1 Introduction and objective

In cutting processes, the tool cutting edge is subject to high loads. These loads lead to wear on the tool, which determines the productivity of the process and the manufactured component surface quality. The shape and sharpness of the cutting edge is of decisive importance. Productivity and process reliability can therefore be increased by a knowledge-based design of the tool cutting edge.

For turning operations, the influence of the tool microgeometry on the tool wear was studied in detail by Basset and Denkena [2, 9, 10]. Basset deducted tool life maps for different workpiece materials, in which the influence of the tool microgeometry on the tool life was shown. TiAlN-coated carbide K30F inserts were used as tools. The applied cutting speeds were in the range of vc = 60 m/min to 300 m/min at a constant maximum uncut chip thickness of hcu,max = 0.2 mm. Basset observed that the tendency for crater wear increased for form-factors K > 1, while the tendency for flank wear increased for K < 1. An optimum cutting edge radius of rβ = 25–30 µm regarding wear resistance was determined. The results of Basset are consistent with the results of Enders, who investigated the influence of the cutting edge radius on tool wear during external cylindrical turning of C45E [13]. Deng showed that increasing the cutting edge radius up to a certain point leads to a reduction in initial wear and an increase in tool life [8]. Other studies on the tool microgeometry in turning were carried out by Coelho [7], Shintani [28], Denkena [11, 12], Özel [15, 22, 24, 25], Ventura [32], Al-Zkeri [1], Wyen [34], Fang [14], and Bergmann [3], among others. Due to the complex chip formations resulting from the multi-flank chip formation and the interrupted cut in gear hobbing, the results from turning cannot be transferred directly to gear hobbing.

The hobbing process has been studied many times in the past regarding tool wear. Most of the studies used the parameters resulting from the process data and the macrogeometry of the workpiece and hob for wear prediction. Especially the chip length and the chip thickness were used [5].

Karpuschewski used an FE analysis to explain the occurring wear phenomena when machining with carbide hobs [18]. He also investigated the influence of various tool macrogeometry parameters on the tool wear during hobbing [17]. Kühn investigated the influence of the effective tool angles on the wear behavior [19].

For gear hobbing, only few investigations on the influence of the cutting edge geometry on the tool wear have been reported. Lux used the fly-cutting trial as an analogy process to gear hobbing and investigated the influence of the cutting edge radius on the wear behavior. He carried out experiments with three different process parameter variations: vc = 80 m/min and hcu,max = 0.3 mm; vc = 80 m/min and hcu,max = 0.33 mm; vc = 120 m/min and hcu,max = 0.3 mm. For all process variations, cutting edge radii of rβ = 15 µm, rβ = 30 µm, and rβ = 50 µm were applied with a brass brush. In all trials, a larger cutting edge radius resulted in increased flank wear and thus a shorter tool life [20].

Winkel reported on the influence of the cutting edge radius on the wear behavior of TiAlN-coated K20 carbide fly-cutters. When machining 20 MnCrS5 case-hardening steel, the initial wear was significantly reduced by applying a radius of rβ = 15 µm compared to an almost ideally sharp tool with rβ ≈ 0 µm. In addition, an optimum range of cutting edge radius of rβ = 10–15 µm was found in fly-cutting trials. In particular, abrasive flank wear was reduced by an optimum cutting edge radius. The reasons given were a better coating resistance and less cutting edge chipping [33].

In addition to Winkel and Rech carried out investigations for optimized cutting edge radius. In the trials, TiAlN-coated S290 tools were used with two different preparation processes: flow grinding and sandblasting. The ground tools achieved higher tool life than the sandblasted tools. The cutting edge radius was varied from rβ = 5 µm to rβ = 30 µm. A tool life-optimized cutting edge radius was identified at rβ = 15 µm to rβ = 20 µm [26].

The compiled results regarding the influence of the cutting edge microgeometry on the cutting process confirm the high potential of cutting edge preparation to increase the tool life. Lux [20], Winkel [33], and Rech [26] only carried out investigations on the influence of the cutting edge radius on the wear behavior. Asymmetrical cutting edges with different form-factors K have not yet been investigated for hobbing.

