Abstract: An apparatus for oil lubrication of a rotationally fixed connection between two shafts. A first shaft engages with a hollow region of the second shaft. The shafts are operatively connected to each other in a form-fitting manner in the overlapping region. Oil is introduced into a first chamber in the hollow region, which chamber is connected to a second chamber in the hollow region. The second chamber is connectable to a third chamber is arranged in the overlapping region. The fluidic connection between the second chamber and the third chamber is separated above a defined oil volume in the second chamber and above a rotational speed threshold of the shafts via a sealing element. The sealing element is reversibly deformable by the oil volume in the second chamber and the centrifugal force acting thereon and, in the deformed state, seals the connection between the second and third chambers.

Abstract: A gas turbine engine has an accessory gearbox disposed outside of a bypass channel and connected to a housing part, which radially delimits the bypass channel, in a connection region near the housing part and in a connection region far from the housing part. A connecting element is provided between the housing part and the connection region far from the housing part. A longitudinal axis of the connecting element includes an angle in the range of 75° to 115° with a vertical axis of the accessory gearbox. The connecting element can vary a distance between the far connection region and a connection point of the connecting element on the housing part such that deformation of the housing part and a resulting position change of the connection point cause a lesser deflection of the accessory gearbox than a deflection with an unchanged length of the connecting element.

Abstract: A gas turbine engine has an accessory gearbox disposed outside of a bypass channel and connected to a housing part, which radially delimits the bypass channel, in a connection region near the housing part and in a connection region far from the housing part. A connecting element is provided between the housing part and the connection region far from the housing part. A longitudinal axis of the connecting element includes an angle in the range of 75° to 115° with a vertical axis of the accessory gearbox.The connecting element can vary a distance between the far connection region and a connection point of the connecting element on the housing part such that deformation of the housing part and a resulting position change of the connection point cause a lesser deflection of the accessory gearbox than a deflection with an unchanged length of the connecting element.

Abstract: An apparatus for oil lubrication of a rotationally fixed connection between two shafts. A first shaft engages with a hollow region of the second shaft. The shafts are operatively connected to each other in a form-fitting manner in the overlapping region. Oil is introduced into a first chamber in the hollow region, which chamber is connected to a second chamber in the hollow region. The second chamber is connectable to a third chamber is arranged in the overlapping region. The fluidic connection between the second chamber and the third chamber is separated above a defined oil volume in the second chamber and above a rotational speed threshold of the shafts via a sealing element. The sealing element is reversibly deformable by the oil volume in the second chamber and the centrifugal force acting thereon and, in the deformed state, seals the connection between the second and third chambers.

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 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: 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.

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 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 pressurized 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 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: A master cylinder for a hydraulic brake or clutch, the master cylinder comprising a lever and a cylinder housing in which a piston is slidably arranged, wherein the piston is secured against rotation in the cylinder housing, and a piston position detection device having a signal member asymmetrically arranged with respect to a circumference of the piston and a detection member that is at least one of assigned to the signal member and opposite to the signal member.

Abstract: 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.

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: A master cylinder for a hydraulic brake or clutch system, in particular, a handlebar steered vehicle, in particular a bicycle, comprises a housing containing a cylinder chamber, in which are disposed a piston slidable therein and a pressure chamber. A compensation chamber is connected with the pressure chamber through at least one compensation bore. Also provided is a cover closing the housing and a counterpart for mounting the master cylinder on a handlebar tube. Further provided is at least one connecting device for connecting the counterpart with the housing of the master cylinder. Included with the connecting device is a first connecting portion for connecting the cover with the housing of the master cylinder and a second connecting portion for connecting the counterpart with the master cylinder and for mounting the master cylinder on a handlebar tube.

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 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 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: 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 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.