooling hole to be formed, and a radius shorter than the radius of the circular cross-section of the cooling hole to be formed.

[0061] The remaining portion has a radially oriented cross-section with an inner diameter equal to the diameter of the circular cross-section of the rough-machined portion and an outer diameter equal to the diameter of the circular cross-section of the cooling hole to be formed, forming an annular shape.

[0062] In this embodiment of the invention, a first laser beam removes the rough-machined portion of the turbine blade to be removed, forming a target through hole. The axis of symmetry of the target through hole is the same as the axis of symmetry of the cooling hole to be formed, and the diameter of the target through hole is smaller than the diameter of the cooling hole to be formed.

[0063] In this embodiment of the invention, the rough-machined portion can be removed according to the diameter of the rough-machined portion, the drilling position of the cooling hole, and the drilling direction.

[0064] In this embodiment of the invention, when the axis of symmetry of the target through-hole is the same as the axis of symmetry of the cooling hole, and the diameter of the target through-hole is smaller than the diameter of the cooling hole, the remaining portion is a circular tube, the axis of symmetry of which is also the same as that of the cooling hole. The circular tube has an axis of symmetry, and the cross-section of its inner wall in the direction perpendicular to the axis of symmetry is a circle with an equal diameter. The diameter of the cross-section of the inner wall of the circular tube in the direction perpendicular to the axis of symmetry is the inner diameter of the circular tube. The diameter of the cross-section of the outer wall of the circular tube in the direction perpendicular to the axis of symmetry is the outer diameter of the circular tube.

[0065] In one embodiment of the present invention, the step of removing the remaining portion of the portion to be removed using a second laser beam includes:

[0066] The remaining portion is irradiated with a second laser beam multiple times, thereby removing a portion of the remaining portion that has a radial cross-section identical to the annular cross-section of the remaining portion and an axial length that is determined according to the pulse width of the second laser beam and is smaller than the axial length of the remaining portion during each irradiation with the second laser beam.

[0067] In this embodiment of the invention, the length along the irradiation direction that can be removed by a single laser beam irradiating a turbine blade with different pulse widths is different. For example, a laser beam with a pulse width of 200 nanoseconds can remove 0.02 mm along the irradiation direction by a single laser beam irradiating a turbine blade, while a laser beam with a pulse width of 300 nanoseconds can remove 0.03 mm along the irradiation direction by a single laser beam irradiating a turbine blade. For ease of description, the portion of the remaining part with a circular cross-section in the radial direction that is the same as the circular cross-section of the remaining part is referred to as the fine-machined part. The length of this fine-machined part along the axial direction can be determined by the pulse width of the second laser beam. Assuming that the pulse width of the second laser beam is d, and the length along the axial direction that can be removed by the second laser beam with a pulse width of d along the axial direction in a single irradiation of the remaining part is k, then the length along the axial direction of the fine-machined part needs to be less than or equal to k. Preferably, the length along the axial direction of the last fine-machined part irradiated by the second laser beam is less than or equal to k, while the length along the axial direction of the other fine-machined parts is equal to k. This ensures that one fine-machined part can be removed each time the second laser beam is irradiated. The length of the remaining portion that can be removed in one axial direction by a second laser beam with a pulse width of d irradiating it along the axial direction can be obtained by measurement.

[0068] In one embodiment of the present invention, the step of performing one second laser beam irradiation in the multiple second laser beam irradiation steps on the remaining portion includes:

[0069] A second laser beam, with a spot diameter equal to the outer diameter of the annular cross-section of the remaining portion, is used to irradiate the remaining portion of the turbine blade to remove a portion of the remaining portion.

[0070] In one embodiment of the present invention, the difference between the outer diameter and the inner diameter of the annular cross-section of the remaining portion is within the range of greater than or equal to 0.1 mm and less than or equal to 0.2 mm.

[0071] In this embodiment of the invention, the diameter of the roughing portion limits the processing time of the second laser beam. The smaller the diameter of the roughing portion, the more residual portion the second laser beam needs to remove, and correspondingly, the longer it takes to form the cooling hole. The larger the diameter of the roughing portion, the less residual portion the second laser beam needs to remove, and correspondingly, the shorter it takes to form the cooling hole.

[0072] In this embodiment of the invention, when the difference between the outer diameter and the inner diameter of the annular cross-section of the remaining portion is greater than or equal to 0.1 mm and less than or equal to 0.2 mm, it can be ensured that the remaining portion to be removed by the second laser beam is small, thereby ensuring that the processing time of the second laser beam is small, and that the recast layer generated during the process of forming the target is mainly in the remaining portion.

