Method for processing hole of titanium alloy fatigue performance test sample

Abstract

The embodiment of the application provides a hole processing inspection method for a titanium alloy hole fatigue performance test sample, and relates to the field of titanium alloy fatigue performance test. The method aims to improve the problem that the titanium alloy hole fatigue performance test accuracy needs to be improved. The hole processing inspection method for the titanium alloy hole fatigue performance test sample comprises the following steps: controlling a drill bit to drill a hole to form an initial hole; and controlling a fine milling cutter to keep the spindle rotating to retreat the cutter to obtain a fine milling hole. The spindle is kept rotating during fine milling and retreat of the cutter, the processing quality of the fine milling hole is improved, the processing quality and the tool life are ensured, the performance detection accuracy is improved, and the fatigue data can truly reflect the fatigue performance of the material itself.

Description

Technical Field

[0001] This invention relates to the field of fatigue performance testing of titanium alloys, and more specifically, to a method for inspecting the hole processing of a titanium alloy fatigue performance test specimen with holes. Background Technology

[0002] To obtain fatigue data for materials under different stress concentration factors and to verify the fatigue data of typical materials under typical load conditions, existing generalized fatigue analysis methods are sufficiently conservative in calculating the life of perforated structures compared to experimentally measured life. Generally, flat plate specimens with circular inner holes are used for fatigue performance testing to achieve these objectives. In addition to the above purposes, perforated specimens are representative, and various types of fatigue performance test specimens require perforation within the gauge length to achieve the testing objectives.

[0003] For perforated specimens, the central hole is the key testing area. Fatigue cracks generally initiate at the inner hole or chamfer, thus the inner hole significantly affects the accuracy of fatigue performance testing. Titanium alloys are highly sensitive to machining damage, i.e., notches, and the inner hole is more difficult to machine than the outer surface. This easily leads to machining defects in the inner hole, causing fatigue cracks to originate from these defects. Consequently, the measured fatigue life is significantly lower than the material's inherent fatigue performance, and the fatigue test fails to achieve the expected results. Alternatively, the inner hole may exhibit extrusion strengthening, resulting in an overestimated fatigue life, which also fails to achieve the desired results. Summary of the Invention

[0004] The following provides a brief overview of one or more aspects to offer a basic understanding of them. This overview is not an exhaustive summary of all conceived aspects, nor is it intended to identify key or decisive elements of all aspects, nor to define the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form to prepare for the more detailed descriptions that follow.

[0005] The present invention aims to provide, for example, a method for inspecting the hole processing of a titanium alloy fatigue performance test specimen with holes, which can improve the problem that the accuracy of titanium alloy fatigue performance testing with holes needs to be improved.

[0006] The embodiments of the present invention can be implemented as follows:

[0007] An embodiment of the present invention provides a method for inspecting the hole processing of a titanium alloy fatigue performance test specimen with holes, comprising:

[0008] Control the drill bit to drill a hole and form an initial hole;

[0009] The finish milling cutter is retracted while keeping the spindle rotating to obtain the finish milled hole.

[0010] In addition, the hole processing inspection method for titanium alloy fatigue performance test specimens with holes provided in the embodiments of the present invention may also have the following additional technical features:

[0011] Optionally, the step of retracting the finish milling cutter while maintaining spindle rotation to obtain the finish milled hole includes:

[0012] While keeping the spindle rotating, the finish milling cutter is retracted, and the retraction speed V of the finish milling cutter is in the range of V≤1mm / s, to obtain a finish milled hole.

[0013] Optionally, the hole machining inspection method for the titanium alloy fatigue performance test specimen with holes further includes, after the step of controlling the drill bit to drill and form an initial hole, and before the step of controlling the milling cutter to retract while keeping the spindle rotating to obtain a milled hole:

[0014] The side cutting edge of the rough milling cutter is controlled to chamfer both ends of the initial hole to obtain a rough milled hole;

[0015] And, the steps following the step of retracting the milling cutter while keeping the spindle rotating to obtain the milled hole:

[0016] The grinding media is controlled to grind the chamfers at both ends of the precision milled hole to obtain the machined hole.

[0017] Optionally, the polishing medium has a conical structure with a apex angle of 30°.

