Patent Application
20240372448
The present invention relates to the field of electric motors and more particularly relates to the field of the rotors of electric motors for aeronautical applications.
In a known manner, with the objective of reducing the overall mass of a helicopter engine or more generally of a propulsion chain for a helicopter, one of the privileged ways is to reduce the mass of the generation and/or starting electric motors or even of electric propulsion motors in the “VTOL” (Vertical Take Off and Landing) or “STOL” (Short Take Off and Landing) field. Indeed, the weight of these systems can reach several tens of kilograms for powers that can go beyond a hundred kilowatts. The current limitations on the electric machines hardly exceed a power/mass ratio of 3.5 kW/kg.
The first limitation of the performances is essentially due to the electromagnetic circuit itself which is governed by the quality of the ferromagnetic materials used or the quality of the magnets (remanent induction Br) when included in these machines.
The current ways of investigation are focused mainly on improving the electromagnetic performances of the electric machines. It is particularly known to try to optimize the material constituting the magnetic circuit, by using the best grades of iron-cobalt or iron-silicon. Another known way of improvement is to minimize losses at the level of the rotor and stator of the machine by refining the sheets making up the stator and/or rotor, thus reducing eddy current losses.
To also improve the torque density of the electric machine, it is known to add permanent magnets to the rotor and/or stator whose remanent magnetic induction can be added to the magnetic field created by the winding which is generally placed in the stator of the electric machine.
The second limitation is the mechanical limitation in the rotational speed of the machines. This speed limitation depends on the nature of the electric machine. There are three main families of electric machines (i.e. electric motors): direct current machines, synchronous machines and asynchronous machines.
Indeed, as shown in the graph of
Today, the target need in terms of electrical power for integration into a helicopter is in a fairly wide range from around 50 kilowatts to several hundred kilowatts per machine. Thus, with reference to the graph of
In
Finally, a third limitation is identified. It is intrinsic to the environment in which the machine is embedded and more specifically to the aeronautical field. This third limitation concerns the integrity of the equipment as well as its environment in the event of an internal defect in the electric machine.
Thus, it is necessary, for rotational speeds ranging from 10,000 rpm to more than 100,000 rpm, for the machine to contain high energy debris coming from rotating portions of the rotor of the machine (i.e. the machine must continue to operate despite the breakage and the presence of rotor parts within it). Additionally, in many other failure cases it is necessary for the electric machine to continue to operate.
In an aeronautical application that is to say within the framework of an on-board system requiring strong constraints in terms of compactness, mass and reliability, different electric machine technologies are used. The best known ones can be cited:
To solve this problem of electromagnetic performance limitation, new topologies of asynchronous machines have recently appeared over the last ten years called solid rotor asynchronous machines. The notion of a solid rotor comes from the fact that the rotor, which can be made of multi-materials, is very compact and the rotor is resistant to much greater mechanical forces than the asynchronous squirrel cage machines.
In this context, the present invention aims to propose a new asynchronous machine rotor topology having better performances at high speed (i.e. speeds greater than 30,000 rpm).
According to a first aspect, the invention proposes a rotor of an aircraft electric motor, comprising a shaft made of a first material and a skin made of a second material different from the first material, in which the shaft has a shoulder portion on which the skin is fixed, at the level of the shoulder portion, the rotor has a layer of interpenetration of the first material and of the second material, the interpenetration layer comprising an alloy of the first material and of the second material.
The skin can comprise two rings, a first ring being fixed to the rotor at a first end region of the shoulder portion and a second ring being fixed to the rotor at a second end region of the shoulder portion.
The skin and the rings can be monoblocs.
The skin can comprise two half-shells welded together.
The first material can contain at least iron and carbon.
The second material can contain at least one of the metals chosen among copper, aluminum or silver.