[0073] In one embodiment of the present invention, the first pulse width threshold is equal to 1 millisecond, and the second pulse width threshold is equal to 500 nanoseconds.

[0074] In this embodiment of the invention, the pulse width of the first laser beam can be 10 milliseconds, 20 milliseconds, 50 milliseconds, 70 milliseconds, 80 milliseconds, 90 milliseconds, 100 milliseconds, etc.

[0075] When the pulse width of the first laser beam is greater than 1 millisecond, the first laser can quickly create a hole. This first laser beam can be generated by a millisecond laser.

[0076] In this embodiment of the invention, the pulse width of the second laser beam can be 100 nanoseconds, 200 nanoseconds, 300 nanoseconds, 400 nanoseconds, etc. This second laser beam can be generated by a nanosecond laser.

[0077] In this embodiment of the invention, preferably, the wall thickness of the remaining portion is greater than or equal to the thickness of the recast layer formed by the first laser beam, ensuring that the recast layer formed by the first laser beam is in the remaining portion. After the second laser beam removes the remaining portion, it also removes the recast layer formed by the first laser beam, thus clearing the crack formed by the first laser beam.

[0078] The diameter of the rough-machined section can be determined based on the material of the turbine blade. For example, some materials have a smaller recast layer thickness after being drilled by the first laser beam, so the diameter of the rough-machined section can be set larger; other materials have a larger recast layer thickness after being drilled by the first laser beam, so the diameter of the rough-machined section can be set smaller.

[0079] The following is a detailed description of a method for forming cooling holes on turbine blades provided by an embodiment of the present invention, using a specific example. Figure 2 As shown, the method includes the following steps:

[0080] Step 201: Based on the target shape of the cooling hole to be formed and the target position of the cooling hole to be formed on the turbine blade, determine the part of the turbine blade to be removed corresponding to the cooling hole to be formed.

[0081] Step 202: Use the first laser beam to remove the rough-machined portion of the turbine blade in the part to be removed.

[0082] Specifically, the pulse width of the first laser beam is greater than 1 millisecond.

[0083] In this step, roughing is performed using a first laser beam to quickly remove the roughed portion. The roughed portion has a circular shape with a radial cross-section having the same center as the circular cross-section of the cooling hole to be formed, and a radius shorter than the radius of the circular cross-section of the cooling hole to be formed.

[0084] The first laser beam has a circular spot, the diameter of which is the same as the diameter of the rough-machined part.

[0085] Step 203: Irradiate the remaining portion multiple times with the second laser beam, thereby removing a portion of the remaining portion with a shape that has a radial cross-section identical to the annular cross-section of the remaining portion and an axial length that is determined according to the pulse width of the second laser beam and is smaller than the axial length of the remaining portion when the remaining portion is irradiated with the second laser beam each time, in order to form a cooling hole.

[0086] Preferably, the spot of the second laser beam is circular, and the diameter of the spot of the second laser beam is equal to the outer diameter of the annular cross-section of the remaining portion.

[0087] Specifically, the pulse width of the second laser beam is less than 500 nanoseconds. The second laser beam can be generated by a nanosecond laser. During the irradiation of the remaining portion, the irradiated portion is vaporized, leaving no residue or forming a recast layer. Therefore, the second laser beam will not cause cracks in the cooling holes.

[0088] In a method for forming cooling holes on turbine blades provided in this embodiment of the invention, a first laser beam with a larger pulse width is used to quickly remove the rough-machined portion, and a second laser beam with a smaller pulse width is used to remove the cracks generated by the first laser beam. This allows for the rapid manufacture of cooling holes with fewer cracks, resulting in high work efficiency. The irradiation time of each laser beam is also short, thereby reducing the cost of manufacturing cooling holes.

[0089] like Figure 3 As shown, the device for forming cooling holes on turbine blades is characterized in that the device includes: a determining module 301, a first processing module 302, and a second processing module 303;

[0090] The determining module 301 is used to determine the part of the turbine blade to be removed corresponding to the cooling hole to be formed, based on the target shape of the cooling hole to be formed and the target position of the cooling hole to be formed on the turbine blade.

[0091] The first processing module 302 is used to remove the rough-machined portion of the turbine blade in the part to be removed using a first laser beam;

[0092] The second processing module 303 is used to remove the remaining portion of the part to be removed, excluding the rough-processed portion, using a second laser beam to form cooling holes.

[0093] Wherein, the pulse width of the first laser beam is greater than a preset first pulse width threshold, the pulse width of the second laser beam is less than a preset second pulse width threshold, and the second pulse width threshold is less than the first pulse width threshold.

