Abstract: A roller element device, in particular for a gas turbine engine, comprises an outer ring with an inner raceway, an inner ring with an outer raceway, and roller elements which are arranged between the raceways so as to roll thereon, wherein the outer ring and the inner ring are each connected via a connecting portion to a respective fixing portion for fixing to one of two components which are rotatable relative to each other about a rotation axis, and the connecting portions are formed such that the two raceways can be jointly tilted at least in portions relative to the rotation axis.

Abstract: A gearbox assembly for a gas turbine engine comprises a planetary gearbox having at least one ring gear and at least one planet gear, which exerts a force on the ring gear in the direction of a force vector as it rolls on said ring gear; and a holding device for fastening the at least one ring gear on another structure, having a first section, which extends in the axial direction on one side of the force vector and/or of a straight-line extension thereof, and having a second section, which extends in the axial direction on the other side of the force vector and/or of the straight-line extension thereof. A gas turbine engine and a method for producing a gearbox assembly are furthermore made available.

Abstract: A roller element device, in particular for a gas turbine engine, comprises an outer ring with an inner raceway, an inner ring with an outer raceway, and roller elements which are arranged between the raceways so as to roll thereon, wherein the outer ring and the inner ring are each connected via a connecting portion to a respective fixing portion for fixing to one of two components which are rotatable relative to each other about a rotation axis, and the connecting portions are formed such that the two raceways can be jointly tilted at least in portions relative to the rotation axis.

Abstract: A jet engine with a chamber which is delimited by a housing and inside of which a rotatable appliance that can be impinged by hydraulic fluid is arranged, wherein hydraulic fluid and air introduced through the housing into the chamber can be discharged from the chamber. In the area through which air and hydraulic fluid can be discharged from the chamber, the housing is embodied with a separating appliance in the area of which air and hydraulic fluid can be separated from each other, and/or a deflector appliance, by means of which air, hydraulic fluid and/or an air-oil mixture in the chamber can be guided in the direction of the area in a targeted manner, is provided upstream of the area of the housing.

Abstract: A heat exchange system for a power gear box mechanically coupling at least low pressure compressor stage with at least one turbine stage in a turbo engine, in particular an aircraft turbo engine, is provided. At least one heat transfer device is enclosed, embedded and/or attached with the casing of the power gear box, wherein at least one airflow is directed to the at least one heat transfer device for thermally controlling the power gear box.

Abstract: A heat exchange system for a power gear box mechanically coupling at least one low pressure compressor stage with at least one turbine stage in a turbo engine, in particular an aircraft turbo engine, is provided. At least one heat transfer device is enclosed, embedded and/or attached with the casing of the power gear box and the casing and/or the heat transfer device comprise at least one heat transfer and/or fluid flow guiding structure, in particular a ribbed surface, a finned surface and/or a studded surface, wherein at least one airflow is directed to the at least one heat transfer device for thermally controlling the power gear box.

Abstract: A gearbox assembly for a gas turbine engine comprises a planetary gearbox having at least one ring gear and at least one planet gear, which exerts a force on the ring gear in the direction of a force vector as it rolls on said ring gear; and a holding device for fastening the at least one ring gear on another structure, having a first section, which extends in the axial direction on one side of the force vector and/or of a straight-line extension thereof, and having a second section, which extends in the axial direction on the other side of the force vector and/or of the straight-line extension thereof. A gas turbine engine and a method for producing a gearbox assembly are furthermore made available.

Abstract: A jet engine with a chamber which is delimited by a housing and inside of which a rotatable appliance that can be impinged by hydraulic fluid is arranged, wherein hydraulic fluid and air introduced through the housing into the chamber can be discharged from the chamber. In the area through which air and hydraulic fluid can be discharged from the chamber, the housing is embodied with a separating appliance in the area of which air and hydraulic fluid can be separated from each other, and/or a deflector appliance, by means of which air, hydraulic fluid and/or an air-oil mixture in the chamber can be guided in the direction of the area in a targeted manner, is provided upstream of the area of the housing.

Abstract: A heat exchange system for a power gear box mechanically coupling at least low pressure compressor stage with at least one turbine stage in a turbo engine, in particular an aircraft turbo engine, is provided. At least one heat transfer device is enclosed, embedded and/or attached with the casing of the power gear box, wherein at least one airflow is directed to the at least one heat transfer device for thermally controlling the power gear box.

Abstract: A heat exchange system for a power gear box mechanically coupling at least one low pressure compressor stage with at least one turbine stage in a turbo engine, in particular an aircraft turbo engine, is provided. At least one heat transfer device is enclosed, embedded and/or attached with the casing of the power gear box and the casing and/or the heat transfer device comprise at least one heat transfer and/or fluid flow guiding structure, in particular a ribbed surface, a finned surface and/or a studded surface, wherein at least one airflow is directed to the at least one heat transfer device for thermally controlling the power gear box.