BE1031525B1 - ORBITAL FRICTION WELDING PROCESS OF BLADES ON A TURBOMACHINE ROTOR WITH OPTIMIZED PARAMETERS - Google Patents

Abstract

The invention provides a method for joining a blade (4) to a stub (6) on a turbomachine rotor (2), by orbital friction welding, comprising the following steps: determining welding parameters for a given section (11) at the junction (10), comprising an eccentricity, a frequency and a pressure; orbital friction welding of the blade to the stub with the determined welding parameters; remarkable in that the determination of welding parameters comprises a determination of transverse forces at the junction and a selection of the eccentricity and the frequency so as to limit said transverse forces, on the basis of a rule according to which a decrease in the frequency causes a decrease in said transverse forces and an increase in the eccentricity causes a decrease in said transverse forces and vice versa.

Description

Description

ORBITAL FRICTION WELDING PROCESS OF BLADES ON A

TURBOMACHINE ROTOR WITH OPTIMIZED PARAMETERS

Technical field

The invention relates to a method of friction welding blades to a turbomachine rotor, and more particularly to a method of orbital friction welding blades to a turbomachine rotor disk, so as to form a turbomachine bladed disk.

Prior art

Climate change is a major concern for many legislative and regulatory bodies around the world. Indeed, various restrictions on carbon emissions have been, are being or will be adopted by various states. In particular, an ambitious standard applies both to new types of aircraft but also to those in circulation requiring the implementation of technological solutions in order to make them compliant with current regulations. Civil aviation has been mobilizing for several years now to make a contribution to the fight against climate change.

Technological research efforts have already made it possible to significantly improve the environmental performance of aircraft. The Applicant takes into consideration the impact factors in all phases of design and development to obtain less energy-intensive, more environmentally friendly aeronautical components and products whose integration and use in civil aviation have moderate environmental consequences with the aim of improving the energy efficiency of aircraft.

Consequently, the Applicant is constantly working to reduce its negative climate impact by using methods and operating virtuous development and manufacturing processes and minimizing greenhouse gas emissions to the minimum possible in order to reduce the environmental footprint of its activity.

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This sustained research and development work covers new generations of aircraft engines, the weight reduction of aircraft, particularly through the materials used and the lighter on-board equipment, the development of the use of electrical technologies to provide propulsion, and, as an essential complement to technological progress, aeronautical biofuels.

To this end, the invention is the result of technological research aimed at significantly improving the performance of aircraft and, in this sense, contributes to reducing the environmental impact of aircraft.

In this context, the invention relates to an orbital friction welding method for producing a bladed disk (commonly referred to as: "blisk") or a bladed drum (commonly referred to as "blum") for a turbomachine compressor.

Orbital friction welding is a welding process in which the parts to be assembled are brought into contact under stress and welded by a circular motion generally defined by an eccentric, and accompanied by a uniform tangential speed, so as to generate friction and homogeneous heating at a weld junction between the two parts.

It is also known to use linear friction welding, this is a welding process in which the necessary heat is created by a back and forth movement of the interfaces to be welded. However, orbital friction welding has several advantages over linear friction, for example, the relative movement between the two interfaces is continuous thanks to the circular friction movement, which provides better thermal homogeneity. Unlike linear movement for which the relative speed of the two parts becomes zero at each half-oscillation period. In addition, the cycle time of orbital welding is considerably lower than that of linear friction welding (respectively approximately 2 minutes compared to approximately 5 minutes).

Published patent document EP 2 535 516 A1 discloses a method of orbital friction welding of blades to a turbomachine rotor, in which, once a

3 BE2023/5299 material consumption is reached, the orbital motion is stopped at a reference position, and a forging force is exerted on the blade against the rotor in order to form the weld.

However, the orbital welding process disclosed in the document has room for improvement. Indeed, it may require better control of the welding parameters in order to obtain a welded junction between the blade and the rotor that is sound, by means of a robust welding process.

Summary of the invention

Technical problem

The invention aims to solve at least one of the problems posed by the prior art. More specifically, the invention aims to propose a simple solution for obtaining a weld of the blade to the rotor, which is sound and free of structural defects.

Technical solution

The present invention relates to a method of joining a blade to a stub on a turbomachine rotor, by orbital friction welding, comprising the following steps: determining welding parameters for a given section of

Blade and stump at the junction, comprising an eccentricity, a frequency and a pressure; orbital friction welding of the blade to the stump with the determined welding parameters; remarkable in that the determination of welding parameters comprises a determination of transverse forces at the junction and a selection of the eccentricity and the frequency so as to limit said transverse forces, based on a rule according to which a decrease in the frequency causes a decrease in said transverse forces and an increase in the eccentricity causes a decrease in said transverse forces and vice versa.