[0018] Optionally, the step of using the controlled grinding medium to grind the chamfers at both ends of the precision-milled hole to obtain the machined hole includes:

[0019] The conical axis of the grinding medium is parallel to the axis of the precision milled hole, and the grinding speed ranges from 100 to 200 rpm. The chamfers at both ends of the precision milled hole are ground to obtain the machined hole.

[0020] Optionally, the hole machining inspection method for the titanium alloy fatigue performance test specimen with holes further includes a step after the hole machining step, whereby the controlled grinding medium grinds the chamfers at both ends of the precision-milled hole.

[0021] The typical and key areas of the machined holes were examined under a microscope at a magnification of 500x.

[0022] Based on the comparison of the diagrams, the machined holes will be rejected if they exhibit burrs, scratches with an angle of less than 60° to the hole axis, excessive cutting accumulation and smearing, or pits with a depth greater than 2μm.

[0023] Optionally, the hole machining inspection method for the titanium alloy fatigue performance test specimen with holes further includes a step after the hole machining step, whereby the controlled grinding medium grinds the chamfers at both ends of the precision-milled hole.

[0024] The machining hole and gauge length are cut along a direction perpendicular to the length of the sample and passing through the diameter of the machining hole to obtain a cutting surface;

[0025] The cut surface was examined under a microscope at a magnification of at least 400 times;

[0026] If the cut surface shows foreign object embedding, cracks, tears, or white layer, the product will be rejected.

[0027] Acceptance is granted if the cut surface exhibits tensile, peeling, or corrosion pits with a size ≤2μm.

[0028] Acceptance is granted if the cut surface exhibits a surface deformation layer and the deposit layer size is ≤5μm.

[0029] Optionally, the hole machining inspection method for the titanium alloy fatigue performance test specimen with holes further includes a step after the hole machining step, whereby the controlled grinding medium grinds the chamfers at both ends of the precision-milled hole.

[0030] The residual stress on the inner wall of the machined hole is tested, and the range of the residual stress on the inner wall of the machined hole is 100 to 300 MPa.

[0031] Optionally, the hole machining inspection method for the titanium alloy fatigue performance test specimen with holes further includes a step after the hole machining step, whereby the controlled grinding medium grinds the chamfers at both ends of the precision-milled hole.

[0032] The machined holes are subjected to fracture fatigue tests. If cracks originate from machining damage, the holes are rejected.

[0033] Optionally, the hole machining inspection method for the titanium alloy fatigue performance test specimen with holes further includes:

[0034] If any sample in a batch exhibits rejection characteristics in its machined hole, the entire batch of samples will be rejected.

[0035] One sample is cut and inspected for each batch of samples. If the cut and inspection reveals rejection characteristics, an additional sample is cut and inspected for each batch of samples.

[0036] The beneficial effects of the hole processing inspection method for titanium alloy fatigue performance test specimens with holes according to embodiments of the present invention include, for example:

[0037] The hole machining inspection method for titanium alloy fatigue performance test specimens includes: controlling the drill bit to drill a hole to form an initial hole; controlling the milling cutter to retract while keeping the spindle rotating to obtain a milled hole.

[0038] Maintaining spindle rotation during finish milling improves the machining quality of finish milled holes, ensures machining quality and tool life, enhances the accuracy of performance testing, and allows fatigue data to truly reflect the fatigue performance of the material itself. Attached Figure Description

[0039] The above-described features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related characteristics or features may have the same or similar reference numerals.

[0040] Figure 1 This is a schematic diagram of a typical fatigue performance test specimen in the hole processing inspection method for titanium alloy perforated fatigue performance test specimens provided in the embodiments of the present invention.

[0041] Figure 2 This is a schematic diagram illustrating the presence of burrs that have not been completely removed at the junction of the chamfer and the hole or surface in the hole processing inspection method for the fatigue performance test specimen of titanium alloy with holes provided in this embodiment of the invention.

[0042] Figure 3 A schematic diagram showing scratches with an angle of less than 60° to the hole axis in the hole machining inspection method for the fatigue performance test specimen of titanium alloy with holes provided in the embodiments of the present invention.

