Rolls-Royce Deutschland Ltd & Co. Kg

Juergen Beier

Gideon Daniel Venter

Markus Blumrich

Soeren Braun

A turbofan engine that comprises a primary flow channel inside of which a primary flow flows through a gas generator during operation, a secondary flow channel inside of which a secondary flow is guided past the gas generator during operation, and an oil separator of a lube oil system that has a pipeline for exhausting breather air, wherein the pipeline forms a pipeline end. It is provided that the pipeline end is arranged inside the secondary flow channel, and is provided and configured for the purpose of discharging breather air directly from the pipeline end into the secondary flow channel.

Turbofan engine and a method for exhausting breather air of an oil separator in a turbofan engine

A device of a turbomachine for separating oil from an air-oil volume flow, with a first separation appliance and a second separation appliance, wherein an air-oil volume flow from an oil-loaded area of the turbomachine can be supplied to the first separation appliance, and wherein the air-oil volume flow, the oil loading of which can be reduced in the area of the first separation appliance, can be supplied to the second separation appliance downstream of the first separation appliance by means of a conduit. An appliance for cooling the air-oil volume flow conducted inside the conduit is provided, being arranged downstream of the first separation appliance and upstream of the second separation appliance.

Device of a turbomachine for separating oil from an air-oil volume flow

The present invention describes a device of a jet engine with at least one component arranged in a casing and designed rotatable relative to said casing. At least one air-oil volume flow can be passed out of an area of the jet engine into the casing. In accordance with the invention the air-oil volume flow can be introduced into the casing via an introducing facility at least approximately tangentially to an area of the rotatable component close to at least an outer circumferential area.

Jet engine device with at least one component that is arranged in a casing and that is rotatable to the casing

An oil circuit of an aircraft engine, includes a tank, a lubricant pump and a recirculation pump. The lubricant pump supplies oil via a supply line from the tank to a load of the engine and to an accessory gearbox. Oil is resupplied via a recirculation conduit to the tank by the recirculation pump. The recirculation conduit is connected to the accessory gearbox via a further recirculation conduit. A valve is provided that can be switched between an open switching state and a closed state. In the open switching state of the valve, oil is supplied to the tank via the recirculation conduit. In the closed state of the valve device, an oil feed to the tank via the recirculation conduit is blocked, and oil from the recirculation conduit is supplied to the accessory gearbox via the further recirculation conduit.

Oil circuit of an aircraft engine

An aero engine with a bearing chamber, which is confined by a first wall area and a second wall area which is embodied so as to be rotatable with respect to the first wall area and in which at least one bearing appliance as well as at least one appliance for introducing oil are arranged. Oil can be introduced into the bearing chamber via at least one appliance for introducing oil substantially against a rotational direction of the first wall area and/or of the second wall area and substantially tangentially to at least one surface of at least one wall area that is facing the bearing chamber.

Aero engine with a bearing chamber and an appliance for introducing oil

The present invention describes a jet engine with a device for spraying oil into an air-oil volume flow guided inside a flow cross-section limited by a wall area. The air-oil volume flow is guidable through an oil separator in order to separate the oil. In accordance with the invention, the oil can be sprayed into the air-oil volume flow in the area of the device via an outlet area rigidly connected to the wall area.

Jet engine comprising a device for spraying oil

A tank device of an aero engine, which has an inlet appliance for the supply of an air-oil volume flow into a tank space of the tank device, a separation appliance for the separation of oil from the air-oil volume flow that is supplied to the tank space, a conduit area which is confined by at least one wall and in which an air-oil volume flow can be guided in the area of the tank space at least in certain areas, and an outlet appliance, in the area of which a volume flow can be discharged via a valve appliance from the tank space of the tank device. At least one appliance for introducing oil is provided, by means of which oil can be supplied into the area of the conduit area substantially against a flow direction of the air-oil volume flow which is forming during operation in the conduit area.

Tank device of an aero engine with an appliance for introducing oil

An aircraft engine having a device for separating oil from an air-oil volume flow, where a fluid volume flow with a lower oil load than the air-oil volume flow supplied to the device can be discharged from the device via a line area. The fluid volume flow can be supplied via the line area to a unit by means of which a pressure in the line area downstream of the unit can be increased.

Aircraft engine with an apparatus for separating oil and a device for increasing pressure

The present invention describes an accessory gearbox with a shaft incorporated into a casing and connectable at least in one lateral end area to an accessory unit, with the shaft at least in the lateral end area being designed as a hollow shaft having an inner toothing. To lubricate the inner toothing in the area of the casing at least one baffle device is provided which is designed for guiding hydraulic fluid present in the area of the casing, under the effect of gravity, in the direction of at least one opening provided in the shaft.

Accessory gearbox device

A device of an aircraft engine for separating oil from an air-oil volume flow and an apparatus for introducing oil into the air-oil volume flow. An outlet area of the apparatus for introducing oil is provided in a closed line section, into which the air-oil volume flow can be introduced via an inlet area. In accordance with the invention, a flow cross-section of the line section downstream of the outlet area of the apparatus tapers at least partially like a nozzle and at least in some sections inside a confusor area.

Device of an aircraft engine for separating oil from an air-oil volume flow

The present invention describes a jet engine with a device for spraying oil into an air-oil volume flow guided inside a flow cross-section limited by a wall area. The air-oil volume flow is guidable through an oil separator in order to separate the oil. In accordance with the invention, the oil can be sprayed into the air-oil volume flow in the area of the device via an outlet area designed movable relative to the wall area.

Jet engine comprising a device for spraying oil into an air-oil volume flow

A jet engine includes at least one oil separator, through which an air-oil volume flow can be guided out of several areas supplied with oil for separating the oil, where a device for spraying oil into the air-oil volume flow is provided. Oil can be sprayed in using the device in the area of each connection between an area supplied with oil and the oil separator and/or downstream of a combining area between at least two air-oil volume flows from two or more areas supplied with oil.

Jet engine with at least one oil separator

The present invention describes a jet engine with at least one oil separator, through which an air-oil volume flow can be guided out of at least one area supplied with oil for separating the oil. In accordance with the invention the air-oil volume flow from the area supplied with oil can be introduced into the oil separator via an interior of an accessory gearbox casing. The air can be discharged from the oil separator via an air outlet and the oil via an oil outlet.

Jet engine with at least one oil separator, through which an air-oil-volume flow can be guided

The present invention proposes a structural unit for an aircraft engine having at least one fuel pump of a fuel circuit and at least one hydraulic fluid pump of a hydraulic fluid circuit, where the structural unit can be coupled to an accessory gearbox shaft of an accessory gearbox of the engine.

Assembly for a jet engine of an aircraft

An accessory gearbox for an engine having at least one accessory gearbox shaft connectable to an auxiliary unit and driveable by a drive shaft, the drive shaft being operatively connectable to an engine shaft of the engine. At least one auxiliary unit can be arranged on the drive shaft and/or in the area of the operative connection between the drive shaft and the engine shaft and/or on an accessory gearbox shaft connectable to a further auxiliary unit.

Growing community of inventors

Schulzendorf, Germany

Juergen Beier