Patent Application
20200093179
The present invention relates to a multi-layer susceptor assembly for inductively heating an aerosol-forming substrate as well as to an aerosol-generating article including such a multi-layer susceptor assembly and an aerosol-forming substrate to be heated.
Aerosol-generating articles, which include an aerosol-forming substrate to form an inhalable aerosol upon heating, are generally known from prior art. For heating the substrate, the aerosol-generating article may be received within an aerosol-generating device comprising an electrical heater. The heater may be an inductive heater comprising an induction source. The induction source generates an alternating electromagnetic field that induces heat generating eddy currents and/or hysteresis losses in a susceptor. The susceptor itself is in thermal proximity of the aerosol-forming substrate to be heated. In particular, the susceptor may be integrated in the article in direct physical contact with the aerosol-forming substrate.
For controlling the temperature of the substrate, bi-layer susceptor assemblies have been proposed comprising a first and a second layer made of a first and a second susceptor material, respectively. The first susceptor material is optimized with regard to heat loss and thus heating efficiency. In contrast, the second susceptor material is used as temperature marker. For this, the second susceptor material is chosen such as to have a Curie temperature lower than a Curie temperature of the first susceptor material, but corresponding to a predefined heating temperature of the susceptor assembly. At its Curie temperature, the magnetic permeability of the second susceptor drops to unity leading to a change of its magnetic properties from ferromagnetic to paramagnetic, accompanied by a temporary change of its electrical resistance. Thus, by monitoring a corresponding change of the electrical current absorbed by the induction source it can be detected when the second susceptor material has reached its Curie temperature and, thus, when the predefined heating temperature has been reached.
While such bi-layer susceptor assemblies provide good controllability of the heating temperature, undesired deformations of the layered structure have been observed during or after a processing of the assembly. Likewise, undesired deformations of the layered structure have also been observed during use of the assembly for inductively heating aerosol-forming substrate.
Therefore, it would be desirable to have a multi-layer susceptor assembly for inductively heating an aerosol-forming substrate with the advantages of prior art solutions but without their limitations. In particular, it would be desirable to have a multi-layer susceptor assembly with improved dimensional stability.
According to the invention there is provided a multi-layer susceptor assembly for inductively heating an aerosol-forming substrate which comprises at least a first layer and a second layer intimately coupled to the first layer. The first layer comprises a first susceptor material. The second layer comprises a second susceptor material having a Curie temperature lower than 500° C. (degree Celsius).
Preferably the first susceptor material is configured for inductively heating the aerosol-forming substrate and the second susceptor material is configured for monitoring a temperature of the susceptor assembly. For this, the Curie temperature of the second susceptor material preferably corresponds to a predefined heating temperature of the susceptor assembly.
As used herein, the term ‘intimately coupled’ refers to a mechanical coupling between two layers within the multilayer assembly such that a mechanical force may be transmitted between the two layers, in particular in a direction parallel to the layer structure. The coupling may be a laminar, two-dimensional, areal or full-area coupling, that is, a coupling across the respective opposing surfaces of the two layers. The coupling may be direct. In particular, the two layers, which are intimately coupled with each other, may be in direct contact with each other. Alternatively, the coupling may be indirect. In particular, the two layers may be indirectly coupled via at least one intermediate layer.
Preferably, the second layer is arranged upon and intimately coupled to, in particular directly connected with the first layer.
According to the invention, it has been recognized that processing and operating a multilayer susceptor assembly at different temperatures may cause deformations due to specific differences between the thermal expansion of the various layer materials. For example, a processing of a bi-layer susceptor assembly as described above may comprise intimately connecting both layer materials to each other at a given temperature. Connecting the layers may be possibly followed by a heat treatment of the assembled susceptor, such as annealing. During a subsequent change of temperature, such as during a cooldown of the susceptor assembly, the individual layers cannot deform freely due to the conjoined nature of the assembly. Consequently, due to different thermal dilatation characteristics one layer may exert a compressive or tensile stress onto another layer, in particular an adjacent layer. This compressive or tensile stress may cause the observed mechanical stress and deformations, in particular an out-of-plane bending of the susceptor assembly.
To counter this, the susceptor assembly according to the present invention further comprises a third layer that is intimately coupled to the second layer. The third layer comprises a specific stress-compensating material and specific layer thickness for compensating differences in thermal expansion occurring in the multi-layer susceptor assembly after a processing of the assembly, in particular after intimately coupling the layers to each other and/or after a heat treatment of the multi-layer susceptor assembly, such that at least in a compensation temperature range an overall thermal deformation of the susceptor assembly is essentially limited to in-plane deformations, wherein the compensation temperature range extends at least from 20 K below the Curie temperature of the second susceptor material up to the Curie temperature of the second susceptor material.