[0043] Figure 4 This is a schematic diagram illustrating the presence of a large amount of cutting deposits and smearing on the hole surface in the hole machining inspection method for the fatigue performance test specimen of titanium alloy with holes provided in the embodiments of the present invention.

[0044] Figure 5 This is a schematic diagram illustrating the presence of a small amount of cutting deposits and smearing on the hole surface in the hole machining inspection method for the fatigue performance test specimen of titanium alloy with holes provided in the embodiments of the present invention.

[0045] Figure 6 This is a schematic diagram illustrating the presence of pits deeper than 2 μm in the hole processing inspection method for the titanium alloy fatigue performance test specimen with holes provided in this embodiment of the invention.

[0046] Figure 7 This is a flowchart illustrating the hole processing inspection method for a titanium alloy perforated fatigue performance test specimen provided in an embodiment of the present invention. Detailed Implementation

[0047] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. It should be noted that the aspects described below with reference to the accompanying drawings and specific embodiments are merely exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0048] In the description of this invention, it should be noted that if terms such as "upper," "lower," "inner," "outer," or "vertical" appear, the orientation or positional relationship indicated is based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of this invention is usually placed when in use, and does not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0049] At the same time, it should be noted that the terms "first" and "second" are used only for distinguishing descriptions and should not be interpreted as indicating or implying relative importance.

[0050] In the description of this invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, an integral connection, or a detachable connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium, or a connection within two components, etc. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0051] The following is combined Figures 1 to 7 The hole processing inspection method for the titanium alloy fatigue performance test specimen with holes provided in this embodiment is described in detail.

[0052] Please refer to Figure 1 and Figure 7 The present invention provides a method for inspecting the hole processing of a titanium alloy fatigue performance test specimen with holes, comprising:

[0053] Step S1: Control the drill bit to drill a hole and form an initial hole;

[0054] Step S3: While keeping the spindle rotating, the finish milling cutter is retracted to obtain the finish milled hole.

[0055] In the pre-drilling stage, the drill bit is controlled to drill, forming an initial hole. Specifically, a 5mm tungsten carbide drill bit is used for pre-drilling, providing an initial hole to facilitate subsequent milling. In the roughing stage, the hole is machined using a CNC machining center. Milling must be done using the side edge of a milling cutter; helical milling is prohibited. CNC stands for Computer Numerical Control, a technology that uses computer programs to control machine tools for automated machining. Roughing is performed using the side edge of a milling cutter, leaving a 0.1mm allowance on both sides. In the finish milling stage, the spindle is kept rotating during tool retraction, and the retraction speed is controlled to not exceed 1mm / s. Specifically, the finish milling of the hole consists of 7 cuts, with a cutting speed S of 1600rpm for all cuts, a depth of cut F of 0.030mm for all cuts, and feed rates r for the 7 cuts of 0.17, 0.13, 0.07, 0.05, 0.04, 0.03, and 0.01mm respectively.

[0056] Maintaining spindle rotation during finish milling allows for smoother contact between the cutting tool and the workpiece, reducing wear caused by friction. This reduced friction helps extend tool life and lower production costs. It also reduces direct impact between the drill bit and the workpiece, lowering the risk of drill breakage, ensuring machining quality, and improving machining efficiency. Furthermore, it reduces machining errors caused by vibration or instability, improving machining accuracy. Finally, it enhances the machining quality of finish-milled holes, ensuring machining quality and tool life, and improving the accuracy of performance testing.

[0057] In this embodiment, step S3, which involves retracting the finish milling cutter while maintaining spindle rotation to obtain the finish milled hole, includes:

[0058] Step S31: While keeping the spindle rotating, the finish milling cutter is retracted, and the retraction speed V of the finish milling cutter is within the range of V≤1mm / s, to obtain the finish milled hole.

[0059] Keep the spindle rotating while retracting the tool, and control the retraction speed to no more than 1 mm / s to ensure machining quality and tool life.

[0060] In this embodiment, the hole machining inspection method for the titanium alloy fatigue performance test specimen with holes further includes the following steps: after step S1, controlling the drill bit to drill and form an initial hole, and before step S3, controlling the milling cutter to retract while keeping the spindle rotating to obtain the milled hole:

[0061] Step S2: Control the side cutting edge of the rough milling cutter to chamfer both ends of the initial hole to obtain the rough milled hole;

[0062] And, in step S3, while controlling the finish milling cutter to keep the spindle rotating, the cutter is retracted to obtain the final milled hole.

