A bearing unit comprising rolling elements, housed in a radially inner mounting seat of a casing. The bearing unit includes a radially outer and stationary coated ring provided with a metal ring and a liner of elastomeric material integral with a radially outer surface of the metal ring, a radially inner ring, which is rotatable with respect to an axis of rotation (X), and a row of rolling elements interposed between the coated ring and the radially inner ring. The elastomeric material of the liner is a vulcanized thermoplastic material. The liner is co-molded onto the radially outer surface of the metal ring and may include a cylindrical body and at least two annular protuberances which fit inside corresponding anchoring grooves formed on the surface of the metal ring.

Provided is a sliding material including a substrate; and a copper alloy layer bonded to the substrate. The copper alloy includes 2.0 to 15.0% by mass of tin. The copper alloy layer includes a sliding body part including a sliding surface, and a gradient region including a bond surface with the substrate. A tin concentration in the gradient region reduces from the sliding body part toward the bond surface. A method for producing the siding material is also provided. The method includes preparing the substrate having a first surface and a second surface opposite to the first surface; melting the copper alloy; casting the molten copper alloy on the first surface of the substrate; and solidifying the copper alloy unidirectionally by cooling the substrate from the second surface by a coolant.

Provided is a sliding material including a substrate; and a copper alloy layer bonded to the substrate. The copper alloy includes 2.0 to 15.0% by mass of tin. The copper alloy layer includes a sliding body part including a sliding surface, and a gradient region including a bond surface with the substrate. A tin concentration in the gradient region reduces from the sliding body part toward the bond surface. A method for producing the siding material is also provided. The method includes preparing the substrate having a first surface and a second surface opposite to the first surface; melting the copper alloy; casting the molten copper alloy on the first surface of the substrate; and solidifying the copper alloy unidirectionally by cooling the substrate from the second surface by a coolant.

Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.

A bearing unit with rolling bodies for use in the food and beverage industry, for example. The bearing unit may have a high resistance to wear and to corrosion and may have a radially outer ring, stationary, a radially inner ring, rotatable with respect to an axis of rotation (X), and a sealing and protection device mounted on the radially inner ring and on opposite sides of the radially outer ring, both to protect the radially outer ring from the action of external contaminants and to prevent any such external contaminants from getting into a gap between the radially outer ring and the radially inner ring. The bearing unit may further have protective layer being arranged in contact with the radially inner ring, and being made of composite polymeric material to isolate and protect the radially inner ring from external contaminants.

A bearing unit comprising rolling elements, housed in a radially inner mounting seat of a casing. The bearing unit includes a radially outer and stationary coated ring provided with a metal ring and a liner of elastomeric material integral with a radially outer surface of the metal ring, a radially inner ring, which is rotatable with respect to an axis of rotation (X), and a row of rolling elements interposed between the coated ring and the radially inner ring. The elastomeric material of the liner is a vulcanized thermoplastic material. The liner is co-molded onto the radially outer surface of the metal ring and may include a cylindrical body and at least two annular protuberances which fit inside corresponding anchoring grooves formed on the surface of the metal ring.

A bearing assembly includes a bearing having a first bearing ring, a second bearing ring rotatably disposed relative to the first bearing ring, and a plurality of rolling elements in a bearing interior defined by the first bearing ring and the second bearing ring. Also, at least one layer of non-metallic material on the first bearing ring configured to conduct heat away from the first bearing ring and to electrically insulate the first bearing ring and to fill at least one cavity between the first bearing ring and a component to which the first bearing ring is mounted. The at least one layer may be a first layer of a heat-conducting material and a second layer of a different, electrically insulating material.

A bearing component such as a bearing ring includes a metallic base body and at least one alloy steel coating on the base body, the coating being applied to the base body by deposition welding. The base body is preferably non-alloy steel or cast iron, and the alloy includes at least one carbide-forming transition metal such as niobium, tantalum, zirconium, titanium, hafnium, tungsten, molybdenum, vanadium, or manganese. The coating can form a raceway of the bearing component or a structural element such as a flange. Also a method of forming such a bearing component is provided.

Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.