As used herein, the term ‘deformation’ implies the change in shape and/or size of the susceptor assembly from an initial or undeformed configuration to deformed configuration. An ‘in-plane deformation’, also called ‘in-plane strain’, as referred to herein is one where the deformation is restricted to a plane parallel to the layer structure of the multi-layer susceptor assembly.
As used herein, the term ‘essentially limited to in-plane deformations’ implies that there might be still small but insignificant out-of-plane deformations in a direction orthogonal to the layer structure of the multi-layer susceptor assembly. However, any out-of-plane deformations are limited such that a curvature at any point on the surface of the susceptor assembly is less than 5% in, in particular less than 1%, preferably less than 0.5% of the thickness of the susceptor assembly. Preferably, an overall thermal deformation of the susceptor assembly is limited to in-plane deformations at least in a compensation temperature range.
Accordingly, the third layer advantageously allows for preserving the original desired shape and preferably also the original desired size of the susceptor assembly in a direction orthogonal to the layer structure of the multi-layer susceptor assembly.
As used herein, the term ‘layer thickness’ refers to dimensions extending between the top and the bottom side a layer. Likewise, the term ‘thickness of the susceptor assembly’ refers to the maximum extension of the susceptor assembly in a direction orthogonal to the layer structure. As used herein, the terms ‘specific stress-compensating material’ and ‘specific layer thickness’ refer to a stress-compensating material and a layer thickness that are specifically chosen for compensating differences in thermal expansion occurring in the multi-layer susceptor assembly after a processing of the assembly such that at least in the compensation temperature range an overall thermal deformation of the susceptor assembly is essentially limited to in-plane deformations. The term ‘specifically chosen’ as referred to herein implies that the stress-compensating material and the layer thickness of the third layer are chosen in due consideration of the first and second susceptor materials and the thicknesses of the first and second layer as well as in due consideration of the conjoined nature of the assembly and its processing, that is, processing history.
As used herein, a processing of the multilayer susceptor assembly may comprise at least one of intimately coupling the layer materials to each other at a given temperature, or a heat treatment of the multilayer susceptor assembly, such as annealing. In particular, the susceptor assembly may be a heat treated susceptor assembly. In any cases, during a processing as referred to herein the temperature of the layers or the assembly, respectively, is different from the operating temperature of the susceptor assembly when being used for inductively heating an aerosol-forming substrate. Typically, the temperatures during intimately connecting the layer materials to each other and during a heat treatment of the multilayer susceptor assembly are larger than the operating temperatures of the susceptor assembly for inductive heating.
The compensation temperature range from 20 K below the Curie temperature of the second susceptor material up to the Curie temperature of the second susceptor material corresponds to a typical range of operating temperatures of the susceptor assembly used for generating an aerosol.
Advantageously, the span of the compensation temperature range may be also larger than 20 K. Accordingly, the compensation temperature range may extend at least from 50 K, in particular 100 K, preferably 150 K below the Curie temperature of the second susceptor material up to the Curie temperature of the second susceptor material. Most preferably, the compensation temperature range may extend at least from ambient room temperature up to the second Curie temperature. Likewise, the compensation temperature range may correspond to a temperature range between 150° C. and the Curie temperature of the second susceptor material, in particular between 100° C. and the Curie temperature of the second susceptor material, preferably between 50° C. and the Curie temperature of the second susceptor material, most preferably between ambient room temperature and the Curie temperature of the second susceptor material.
When approaching the second Curie temperature from below, magnetization and therefore any magnetostriction effect in the second susceptor material disappear. Therefore, an upper limit of the compensation temperature range preferably corresponds to the Curie temperature of the second susceptor material. However, the upper limit of the compensation temperature range may be also higher than the Curie temperature of the second susceptor material. For example, an upper limit of the compensation temperature range may be at least 5 K, in particular at least 10 K, preferably at least 20K higher than the Curie temperature of the second susceptor material.