It was shown that not only the influence of the cutting edge geometry on the wear behavior is of decisive importance for the performance of a hob cutting edge, but also the influence of the preparation process on the wear behavior [7]. Therefore, the objective of this report is to review the findings from other processes in hobbing and, building on the studies already conducted in hobbing, to identify the influence of the cutting edge radius, the form-factor K, and the preparation process on the wear behavior for hobbing with PM-HSS tools with AlCrN coating. The focus is on the interaction of the tool microgeometry with the coating thickness and its influence on the tool wear. An important factor that has not been investigated in detail before is the coating thickness distribution, which results from the PVD coating process. For this purpose, the cutting edge radius, the form-factor K, and the preparation process are varied. In fly-cutting trials, the influence of the variation parameters on the tool wear is investigated.

2 Materials and methods

2.1 Workpiece geometry and material

The gear used for the experiments is shown in Table 1. The workpiece has a normal module of mn2 = 2.557 mm, a number of teeth of z2 = 39, a pressure angle of αn2 = 17.5°, a helix angle of β2 = 23°, and a tip diameter of da2 = 116.2 mm. The material used was case-hardened steel 18CrNiMo7-6. The gear geometry is based on a typical automotive crankshaft gear.

Table 1 Gear geometry
Full size table

Figure 1 shows a micrograph of the workpiece material microstructure. The material 18CrNiMo7-6 had a ferritic-pearlitic microstructure. The chemical composition of the material, shown in Table 2, was determined by optical emission spectrometry (OES). An indentation hardness of 160 HV30 was measured on the material surface, which corresponds to a tensile strength of Rm = 510 MPa according to DIN EN ISO 18265 [21]

Fig. 1
figure 1

Workpiece material characterization

Full size image
Table 2 Chemical composition
Full size table

2.2 Tool geometry and preparation

The trials were performed using the fly-cutting process as analogy process to gear hobbing. Fly-cutting trials have already been used in several investigations [4, 16, 27]. The tool data are shown in Table 3. The tools used in these investigations were double-start, right-handed hobs with an outer diameter of da0 = 80 mm, a number of gashes of ni0 = 17, and a module of mn0 = 2.557 mm. The cutting substrate was a powder metallurgical high-speed steel (PM-HSS) S390, which was initially coated with AlCrN.

Table 3 Tool data
Full size table

The required fly-cutting tools were segmented from a common hob by wire erosion. After segmentation, the tools were de-coated and ground. The cutting edge was then treated by abrasive stream grinding. In this process, an abrasive fluid flows around the cutting edge. The cutting edge geometry can then be adjusted by changing the process setting like time, pressure, pressure change, and impact angle. After preparation, all fly-cutters were coated in the same batch with AlCrN. Figure 2 shows the SEM micrographs after the different preparation steps. In the uncoated, unprepared state, the cutting material appears brittle. The machining marks from the grinding process are clearly visible on the rake face and the flank. The cutting edge appears very sharp due to a low cutting edge radius. After abrasive stream grinding, the cutting edge radius was increased. The rounding is homogeneous along the cutting edge, and the machining marks from the grinding process are barely visible. After the coating process, the cutting edge rounding still appeared homogeneous. No further process steps were carried out to increase the coating quality, as, for example, in other studies [6]. The coating thickness was constant over the radius. White spots were observed on the tool, which can be attributed to coating defects. Since these defects only occurred in isolated cases on the surface, the tool quality was considered to be suitable for the experiments. All tools were examined optically at the beginning of the trials to ensure that only defect-free tools were used.

Fig. 2
figure 2

SEM micrographs of individual preparation steps of the tools

Full size image

The initial state of the tool is documented in Fig. 3. The roughness and coating thickness of the rake face and the clearance flanks (LF and TF) as well as the cutting edge roughness are shown. The coating thickness was s = 2.25 µm on the rake face and s = 1.63 µm or s = 1.94 µm on the clearance flanks. All values correspond to standard industrial values.

Fig. 3
figure 3

Tool characterization

Full size image

The fly-cutters, which are listed in the experimental design under the wet blasting preparation process, were used in the cutting trials after segmentation from the hob. The cutting edge preparation was carried out during the normal production process of the hob by the tool manufacturer using wet blasting. The wet blasting process is similar to the abrasive stream grinding process. However, in the wet process, the abrasive fluid is directed through a nozzle with compressed air onto the cutting edge. Thus, the fly-cutters, which were prepared by wet blasting, were not coated in the same batch as the fly-cutters prepared by abrasive stream grinding. However, the specification of the coating was identical.

