There is disclosed a tool for filtering a lubricant to meet a target ISO cleanliness code. The tool includes a skid-mounted integrated filtration system having a pump that circulates a flow of lubricant from an inlet port, through a heater, through a series of specifically sized filters, and past a digital particle counter. The filtration system also includes a user interface and a programmable logic controller (PLC) configured to track outputs from the pump, the oil heater, and the particle counter to monitor a cleanliness of the circulating lubricant. The filtration system also includes a filtration operations server in communication with the PLC and configured to implement a tracking and monitoring software application enabling control of the filtration system from the system itself or remotely through one or more remote user terminals such as a smartphone, a laptop or tablet computer, and the like. Other embodiments are disclosed.

An engine oil filtration and temperature regulation assembly (1) mountable on a vehicle engine fluidically connectable to an engine oil circulation system (1). The assembly includes an oil filtration group (2), a heat exchanger group (3) and a support and fluidic connection group (5) to engage to the engine and to support the filtration group (2) and the heat exchanger group (3). The group (5) includes a base plate (50) fluidically connected to receive and return oil from and to the engine. The group (5) includes a support and fluidic connection device (500), between the base plate (50) and the filtration group (2) and/or heat exchanger group (3) having a multi-layer assembly (510) having plate-shaped elements (5101, 5102, 5103, 5104, 5105, 5106) overlappable to constitute respective ducts to create a fluidic connection between the engine and oil filtration group (2) and/or heat exchanger group (3).

An aircraft engine circulation system comprises a conduit arranged in use to communicate a lubricant to and from one or more bearings of an engine. The conduits define a space which comprises a material that is selected to change phase at a predetermined temperature.

An aircraft engine circulation system comprises a conduit arranged in use to communicate a lubricant to and from one or more bearings of an engine. The conduits define a space which comprises a material that is selected to change phase at a predetermined temperature.

An engine assembly for an aircraft including a bypass turbomachine as well as a turbomachine attachment pylon including an air-oil exchanger system arranged in an inter-ducts compartment between the flow ducts, the compartment being delimited radially on the outside by an inter-ducts cowling, the exchanger system being supplied with air from a secondary flow duct of the turbomachine delimited radially on the inside by the inter-ducts cowling, and the exchanger system being supported by a support arranged in the inter-ducts compartment, this support being mechanically connected to the attachment pylon by connecting means passing through the inter-ducts cowling.

An apparatus for cooling a high heat-generating vehicle component includes an air compressor assembly operable in a heat-generating mode, in which the air compressor assembly has a relatively low capability to absorb heat energy from a coolant that has passed through a high heat-generating vehicle component. The coolant may be passed through a heat exchanger submerged in an oil reservoir of the air compressor assembly to facilitate the heat exchange. The air compressor assembly can also be operated in a non-heat-generating mode, in which the air compressor assembly has a relatively higher capability to absorb heat energy from the coolant that has passed through the high heat-generating vehicle component.

An apparatus for cooling a high heat-generating vehicle component includes an air compressor assembly operable in a heat-generating mode, in which the air compressor assembly has a relatively low capability to absorb heat energy from a coolant that has passed through a high heat-generating vehicle component. The coolant may be passed through a heat exchanger submerged in an oil reservoir of the air compressor assembly to facilitate the heat exchange. The air compressor assembly can also be operated in a non-heat-generating mode, in which the air compressor assembly has a relatively higher capability to absorb heat energy from the coolant that has passed through the high heat-generating vehicle component.

A lubricant filter housing comprises a top plate defining a first opening. A base plate is positioned opposite the top plate. The lubricant filter housing further comprises at least one sidewall which cooperatively with the top plate and the base plate defines an internal volume. A plurality of plates are axially positioned in the internal volume between the top plate and the base plate. Each plate defines a plate opening axially aligned with the first opening which cooperatively with the first opening and a portion of the base plate, defines an internal cavity for housing a filter element. The plates define a first set of fluid channels structured to deliver a lubricant to the internal cavity, and a second set of fluid channels structured to provide a coolant around the first set of fluid channels.

A lubricant filter housing comprises a top plate defining a first opening. A base plate is positioned opposite the top plate. The lubricant filter housing further comprises at least one sidewall which cooperatively with the top plate and the base plate defines an internal volume. A plurality of plates are axially positioned in the internal volume between the top plate and the base plate. Each plate defines a plate opening axially aligned with the first opening which cooperatively with the first opening and a portion of the base plate, defines an internal cavity for housing a filter element. The plates define a first set of fluid channels structured to deliver a lubricant to the internal cavity, and a second set of fluid channels structured to provide a coolant around the first set of fluid channels.

An oil supply device of an aircraft gas turbine includes: a lubrication extraction pipe including a first end and a second end, the first end communicating with a compressor of the gas turbine, an ejection port being provided at the second end and directed to a lubricated member; an oil tank configured to store oil; an oil pipe including a first end and a second end, the first end communicating with the oil tank, the second end communicating with the lubrication extraction pipe; and an electric pump interposed on a portion of the oil pipe and configured to suck the oil from the oil tank and supply the oil to an inside of the lubrication extraction pipe.