[0094] In one embodiment of the present invention, the cooling hole to be formed has a target shape with a circular cross-section along the radial direction.

[0095] The rough-machined portion has a circular shape with a radial cross-section having the same center as the circular cross-section of the cooling hole to be formed, and a radius shorter than the radius of the circular cross-section of the cooling hole to be formed.

[0096] The remaining portion has a radially oriented cross-section with an inner diameter equal to the diameter of the circular cross-section of the rough-machined portion and an outer diameter equal to the diameter of the circular cross-section of the cooling hole to be formed, forming an annular shape.

[0097] In one embodiment of the present invention, the second processing module 303 is used to irradiate the remaining portion multiple times with a second laser beam, thereby removing a portion of the remaining portion having a shape in which the radial cross section is the same as the annular cross section of the remaining portion, and the axial length is determined according to the pulse width of the second laser beam and is smaller than the axial length of the remaining portion.

[0098] In one embodiment of the present invention, the second processing module 303 is used to irradiate the remaining part of the turbine blade with a second laser beam whose diameter is equal to the outer diameter of the annular cross section of the remaining part, so as to remove a portion of the remaining part.

[0099] In one embodiment of the present invention, the difference between the outer diameter and the inner diameter of the annular cross-section of the remaining portion is within the range of greater than or equal to 0.1 mm and less than or equal to 0.2 mm.

[0100] In one embodiment of the present invention, the first pulse width threshold is equal to 1 millisecond, and the second pulse width threshold is equal to 500 nanoseconds.

[0101] This invention provides an apparatus for forming cooling holes on turbine blades, the apparatus comprising: at least one memory and at least one processor;

[0102] The at least one memory is used to store a machine-readable program;

[0103] The at least one processor is configured to invoke the machine-readable program to execute any of the methods for forming cooling holes on turbine blades as described in the embodiments of the present invention.

[0104] This invention provides a computer-readable medium, characterized in that the computer-readable medium stores computer instructions, which, when executed by a processor, cause the processor to perform any of the methods for forming cooling holes on turbine blades described in this invention.

[0105] like Figure 4 As shown, an embodiment of the present invention provides an apparatus for forming cooling holes on turbine blades, the apparatus comprising: an input unit (not shown), a first laser 401, and a second laser 402.

[0106] The input unit can be operated to input the portion of the turbine blade to be removed corresponding to the cooling hole to be formed, determined based on the target shape of the cooling hole to be formed and the target position of the cooling hole on the turbine blade. This determination can be accomplished, for example, by the determination module 301 described above. For instance, the input unit can be connected to the determination module 301 to receive and input the portion of the turbine blade to be removed corresponding to the cooling hole to be formed, determined by the determination module 301.

[0107] The first laser 401 (e.g., the first processing module 302 described above) is used to remove the roughing portion of the part to be removed corresponding to the cooling hole to be formed on the turbine blade using the first laser beam, wherein the part to be removed is the part of the turbine blade corresponding to the cooling hole to be formed, determined according to the target shape of the cooling hole to be formed and the target position of the cooling hole to be formed on the turbine blade.

[0108] The second laser 402 (e.g., the second processing module 303 described above) is used to remove the remaining portion of the part to be removed, excluding the rough-processed portion, using a second laser beam to form cooling holes.

[0109] Wherein, the pulse width of the first laser beam is greater than a preset first pulse width threshold, the pulse width of the second laser beam is less than a preset second pulse width threshold, and the second pulse width threshold is less than the first pulse width threshold. In one embodiment of the present invention, the second laser 402 is used to irradiate the remaining portion multiple times with the second laser beam, thereby removing a portion of the remaining portion having a shape in which the radial cross-section is the same as the annular cross-section of the remaining portion, and the axial length is determined according to the pulse width of the second laser beam and is less than the axial length of the remaining portion.

[0110] In one embodiment of the present invention, the second laser 402 is used to irradiate the remaining part of the turbine blade with a second laser beam whose spot diameter is equal to the outer diameter of the annular cross section of the remaining part, so as to remove a portion of the remaining part.

[0111] In one embodiment of the present invention, the pulse width of the first laser beam output by the first laser 401 is greater than 1 millisecond;

[0112] The pulse width of the second laser beam output by the second laser 402 is less than 500 nanoseconds.

[0113] It is understood that the structures illustrated in the embodiments of the present invention do not constitute a specific limitation on the apparatus for forming cooling holes on turbine blades. In other embodiments of the present invention, the apparatus for forming cooling holes on turbine blades may include more or fewer components than illustrated, or combine some components, or split some components, or have different component arrangements. The illustrated components may be implemented in hardware, software, or a combination of software and hardware.