Advantageously, the pressure corresponds to a pressure applied during an orbital movement of the orbital friction weld.

4 BE2023/5299

According to an advantageous embodiment of the invention, the determination of the transverse forces is based on the eccentricity, the frequency, the forging pressure and the section of the blade and the stump at the junction.

According to an advantageous embodiment of the invention, the determination of the transverse forces is made by means of a modeling of said transverse forces as a function of the eccentricity, the frequency, the pressure and the section of the blade and the stump at the junction, said modeling comprising a numerical simulation. Preferably, the pressure corresponds to the pressure applied during the orbital movement.

According to an advantageous embodiment of the invention, the modeling is based on experimental results of orbital friction welding junction.

According to an advantageous embodiment of the invention, the determination of the transverse forces is based on a geometric parameter z of the section of the blade and the stump at the junction, where z is an average of the mean radii Zi sweeping said section at any point / of the periphery of said section.

According to an advantageous embodiment of the invention, the determination of the transverse forces is based on a material consumption rate during orbital friction welding.

According to an advantageous embodiment of the invention, the material consumption rate is determined as a function of the eccentricity, the frequency, the pressure and the geometric parameter z.

According to an advantageous embodiment of the invention, the material consumption rate is measured during a parameterization orbital friction welding.

According to an advantageous embodiment of the invention, the pressure used during the parameterization orbital friction welding corresponds to a pressure applied during the orbital movement of the orbital friction welding of the blade to the stump with the determined welding parameters.

According to an advantageous embodiment of the invention, the parameterization orbital friction welding comprises an evaluation of the quality of the welded joint.

According to an advantageous embodiment of the invention, orbital friction welding of the blade to the stump with the determined welding parameters comprises a measurement of an actual eccentricity and/or actual transverse forces by means of data acquisition. 5 According to an advantageous embodiment of the invention, the section of the blade and the stump at the junction is between 200 mm? and 7000 mm.

According to an advantageous embodiment of the invention, the section of the blade and the stump at the junction is between 2000 mm? and 3000 mm°.

According to an advantageous embodiment of the invention, the frequency comprises a speed of rotation of the blade around an axis of the junction.

The measures of the invention are advantageous in that the determination of the welding parameters including the determination of transverse forces at the junction, makes it possible to effectively minimize said transverse forces while optimizing the eccentricity and the frequency, in order to obtain an actual eccentricity measured at the welded section which is closer to the controlled eccentricity, i.e. input setpoint defined by the method to ensure orbital welding.

The optimum welding parameters determined by the process allow, prior to the manufacture of the bladed disc, to ensure an optimization of the shape and dimension of the junction section, which allows the obtaining of a homogeneous material mixing during welding so as to improve the material health at the welded junction.

Thus, the bladed disc obtained by orbital welding of the blades to the stubs according to the method of the invention, advantageously comprises junctions free from any defect and having overall improved structural and dimensional quality.

The invention is also advantageous because it makes it possible to optimize the shape of the welded blades and therefore to reduce the mass of the bladed disk, resulting in a reduction in manufacturing costs, and in a reduction in the total mass of the turbomachine, which translates into a reduction in greenhouse gas emissions.

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It is understood that each detail of an embodiment below can be combined with each other detail of the other embodiments.

Brief description of the drawings

Figure 1 schematically represents a perspective view, during orbital friction welding, of a blade to a stub of a turbomachine rotor;

Figure 2 schematically illustrates a section of the blade and/or stump at the junction visible in Figure 1;

Figure 3 illustrates the junction section of Figure 2 when determining a mean radius Za sweeping said section from a point A on the periphery of said section;

Figure 4 illustrates the junction section of Figure 2 when determining a mean radius zs sweeping said section from a point B on its periphery.

Detailed description of the embodiments

In the following description, the terms “internal” and “external” refer to a positioning relative to the axis of rotation of an axial turbomachine.

The axial direction corresponds to the direction along the axis of rotation of the turbomachine, with lengths measured axially. Widths are measured circumferentially. The radial direction is perpendicular to the axis of rotation. Upstream and downstream refer to the main flow direction of the flow in the turbomachine.