Preferably, a coefficient of thermal expansion of the stress-compensating material is essentially equal to a coefficient of thermal expansion of the first susceptor material. The term ‘essentially equal’ as used herein implies that there might be a small but insignificant difference between the coefficients of thermal expansion of the first and third layer material. However, any possible difference is limited such that a coefficient of thermal expansion of the stress-compensating material deviates by less than ±5%, in particular less than ±1%, preferably less than ±0.5% from a coefficient of thermal expansion of the first susceptor material. Most preferably, a coefficient of thermal expansion of the stress-compensating material is equal to a coefficient of thermal expansion of the first susceptor material.
In particular, the stress-compensating material of the third layer may be even the same as the first susceptor material of the first layer.
Furthermore, the layer thickness of the third layer may essentially equal to the layer thickness of the first layer. The term ‘essentially equal’ as used herein implies that there might be a small but insignificant difference between the layer thicknesses of the first and third layer. However, any possible difference is limited such that a layer thickness of the third layer deviates by less than ±5%, in particular less than ±1%, preferably less than ±0.5% from a layer thickness of the first susceptor material. Most preferably, the layer thickness of the third layer is equal to the layer thickness of the first layer.
In a preferred configuration of the susceptor assembly, the layer thickness of the third layer is equal to the layer thickness of the first layer and the coefficient of thermal expansion of the stress-compensating material is essentially equal to a coefficient of thermal expansion of the first susceptor material, in particular the stress-compensating material of the third layer is the same as the first susceptor material of the first layer. Advantageously, this preferred configuration provides a symmetric layer structure with regard to the thermal expansion.
Alternatively, a coefficient of thermal expansion of the stress-compensating material may be different from a coefficient of thermal expansion of the first susceptor material, and preferably also from different from a coefficient of thermal expansion of the second susceptor material. Accordingly, a coefficient of thermal expansion of the second susceptor material may be larger than a coefficient of thermal expansion of the first susceptor material and smaller than a coefficient of thermal expansion of the stress-compensating material. Vice versa, a coefficient of thermal expansion of the second susceptor material may be smaller than a coefficient of thermal expansion of the first susceptor material and larger than a coefficient of thermal expansion of the stress-compensating material. In these cases, a compensating of differences in thermal expansion may be primarily achieved by choosing an appropriate layer thickness of the third layer.
The stress-compensating material of the third layer may be different from the first susceptor material of the first layer. This does not exclude that a coefficient of thermal expansion of the stress-compensating material is essentially equal to a coefficient of thermal expansion of the first susceptor material.
According to the invention, the third layer is intimately coupled to the second layer. In this context, the term ‘intimately coupled’ is used in the same way as defined above with regard to the first and second layer.
As used herein, the terms ‘first layer’, ‘second layer’ and ‘third layer’ are only nominal without necessarily specifying a particular order or sequence of the respective layers.
Preferably, the third layer is arranged upon and intimately coupled to the second layer, which in turn may be arranged upon and intimately coupled to the first layer.
Alternatively, the third layer may be intimately coupled to the second layer via the first layer. In this case, the first layer may be an intermediate layer between the third layer and the second layer. In particular, the second layer may be arranged upon and intimately coupled to the first layer, which in turn may be arranged and intimately coupled to the first layer.
Preferably, the first layer, the second layer and the third layer are adjacent layers of the multilayer susceptor assembly. In this case, the first layer, the second layer and the third layer may be in direct intimate physical contact with each other. In particular, the second layer may be sandwiched between the first layer and the third layer.
Alternatively, the susceptor assembly may comprise at least one further layer, in particular at least one intermediate layer that is arranged between two respective ones of the first layer, the second layer and the third layer.
At least one of the first layer or the third layer may be an edge layer of the multilayer susceptor assembly.
With regard to the processing of the susceptor assembly, in particular with regard to assembling the various layers, each of the layers may be plated, deposited, coated, cladded or welded onto a respective adjacent layer. In particular, any of these layers may be applied onto a respective adjacent layer by spraying, dip coating, roll coating, electroplating or cladding. This holds in particular for the first layer, the second layer and the third layer and—if present—the at least one intermediate layer.
Either way, any of the configurations or layer structures described above falls within the term ‘intimately coupled’ as used herein and defined further above.
As used herein, the term ‘susceptor’ refers to an element that is capable to convert electromagnetic energy into heat when subjected to a changing electromagnetic field. This may be the result of hysteresis losses and/or eddy currents induced in the susceptor material, depending on its electrical and magnetic properties. The material and the geometry for the susceptor assembly can be chosen to provide a desired heat generation.