[0114] The information interaction and execution process between the various units in the above-mentioned device are based on the same concept as the method embodiment of the present invention, and the specific details can be found in the description of the method embodiment of the present invention, and will not be repeated here.

[0115] The present invention also provides a computer-readable medium storing instructions for causing a computer to perform a method for forming cooling holes on turbine blades as described herein. Specifically, a system or apparatus equipped with a storage medium storing software program code that implements the functions of any of the embodiments described above, and causing the computer (or CPU or MPU) of the system or apparatus to read and execute the program code stored in the storage medium.

[0116] In this case, the program code read from the storage medium can itself implement the function of any of the above embodiments, and therefore the program code and the storage medium storing the program code constitute part of the present invention.

[0117] Examples of storage media used to provide program code include floppy disks, hard disks, magneto-optical disks, optical disks (such as CD-ROM, CD-R, CD-RW, DVD-ROM, DVD-RAM, DVD-RW, DVD+RW), magnetic tapes, non-volatile memory cards, and ROMs. Alternatively, program code can be downloaded from a server computer via a communication network.

[0118] Furthermore, it should be clear that not only can the program code read by the computer be executed, but also the operating system or other components operating on the computer can be instructed based on the program code to perform some or all of the actual operations, thereby achieving the function of any of the embodiments described above.

[0119] Furthermore, it is understood that the program code read from the storage medium is written to the memory set in the expansion board inserted into the computer or to the memory set in the expansion unit connected to the computer. Then, based on the instructions of the program code, the CPU or other components installed on the expansion board or expansion unit execute some and all of the actual operations, thereby realizing the function of any of the embodiments described above.

[0120] It should be noted that not all steps and modules in the above processes and system structure diagrams are mandatory; some steps or modules can be omitted as needed. The execution order of each step is not fixed and can be adjusted as required. The system structure described in the above embodiments can be a physical structure or a logical structure. That is, some modules may be implemented by the same physical entity, or some modules may be implemented by at least two physical entities, or they may be jointly implemented by certain components in at least two independent devices.

[0121] In the above embodiments, the hardware units can be implemented mechanically or electrically. For example, a hardware unit may include permanent dedicated circuitry or logic (such as a dedicated processor, FPGA, or ASIC) to perform the corresponding operation. The hardware unit may also include programmable logic or circuitry (such as a general-purpose processor or other programmable processor), which can be temporarily configured by software to perform the corresponding operation. The specific implementation method (mechanical, dedicated permanent circuitry, or temporarily configured circuitry) can be determined based on cost and time considerations.

[0122] The present invention has been shown and described in detail above with reference to the accompanying drawings and preferred embodiments. However, the present invention is not limited to these disclosed embodiments. Based on the above at least two embodiments, those skilled in the art will know that more embodiments of the present invention can be obtained by combining the code review methods in the different embodiments described above. These embodiments are also within the protection scope of the present invention.

Claims

1. A method for forming cooling holes on turbine blades, characterized in that, The method includes: Based on the target shape of the cooling hole to be formed and the target position of the cooling hole to be formed on the turbine blade, determine the part of the turbine blade to be removed corresponding to the cooling hole to be formed. The rough-machined portion of the turbine blade is removed using a first laser beam; A second laser beam is used to remove the remaining portion of the part to be removed, excluding the rough-machined portion, to form cooling holes. Wherein, the pulse width of the first laser beam is greater than a preset first pulse width threshold, the pulse width of the second laser beam is less than a preset second pulse width threshold, and the second pulse width threshold is less than the first pulse width threshold. The cooling holes to be formed have a target shape with a circular cross-section along the radial direction. The rough-machined portion has a circular shape with a radial cross-section having the same center as the circular cross-section of the cooling hole to be formed, and a radius shorter than the radius of the circular cross-section of the cooling hole to be formed. The remaining portion has an annular shape with a radial cross-section having an inner diameter equal to the diameter of the circular cross-section of the rough-machined portion and an outer diameter equal to the diameter of the circular cross-section of the cooling hole to be formed. The step of removing the remaining portion from the portion to be removed using a second laser beam includes: The remaining portion is irradiated multiple times with a second laser beam, thereby removing, during each irradiation of the remaining portion, a portion of the remaining portion having a radial cross-section identical to the annular cross-section of the remaining portion, and an axial length that is determined according to the pulse width of the second laser beam and is smaller than the axial length of the remaining portion. The step of subjecting the remaining portion to multiple second laser beam irradiations includes: Along the axial direction, a second laser beam with a spot diameter equal to the outer diameter of the annular cross-section of the remaining portion is used to irradiate the remaining portion of the turbine blade to remove a portion of the remaining portion.