The dimensions of the figures are not to scale and in particular the thicknesses or radial dimensions are exaggerated to facilitate reading of the figures.

Figure 1 schematically represents a perspective view, during orbital friction welding, of a blade 4 to a stub 6 of a turbomachine rotor 2.

The rotor 2 corresponds to a rotor disk 2 comprising an annular row of stubs 6 extending radially outwardly from an external surface 8 of the rotor 2.

The present invention proposes a method of joining the blades 4 to the stubs 6 so as to allow the manufacture of a bladed disk for a turbomachine.

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Preferably, the bladed disc is a mobile wheel intended to be arranged upstream of an air flow separation nozzle in a turbomachine.

For this purpose, the external surface 8 corresponds to an air guiding surface of a fluid stream along the turbomachine. Alternatively, the bladed disk may correspond to a drum-type rotor belonging to a high-pressure or low-pressure compressor.

Preferably, the bladed disk is a so-called “bi-material” disk comprising two different titanium alloys. For example, the blades 4 can be made from a Ta6v alloy, and the rotor disk 2 from one of the following alloys: Ti17, Ti575, Ti1023.

Advantageously, the mixture of the two different titanium alloys (Ta6v and Ti17) presents easier machinability, and makes it possible to achieve a gain in mass compared to a solution based, for example, solely on a Ti17 alloy, this is notably due to a density of Ta6v which is slightly lower than that of Ti17.

In fact, the Ti17 alloy was preferentially chosen for the disc part for its good HCF fatigue characteristics (English acronym for: “High Cycle

Fatigue”) and LFC (“Low Cycle Fatigue”). A Ti17 disc will also show a greater margin in burst speed than a Ta6v disc.

For the blades, the Ta6v alloy was chosen because it provides the blades with a higher elongation at break (better impact resistance), and better crack propagation behavior which results in better durability to low energy impacts.

The blade 4 is welded to the stub 6 by means of a joining section 11 corresponding to a contact interface during orbital welding. In this regard, the blade 4 is moved circularly about an axis A by an orbital oscillation movement 14, the axis A extending radially from a center of the joining section 11 of the stub 6. Preferably, each of the blade 4 and the stub 6 comprises the joining section 11 identically.

Preferably, the orbital oscillation movement 14 is uniform and has an eccentricity corresponding to a tangential deviation (coplanar to the section 11) between a center of the junction section 11 of the blade 4 and the axis A.

8 BE2023/5299

Prior to orbital friction welding by means of the orbital oscillation movement 14, a sacrificial volume of material (extending essentially radially) is provided on each of the blades 4 and the stubs 6 to be assembled. This sacrificial volume is caused to be extruded outside the contact interface between the two junction sections S, thus forming a burr, commonly referred to as: "flash", which will then be removed, preferably, by machining, in order to arrive at the final section (corresponding to the aerodynamic profile 4.1 of the blade 4) to form the bladed disk.

The blade 4 may comprise a lower end 4.4 provided with a reinforcement 4.5 which will be machined after the welding operation together with a volume 6.1 of reinforcement of the stump 6 on the disk 2.

Preferably, the junction section 11 of each of the blades 4 and stub 6 comprises a total surface area greater than or equal to 500 mm° and less than or equal to 7000 mm”, and more preferably between approximately 2000 mm? and 3000 mm? (the term “approximately” corresponding here to +10% of the nominal value).

In this configuration, [the tooling performing the orbital welding is subjected to greater mechanical stress.

The inventors were able to determine a difference between the actual eccentricity measured during orbital welding of large sections, and the controlled eccentricity, i.e. the instruction given to the machine to ensure said orbital welding. Such a difference is synonymous with an undesirable deformation of the blade 4 and the stump 6 which is due to poor mixing of the material of the stump with that of the blade at the right of the junction section, caused essentially by high transverse forces.

The method of joining the blades 4 to the stubs 6 of the present invention makes it possible to minimize the transverse forces. In this regard, said method comprises a step of determining the following welding parameters:

Eccentricity; frequency (including the oscillation speed of the orbital motion); and the pressure applied during the maximum axial consumption phase during the orbital motion, these parameters correspond to instructions that can control the orbital welding.

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Figure 2 schematically illustrates section 11 at the junction 10 between blade 4 and stub 6 visible in Figure 1.

The illustrated section 11 corresponds to an initial modeling of the junction section 11, the latter being modeled from an aerodynamic profile 4.1 of the blade 4, preferably, with a section widening by means of an excess thickness e corresponding, more preferably, to the eccentricity e of the orbital oscillation movement.

