A gas turbine engine for an aircraft may include a shaft fixed to a compressor of the gas turbine engine, at least one of a turboprop and a turbofan, a power gearbox having a power output shaft fixed to the at least one of the turboprop and the turbofan, wherein the power gearbox receives an input rotation from the shaft, an auxiliary gearbox having an auxiliary output shaft powering at least one auxiliary component of the gas turbine engine, a first lubrication system, and a second lubrication system that is separated from the first lubrication system. The first lubrication systems may circulate a first lubricant through the power gearbox, and the second lubrication system may circulate a second lubricant through the auxiliary gearbox.

A system. The system includes a valve assembly. The valve assembly includes a first port, a second port fluidically couplable with the first port upon application of negative pressure at the first port, a third port fluidically couplable with the first port upon application of positive pressure at the first port, and a first check valve positioned between the first port and the second port. The system also includes a second check valve fluidically couplable with the third port upon the application of the positive pressure at the first port. The second check valve is positioned external to the valve assembly.

An engine assembly includes a small air-cooled engine and a dry sump lubrication system including an external oil reservoir, wherein the dry sump lubrication system has an overall oil capacity that provides at least five hundred hours of engine oil life.

The invention relates to a system (1) for lubricating an aeronautical engine (5) and a reduction gearbox (4) associated with the engine (5), the system (1) comprising an oil reservoir (2) feeding at least one first supply pump (3) supplying a first circuit (6) of the gearbox (4) opening into at least one chamber (4a) of the gearbox (4) and, in parallel, a second circuit (7) of the engine (5) opening into chambers (5a) of the engine (5). The second circuit (7) comprises a jet pump (9) of variable cross section supplied at least by the first supply pump (3), bypassing the first circuit (6), a second driven supply pump (10) being integrated into the second circuit (7) downstream of the jet pump (9), a portion of a flow (Qp) in the first circuit (6) being drawn off by the jet pump (9) to supply the second circuit (7).

A cooling lubrication system comprises a dry sump, an oil tank, and a pump system that operates an oil circuit in which an oil pump delivers oil from the dry sump into the oil tank, and the pump system comprises a vane cell pump and a gerotor pump on a shaft.

A cooling lubrication system comprises a dry sump, an oil tank, and a pump system that operates an oil circuit in which an oil pump delivers oil from the dry sump into the oil tank, and the pump system comprises a vane cell pump and two gerotor pumps on a shaft.

A housing of a drive device includes a refrigerant flow path through which a refrigerant flows. The refrigerant flow path includes a first flow path, a second flow path, and a connection flow path. The refrigerant to be sent from a pump flows through the first flow path. The refrigerant to be supplied to the motor portion flows in the second flow path. The first flow path and the second flow path are connected to the connection flow path. At least a part of the connection flow path is disposed in the motor accommodation space for accommodating the motor portion.

A pump stage assembly for supplying lubricating oil, comprising: at least two pump suction stages and at least one pump pressure stage. The pump suction stages and the pump pressure stage are spaced apart from one another in a pump housing PG and have a common drive shaft. The pump suction stages are formed by a first assembly of at least three intermeshing external gearwheels and wherein the pump pressure stage is formed by a second assembly of two intermeshing external gearwheels. Here at least two respective tooth center points of the first external gearwheel assembly and the respective tooth center points of the second external gearwheel assembly are arranged in a common plane E-E which intersects the pump housing PG in a longitudinal direction.

A system. The system includes a power source, a control module of a machine, and a fluid component. The fluid component is configured to establish an electrical connection between the power source and the control module during performance of a fluid operation on the machine when the machine is powered down.

An engine assembly includes a small air-cooled engine and a dry sump lubrication system including an external oil reservoir, wherein the dry sump lubrication system has an overall oil capacity that provides at least five hundred hours of engine oil life.