Abstract: The invention relates to a device forming a foil air bearing, comprising a cylindrical sleeve (10) extending along a longitudinal direction, and having an inner surface (11) which defines a central bore, characterized in that it further comprises: at least one longitudinal notch (40, 50, 60) formed in said cylindrical sleeve and opening radially into said central bore; a first peripheral inner lining, called the bump lining, comprising at least one metal foil equipped with radial projections, called the bump foil (22, 23, 24), each bump foil having, at each end, a radial tongue, called the radial bump tongue (22a, 22b, 23a, 23b, 24a, 24b), housed freely in a longitudinal notch (40, 50, 60); a second peripheral inner lining, called the top lining, comprising at least one metal foil, called the top foil (32, 33, 34), each top foil having, at each end, a radial tongue, called the radial top tongue (32a, 32b, 33a, 33b, 34a, 34b), housed freely in a longitudinal notch (40, 50, 60).

Abstract: The invention relates to a device forming a foil air bearing, comprising a cylindrical sleeve (10) extending along a longitudinal direction, and having an inner surface (11) which defines a central bore, characterized in that it further comprises: at least one longitudinal notch (40, 50, 60) formed in said cylindrical sleeve and opening radially into said central bore; a first peripheral inner lining, called the bump lining, comprising at least one metal foil equipped with radial projections, called the bump foil (22, 23, 24), each bump foil having, at each end, a radial tongue, called the radial bump tongue (22a, 22b, 23a, 23b, 24a, 24b), housed freely in a longitudinal notch (40, 50, 60); a second peripheral inner lining, called the top lining, comprising at least one metal foil, called the top foil (32, 33, 34), each top foil having, at each end, a radial tongue, called the radial top tongue (32a, 32b, 33a, 33b, 34a, 34b), housed freely in a longitudinal notch (40, 50, 60).

Abstract: A method for coating a turbomachine part with a self-lubricating includes: providing a rotor or thrust disc of the turbomachine; applying, by a thermal spraying process, a self-lubricating coating having of a mixture of 50 to 90 wt % of alumina (Al2O3) with titanium oxide (TiO2) to a surface of the rotor and/or a surface; and finishing the coated surface of the rotor and/or thrust disc.

Abstract: A method for coating a turbomachine part with a self-lubricating includes: providing a rotor or thrust disc of the turbomachine; applying, by a thermal spraying process, a self-lubricating coating having of a mixture of 50 to 90 wt % of alumina (Al2O3) with titanium oxide (TiO2) to a surface of the rotor and/or a surface; and finishing the coated surface of the rotor and/or thrust disc.

Abstract: A method for producing a corrugated foil bearing stiffener involves starting with an austenitic nickel superalloy sheet (15) having an elasticity limit higher than 500 MPa, and subjecting the sheet (15) to at least one step of press bending plastic deformation of the entire thickness of same with a deformation energy higher than 10 kJ in a time shorter than 10?5 s in such a way as to create corrugations.

Abstract: This aerodynamic foil bearing has a sleeve (4) inside which are arranged: a foil referred to as the top foil (16), and a bump foil (14) arranged between the top foil (16) and the sleeve (4), a foil (12) of viscoelastic material arranged between an inner face of the sleeve (4) and the bump foil (14).

Abstract: High temperature use of a self lubricating coating material in a foil bearing and part coated with such a material. A material according to the disclosure includes between 50 and 90 wt % of alumina (Al2O3), as well as an oxide selected from the group consisting of titanium oxide (TiO2), chromium oxide (Cr2O3), and a mixture of these. Application to a rotor and/or a thrust disc at least partially covered with such a material.

Abstract: This aerodynamic foil bearing has a sleeve (4) inside which are arranged: a foil referred to as the top foil (16), and a bump foil (14) arranged between the top foil (16) and the sleeve (4), a foil (12) of viscoelastic material arranged between an inner face of the sleeve (4) and the bump foil (14).

Abstract: The aerodynamic foil bearing in the form of a radial or axial thrust bearing, includes a rotor and a stator including a support designed to support, facing the rotor, a lift device including: a plurality of evenly distributed elastic foils fixed by a fixing edge to a surface of the lift device facing the rotor; rows of ventilation orifices passing through the lift device and opening between a free edge of each elastic foil and the fixing edge of the next foil, wherein the support includes a cavity having grooves extending under the rows of ventilation orifices and at least one circular groove intersecting the grooves and supplied with a stream of pressurized cooling gas to distribute same so as to cool the underside of each foil and provide a supply of fresh gas above the next foil to compensate for gas losses at the ends of the bearing.

Abstract: A method for producing a corrugated foil bearing stiffener involves starting with an austenitic nickel superalloy sheet (15) having an elasticity limit higher than 500 MPa, and subjecting the sheet (15) to at least one step of press bending plastic deformation of the entire thickness of same with a deformation energy higher than 10 kJ in a time shorter than 10?5 s in such a way as to create corrugations.

Abstract: The aerodynamic foil bearing in the form of a radial or axial thrust bearing, includes a rotor and a stator including a support designed to support, facing the rotor, a lift device including: a plurality of evenly distributed elastic foils fixed by a fixing edge to a surface of the lift device facing the rotor; rows of ventilation orifices passing through the lift device and opening between a free edge of each elastic foil and the fixing edge of the next foil, wherein the support includes a cavity having grooves extending under the rows of ventilation orifices and at least one circular groove intersecting the grooves and supplied with a stream of pressurized cooling gas to distribute same so as to cool the underside of each foil and provide a supply of fresh gas above the next foil to compensate for gas losses at the ends of the bearing.