[0063] Step S4: Control the grinding medium to grind the chamfers at both ends of the precision milled hole to obtain the machined hole.

[0064] During the rough milling stage, C0.5 chamfers are machined at both ends of the hole to ensure that the chamfers meet the drawing requirements. Then, finish milling is performed, and the finish milled holes are chamfered and ground using 800# or finer conical abrasive media to remove burrs from the chamfers at the hole openings.

[0065] In this embodiment, the polishing medium has a conical structure with a vertices of 30°.

[0066] In this embodiment, the step of controlling the grinding medium to grind the chamfers at both ends of the precision-milled hole to obtain the machined hole includes:

[0067] The conical axis of the grinding medium is parallel to the axis of the precision milled hole, and the grinding speed ranges from 100 to 200 rpm. The chamfers at both ends of the precision milled hole are ground to obtain the machined hole.

[0068] Use electric or pneumatic tools, controlling the rotation speed between 100 and 200 rpm. During grinding, keep the axis of the conical structure parallel to the axis of the milled hole, and continuously move the grinding tool to avoid grinding the same position repeatedly. The grinding media and the part should remain rotating during contact and withdrawal to ensure effective grinding.

[0069] Reference Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6 In this embodiment, the hole machining inspection method for the titanium alloy fatigue performance test specimen with holes further includes controlling the grinding medium to grind the chamfers at both ends of the precision-milled hole, resulting in a step after the hole machining step:

[0070] The typical and key areas of the machined holes were examined under a microscope at a magnification of 500x.

[0071] Based on the comparison of the diagrams, the machined holes are rejected if they have burrs, scratches with an angle of less than 60° to the hole axis, a large amount of cutting accumulation and smearing, or pits with a depth greater than 2μm.

[0072] After the first piece is machined, the holes are cut open, and the holes and gauge length sections are inspected using a stereomicroscope and an electron microscope. Typical and key areas are examined at up to 500x magnification, and compared against the atlas to ensure no rejection features are found. Figure 2 As shown, the white dotted line represents the hole axis, and the white arrow represents burrs in the transition area between the chamfer and the hole. If burrs are present at the junction of the chamfer and the hole or surface that have not been completely removed, the product will be rejected. Figure 3As shown, the white dotted line represents the hole axis, and the white arrows represent scratches on the chamfer and the hole. Scratches with an angle less than 60° to the hole axis are rejected. Figure 4 As shown, there is a large amount of cutting material and coating on the hole surface, therefore the sample is rejected. Figure 5 As shown, a small amount of cutting deposits and smearing on the hole surface is acceptable for acceptance. Figure 6 As shown, pits deeper than 2μm are present, and the product is rejected. This embodiment only lists a portion of the patterns; in actual testing, more patterns can be listed, and the determination of whether to reject or accept the product can be made by comparing the microscopic observations with the patterns.

[0073] It should be noted that the degree of "extensive cutting accumulation and application" can be set according to the actual situation, and the proportion of the cutting accumulation and application area can be set. If the proportion of the cutting accumulation and application area is greater than the set area, it is considered extensive cutting accumulation and application; if the proportion of the cutting accumulation and application area is less than the set area, it is not considered extensive cutting accumulation and application.

[0074] Reference Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6 In this embodiment, the hole machining inspection method for the titanium alloy fatigue performance test specimen with holes further includes controlling the grinding medium to grind the chamfers at both ends of the precision-milled hole, resulting in a step after the hole machining step:

[0075] The machining hole and gauge length are cut along a direction perpendicular to the length of the sample and passing through the diameter of the machining hole to obtain a cutting surface;

[0076] The cut surface was examined under a microscope at a magnification of at least 400 times;

[0077] If the cut surface shows foreign objects embedded, cracks, tears, or white layers, the product will be rejected.

[0078] Acceptance is granted if the cut surface exhibits tensile, spalling, or corrosion pits with a size ≤2μm.