2.3 Design of experiments

The tool wear investigations were carried out on a Liebherr LC180 hobbing machine. The fly-cutting process kinematic and the trial setup are shown in Fig. 4. In addition, a detailed view of a fly-cutter is shown on the right side of the image. For each trial the wear mark width was measured at the marked areas. The areas were divided into the leading flank LF-B, the transition of the leading flank to the tip LF-A, the tip T, the transition of the trailing flank to the tip TF-A, and the trailing flank TF-B. As wear criteria, a maximum permissible wear mark width of VBmax,perm = 150 µm and a maximum permissible crater depth of KTmax,perm = 100 µm were chosen. The wear criteria were adopted from previous studies [17, 28] which showed that exponential wear growth starts at these wear mark widths.

Fig. 4
figure 4

Experimental setup

Full size image

To investigate the influence of the cutting edge radius, the form-factor K, and the preparation process on the wear behavior, the experiments were designed according to Fig. 5. The tool microgeometry variation was introduced by the preparation process abrasive stream grinding. The corresponding trials were carried out with a cutting speed of vc = 200 m/min and a feed rate of fa = 2.5 mm, which corresponds to a maximum uncut chip thickness of hcu,max = 0.2 mm. All trials were conducted without cutting fluid. In this trial, the cutting edge radius and the form-factor K were examined full factorial within the manufacturing limits. The cutting edge radius was rβ = 10 µm, rβ = 18 µm, rβ = 22 µm, and rβ = 30 µm and the form-factor K = 0.3, K = 1, and K = 3.

Fig. 5
figure 5

Design of experiments

Full size image

In addition, the influence of the preparation process was examined for tools with rβ = 22 µm and K = 1 for two different cutting speeds vc = 150 m/min and vc = 200 m/min. The wet-blasted fly-cutters used were segmented from a hob. The abrasive stream ground fly-cutters were first separated, de-coated, and then rounded and coated. In contrast to the coating of individual cutter teeth, shading effects occur when coating the entire hob. Shading effects occur when the tool surface is not freely accessible from all directions. These effects lead to different coating thicknesses over the tool profile. Therefore, the results were mainly examined with regard to the coating thickness distribution.

2.4 Measuring strategy for the characterization of the cutting edge microgeometry

The profile of the cutting edge geometry was documented by means of tactile measurement at five positions on the leading flank, three at the tip, and five on the trailing flank; see Fig. 6. More measuring positions were defined at the wear-critical area at the tip and at the transition from the tip to the leading and trailing flanks. The advantage of a tactile measurement compared to an optical is that information about the cutting edge radius, the shape of the cutting edge, and the amount of wear can be determined even on worn cutting edges. Optical measuring systems showed deficiencies in the evaluation of worn cutting edges. Often, the system did not identify the correct edge, so that it was not possible to characterize the cutting edge.

Fig. 6 
figure 6

Measuring strategy for the characterization of the tool micro geometry

Full size image

3 Wear investigations in fly-cutting trials

3.1 Influence of the preparation process on the wear behavior

The trials were carried out for each preparation process at two different cutting speeds vc = 150 m/min and vc = 200 m/min. The axial feed was kept constant at fa = 2.5 mm for all trials. The workpieces were manufactured in climb cut and without cooling lubricant. For each fly-cutter, the maximum flank wear VBmax and the maximum crater depth KTmax for different areas along the tool profile were plotted over the machined length L; see Fig. 7. The machined length is the product of the number of teeth z2 and the width b2 of the workpiece divided by the cosine of the helix angle β2. The tool life LT is defined as the machined length after the tool wear has reached one of the wear criteria VBmax,perm. or KTmax,perm..

Fig. 7
figure 7

Wear curves of the differently prepared fly-cutters

Full size image

The abrasive stream ground fly-cutters reached the wear criterion due to flank wear in the TF-A area. With a cutting velocity of vc = 200 m/min, a tool life of LT = 19.1 m was achieved, and with a cutting velocity of vc = 150 m/min, a tool life of LT = 22.8 m was achieved. The wet-blasted fly-cutters reached the wear criterion due to flank wear in area TF-B after a tool life of LT = 11.4 m with vc = 200 m/min and a tool life of LT = 13.9 m with vc = 150 m/min. The characteristics of the wear curves at TF-A are comparable for abrasive stream ground and wet-blasted fly-cutters. The wear in the TF-A area is typical for HSS tools in the given process, since the largest chip lengths occur in this area [31]. Crater wear occurred on all fly-cutters. The crater initiation occurred earlier for the wet-blasted fly-cutters than for the abrasive stream ground fly-cutters.