Preferably, the excess thickness e is homogeneous and omnidirectional along the entire periphery of the profile 4.1, however, said excess thickness e may vary around the profile and/or be higher in places, in particular at the leading edge 4.2 and/or the trailing edge 4.3 of the profile 4.1. The widening of the section 11 by the excess thickness e may be carried out manually using modeling software, or in an automated manner by a specific computer algorithm.

During welding, the flash may cause material recirculation within the narrowest regions of the contact section 11 and may create recesses in the welded joint, which is detrimental to the quality of the weld. Advantageously, the widening of the section 11 by means of the eccentricity e makes it possible to avoid the recirculation of the material (potentially harmful because it prevents the evacuation of impurities) towards narrower regions of the section of the final aerodynamic profile 4.1 of the blade and thus to ensure thermal homogeneity during the mixing of the material during welding, precisely in the final section 4.1 of the blade 4. Indeed, if an excess thickness e is added at least equal to the value of the eccentric, this means that the points of the final aerodynamic surface 4.1 are always in contact during welding (between the stump and the blade). Unlike the points in this excess thickness e which, by the orbital movement, are in contact with the opposite surface only during part of the orbit.

Preferably, the determination of the welding parameters comprises, according to a first embodiment of the invention, the production of a first parameter weld, using the modeled section 11, said weld can, for example, be carried out by means of test specimens which will be welded

10 BE2023/5299 with the same tooling as that used to weld the bladed disc. In this regard, an initial and/or preliminary choice of the eccentricity e, the frequency and the pressure is made.

The parameterization weld makes it possible to determine for the modeled section 11, by means of a measurement by data acquisition directly on the machine during welding, the transverse forces and/or the actual eccentricity, and more preferably makes it possible to determine a material consumption rate VCA (which can be expressed in mm/s) presented at the level of the contact interface between the two sections 11.

The inventors observed that decreasing the eccentricity and increasing the oscillation frequency makes it possible to reduce the transverse forces, and this according to a hypothesis (without being limited by a particular theory) according to which: during orbital welding, and when all things being equal, the higher the rotation frequency of the welding tool, the greater the transverse forces at the joint will be, and that, all things being equal, the greater the eccentricity, the less the transverse forces at the joint will be. In other words, eccentricity and frequency have an inverse effect on the transverse forces at the joint during orbital friction welding.

Indeed, this inverse effect is present when the friction speed is constant, it is the tangential speed v of the orbital movement, defined according to the equation: v=2.n.e.f

Where f corresponds to the oscillation frequency; e corresponds to the value of the eccentric.

Thus, at an unchanged speed v and surface to be welded, if we reduce e by increasing f to keep the product e.f = cte, we increase the transverse forces.

Conversely, if we increase e by decreasing f, while keeping the product e.f = cte, we reduce the transverse forces.

Following the parameter welding, the eccentricity is increased, preferably by an interval of between 5% and 50% more than the initial value of said eccentricity, and the frequency is decreased.

11 BE2023/5299 preferentially inversely to the eccentricity (a decrease of between 5% and 50% less compared to the initial frequency), and the pressure applied during welding remains constant.

In this configuration, the increase in eccentricity advantageously involves modifying the modeling of section 11, by applying a new excess thickness equal to the new value of the increased eccentricity.

One or more parameter welds can be made, each time modifying the eccentricity, the shape of the section 11 and the frequency, until reaching a real measured transverse force value which is lower by a certain percentage (predefined according to the need) compared to the transverse force value measured during the first parameter weld.

Preferably, the welding parameters are retained (to be used when welding the blade to the stump) for any reduction in transverse forces between 1% and 30%.

A decrease in transverse forces of more than 30% is accompanied by a high increase in eccentricity, and therefore in the excess thickness of the junction section.

Advantageously, the VCA speed remains unchanged following the different parameter welds.

An assessment of the quality of the junction(s) obtained by the parameterization weld(s) can be carried out, for example, by means of a micrographic section of the junctions.

The parameter welds make it possible to estimate the transverse forces from the modeling of the junction section.

According to a second embodiment, and in order to further improve the precision of the determination of the welding parameters, the transverse forces are preferably determined as a function of a geometric parameter z of the junction section 11.

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Indeed, the first modeled section 11 comprising the initial eccentricity e further comprises, according to the second embodiment, the measurement of the geometric parameter z which corresponds to an average of the mean radii Zi sweeping said section 11 at any point i of its periphery 11.

