An inductor array of the invention includes a magnetic base body, a first internal conductor within the base body, and a second internal conductor adjacent to the first internal conductor. The first and second internal conductors are arranged along a reference axis. The base body includes an inter-conductor region between the first and second internal conductors. The inter-conductor region has a first section cut along a reference plane including the reference axis, and a first reference axis direction dimension of the first section in the reference axis direction may be less than double a shortest distance between the first internal conductor and a surface of the base body in the reference plane. A first aspect ratio of the first section, which is a ratio of a first orthogonal direction dimension in a direction orthogonal to the reference axis to the first reference axis direction dimension, may be less than 1.

An inductor array of the invention includes a magnetic base body, a first internal conductor within the base body, and a second internal conductor adjacent to the first internal conductor. The first and second internal conductors are arranged along a reference axis. The base body includes an inter-conductor region between the first and second internal conductors. The inter-conductor region has a first section cut along a reference plane including the reference axis, and a first reference axis direction dimension of the first section in the reference axis direction may be less than double a shortest distance between the first internal conductor and a surface of the base body in the reference plane. A first aspect ratio of the first section, which is a ratio of a first orthogonal direction dimension in a direction orthogonal to the reference axis to the first reference axis direction dimension, may be less than 1.

The invention relates to an electromechanical device (10) for an aircraft, comprising: —a housing (12) having a radially internal surface (S12), —a magnetic circuit formed by a stack of laminated sheets and composed of an annular yoke (16), said yoke being arranged on the radially internal surface of said housing, said yoke having a radially internal surface (S16), —at least one low-frequency coil component (18), said coil component being integrated over at least part of the radially internal surface of said yoke.

The invention relates to an electromechanical device (10) for an aircraft, comprising: —a housing (12) having a radially internal surface (S12), —a magnetic circuit formed by a stack of laminated sheets and composed of an annular yoke (16), said yoke being arranged on the radially internal surface of said housing, said yoke having a radially internal surface (S16), —at least one low-frequency coil component (18), said coil component being integrated over at least part of the radially internal surface of said yoke.

An electromagnetic induction device comprises a closed magnetic circuit, without air gap, of which at least one first part is substantially rectilinear and surrounded by a sleeve, the sleeve being surrounded by an electrical conductor which comprises at least one metal sheet electrically insulated on at least one of its faces, wherein at least the first part of the magnetic circuit has a section of circular form.

An electromagnetic induction device comprises a closed magnetic circuit, without air gap, of which at least one first part is substantially rectilinear and surrounded by a sleeve, the sleeve being surrounded by an electrical conductor which comprises at least one metal sheet electrically insulated on at least one of its faces, wherein at least the first part of the magnetic circuit has a section of circular form.

A core includes a laminated body. The laminated body includes a plurality of electrical steel sheets stacked one on another. The laminated body includes a contact area between a pair of adjacent electrical steel sheets of the plurality of electrical steel sheets. The contact area includes a first friction area and a second friction area with friction coefficients different from each other.

Provided is a grain-oriented electrical steel sheet having better transformer iron loss property than conventional grain-oriented electrical steel sheets. A grain-oriented electrical steel sheet comprises: a steel substrate; a forsterite film on a surface of the steel substrate; and a Cr-depleted layer at a boundary between the steel substrate and the forsterite film, the Cr-depleted layer having a Cr concentration that is 0.70 times to 0.90 times a Cr concentration of the steel substrate.

Provided is a grain-oriented electrical steel sheet having better transformer iron loss property than conventional grain-oriented electrical steel sheets. A grain-oriented electrical steel sheet comprises: a steel substrate; a forsterite film on a surface of the steel substrate; and a Cr-depleted layer at a boundary between the steel substrate and the forsterite film, the Cr-depleted layer having a Cr concentration that is 0.70 times to 0.90 times a Cr concentration of the steel substrate.

In at least some implementations, a lamination stack includes a plurality of plates coupled together, each plate including at least one leg that collectively define a leg of the stack, with the leg of the stack arranged so that a wire coil may be arranged on the leg of the stack, and wherein the leg of the stack includes a location feature arranged to facilitate location of the stack relative to an adjacent component. In at least some implementations, the location feature may be integrally formed with at least one of the plates, and may be defined by a projection extending from a free end of at least one leg of the stack.