[0079] Acceptance is granted if the cut surface shows a surface deformation layer and the size of the deposited layer is ≤5μm.

[0080] Cut the sample along the diameter of the hole and the gauge length, perpendicular to the length of the sample, and observe the details of the entire cross-section using a magnification of no less than 400x.

[0081] The following characteristics are not allowed to exceed the specified limits: foreign matter embedding, cracks, tears, white layer; pulling, peeling, corrosion pits: ≤2μm; surface deformation layer, deposition layer: ≤5μm.

[0082] In this embodiment, the hole machining inspection method for the titanium alloy fatigue performance test specimen with holes further includes controlling the grinding medium to grind the chamfers at both ends of the precision-milled hole, resulting in a step after the hole machining step:

[0083] The residual stress on the inner wall of the machined hole was tested, and the range of residual stress on the inner wall of the machined hole was 100 to 300 MPa.

[0084] Residual stress testing can be performed using X-ray diffraction or other methods, depending on the circumstances. A compressive stress of 100–300 MPa is recommended, but this is not required for acceptance or rejection.

[0085] In this embodiment, the hole machining inspection method for the titanium alloy fatigue performance test specimen with holes further includes controlling the grinding medium to grind the chamfers at both ends of the precision-milled hole, resulting in a step after the hole machining step:

[0086] The machined holes are subjected to fracture fatigue tests. If cracks originate from machining damage, the samples are rejected.

[0087] Fatigue testing, conducted as needed. Fracture surface analysis ensures that no cracks originate from processing damage.

[0088] In this embodiment, the hole machining inspection method for the titanium alloy fatigue performance test specimen with holes further includes:

[0089] If any sample in a batch exhibits rejection characteristics in its machined hole, the entire batch of samples is rejected. If one sample in each batch is cut and inspected, and the cut and inspection reveals rejection characteristics, an additional sample in each batch is cut and inspected.

[0090] Batch processing quality inspection and judgment method: Visually inspect each piece. There should be no rejection characteristics. If there are suspected rejection features, randomly select one piece from each batch for dissection. If rejection features are still present, dissect two pieces. If no rejection features are present, the whole batch is accepted. If rejection features are present, the whole batch is rejected.

[0091] According to the hole machining inspection method for a titanium alloy fatigue performance test specimen with holes provided in this embodiment, the working principle of the hole machining inspection method for the titanium alloy fatigue performance test specimen with holes includes:

[0092] Considering the processing cost of material-grade specimens, the processing of inner holes cannot be done using overly advanced and costly methods. However, if processing is done arbitrarily based on experience, it is easy to cause poor processing quality, invalid fatigue data, and a waste of a lot of resources and time. This embodiment optimizes and controls the processing technology, and provides inspection methods and standards. This method can be used to process the holes of titanium alloy fatigue performance test specimens with holes, so that the fatigue data can truly reflect the fatigue performance of the material itself, and the processing route and parameters are optimized.

[0093] The hole machining inspection method for a titanium alloy fatigue performance test specimen with holes provided in this embodiment has at least the following advantages:

[0094] Maintaining spindle rotation during finish milling improves the machining quality of finish milled holes, ensures machining quality and tool life, enhances the accuracy of performance testing, and allows fatigue data to truly reflect the fatigue performance of the material itself.

[0095] An optimized machining process route is adopted, such as chamfering before precision milling of holes, and key parameters and operating methods are provided. Grinding consumables suitable for chamfering holes are used to grind the precision-milled chamfers. This improves machining quality and more accurately reflects the fatigue performance of the material, avoiding both excessively short lifespan due to machining defects and excessively long lifespan due to machining stress, while also achieving good cost-effectiveness.

[0096] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A method for inspecting the hole machining of a titanium alloy fatigue performance test specimen with holes, characterized in that, include: Control the drill bit to drill a hole and form an initial hole; The finish milling cutter is retracted while keeping the spindle rotating to obtain the finish milled hole.

2. The method for inspecting the hole processing of a titanium alloy fatigue performance test specimen with holes according to claim 1, characterized in that, The step of retracting the finish milling cutter while keeping the spindle rotating to obtain the finish milled hole includes: While keeping the spindle rotating, the finish milling cutter is retracted, and the retraction speed V of the finish milling cutter is in the range of V≤1mm / s, to obtain a finish milled hole.