Preferably, the first susceptor material may also have a Curie temperature. Advantageously, the Curie temperature of the first susceptor material is distinct from, in particular higher than the Curie temperature of the second susceptor material. Accordingly, the first susceptor material may have a first Curie temperature and the second susceptor material may have a second Curie temperature. The Curie temperature is the temperature above which a ferrimagnetic or ferromagnetic material loses its ferrimagnetism or ferromagnetism, respectively, and becomes paramagnetic.
By having at least a first and a second susceptor material, with either the second susceptor material having a Curie temperature and the first susceptor material not having a Curie temperature, or first and second susceptor materials having each Curie temperatures distinct from one another, the susceptor assembly may provide multiple functionalities, such as inductive heating and controlling of the heating temperature. In particular, these functionalities may be separated due to the presence of at least two different susceptors.
Preferably, the first susceptor material is configured for heating the aerosol-forming substrate. For this, the first susceptor material may be optimized with regard to heat loss and thus heating efficiency. The first susceptor material may have a Curie temperature in excess of 400° C.
Preferably, the first susceptor material is made of an anti-corrosive material. Thus, the first susceptor material is advantageously resistant to any corrosive influences, in particular in case the susceptor assembly is embedded in an aerosol-generating article in direct physical contact with aerosol-forming substrate.
The first susceptor material may comprise a ferromagnetic metal. In that case, heat cannot only by generated by eddy currents, but also by hysteresis losses. Preferably the first susceptor material comprises iron (Fe) or an iron alloy such as steel, or an iron nickel alloy. In particular, the first susceptor material may comprise stainless steel, for example ferritic stainless steel. It may be particularly preferred that the first susceptor material comprises a 400 series stainless steel such as grade 410 stainless steel, or grade 420 stainless steel, or grade 430 stainless steel, or stainless steel of similar grades.
The first susceptor material may alternatively comprise a suitable non-magnetic, in particular paramagnetic, conductive material, such as aluminum (Al). In a paramagnetic conductive material inductive heating occurs solely by resistive heating due to eddy currents.
Alternatively, the first susceptor material may comprise a non-conductive ferrimagnetic material, such as a non-conductive ferrimagnetic ceramic. In that case, heat is only by generated by hysteresis losses.
In contrast, the second susceptor material may be optimized and configured for monitoring a temperature of the susceptor assembly. The second susceptor material may be selected to have a Curie temperature which essentially corresponds to a predefined maximum heating temperature of the first susceptor material. The maximum desired heating temperature may be defined to be approximately the temperature that the susceptor assembly should be heated to in order to generate an aerosol from the aerosol-forming substrate. However, the maximum desired heating temperature should be low enough to avoid local overheating or burning of the aerosol-forming substrate. Preferably, the Curie temperature of the second susceptor material should be below an ignition point of the aerosol-forming substrate. The second susceptor material is selected for having a detectable Curie temperature below 500° C., preferably equal to or below 400° C., in particular equal to or below 370° C. For example, the second susceptor may have a specified Curie temperature between 150° C. and 400° C., in particular between 200° C. and 400° C. Though the Curie temperature and the temperature marker function is the primary property of the second susceptor material, it may also contribute to the heating of the susceptor assembly.
It is preferred that the second susceptor is present as a dense layer. A dense layer has a higher magnetic permeability than a porous layer, making it easier to detect fine changes at the Curie temperature.
Preferably, the second susceptor material comprises a ferromagnetic metal such as nickel (Ni). Nickel has a Curie temperature in the range of about 354° C. to 360° C. or 627 K to 633 K, respectively, depending on the nature of impurities. A Curie temperature in this range is ideal because it is approximately the same as the temperature that the susceptor should be heated to in order to generate an aerosol from the aerosol-forming substrate, but still low enough to avoid local overheating or burning of the aerosol-forming substrate.
Alternatively, the second susceptor material may comprise a nickel alloy, in particular a Fe-Ni-Cr alloy. Advantageously, Fe-Ni-Cr alloys are anti-corrosive. As an example, the second susceptor may comprise a commercial alloy like Phytherm 230 or Phytherm 260. The Curie temperature of these Fe-Ni-Cr alloys can be customized. Phytherm 230 has a composition (in % by weight=wt %) with 50 wt % Ni, 10 wt % Cr and rest Fe. The Curie temperature of Phytherm 230 is 230° C. Phytherm 260 has a composition with 50 wt % Ni, 9 wt % Cr and rest Fe. The Curie temperature of Phytherm 260 is 260° C.
