Abstract: A tank device of an oil circuit of an aircraft engine for stocking oil inside an interior space that is delimited by a wall, having at least one appliance for introducing oil into the interior space. By means of the appliance for introducing oil, the area of the wall that is arranged above a minimal filling level, as it occurs during operation of an aircraft engine, can be impinged with oil.

Abstract: 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.

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 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: An oil tank includes an outer wall with a side limitation and an interior enclosed by the outer wall. A view passage extending from the side limitation into the interior of the tank allows external visual reading of the oil fill level of the tank at or close to the tank center, where changes in the oil fill level caused by inclined positions of the tank are minimal. The view passage includes a beginning of the passage formed in the area of the side limitation that includes a first optically transparent window. An end of the passage includes a second optically transparent window. A passage wall extending between the beginning and end of the passage delimits the view passage against the interior of the tank.

Abstract: A gas turbine engine assembly is connected to a pylon for mounting the gas turbine engine to an aircraft. The assembly has a frame supporting at least one accessory independently of the gas turbine engine. Frame is attached to the pylon at forward and rearward engine mounting locations. The frame includes at least one hollow tube and at least one hollow tube is fluid tight. The one hollow tube is evacuated or contains pressurised fluid and a pressure sensor is provided to detect a change in pressure in the at least one hollow tube to determine if there is a leak in the at least one hollow tube and hence if the frame is damaged. This ensures that the frame may be repaired or replaced before there is a loss of operation of one or more of the accessories which may result in a failure of the gas turbine engine.

Abstract: A turbomachine having a wall that extends circumferentially to a central axis of the turbomachine at least in certain areas, and having at least one insert device that can be connected in a releasable manner to a wall in the area of a recess which is arranged inside the wall. The insert device has a connection device by means of which the insert device can be brought into operative connection with a connection device of the wall. The connection device of the insert device has a projection that extends in the radial direction of the turbomachine at least in certain areas in the mounted state of the insert device, and that in the mounted state of the insert device meshes in a groove of the connection device of the wall. The connection device of the wall has a projection that extends in the radial direction of the turbomachine at least in certain areas in the mounted state of the insert device, and that, in the mounted state of the insert device, meshes in a groove of the connection device of the insert device.

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: An electronically controlled suspension system for a bicycle includes at least one spring element between first and second parts the bicycle, both parts being movably interconnected. At least one parameter of the spring element is modified. At least one actuator influences the spring element to modify the at least one parameter. An electronic module produces a control signal for the at least one actuator. A control device is influenced by the control signal produced by the electronic module. The control device is connected to at least one of the electronic module and the actuator through a radio signal. A corresponding method controls the suspension system for the bicycle and a computer program executes the method.

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: A gas turbine engine assembly is connected to a pylon for mounting the gas turbine engine to an aircraft. The assembly has a frame supporting at least one accessory independently of the gas turbine engine. The frame is attached to the pylon at forward and rearward engine mounting locations. The frame comprises at least one hollow tube and at least one duct is arranged to supply coolant into the at least one hollow tube and the at least one hollow tube is arranged to supply coolant to the at least one accessory.

Abstract: An aircraft engine with a fuel supply appliance and with at least one hydraulic fluid circuit that includes a hydraulic fluid reservoir, and with a heat exchanger. In the area of the heat exchanger, thermal energy can be exchanged between the hydraulic fluid conducted inside the hydraulic fluid circuit and the fuel of the fuel supply appliance. The pressure inside the hydraulic fluid circuit is higher in the area of the heat exchanger than the pressure in the fuel supply appliance. The heat exchanger is connected to the hydraulic fluid reservoir. Outer walls of the heat exchanger and outer walls of the hydraulic fluid reservoir at least partially shield an overlap area between the heat exchanger and the hydraulic fluid reservoir against an environment of the heat exchanger and of the hydraulic fluid reservoir.

Abstract: A seat post for a bicycle comprises a post body having a first end shaped to be connected to a bicycle frame, a second end shaped to be connected to a saddle, at least two longitudinal portions meshing with each other and slidable relative to one another along a longitudinal extension, and a fixing apparatus by which the two longitudinal portions can be fixed to one another in a settable relative position, the fixing apparatus being influenced to selectively fix and unfix by a radio signal.

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: 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: The present invention provides an integrated control device of hydraulic brake for a handlebar of bicycle. The integrated control device includes a brake actuator of hydraulic type mounted on a housing body. The housing body comprises a handgrip portion and an attachment portion to the bicycle handlebar. The brake actuator includes a brake lever hinged on the housing body through a pin. A hydraulic cylinder is provided wherein a slidable piston is slidable that is kinematically connected to the brake lever through kinematic connection elements. A tank for hydraulic fluid is in fluid communication with the hydraulic cylinder. The control device includes an autonomous cartridge that comprises the hydraulic cylinder and the tank, and is removably inserted into a corresponding seat of the housing body. The seat is formed in a head portion of the housing body that is substantially opposite the attachment portion.

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: What is proposed is an aero engine (1) with a bearing chamber (12), which is confined by a first wall area (32) and a second wall area (33) which is embodied so as to be rotatable with respect to the first wall area (32) and in which at least one bearing appliance as well as at least one appliance (38, 39, 40) for introducing oil are arranged. Oil can be introduced into the bearing chamber (12) via at least one appliance (38, 39, 40) for introducing oil substantially against a rotational direction of the first wall area (32) and/or of the second wall area (33) and substantially tangentially to at least one surface (43) of at least one wall area (32, 33) that is facing the bearing chamber (12).

Abstract: 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.

Abstract: 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.