Abstract: An oil supply system for a propeller turbine engine includes a first oil circuit for supplying the turbomachine and a second oil circuit for supplying the propeller gearbox and the high-pressure pump associated with a propeller adjusting device. The two oil circuits are integrated into a common oil tank and connected to one another by means of an oil supply line in the flow direction downstream of the first and the second oil conveying pumps in such a way that a limited oil volumetric flow can flow from the first oil circuit into the second oil circuit, and only in this direction, if the pressure difference between the first and the second oil circuits falls below a certain level in the event of a pressure reduction in the second oil circuit.

Abstract: An oil supply system for a propeller turbine engine including a propeller, a propeller gearbox connected to the propeller and a propeller adjusting device for altering the pitch angle of the propeller blades. The system includes an oil circuit and a propeller main pump for supplying the propeller gearbox and a propeller high-pressure pump supplying the propeller adjusting device with oil. The system includes an oil accumulator for providing, in the event of an undersupply of oil by the propeller main pump, oil contained in the oil accumulator to the inlet of the propeller high-pressure pump such that the pump inlet pressure at the inlet of the propeller high-pressure pump does not fall short of a certain minimum value. The oil accumulator is incorporated into the inflow to the propeller high-pressure pump to be continuously supplied and charged with oil of the propeller main pump.

Abstract: An oil supply system for an aircraft engine, includes at least one oil circuit including an oil tank having a closing valve associated with an outlet opening of the oil tank into a suction line, an oil pump, and at least one consumer to be supplied oil via a pressure line. A negative pressure relief line having a shut-off valve is connected to the suction line for ensuring pressure relief in the suction line after shutdown. Via a diaphragm volume flow limiter alternatively incorporated into the relief line, the suction line can also be connected permanently to the pressure line. A negative pressure occurring in the suction line after shutdown of the engine when the closing valve is closed and the plastic deformation of the suction line as well as a reduction of the pump suction capacity are thus avoided.

Abstract: A casing arrangement of a gas turbine includes a sensor element of elongated design that when seen in the longitudinal direction has a front end and a rear end, a first casing structure, a second casing structure arranged at a distance from the first casing structure and having a receptacle for the front end of the sensor element, and a guide structure having an elongated guide opening for the sensor element. The sensor element extends between the first casing structure and the second casing structure, while being arranged along a section in the elongated guide opening of the guide structure, where the sensor element due to the elongated guide opening is aligned and positioned such that its front end is located, and can only be located, inside the receptacle of the second casing structure.

Abstract: A bearing chamber venting system for an aircraft engine includes at least one bearing chamber air-sealed by sealing air via bearing chamber seals, a vent line connected to the bearing chamber, via which an oil/air mixture present in the bearing chamber is vented out, and an oil separator connected to the vent line. An oil return line is connected to the oil separator via which oil separated from the mixture is discharged. An air outlet line is connected to the oil separator, via which cleaned air is passed to the environment. An air ejector is arranged in the air outlet line to eject gas supplied to the air ejector into the air outlet line at a speed which is greater than the speed of the air flowing in the air outlet line and passed to the environment out of the oil separator.

Abstract: An oil supply system for a propeller turbine engine includes a first oil circuit for supplying the turbomachine and a second oil circuit for supplying the propeller gearbox and the high-pressure pump associated with a propeller adjusting device. The two oil circuits are integrated into a common oil tank and connected to one another by means of an oil supply line in the flow direction downstream of the first and the second oil conveying pumps in such a way that a limited oil volumetric flow can flow from the first oil circuit into the second oil circuit, and only in this direction, if the pressure difference between the first and the second oil circuits falls below a certain level in the event of a pressure reduction in the second oil circuit.

Abstract: In an oil supply system for an aircraft engine, including at least one oil circuit, into which an oil tank having a closing valve associated with the outlet opening of the oil tank into a suction line, an oil pump and at least one consumer to be supplied with oil by means of a pressure line are integrated, a negative pressure relief line having a shut-off valve incorporated is connected to the suction line, said negative pressure relief line for ensuring pressure relief in the suction line being connectable after shutdown of the engine to the pressure line or to the ambient air. Via a volume flow limiter designed as a diaphragm and alternatively incorporated into said negative pressure relief line, the suction line can also be connected permanently to the pressure line. A negative pressure occurring in the suction line after shutdown of the engine when the closing valve is closed and the plastic deformation of the suction line as well as a reduction of the pump suction capacity are thus avoided.

Abstract: An oil supply system for a propeller turbine engine including a propeller, a propeller gearbox connected to the propeller and a propeller adjusting device for altering the pitch angle of the propeller blades. The system includes an oil circuit and a propeller main pump for supplying the propeller gearbox and a propeller high-pressure pump supplying the propeller adjusting device with oil. The system includes an oil accumulator for providing, in the event of an undersupply of oil by the propeller main pump, oil contained in the oil accumulator to the inlet of the propeller high-pressure pump such that the pump inlet pressure at the inlet of the propeller high-pressure pump does not fall short of a certain minimum value. The oil accumulator is incorporated into the inflow to the propeller high-pressure pump to be continuously supplied and charged with oil of the propeller main pump.