Each of the mean rays z; corresponds to an average length Zi of rays

Zia Extending entirely in the section 11 from a point / to its periphery 11.1 and sweeping said section 11. Preferably, the Zia rays correspond to projections of the point / onto an entire portion of the periphery 11.1 which is opposite said point /. In this regard, the determination of the geometric parameter z comprises the determination of the mean radius z; for the plurality of points i on the entire periphery 11.1.

Advantageously, the evolution of the mean radii z; on the periphery of the section 11 to be welded physically represents the homogeneity of the length to be sheared during rotation (orbital movement during welding) and therefore the homogeneity of the material flow expelled in the flash along the contour of the blade. It is representative of the homogeneity of ejection of contaminants from the weld.

The geometric parameter z allows to take into account the specificities of orbital friction welding in the manufacturing process. Indeed, the friction force provided during welding rotates cyclically, which implies that a weld point at the end of section 11 (e.g. point A or B) sees a fraction of section 11 of the blade between the two extreme projected radii (ZA,a OR ZB,a), the latter can therefore be assimilated to equivalent lengths of material to be sheared.

Preferably, the determination of the geometric parameter z is an automated process using a computer algorithm. In this regard, an algorithm of the “ray tracing” type can be adapted.

Figures 3 and 4 illustrate an example of projection of rays ZAa and Ze, respectively, from points A and B of the periphery 11.1.

Figure 3 illustrates section 11 when determining a mean radius za — scanning said section 11 from a point A of the periphery 11.1.

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It can be seen that from point A, a plurality of rays Za are projected onto a portion of the periphery 11.1 visible from said point A. In this configuration, the rays zac can be included between two rays Zaa tangent to the periphery 11.1.

The number of projected rays Za,a may depend on the chosen angle a, the latter allows to establish the precision of determination of the mean radius za. For this purpose, the angle a may be between 0.001° and 10°.

The mean radius za thus corresponds to the average of all the projections ZA, a.

Figure 4 illustrates section 11 when determining a mean radius Ze sweeping said section 11 from a point B of the periphery 11.1.

Preferably, the angle a is identical for all projections of the rays

Zia for the plurality of points / of the periphery 11.1. Preferably, the number of points / of the periphery 11.1 from which the rays will be projected, is approximately 2000 points, this number being able to vary according to the desired calculation precision.

Similarly to point A, the rays Ze, are projected from point B onto a portion of the periphery 11.1 visible at said point B. The mean radius ze corresponds to the average of all the projections Z8,a.

The geometric parameter z is therefore the average of all the mean radii Zi (including the mean radii za and ze) of the points i of the entire periphery 11.1.

The geometric parameter z corresponds to a geometric dimension that can be expressed in mm. Advantageously, this parameter z is the optimal dimension that best distinguishes the geometric shape of the section 11 and thus ensures a precise correlation between the welding parameters and/or the VCA speed with the transverse forces.

Indeed, the surfaces of section 11 comprising the projected rays Zia from each point i can be assimilated to the mixing surface of the material during orbital welding (without being limited by a particular theory). In addition, the parameter z is relevant because it allows to take into account more the

14 BE2023/5299 camber of the specific shape of the periphery 11.1, better than the area of said section 11 or the chord of its profile.

After each parameterization weld and/or modification of the excess thickness e of the modeled section 11, the corresponding new geometric parameter z will be recalculated. Indeed, a modification of the eccentricity e implies the modification of the parameter z.

Similar to the first embodiment, one or more parameter welds can be made, by modifying each time the eccentricity, the shape of the section 11 and the frequency, until reaching a measured actual transverse force value which is at least 1% lower than the first parameter weld. So as to retain the welding parameters ensuring a reduction in transverse forces of between 1% and 30%.

According to the second embodiment, the parameter welds make it possible to establish, by correlation, a modeling of the transverse forces allowing them to be determined using the following equation:

Fr=k.z2. PD. 8. Pat +j

In which j, k, a, b, c and d are constants dependent on the machine and the tools; z corresponds to the calculated geometric parameter z (can also be replaced by the value of the section); f corresponds to the oscillation frequency; e corresponds to the eccentric; and P2 corresponds to the pressure exerted on the junction during the orbital movement of the orbital welding of the blade with the stump, the pressure P2 results from an initiation effort of a material consumption phase, this is the phase in which the transverse force is the greatest.

Preferably, the pressure P:2 used during the experimental tests is also used, unchanged, when welding the blade to the stump.