According to a second aspect, the invention relates to a method for manufacturing a rotor according to the invention, comprising at least one of the steps of:
The step of inserting the shaft and an element intended to form the skin in a tubular protective casing can comprise the phases of:
The step of inserting the shaft and an element intended to form the skin in a tubular protective casing can comprise a phase of positioning, around the shaft, a powder intended to form the skin.
The step of heating and pressurizing the assembly can be carried out in a dedicated enclosure and in a neutral atmosphere.
The heat treatment step can comprise a quenching chosen among natural or forced convection gas quenching, water quenching or oil quenching.
The heat treatment step can be carried out until the first stainless steel material becomes martensitic.
Other characteristics, aims and advantages of the invention will emerge from the following description, which is purely illustrative and not limiting, and which should be read in relation to the appended drawings in which:
According to a first aspect, the invention proposes a rotor 1 of an aircraft electric motor, comprising a shaft 2 made of a first material and a skin 4 made of a second material different from the first material.
The shaft 2 is a one-piece revolution part having in particular a shoulder portion 6. It is specified that by “shoulder portion” it is meant a portion comprised between two circular crowns normal to the axis of revolution of the shaft 2 and resulting from a sudden variation in diameter.
The shoulder portion 6 has two end regions 8 (i.e. each being a circular crown). Each end region 8 of the shoulder portion 6 has a groove intended to accommodate a ring 12.
In addition, as represented in
Typically, the shaft 2 is made of a magnetic material comprising an alloy of iron and carbon.
Preferably, the alloy of the shaft is a steel comprising mainly iron and carbon. In a particularly preferable manner, the alloy is a martensitic steel comprising more than 1% carbon. This steel structure allows the shaft 2 to channel the magnetic field lines coming from the windings to the stator (when the rotor is operating in an electric motor) so that the skin 4 receives as much magnetic field as possible.
For example, the alloy of the shaft can be chosen from 17-4PH, AISI 416 (EN-1-4005), AISI 431 (EN-1-4057), AISI 1020 (XC18), AISI 1045 (XC48).
It is specified that this alloy can comprise other components in addition to iron and carbon, for example in order to make the steel stainless (example: Chrome Cr, Nickel Ni . . . ).
The geometry of the shaft 2 can for example be obtained by turning and the martensitic structure is obtained by heat treatment.
The skin 4 is a copper cylinder positioned on the shoulder region 6.
Copper is chosen for its excellent conductivity. According to another embodiment, the skin 4 could for example be made of silver or aluminum.
It is specified that the material, such as copper or silver, constituting the skin 4 is not necessarily a pure material and can be a copper-based, an aluminum-based or a silver-based alloy. For example, the copper alloy can comprise alloying elements such as chromium and zirconium or cobalt or even Beryllium.
According to the embodiment presented here and with reference to
The skin can advantageously have a thickness of the order of 1 to 5 millimeters.
The skin 4 can comprise two rings 12 which are each intended to be positioned in a groove of an end region 8.
Preferably, each ring 12 is monobloc with a respective half-shell 18. In other words, preferably, each ring 12 is made integrally with a respective half-shell 18. Thus, the rings 12 are comparable to thicker skin portions 4. The rings 12 have a short-circuit function and serve to loop the induced currents to the rotor.
The structure in two half-shells 18 makes it possible to assemble the skin 4 on the shaft 2.
According to the embodiment presented here, each half-shell 18 has a first end comprising a ring 12 and a second end having a chamfer 22.
The chamfers 22 of the two half-shells 18 are complementary to each other to facilitate the assembly of the two half-shells 18. Typically one half-shell 18 can have a chamfer at +45° and the other half-shell 18 can have a chamfer 22 at −45°. By “complementary assembly” it is meant that once assembled the two half-shells 18 form a complete cylinder (i.e. without hole or aperture at the junction between the two half-shells 18).
According to one particularly advantageous arrangement of the invention, the skin 4 is welded to the shoulder portion 6 and the end regions 8 of the shaft 2.