The wear criterion was achieved by flank wear in different areas of the cutting edge. Especially the lower area of the trailing flank TF-B was not classified as wear-critical in previous research [30, 31]. For this reason, further analyses were carried out. Figure 8 compares the wear images of the trailing flank after reaching the wear criterion. The amount of wear of the wet-blasted fly-cutters increases continuously from tip to root until the largest amount of wear in the lower area occurs on the trailing flank. The flank wear of the abrasive stream ground fly-cutters did not show this amount of wear. At the abrasive stream ground fly-cutters, the wear of the flank increased from the root towards the tip.

Fig. 8
figure 8

Wear and coating thickness analysis

Full size image

To analyze the different wear behavior along the flank, the coating thickness of the fly-cutters was analyzed. The micrographs of the coating thickness in Fig. 8 were taken in the unused condition of the tool. The coating thickness of the abrasive stream ground fly-cutters had a comparable coating thickness of s = 1.54 µm to s = 1.91 µm along the entire tool profile. On the wet-blasted fly-cutters, the coating thickness decreased significantly from the tip towards the root until there is only a coating thickness of s = 0.74 µm in the lower area of the profile. This effect results from the line of sight characteristic of the PVD coating process. The coating process of a full hob results in the highest coating thicknesses at the tip. The coating thickness decreases at the clearance flank towards the root. The accessibility in the tooth root and the shading effects of adjacent teeth reinforce this effect. The analysis of the coating thickness provided an explanation for the unusual wear behavior. It was also shown that a uniform coating thickness is important for the achievable tool life.

3.2 Influence of the cutting edge radius rβ on the wear behavior

In this section the influence of the cutting edge radius rβ on the wear behavior of fly-cutters is analyzed. For this purpose, fly-cutters with different cutting edge radii were prepared by abrasive stream grinding. The measured cutting edge radii were classified into rβ = 10 µm, rβ = 18 µm, rβ = 22 µm, and rβ = 30 µm after the coating process. The form-factor was symmetric for all tools with K = 1. For the fly-cutters with a cutting edge radius of rβ = 10 µm, rβ = 22 µm, and rβ = 30 µm, the initial condition of the tools was documented with SEM micrographs; see Fig. 9. Several fly-cutters were prepared for the respective tool microgeometry in the same batch, and the coating was also applied to all tools in the same batch. Thus, the initial conditions for the respective tool microgeometry are comparable. The different cutting edge radii are clearly visible in the images. All tools have a homogeneous and defect-free cutting edge along the entire tool profile. In some cases, small coating defects in the form of small white dots are visible on the rake face and flank. However, the tool defects did not occur over a large area and only occurred with a low frequency. Therefore, the tools were used in the trials.

Fig. 9
figure 9

Initial condition of fly-cutters with different cutting edge radii rβ

Full size image

Figure 10 shows the wear curves for the different cutting edge radii. For each fly-cutter, the maximum flank wear VBmax and the maximum crater depth KTmax for different areas along the tool profile were plotted over the machined length L. The process parameters were kept constant with vc = 200 m/min and fa = 2.5 mm. Machining took place without cooling lubricant.

Fig. 10
figure 10

Wear curves for variation of the cutting edge radius rβ

Full size image

The characteristics of the wear curves are comparable for the fly-cutters with different cutting edge radii. At the beginning of the cutting process, an initial wear of VBmax ≈ 50 µm occurred. This was followed by a linear uniform increase in wear up to a machined length of L = 16.5 m, from which the exponential wear range or exceeding of the wear criterion was reached. The wear criterion was reached after a machined length of Lrβ=10 = 20.3 m, Lrβ=18 = 17.8 m, Lrβ=22 = 19.1 m, and Lrβ=30 = 17.8 m. For all tools, the wear criterion was achieved by flank wear at area TF-A. Also, the distribution of the wear on the trailing flank, the tip area, and the leading flank was comparable for all tools. The lowest wear always occurred on the leading flank. Crater wear occurred for all tools on the rake face in the TF-A area, but did not lead to tool failure. Based on the wear curves, no clear influence on the wear behavior of the fly-cutters could be observed by varying the cutting edge radius. Effects of higher wear due to higher tool loads with larger cutting edge radii, which were demonstrated by Ozturk [23], could not be observed.