Advantageously, the equation established empirically according to the second embodiment makes it possible to precisely estimate the efforts

15 BE2023/5299 transverse from the modeling of the bladed disc, and prior to its manufacture.

Alternatively, the determination of the transverse forces is based on the material consumption rate VCA, the latter corresponding to an analytical estimate that can be determined based on the welding parameters (eccentricity, frequency and applied pressure) and the geometric parameter z of the section. A correlation between these different parameters and the VCA speed is advantageously carried out during parameterization welds, in particular following the correlation between the actual measured VCA speed and said parameters, so as to determine a relationship between the transverse forces and the VCA speed when welding the blade with the stump.

To this end, the said relationship allows us to establish that an increase in eccentricity implies a modification of the geometric parameter z and of the VCA speed, followed by a decrease in transverse forces.

Orbital friction welding of the blade to the stump with the welding parameters determined by the process, advantageously includes a measurement of the actual eccentricity and the actual transverse forces by a measurement at the blade and stump section during welding, by means of data acquisition. This allows the weld to be monitored and validated.

Advantageously, the method of joining the blade to the stump according to the invention makes it possible to define the optimal welding parameters in order to effectively minimize the transverse forces and to improve the material health at the welded junction, and this prior to the manufacture of the bladed disk, so as to make it possible to ensure optimization of the shape and dimension of the junction section.

Thus, the bladed disc obtained by orbital welding of the blades to the stubs according to the process, advantageously includes junctions having an improved structural and dimensional quality.

Claims (14)

16 BE2023/5299 Claims 1. A method of joining a blade (4) to a stub (6) on a turbomachine rotor (2), by orbital friction welding, comprising the following steps: determining welding parameters for a given section (11) of the blade (4) and the stub (6) at the junction (10), comprising an eccentricity, a frequency and a pressure; orbital friction welding of the blade (4) to the stub (6) with the determined welding parameters; characterized in that the determination of welding parameters comprises a determination of transverse forces at the junction (10) and a selection of the eccentricity and the frequency so as to limit said transverse forces, on the basis of a rule according to which a decrease in the frequency causes a decrease in said transverse forces and an increase in the eccentricity causes a decrease in said transverse forces and vice versa. 2. Method according to claim 1, in which the determination of the transverse forces is based on the eccentricity, the frequency, the pressure and the section (11) of the blade (4) and the stub (6) at the junction (10). 3. Method according to one of claims 1 and 2, in which the determination of the transverse forces is made by means of a modeling of said transverse forces as a function of the eccentricity, the frequency, the pressure and the section (11) of the blade (4) and the stump (6) at the junction (10), said modeling comprising a numerical simulation. 4. The method of claim 3, wherein the modeling is based on experimental results of orbital friction welding joining. 5. Method according to one of claims 1 to 4, in which the determination of the transverse forces is based on a geometric parameter z of the section (1) of the blade (4) and of the stump (6) at the junction (10), where z is 17 BE2023/5299 an average of the mean radii z; scanning said section (11) at any point / of the periphery of said section (11). 6. Method according to one of claims 1 to 5, in which the determination of the transverse forces is based on a material consumption rate during orbital friction welding. 7. Method according to one of claims 5 and 6, in which the material consumption rate is determined as a function of the eccentricity, the frequency, the pressure and the geometric parameter Z. 8. The method of claim 6, wherein the material consumption rate is measured during a setup orbital friction weld. 9. A method according to claim 8, wherein the pressure used during the parameterization orbital friction welding corresponds to a pressure applied during the orbital movement of the orbital friction welding of the blade (4) to the stump (6) with the determined welding parameters. 10. Method according to one of claims 8 and 9, in which the parameterization orbital friction welding comprises an evaluation of the quality of the welded joint. 11. Method according to one of claims 1 to 10, in which the orbital friction welding of the blade to the stump with the determined welding parameters comprises a measurement of an actual eccentricity and/or actual transverse forces by means of data acquisition. 12. Method according to one of claims 1 to 11, in which the section (11) of the blade (4) and the stub (6) at the junction (10) is between 500 mm? and 7000 mm°. 13. Method according to one of claims 1 to 11, in which the section (11) of the blade (4) and the stub (6) at the junction (10) is between 2000 mm? and 3000 mm. 18 BE2023/5299 14. Method according to one of claims 1 to 13, in which the frequency comprises a rotation speed of the blade (4) around an axis (A) of the junction (10).