This welding is carried out so that the rotor 1 has an interpenetration layer due to the existence of a diffusion of material between the skin 4 and the shaft 2, at the level of the shoulder portion 6 and of the end regions 8.
In other words, at the level of the shoulder portion 6 and of the end regions 8, the rotor has a layer of interpenetration of the material of the shaft 2 and of the material of the skin 4.
By interpenetration it is meant an alloy layer for alloying the material of the shaft 2 (first material) and the material of the skin 4 (second material).
It is specified that in a particularly advantageous manner, this interpenetration is carried out without the addition of a third material. In other words, the welding of the skin 4 and of the shaft 2 only comprises the skin 4 and the shaft 2 and does not involve any additional material.
Advantageously, and as will be described below, the interpenetration layer is the result of a diffusion welding of the skin 4 and of the shaft 2. This arrangement very advantageously makes it possible to have an excellent mechanical resistance over the entire surface of the shoulder portion 6, which allows the rotor 1 to withstand rotational speeds greater than 50,000 rpm in the present configuration.
According to a second aspect, the invention relates to a method for manufacturing a rotor 1 as described above.
With reference to
It is specified that the diffusion welding is a technique allowing the assembly of elements in solid phase that is to say without fusion, thanks to the simultaneous application of a temperature and of a high pressure over a determined time.
More specifically, according to a first embodiment, the step of inserting the shaft 2 and an element intended to form the skin 4 in a tubular protective casing 30 comprises the phases of:
According to a second embodiment, the step of inserting the shaft 2 and an element intended to form the skin 4 in a tubular protective casing 30 comprises a phase of positioning, around the shaft, a powder intended to form the skin 4.
According to this second embodiment, the powder, during the heating and pressurization process in the casing 30, binds and becomes a homogeneous element to form the skin 4.
Advantageously, the diffusion welding phase can be performed in an enclosure according to a hot isostatic pressing (HIP) method.
It is specified that the diffusion welding is a technique allowing the assembly of elements in solid phase that is to say without fusion thanks to the simultaneous application of a high temperature and pressure.
Typically, a hot isostatic pressing (HIP) method can comprise a step of degreasing and stripping the surfaces of the elements to be assembled, a step of directly contacting the degreased and stripped surfaces of the elements to be assembled, and a step of assembling by diffusion welding the surfaces of the elements in contact.
The step of degreasing and stripping the surfaces of the elements to be assembled can consist of conventional treatments for degreasing and stripping metal surfaces.
The aim of this step is to obtain clean, degreased and oxidation-free surfaces. The degreasing of these surfaces can for example be performed by means of a solvent or of a detergent conventional for degreasing metals. The stripping can be chemical or mechanical stripping, it can for example be carried out by means of an acidic or basic solution, or by rectification or polishing. In a known manner, the stripping technique can be chemical stripping followed by rinsing with water during which the surface of the materials is rubbed using an abrasive pad, for example based on alumina fibers. This treatment can be repeated several times, the last rinse being carried out with demineralized water.
This list is not exhaustive, the choice of any technique making it possible to eliminate traces of pollution and oxidation on the surfaces of the elements to be assembled is possible.
For the surface of the martensitic stainless steel element to be assembled, the degreasing solvent can be an organic solvent, for example of the acetone, ether, alcohol, alkane type, or of the chlorinated alkene type such as trichloroethylene, or a mixture of these solvents, etc.
A preferred solvent is a mixture in equal proportions of ethyl alcohol, ether and acetone. Another preferred solvent is trichloroethylene. Chemical stripping can be carried out with an acid solution, for example a 10% hydrofluoric acid bath or a mixture comprising 1 to 5% hydrofluoric acid with 30 to 40% nitric acid. The stripping time can be for example from 10 seconds to 5 minutes, for example from 20 to 30 seconds, at a temperature of 15° C., for example 20° C. The stripped surfaces can then be rinsed in one or several successive baths, for example of demineralized water.