Figure 11 shows the tactile measurement of the cutting edge of the tool with rβ = 22 µm and K = 1. The cutting edge was measured at five positions. On the left, the tool is shown in its initial state. The cutting edge radii and form-factors vary only slightly over the five positions. After L = 10.2 m machined length, the cutting edge is recessed at all positions due to flank wear along the entire tool profile. With the exception of the tip area, the cutting edge radii have significantly smaller values than at the beginning. The form-factors also change significantly in some cases. At position 2, the form-factor is doubled, while it drops from K = 1.1 to K = 0.4 at position 5.

Fig. 11
figure 11

Cutting edge geometry after defined machined lengths at the tool with rβ = 22 µm and K = 1

Full size image

After reaching the end of the tool life at L = 19.1 m, the cutting edge offset is even more visible at all positions. The radii remain very low at all positions with the exception of position 4, where the radius increases. Here a superposition of flank and crater wear occurred.

Figure 12 shows the wear appearance after reaching the wear criterion of the fly-cutters with K = 1 and rβ = 30 µm. SEM micrographs of the leading flank, the tip area, and the trailing flank are shown.

Fig. 12
figure 12

SEM micrographs of the fly-cutters with a cutting edge radius rβ = 30 µm

Full size image

Material adhesion can be seen on the rake face and on the flank. The tool profile is clearly worn over the entire flank. In [29], it was shown that wear on the cutting edge of the tool is cyclical. The adhesion of the material to the cutting edge facilitates increased abrasion. The resulting coating delamination leads to adhesion of the new material again [29]. The cutting edge was reset along the entire tool profile due to flank wear. Crater wear only occurred on the rake face in the transition from the trailing flank to the tip area. In this area, however, the crater wear was formed from the cutting edge towards the center of the rake face, as a result of which the cutting edge was also reset on the rake face due to crater wear. The wear along the tool profile was similar for all cutting edge radii. Therefore, no influence of the cutting edge radius on the wear behavior could be shown on the wear images. Overall, no influence on the wear behavior could be identified by varying the cutting edge radius. The analysis of the wear curves and the wear images could not reveal any clear differences. All tests showed an offset of the cutting edge with the occurrence of flank wear and thus the formation of a new cutting edge with a small cutting edge radius. The same behavior can be related to the fact that all test results showed an offset of the cutting edge when flank wear occurred, resulting in the formation of a new cutting edge with a small cutting edge radius.

3.3 Influence of the form-factor K on the wear behavior

To analyze the influence of the form-factor K on the wear behavior, three fly-cutters were examined. They were prepared with a symmetrical microgeometry (K = 1) and two asymmetrical microgeometries, one displaced to the rake face (K < 1) and one to the flank (K > 1). After the coating process, the fly-cutter was classified into K = 0.3, K = 1, and K = 3. The target value for the cutting edge radius was rβ = 18 µm for all tools. The prepared and coated state of the fly-cutter was documented with the help of SEM micrographs and compared in Fig. 13. The images show the leading and trailing flanks of each fly-cutter.

Fig. 13
figure 13

Initial condition of the fly-cutters with different form-factors K

Full size image

The different tool microgeometries of the cutting edge can be seen in the SEM micrographs. In the case of the fly-cutter with K = 0.3, the cutting edge is displaced towards the rake face, in the case of the fly-cutter K = 1, there is a symmetrical cutting edge, and in the case of the tool with K = 3, the cutting edge is displaced towards the clearance face. The cutting edge of all tools is homogeneously and defect-free prepared along the tool profile. Figure 13 shows partially small coating defects in the form of small white dots on the rake and clearance surfaces. However, the tool defects did not occur over a large area and only with a low frequency. Therefore, the tools from the respective batches were used in the trials.

The wear behavior of the fly-cutters with different form-factors is shown in Fig. 14. All tools reached the wear criterion by flank wear at TF-A. The fly-cutter with a form-factor of K = 3 reached the wear criterion after N = 13 workpieces, which corresponds to a tool life of LT = 16.5 m. Using the fly-cutters with K = 1 and K = 0.3, N = 14, workpieces could be machined before the wear criterion was reached, which corresponds to a tool life of LT = 17.8 m. In the wear-critical area AF-A, differences can be seen in the course of the maximum flank wear. The higher the form-factor K, the higher the initial wear. The stable operating phase (linear range) is reached earlier but also with a higher initial wear. The slope of the linear range is comparable between the tools. All fly-cutters reached the exponential wear range after a comparable machined length. Crater wear occurred with all tools on the rake face at TF-A, which however did not lead to tool failure. Cutting edge chipping did not occur in the trials.

