Back to results
US 2021/0062680 A1Published application
Gas turbine engine of an aircraft
AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorStefan FECHNER
Life of this patent
Estimating the term…
Loading patent…
Loading patent…
AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorStefan FECHNER
Estimating the term…
A description is given of a gas turbine engine of an aircraft, having an engine core which comprises at least one compressor and at least one turbine, through which a core air flow is passed and which are rotatably mounted in the region of bearings. Part of the core air flow flows out of the engine core as a partial air flow into a region situated radially inside the engine core. A device which at least partially deflects the flow of the partial air flow in such a way that a static pressure in the region downstream of the device is lower than upstream of the device is provided in the flow path of the partial air flow, in the transitional region between the engine core and the radially inner region, and thus an axial bearing force starting from a surface on which the lower pressure acts is reduced.
A gas turbine engine of an aircraft, having an engine core which comprises at least one compressor and at least one turbine, through which a core air flow is passed and which are rotatably mounted in the region of bearings, wherein part of the core air flow flows out of the engine core as a partial air flow into a region situated radially inside the engine core, and wherein a device which at least partially deflects the flow of the partial air flow in such a way that a static pressure in the region downstream of the device is lower than upstream of the device is provided in the flow path of the partial air flow, in the transitional region between the engine core and the radially inner region.
Dependencies are inferred from the claim text.