Likewise, the second susceptor material may comprise a Fe-Ni-Cu-X alloy, wherein X is one or more elements taken from Cr, Mo, Mn, Si, Al, W, Nb, V and Ti.
As regards the third layer, the stress-compensating material preferably may be the same material as the first susceptor material of the first layer. Accordingly, the stress-compensating material may comprise a ferromagnetic metal, preferably iron (Fe) or an iron alloy such as steel, or an iron nickel alloy. In particular, the the stress-compensating material may comprise stainless steel, for example ferritic stainless steel. It may be particularly preferred that the stress-compensating material comprises a 400 series stainless steel such as grade 410 stainless steel, or grade 420 stainless steel, or grade 430 stainless steel, or stainless steel of similar grades. The stress-compensating material may also comprise a suitable non-magnetic, in particular paramagnetic, conductive material, such as aluminum (Al). Alternatively, the stress-compensating material may include an austenitic stainless steel. For example, the third layer may include X5CrNi18-10 (according to EN (European Standards) nomenclature, material number 1.4301, also known as V2A steel) or X2CrNiMo17-12-2 (according to EN (European Standards) nomenclature, material number 1.4571 or 1.4404, also known as V4A steel). Advantageously, due to its paramagnetic characteristics and high electrical resistance, austenitic stainless steel only weakly shields the second susceptor material from the electromagnetic field to be applied to the first and second susceptors.
The layer thickness of the third layer may be in a range of 0.5 to 1.5, in particular 0.75 to 1.25, times a layer thickness of the first layer. A layer thickness of the third layer within these ranges may prove advantageous for counteracting or even compensating differences in thermal expansion occurring in the multi-layer susceptor assembly during or after processing. Preferably the layer thickness of the third layer is equal to a layer thickness of the first layer.
As used herein, the term ‘thickness’ refers to dimensions extending between the top and the bottom side, for example between a top side and a bottom side of a layer or a top side and a bottom side of the multilayer susceptor assembly. The term ‘width’ is used herein to refer to dimensions extending between two opposed lateral sides. The term ‘length’ is used herein to refer to dimensions extending between the front and the back or between other two opposed sides orthogonal to the two opposed lateral sides forming the width. Thickness, width and length may be orthogonal to each other.
The multilayer susceptor assembly may be an elongated susceptor assembly having a length of between 5 mm and 15 mm, a width of between 3 mm and 6 mm and a thickness of between 10 μm and 500 μm. As an example, the multilayer susceptor assembly may be an elongated strip, having a first layer which is a strip of 430 grade stainless steel having a length of 12 mm, a width of between 4 mm and 5 mm, for example 4 mm, and a thickness of between 10 μm and 50 μm, such as for example 25 μm. The grade 430 stainless steel may be coated with a second layer of nickel as second susceptor material having a thickness of between 5 μm and 30 μm, for example 10 μm. On top of the second layer, opposite to the first layer, a third layer may be coated which is also made of 430 grade stainless steel having the same layer thickness as the first layer. Advantageously, this configuration provides a highly symmetric layer structure with regard to the thermal expansion, showing essentially no out-of-plane deformations.
The susceptor assembly according to the present invention may be preferably configured to be driven by an alternating, in particular high-frequency electromagnetic field. As referred to herein, the high-frequency electromagnetic field may be in the range between 500 kHz to 30 MHz, in particular between 5 MHz to 15 MHz, preferably between 5 MHz and 10 MHz.
The susceptor assembly preferably is a susceptor assembly of an aerosol-generating article for inductively heating an aerosol-forming substrate which is part of the aerosol-generating article.
According to the invention there is also provided an aerosol-generating article comprising an aerosol-forming substrate and a susceptor assembly according to the present invention and as described herein for inductively heating the substrate.
Preferably, the susceptor assembly is located or embedded in the aerosol-forming substrate.
As used herein, the term ‘aerosol-forming substrate’ relates to a substrate capable of releasing volatile compounds that can form an aerosol upon heating the aerosol-forming substrate. The aerosol-forming substrate may conveniently be part of an aerosol-generating article. The aerosol-forming substrate may be a solid or a liquid aerosol-forming substrate. In both cases, the aerosol-forming substrate may comprise both solid and liquid components. The aerosol-forming substrate may comprise a tobacco-containing material containing volatile tobacco flavour compounds, which are released from the substrate upon heating. Alternatively or additionally, the aerosol-forming substrate may comprise a non-tobacco material. The aerosol-forming substrate may further comprise an aerosol former. Examples of suitable aerosol formers are glycerine and propylene glycol. The aerosol-forming substrate may also comprise other additives and ingredients, such as nicotine or flavourants. The aerosol-forming substrate may also be a paste-like material, a sachet of porous material comprising aerosol-forming substrate, or, for example, loose tobacco mixed with a gelling agent or sticky agent, which could include a common aerosol former such as glycerine, and which is compressed or molded into a plug.