Fig. 14
figure 14

Wear curves for variation of the form-factor K

Full size image

For the two fly-cutters with the biggest difference in microgeometry, K = 0.3 and K = 3, SEM micrographs of the leading flank, the tip area, and the trailing flank were taken after the wear criterion was exceeded, see Figs. 15 and 16. On both fly-cutters, material adhesion can be seen on the rake and clearance surfaces. The flank wear of both tools occurred continuously along the entire tool profile. The cutting edge was set back along the entire tool profile due to flank wear. Surface breakage on the rake face did not occur. No major differences in the forms and amounts of wear were apparent between the two tools.

Fig. 15
figure 15

SEM images of the tool with the form-factor K = 3

Full size image
Fig. 16
figure 16

SEM images of the tool with the form-factor K = 0.3

Full size image

In addition to the described fly-cutting trials, further fly-cutters were used in the design of experiments. The achieved tool life is shown in Fig. 17. The largest tool life with LT = 20.3 m was achieved with a tool microgeometry of rβ = 10 µm and K = 1.

Fig. 17
figure 17

Summary of all wear curves for micro geometry variation

Full size image

In general, the best results were achieved with a symmetrical cutting edge (K = 1). The initial wear was the lowest regarding all test points, and the range of linear wear growth was the longest with a low gradient. With a high form-factor of K = 3, 7–25% shorter tool lives were achieved. This is mainly due to the fact that the slope in the linearly growing wear section was higher and thus no stable cutting edge was formed. A small form-factor with K = 0.3 could only be produced for small cutting edge radii due to limitations resulting from the manufacturing process. For the trial point with a cutting edge radius of rβ = 10 µm, a smaller tool life was achieved with a low form-factor K = 0.3. For a radius of rβ = 18 µm, this effect could not be proven. An influence of the cutting edge radius on the wear behavior could not be verified by the trials.

In summary, the variation of the form-factor has shown a small influence on the wear behavior along the machined length. The tools with a high form-factor K = 3 reached the shortest tool life until the wear criterion was exceeded. The fly-cutters with the low form-factor achieved shorter or similar tool lives than the tools used with a symmetrical cutting edge (K = 1). An influence of the cutting edge radius on the wear behavior could not be identified.

4 Summary and outlook

The influence of the cutting edge geometry was analyzed in fly-cutting trials. For this purpose, PM-HSS tools with a normal module of mn0 = 2.557 mm with constant, industry-standard process parameters were used. The cutting velocity was vc = 200 m/min and the axial feed with fa = 2.5 mm for all trials. The workpieces made of 18CrNiMo7-6 were machined without cooling lubricant. The cutting edge radius was varied in the steps rβ = 10 µm, rβ = 18 µm, rβ = 22 µm, and rβ = 30 µm and the form-factor in the steps K = 0.3, K = 1, and K = 3. The variation of the form-factor showed a minor influence on the wear behavior of the fly-cutters. The tools with a high form-factor K = 3 achieved the shortest tool life. Fly-cutters with a low form-factor K = 0.3 achieved shorter to similar tool lives than tools with a symmetrical cutting edge form-factor K = 1. An asymmetric cutting edge resulted in higher initial wear or a shorter or more increasing linear wear growth range. Overall, tool lives of LT ≥ 14 m could be achieved. An influence of the cutting edge radius on the wear behavior could not be identified. The cutting edge was reset by flank wear in all trials. The influence of the preparation process on the wear behavior was mainly attributed to the coating thickness distribution. In this context, it was shown that a sufficient and uniform coating thickness is of fundamental importance for good wear protection.

For the results presented in this report, the experimental data basis will have to be increased in the future so that the identified effects can be statistically verified. Furthermore, the tool microgeometry in the form of cutting edge radius and form-factor must be further investigated in future work. In particular, the machining of the common gear materials 16MnCr5, C45, and 42CrMo4 with PM-HSS tools with and without the use of cooling lubricant holds great potential for increasing tool performance. The investigation of alternative cutting materials such as carbide or Fe-Co-Mo also suggests high potential. With a larger database, the cutting edge geometry of the tools can be designed in a process-oriented manner in the future, and longer tool lives can be achieved.