2. The method according to claim 1, characterized in that, The difference between the outer diameter and the inner diameter of the annular cross-section of the remaining portion is greater than or equal to 0.1 mm and less than or equal to 0.2 mm.

3. The method according to any one of claims 1 to 2, characterized in that, The first pulse width threshold is equal to 1 millisecond, and the second pulse width threshold is equal to 500 nanoseconds.

4. An apparatus for forming cooling holes on turbine blades, characterized in that, The device includes: a determining module (301), a first processing module (302), and a second processing module (303); The determining module (301) is used to determine the part of the turbine blade to be removed corresponding to the cooling hole to be formed, based on the target shape of the cooling hole to be formed and the target position of the cooling hole to be formed on the turbine blade. The first processing module (302) is used to remove the rough-machined portion of the turbine blade in the part to be removed using a first laser beam; The second processing module (303) is used to remove the remaining portion of the part to be removed, excluding the rough-processed portion, using a second laser beam to form cooling holes. Wherein, the pulse width of the first laser beam is greater than a preset first pulse width threshold, the pulse width of the second laser beam is less than a preset second pulse width threshold, and the second pulse width threshold is less than the first pulse width threshold. in, The cooling holes to be formed have a target shape with a circular cross-section along the radial direction. The rough-machined portion has a circular shape with a radial cross-section having the same center as the circular cross-section of the cooling hole to be formed, and a radius shorter than the radius of the circular cross-section of the cooling hole to be formed. The remaining portion has an annular shape with a radial cross-section having an inner diameter equal to the diameter of the circular cross-section of the rough-machined portion and an outer diameter equal to the diameter of the circular cross-section of the cooling hole to be formed. The second processing module (303) is used to irradiate the remaining portion multiple times with a second laser beam, thereby removing a portion of the remaining portion having a radial cross-section identical to the annular cross-section of the remaining portion, and an axial length that is determined according to the pulse width of the second laser beam and is smaller than the axial length of the remaining portion during each second laser beam irradiation. The second processing module (303) uses a second laser beam, whose diameter is equal to the outer diameter of the annular cross-section of the remaining part, to irradiate the remaining part of the turbine blade along the axial direction, so as to remove a portion of the remaining part.

5. The apparatus according to claim 4, characterized in that, The difference between the outer diameter and the inner diameter of the annular cross-section of the remaining portion is greater than or equal to 0.1 mm and less than or equal to 0.2 mm.

6. The apparatus according to any one of claims 4 to 5, characterized in that, The first pulse width threshold is equal to 1 millisecond, and the second pulse width threshold is equal to 500 nanoseconds.

7. An apparatus for forming cooling holes on turbine blades, characterized in that, The device includes: at least one memory and at least one processor; The at least one memory is used to store a machine-readable program; The at least one processor is configured to invoke the machine-readable program to execute the method described in any one of claims 1-3.

8. A computer-readable medium, characterized in that, The computer-readable medium stores computer instructions that, when executed by a processor, cause the processor to perform the method described in any one of claims 1-3.

9. An apparatus for forming cooling holes on turbine blades, characterized in that, The device includes: a first laser (401) and a second laser (402); The first laser (401) is used to remove the rough-machined portion of the part to be removed corresponding to the cooling hole to be formed on the turbine blade using the first laser beam, wherein the part to be removed is the part of the turbine blade corresponding to the cooling hole to be formed, determined according to the target shape of the cooling hole to be formed and the target position of the cooling hole to be formed on the turbine blade. The second laser (402) is used to remove the remaining portion of the part to be removed, excluding the rough-machined portion, using a second laser beam to form a cooling hole. Wherein, the pulse width of the first laser beam is greater than a preset first pulse width threshold, the pulse width of the second laser beam is less than a preset second pulse width threshold, and the second pulse width threshold is less than the first pulse width threshold. The second laser (402) is used to irradiate the remaining portion multiple times with a second laser beam, thereby removing a portion of the remaining portion having a radially annular cross-section identical to the annular cross-section of the remaining portion, and an axial length determined according to the pulse width of the second laser beam and smaller than the axial length of the remaining portion during each irradiation with a second laser beam. Wherein, the second laser (402) along the axial direction uses a second laser beam with a spot diameter equal to the outer diameter of the annular cross section of the remaining part to irradiate the remaining part of the turbine blade, so as to remove a portion of the remaining part.

10. The apparatus according to claim 9, characterized in that, The pulse width of the first laser beam output by the first laser (401) is greater than 1 millisecond; The pulse width of the second laser beam output by the second laser (402) is less than 500 nanoseconds.

Images