3. The method for inspecting the hole processing of a titanium alloy fatigue performance test specimen with holes according to claim 1, characterized in that, The hole machining inspection method for the titanium alloy fatigue performance test specimen with holes further includes the following steps: after the step of controlling the drill bit to drill and form an initial hole, and before the step of controlling the milling cutter to retract while keeping the spindle rotating to obtain the milled hole: The side cutting edge of the rough milling cutter is controlled to chamfer both ends of the initial hole to obtain a rough milled hole; And, the steps following the step of retracting the milling cutter while keeping the spindle rotating to obtain the milled hole: The grinding media is controlled to grind the chamfers at both ends of the precision milled hole to obtain the machined hole.

4. The method for inspecting the hole processing of a titanium alloy fatigue performance test specimen with holes according to claim 3, characterized in that, The polishing medium has a conical structure with a vertices angle of 30°.

5. The method for inspecting the hole processing of a titanium alloy fatigue performance test specimen with holes according to claim 3, characterized in that, The step of using the controlled grinding medium to grind the chamfers at both ends of the precision-milled hole to obtain the machined hole includes: The conical axis of the grinding medium is parallel to the axis of the precision milled hole, and the grinding speed ranges from 100 to 200 rpm. The chamfers at both ends of the precision milled hole are ground to obtain the machined hole.

6. The method for inspecting the hole processing of a titanium alloy fatigue performance test specimen with holes according to claim 3, characterized in that, The hole machining inspection method for the titanium alloy fatigue performance test specimen with holes further includes grinding the chamfers at both ends of the precision-milled hole using the controlled grinding medium, resulting in a step after the hole machining step: The typical and key areas of the machined holes were examined under a microscope at a magnification of 500x. Based on the comparison of the diagrams, the machined holes will be rejected if they exhibit burrs, scratches with an angle of less than 60° to the hole axis, excessive cutting accumulation and smearing, or pits with a depth greater than 2μm.

7. The method for inspecting the hole processing of a titanium alloy fatigue performance test specimen with holes according to claim 3, characterized in that, The hole machining inspection method for the titanium alloy fatigue performance test specimen with holes further includes grinding the chamfers at both ends of the precision-milled hole using the controlled grinding medium, resulting in a step after the hole machining step: The machining hole and gauge length are cut along a direction perpendicular to the length of the sample and passing through the diameter of the machining hole to obtain a cutting surface; The cut surface was examined under a microscope at a magnification of at least 400 times; If the cut surface shows foreign object embedding, cracks, tears, or white layer, the product will be rejected. Acceptance is granted if the cut surface exhibits tensile, peeling, or corrosion pits with a size ≤2μm. Acceptance is granted if the cut surface exhibits a surface deformation layer and the deposit layer size is ≤5μm.

8. The method for inspecting the hole processing of a titanium alloy fatigue performance test specimen with holes according to claim 3, characterized in that, The hole machining inspection method for the titanium alloy fatigue performance test specimen with holes further includes grinding the chamfers at both ends of the precision-milled hole using the controlled grinding medium, resulting in a step after the hole machining step: The residual stress on the inner wall of the machined hole is tested, and the range of the residual stress on the inner wall of the machined hole is 100 to 300 MPa.

9. The method for inspecting the hole processing of a titanium alloy fatigue performance test specimen with holes according to claim 3, characterized in that, The hole machining inspection method for the titanium alloy fatigue performance test specimen with holes further includes grinding the chamfers at both ends of the precision-milled hole using the controlled grinding medium, resulting in a step after the hole machining step: The machined holes are subjected to fracture fatigue tests. If cracks originate from machining damage, the holes are rejected.

10. The method for inspecting the hole processing of a titanium alloy fatigue performance test specimen with holes according to any one of claims 6-9, characterized in that, The hole machining inspection method for the titanium alloy fatigue performance test specimen with holes also includes: If any sample in a batch exhibits rejection characteristics in its machined hole, the entire batch of samples will be rejected. One sample is cut and inspected for each batch of samples. If the cut and inspection reveals rejection characteristics, an additional sample is cut and inspected for each batch of samples.

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