Abstract: A centrifugal oil separator (3) provided with a metallic foam structure (4) and at least one high-voltage discharge electrode (5) arranged upstream of the metallic foam structure (4) is a component of a hollow engine shaft (2), with the metallic foam structure (4) and the high-voltage discharge electrode(s) (5) being integrated into the engine shaft (2) and energy transmission to the high-voltage discharge electrodes (5) being transformatory. Such a centrifugal oil separator, space-savingly arranged in an engine shaft, enables a high rate of oil separation to be achieved despite the centrifugal forces being low in particular in the area of the engine shaft, thus ensuring low oil consumption and preventing oil-contaminated air from getting into the atmosphere.

Abstract: On a centrifugal oil separator for an aircraft engine for separating the oil particles contained in the vent air, a metallic foam body (7), into which the loaded vent airflow (3) is introduced, is firmly integrated into a hollow-type engine shaft (1), while high-voltage electrodes (6), which electrostatically charge the oil droplets in the vent air, are arranged outside the engine shaft (1) within the vent airflow (3) forwarded to the engine shaft (1). The simply designed oil separator, which can be space-savingly arranged and cost-effectively produced, ensures efficient separation of even minute oil droplets from the air-oil mixture.

Abstract: An oil pre-heating apparatus for an aircraft gas turbine has a suction line 2 connectable to an oil tank 1 of an aircraft gas turbine, with a heat source 3 connected to the suction line 2 and operated independently of the aircraft and with a return line 4 connected to the heat source 3 and connectable to the oil tank 1.

Abstract: An aircraft gas-turbine oil tank has a breather outlet tube 2 branching off from an upper area of the oil tank 1 and connecting to a breather and a connecting tube 6 joining to a bottom area of the oil tank 1. An air guide tube which is open at both ends is arranged in the upper area of the oil tank 1, with the air guide tube 3 protruding into the breather outlet tube 2 and extending into a middle area of the oil tank 1.

Abstract: On a centrifugal oil separator for an aircraft engine for separating the oil particles contained in the vent air, a metallic foam body (7), into which the loaded vent airflow (3) is introduced, is firmly integrated into a hollow-type engine shaft (1), while high-voltage electrodes (6), which electrostatically charge the oil droplets in the vent air, are arranged outside the engine shaft (1) within the vent airflow (3) forwarded to the engine shaft (1). The simply designed oil separator, which can be space-savingly arranged and cost-effectively produced, ensures efficient separation of even minute oil droplets from the air-oil mixture.

Abstract: A centrifugal oil separator (3) provided with a metallic foam structure (4) and at least one high-voltage discharge electrode (5) arranged upstream of the metallic foam structure (4) is a component of a hollow engine shaft (2), with the metallic foam structure (4) and the high-voltage discharge electrode(s) (5) being integrated into the engine shaft (2) and energy transmission to the high-voltage discharge electrodes (5) being transformatory. Such a centrifugal oil separator, space-savingly arranged in an engine shaft, enables a high rate of oil separation to be achieved despite the centrifugal forces being low in particular in the area of the engine shaft, thus ensuring low oil consumption and preventing oil-contaminated air from getting into the atmosphere.

Abstract: An aircraft gas-turbine oil tank has a breather outlet tube 2 branching off from an upper area of the oil tank 1 and connecting to a breather and a connecting tube 6 joining to a bottom area of the oil tank 1. An air guide tube which is open at both ends is arranged in the upper area of the oil tank 1, with the air guide tube 3 protruding into the breather outlet tube 2 and extending into a middle area of the oil tank 1.

Abstract: An oil pre-heating apparatus for an aircraft gas turbine has a suction line 2 connectable to an oil tank 1 of an aircraft gas turbine, with a heat source 3 connected to the suction line 2 and operated independently of the aircraft and with a return line 4 connected to the heat source 3 and connectable to the oil tank 1.