Abstract: A device has two components that delimit a space containing oil. A rotationally fixed component is moved axially to press against an axial sealing surface of a rotatable component by an actuating force to seal the space in a region of another axial sealing surface. An air flow between the two sealing surfaces results in a further actuating force, acting on the fixed component in the axial direction to counteract the actuating force and move the fixed component away from the rotatable component once a defined speed of rotation of the rotatable component is reached. The rotatable component and the fixed component are supplied with oil close to the sealing surfaces. In the installed position of the fixed component, oil is passed from an upper region of the fixed component in the circumferential direction of the fixed component in the direction of a lower region of the fixed component.

Abstract: A device has two components that delimit a space containing oil. A rotationally fixed component is moved axially to press against an axial sealing surface of a rotatable component by an actuating force to seal the space in a region of another axial sealing surface. An air flow between the two sealing surfaces results in a further actuating force, acting on the fixed component in the axial direction to counteract the actuating force and move the fixed component away from the rotatable component once a defined speed of rotation of the rotatable component is reached. The rotatable component and the fixed component are supplied with oil close to the sealing surfaces. In the installed position of the fixed component, oil is passed from an upper region of the fixed component in the circumferential direction of the fixed component in the direction of a lower region of the fixed component.

Abstract: 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.

Abstract: A heat-exchanger device for an aircraft engine, having a fuel-oil heat exchanger for exchanging heat between fuel and oil, and a housing with an air inlet and an air outlet, wherein the fuel-oil heat exchanger is arranged at least partially within the housing such that air flowing from the air inlet to the air outlet can flow over or around the fuel-oil heat exchanger. The invention further relates to a method for operating an aircraft engine.

Abstract: 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.

Abstract: A valve device of a jet engine includes a body, a seat and a flow path between an inlet and an outlet that can be closed and opened. Depending on an actuating force that results from a fluid pressure at a front surface of the body facing the inlet, as well as from a closing force applied to the body, the body can be transferred between open and closed states, and can be transferred into an operational state in which the flow path is opened by a setting device depending on an ambient pressure. The flow path can be opened via the setting device such that a flow cross-section of the flow path corresponds to at least 80% of the flow cross-section of the flow path in the area of the inlet across the entire extension of the flow path between the inlet and the outlet.

Abstract: 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.

Abstract: 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.

Abstract: A method for detecting a fuel leak in a fuel system of an aircraft having at least two engines, where both a first engine and a second engine are each assigned a tank device and each at least one sensor device connected to a control and evaluation device. By means of the at least one sensor device, values for the assigned engine are determined from a group of defined parameters. The control and evaluation device compares the values determined by the sensor devices, corresponding with one another, and detects a fuel leak of the fuel system when there is a divergence in the values of a parameter that exceeds a predetermined threshold value.

Abstract: A heat-exchanger device for an aircraft engine, having a fuel-oil heat exchanger for exchanging heat between fuel and oil, and a housing with an air inlet and an air outlet, wherein the fuel-oil heat exchanger is arranged at least partially within the housing such that air flowing from the air inlet to the air outlet can flow over or around the fuel-oil heat exchanger. The invention further relates to a method for operating an aircraft engine.

Abstract: 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.

Abstract: 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.

Abstract: A valve device of a jet engine includes a body, a seat and a flow path between an inlet and an outlet that can be closed and opened. Depending on an actuating force that results from a fluid pressure at a front surface of the body facing the inlet, as well as from a closing force applied to the body, the body can be transferred between open and closed states, and can be transferred into an operational state in which the flow path is opened by a setting device depending on an ambient pressure. The flow path can be opened via the setting device such that a flow cross-section of the flow path corresponds to at least 80% of the flow cross-section of the flow path in the area of the inlet across the entire extension of the flow path between the inlet and the outlet.

Abstract: A method for detecting a fuel leak in a fuel system of an aircraft having at least two engines, where both a first engine and a second engine are each assigned a tank device and each at least one sensor device connected to a control and evaluation device By means of the at least one sensor device, values for the assigned engine are determined from a group of defined parameters. The control and evaluation device compares the values determined by the sensor devices corresponding with one another, and detects a fuel leak of the fuel system when there is a divergence in the values of a parameter that exceeds a predetermined threshold value.