For the surface of the element comprising copper, the degreasing can be performed by means of an organic solvent such as those cited above, for example by means of acetone or a ternary mixture of acetone-ethyl alcohol-ether preferably in equal proportions. The degreasing of this surface can possibly be followed by sonicating for a duration of one minute for example. The surface can then be degreased in ethanol under ultrasound and then dried, for example by means of hot air.
This surface can then be stripped for example by means of a bath of potassium dichromate for example at a concentration of 0.23 to 0.30 moles/liter, of sulfuric acid at a concentration of 0.1 to 0.13 moles/liter for example, and of demineralized water, for 1 to 3 minutes for example, for approximately 1 minute and 30 seconds for example. The surface can then be rinsed in ethanol, for example, under ultrasound, then in demineralized water and dried, for example, by means of hot air.
In a known manner, the following step is a step of directly contacting the degreased and stripped surfaces of the elements. This contacting corresponds to placing or positioning the elements to be assembled surface-to-surface, according to a desired stacking. Preferably, this contacting is made within a period of less than one hour following the step of degreasing and stripping the surfaces to be assembled, so as to limit the risks of oxidation, except in the case where special precautions have been taken to store the degreased and stripped elements, these precautions can consist for example in maintaining the elements in a clean and non-oxidizing atmosphere such as nitrogen by means of bagging in sealed bags. This contacting is called “direct” contacting, because it is done according to the present invention without disposing on the surfaces to be assembled an intermediate layer of an alloy as the one described in the prior art. According to the invention, the step that follows the contacting of the surfaces of the elements to be assembled is a step of assembling by diffusion welding the surfaces brought into direct contact. The diffusion welding can be performed for example by isostatic pressing or by uniaxial hot pressing, for example by conventional techniques known to those skilled in the art.
When the diffusion welding is performed by hot isostatic pressing, the materials brought into contact can be introduced into a casing which makes it possible to isolate the elements to be assembled from the atmosphere and to discharge the gases in the casing for the assembly of the elements by diffusion welding therein. The contacting step can also be done in the casing directly.
It is specified that the casing 30 can be made up of any sealed material sufficiently resistant to withstand at least a partial vacuum therein and to withstand the high temperatures and pressures necessary to assemble the elements. For example, the casing can be a metal casing, for example made of stainless steel, mild steel or titanium and its alloys. It can for example be formed from a sheet metal having a thickness for example of approximately 1 to 20 mm, for example of approximately 1 to 10 mm. Preferably, the casing can match the external shape of the elements to be assembled.
In a known manner, the martensitic stainless steel element (the shaft 2) can close the casing 30 by playing the role of a cover of the casing 30, the shaft 2 can then be welded to the casing 30. In a known manner, this casing 30 can be made by cutting, possibly by bending then by welding of a sheet metal or by any method known to those skilled in the art.
The casing 30 is then degassed so as to create a vacuum therein. The degassing can be carried out by means of a vacuum pump and of a heating of the assembly comprising the elements to be assembled and the casing.
An example of degassing can consist in discharging the casing 30 at ambient temperature until a residual vacuum less than or equal to 10 Pa is obtained, then in heating the assembly to a moderate temperature, for example less than 300 C, for a few hours, for example 5 hours, while continuing the discharge.
It may be useful to check that the casing is sealed, before carrying out the diffusion welding operation, for example by means of a helium test.
Once the degassing step is performed, the casing 30 is made completely sealed by the obturation of the aperture used for its discharge, the obturation being carried out for example using TIG welding.
The elements brought into contact in the degassed casing can then be assembled by diffusion welding. The assembly can be carried out in a hot isostatic pressing enclosure.
More specifically, the heating step comprises a phase of pressurizing the assembly 32. Typically, the pressure inside a heating enclosure (i.e. a furnace) can be brought to a value comprised between 1,000 and 2,000 bars (preferably the pressure can be around 1,500 bars).
