Abstract: 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.

Abstract: A device with a torque-proof first structural component and a second structural component that is connected at least in certain areas in a rotatable manner to the first structural component, wherein hydraulic fluid can be guided to lubrication points via the first structural component and the second structural component. The second structural component is embodied with blade areas which are extending substantially at a defined angle in the radial direction inside the second structural component and between which transmission areas for hydraulic fluid of the second structural component are provided, with their flow cross sections decreasing in the transmission areas in the flow direction of the hydraulic fluid.

Abstract: 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.

Abstract: A device includes a torque-proof first structural component and a second structural component rotatably connected to the first component. Hydraulic fluid is guided to lubrication points via the components. A sealing device seals an interface between the components. The interface includes a transition area limited by areas of the components that overlap in the radial direction and which carries hydraulic fluid, and which is connected to supply areas for hydraulic fluid of the first component and transmission areas for hydraulic fluid of the second component. The hydraulic fluid forms a floating hydrodynamic bearing between the components. The sealing device includes at least one thread area in the area of a surface of the second component or of the first component that is facing towards the surface of the first component or the second component.

Abstract: The present invention describes a gas turbine having two shafts, which are rotatably mounted using bearing devices in the area of a casing. An intermediate shaft sealing device is arranged between the bearing devices, which includes a sealing element connected to a first shaft, in which a further sealing element connected to the second shaft radially engages. An operating pressure is applied, in the area limited by the shafts in the axial direction of the shafts, to facing effective areas of the sealing elements, while the pressure prevailing in the area outside the shafts in the axial direction acts on effective areas of the sealing elements facing away from one another. A ratio between the outer diameters limiting the facing effective areas and the inner diameters likewise limiting these effective areas is in each case greater than or equal to 1.25.

Abstract: What is described is an aircraft engine with a compressor device and with a fan device. In the area of a compressor shaft, the compressor device is connected via an epicyclic gear to a fan shaft. A planetary web is operatively connected via bearing devices to the planetary gears. A ring gear is coupled with the fan shaft and a sun gear of the epicyclic gear is coupled with the compressor shaft, while the planetary carrier is held at the housing side in a torque-proof manner. The ring gear is connected via a flexible connection device to the fan shaft and/or the planetary carrier is connected via a flexible connection device to the housing. In the area of the connection device, movements between the ring gear and the planetary gears and/or between the planetary carrier and the housing can be at least approximately compensated in the radial and the axial direction.

Abstract: 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.

Abstract: An aircraft engine includes at least one electrical apparatus, which can be driven by a driveshaft in order to generate electrical energy. A hydrodynamic torque converter, with guide blades, which can be adjusted via a mechanism, is arranged between the driveshaft and the electrical apparatus. The guide blades are adjusted as a function of a rotational speed of the driveshaft, wherein the rotational speed of a shaft of the electrical apparatus operated as a generator can be adjusted, essentially within a predefined rotational speed range, via the adjustment of the guide blades.

Abstract: 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.

Abstract: The present invention proposes a structural unit (21) for arrangement on a hydraulic fluid tank of a jet engine having a vision device (23) and a sensor device (25), which can independently of one another determine a level of a hydraulic fluid present in a hydraulic fluid tank (1) when the structural unit (21) is arranged on a hydraulic fluid tank. A fastening device (27) is provided to fix the structural unit (21) on the hydraulic fluid tank.

Abstract: 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.

Abstract: 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.

Abstract: The present invention proposes an accessory gearbox for an engine with a drive shaft operatively connectable to a main shaft of the engine, with an extension shaft being provided which can be put into a detachable operative connection to the drive shaft substantially coaxially to said drive shaft of the accessory gearbox At least one auxiliary unit can be detachably arranged on the extension shaft.

Abstract: 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.

Abstract: 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.

Abstract: The present invention proposes an accessory gearbox (9) for an engine with a drive shaft (12) operatively connectable to a main shaft of the engine, with an extension shaft (29) being provided which can be put into a detachable operative connection to the drive shaft (12) substantially coaxially to said drive shaft (12) of the accessory gearbox (9). At least one auxiliary unit (39) can be detachably arranged on the extension shaft (29).

Abstract: On a gas-turbine engine, in particular an aircraft engine, with a fan, a fan casing and a fan duct as well as with high-pressure and low-pressure turbines arranged behind each other in flow direction in the casing of the engine, the auxiliaries connected are to be operated with only a small increase in engine power. For this purpose in the flow direction of the airflow (20) exiting from the high-pressure turbine (15) a bleeding mechanism is provided for bleeding radially into the fan duct (4) at least part of the airflow (20) leaving the high-pressure turbine (15) on the upstream side of the low-pressure turbine (16).

Abstract: On a two-shaft engine for an aircraft gas-turbine with a central low-pressure shaft, with a high-pressure shaft co-axially surrounding the low-pressure shaft and with bearing units supporting the shafts on the engine casing, the bearing loads of the high-pressure shaft are directed upstream towards the fan and the bearing loads of the low-pressure shaft are directed downstream. In order to reduce axial bearing load of the high-pressure bearing unit, the oppositely directed bearing loads of the low-pressure shaft (3) and of the high-pressure shaft (6) partly compensate one another, in that the front thrust bearing unit (10) of the high-pressure shaft (6) is supported on the engine casing (1) and the front thrust bearing unit (12) of the low-pressure shaft (3) is supported on the high-pressure shaft (6).

Abstract: With a two-shaft engine, the accessory drive gearbox (5) for the operation of a generator and other auxiliaries (6) is connected to the high-pressure shaft (1) via a high-pressure shaft gearbox (3), which is coupled to a low-pressure shaft gearbox (8) connecting to the low-pressure shaft (7), via an overrunning clutch (11), a conical-pulley variable transmission (10) settable on the basis of the shaft speed on both sides, and a first switchable clutch (9). Under certain operating conditions with low speed of the high-pressure shaft or in case of engine failure, the power of the low-pressure shaft, with the clutch (9) engaged, is transferred to the high-pressure shaft gearbox and hence to the accessory drive gearbox via the conical-pulley variable transmission, which compensates for shaft speed difference, and the overrunning clutch, in order to reliably further operate the generator and other accessories with low fuel consumption or by windmilling only.

Abstract: On a two-shaft engine for an aircraft gas-turbine with a central low-pressure shaft, with a high-pressure shaft co-axially surrounding the low-pressure shaft and with bearing units supporting the shafts on the engine casing, the bearing loads of the high-pressure shaft are directed upstream towards the fan and the bearing loads of the low-pressure shaft are directed downstream. In order to reduce axial bearing load of the high-pressure bearing unit, the oppositely directed bearing loads of the low-pressure shaft (3) and of the high-pressure shaft (6) partly compensate one another, in that the front thrust bearing unit (10) of the high-pressure shaft (6) is supported on the engine casing (1) and the front thrust bearing unit (12) of the low-pressure shaft (3) is supported on the high-pressure shaft (6).