The aerosol-generating article is preferably designed to engage with an electrically-operated aerosol-generating device comprising an induction source. The induction source, or inductor, generates a fluctuating electromagnetic field for heating the susceptor assembly of the aerosol-generating article when located within the fluctuating electromagnetic field. In use, the aerosol-generating article engages with the aerosol-generating device such that the susceptor assembly is located within the fluctuating electromagnetic field generated by the inductor.
Further features and advantages of the aerosol-generating article according to the present invention have been described with regard to susceptor assembly and will not be repeated.
The invention will be further described, by way of example only, with reference to the accompanying drawings, in which:
The susceptor assembly 1 according to the embodiment shown in
However, the fact that the first and second susceptor materials have different coefficients of thermal expansion may cause undesired deformations of the susceptor assembly when the first and second layers 10, 20 are intimately coupled to each other. This will be explained in the following. During some stage of the processing of the susceptor assembly 1, the first and second layer 10, 20 are connected to each other at a given temperature, typically followed by a heat treatment, such as annealing. During a subsequent change of temperature, such as during a cooldown of the susceptor assembly 1, the individual layers 10, 20 cannot deform freely due to the conjoined nature of the assembly 1. Consequently, as the nickel material within the second layer 20 has a coefficient of thermal expansion larger than that one of the stainless steel within the first layer 10, the susceptor assembly 1 may be subject to mechanical stress and deformations upon cooldown. These deformations may be in particular present in use of the susceptor assembly, that is, when the susceptor assembly is driven at a temperature within the range of typical operating temperatures used for generating an aerosol. Typical operating temperatures may be in close vicinity of the Curie temperature of the second susceptor material.
In order to counteract the undesired mechanical stress and deformations, in particular an out-of-plane bending of the susceptor assembly 1, the susceptor assembly 1 according to the present invention further comprises a third layer 30 that is intimately coupled to the second layer 20. The third layer 30 comprises a specific stress-compensating material and specific layer thickness T30 for compensating differences in thermal expansion occurring in the multi-layer susceptor assembly after a processing of the assembly such that at least in a compensation temperature range an overall thermal deformation of the susceptor assembly 1 is essentially limited to in-plane deformations. The compensation temperature range extends at least from 20 K below the Curie temperature of the second susceptor material up to the Curie temperature of the second susceptor material. Accordingly, the third layer advantageously allows for preserving the original desired shape and preferably also the original desired size of the susceptor assembly in a direction orthogonal to the layer structure of the multi-layer susceptor assembly.
In the present embodiment, the third layer preferably comprises the same material as the first layer, that is, a ferromagnetic stainless steel. Additionally, the layer thickness T30 of the third layer 30 preferably is equal to the layer thickness T10 of the first layer 10. This may prove particularly advantageous for providing a highly symmetric layer structure showing essentially no out-of-plane deformations.
With regard to the embodiment shown in
As the first and third layer 10, 30 are made of stainless steel they advantageously provide an anti-corrosion covering for the nickel material in the second layer 20.
Alternatively, the third layer 30 may comprise a different material and/or thickness as compared to the first layer 10. For example, the third layer 30 may comprise an austenitic stainless steel as stress-compensating material, such as V2a or V24 steel. Advantageously, due to its paramagnetic characteristics and high electrical resistance, austenitic stainless steel only weakly shields the nickel material of the second layer 20 from the electromagnetic field to be applied thereto.
An elongate susceptor assembly 1 is located within the aerosol-forming substrate 102, in contact with the aerosol-forming substrate 102. The susceptor assembly 1 as shown in
The susceptor assembly 1 may be inserted into the aerosol-forming substrate 102 during the process used to form the aerosol-forming substrate, prior to the assembly of the plurality of elements to form the aerosol-generating article.
The aerosol-generating article 100 illustrated in
| Number | Date | Country | Kind |
|---|---|---|---|
| 17164358.8 | Mar 2017 | EP | regional |
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/EP2018/058042 | 3/29/2018 | WO | 00 |