In addition, preferably, the heating is carried out in an atmosphere called neutral atmosphere. To do so, the heating enclosure of the furnace used is saturated with a neutral gas (i.e. a rare gas according to the periodic classification of the elements). Preferably, the neutral gas used may be argon. According to another arrangement, the atmosphere of the heating enclosure can be saturated with nitrogen.
One of the objectives of the saturation of the heating enclosure with argon or nitrogen is to remove the oxygen in order to avoid a potential oxidation reaction.
Furthermore, preferably, the heating step is carried out by bringing the assembly 32 to a temperature allowing the diffusion welding but lower than a liquefaction temperature of the copper (and therefore of the steel).
It is specified that by “bringing the assembly to a temperature allowing diffusion welding”, it is meant that the temperature of the assembly 32 is increased gradually (linearly) up to a maximum temperature, then the maximum temperature is maintained for a determined period of time.
In a particularly preferred manner, the maximum heating temperature can be comprised between 900° C. and 1,040° C. to dissolve the metal components present in the casing 30.
Preferably, the heating step is carried out gradually over several hours. In a particularly preferred manner, the heating stage lasts around ten hours.
Preferably, the heat treatment step can comprise a quenching chosen among open air quenching, water quenching or oil quenching.
It is specified that the quenching can be homogeneous for the entire assembly 32 or can be monitored by in-situ measurements.
Preferably, the quenching heat treatment step is determined so that the steel of the shaft 2 becomes martensitic. More specifically, the heat treatment step makes it possible to remove any possible presence of residual austenite in the steel of the shaft 2.
Preferably, the quenching must correspond to a cooling speed greater than the critical speed to create the martensitic phase, i.e. several degrees/second even several tens of degrees/second (°/s).
With reference to the diagram presented in
The quenching step is very advantageous in improving the electromagnetic properties as shown in
After the quenching, it is possible to continue this heat treatment phase by immersing the assembly 32 in a cryogenic bath in order to reduce the presence of residual austenite. Typically the cryogenic bath can be at a temperature below −20° C. In a preferred manner, the assembly 32 is immersed in the cryogenic bath for a period that can be comprised between 10 minutes and 60 minutes.
Following the quenching heat treatment, the tempering step makes it possible to obtain the desired characteristics for the copper constituting the skin 4 (mechanical resistance, electrical conductivity, etc.), and makes it possible to soften the martensitic steel to increase its ductility while preserving its electromagnetic properties, which makes it possible to optimize the overall performance of the rotor 1.
The tempering step is a known step in the field of metallurgy. Usually, the tempering can also be called “aging”.
Preferably, the tempering is carried out by bringing the assembly 32 to a bearing temperature comprised between 450° C. and 650° C., over a duration comprised between 1 hour and 4 hours. This optimized treatment ensures that the copper alloy has a conductivity equal to or greater than 90% of the conductivity of the pure copper (% IACS) and ensures that the desired mechanical properties are maintained.
The separation of the casing 30 and of the rotor 1 is carried out by machining the casing 30 to retain only the rotor 1. In other words, the casing 30 is extracted by machining, typically by turning.
The rotor 1 obtained then has blank dimensions, as represented in
Then, the rotor 1 and more particularly its skin 4 are machined to have the final dimensions and geometries.
At the end of this last finishing machining step, the rotor 1 obtained has the geometric characteristics necessary for its use, and also has structural and electromagnetic characteristics guaranteeing its resistance during use at rotational speeds greater than 50,000 rpm.
The interdiffusion interlinked area on the part obtained according to the method typically has a thickness of a few tens of μm.
The rotor 1 having a monolithic type structure can be easily balanced statically and dynamically (by localized material removal), which makes it possible to guarantee the lowest vibration level possible and compatible for a high speed operation.
| Number | Date | Country | Kind |
|---|---|---|---|
| FR2109612 | Sep 2021 | FR | national |
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/FR2022/051731 | 9/14/2022 | WO |
