Methods and systems of estimating a size of a chip in engine fluid of an engine are provided. One method comprises detecting the chip at a magnetic chip detector immersed in the engine fluid, burning the chip by Joule heating using a single delivery of electric current through the chip via the first and second terminals of the magnetic chip detector, determining an amount of energy consumed to burn the chip, and estimating the size of the chip based on the amount of energy consumed to burn the chip.

An oil distribution system uses an oil storage container to contain an air/oil separation unit, a heat exchanger, and an oil reservoir. The functions of oil storage, air/oil separation, and cooling are integrated in the container. Hot aerated oil enters the container at an air/oil separation unit. The air/oil separator deposits hot de-aerated oil into the oil reservoir. The oil reservoir transfers hot de-aerated oil to conduits in a heat exchanger. The heat exchanger uses fuel to cool the oil and warm the fuel. Cooled de-aerated oil is provided to a mechanical device for lubrication and warmed fuel is provided to power an engine. The container may alternatively receive hot aerated oil into the conduits in the heat exchanger. Cooled aerated oil is delivered to the air/oil separation unit to deposit cooled de-aerated oil into the reservoir. Cooled de-aerated oil is pumped to a mechanical device to provide lubrication.

An oil tank system (100) for a gas turbine engine is provided. The oil tank system (100) includes an oil tank (102) having an upper tank portion (112) and a lower tank portion (114), a waisted section (118) being provided between the upper tank portion (112) and the lower tank portion (114). Oil is received by a de-aerator (104) of the system (100) which supplies de-aerated oil to the upper tank portion (112). The waisted section (118) includes an upper face (119) configured to catch oil drips from above the waisted section (118) and to guide oil to a lower face (121) of the waisted section (118).

An aircraft engine assembly includes a dual-flow turbine engine, a pylon for mounting the turbine engine, thrust-absorbing rods connecting the turbine engine to the pylon, and an inter-flow compartment housing a lubricant tank. In order to facilitate the filling of the tank, a lubricant supply path is fluidly connected to the tank, this path passing through an inner hollow region of at least one of the two thrust-absorbing rods.

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.

A lubricating oil tank includes: a tank casing having an introduction part into which lubricating oil is introduced and a discharge part through which the lubricating oil is discharged; a plurality of receiving parts which are disposed between the introduction part and the discharge part in the tank casing and which is configured to receive the lubricating oil introduced from the introduction part: and a lubricating oil delivery part which is configured to deliver the lubricating oil from one of the plurality of receiving parts to another one of the plurality of receiving parts between the plurality of receiving parts.

Oil system for a turbomachine, making it possible to continue the supply of oil to the pieces of equipment of the turbomachine in case of occurrence of a fire within the turbomachine, including an oil circuit, at least one oil-consuming piece of equipment, supplied by the oil circuit, a pumping unit, including at least one speed-pilotable electrically driven pump, supplying the oil circuit, and an electronic control unit, configured to pilot the electrically driven pump, wherein the electronic control unit includes two separate logics of piloting the electrically driven pump, and wherein the electronic control unit is configured to pilot the electrically driven pump according to the first logic by default and to switch to the second logic in case of receipt of a signal representative of the presence of a fire or of an overheating.

A system and methods according to which a controller communicates control signals to a first frac leg, which includes a wellhead operably associated with a first wellbore, a valve operably coupled to the wellhead, opposite the first wellbore, a frac line operably coupled to the wellhead, and a zipper module operably coupled to the frac line, opposite the wellhead. The first frac leg includes a first sub-controller that receives control signals from the controller. A grease system lubricates the first frac leg and the zipper module. The grease system includes a second sub-controller that receives control signals from the controller. A second frac leg is operably associated with a second wellbore. The second frac leg includes a third sub-controller that receives control signals from the controller. The first, second, and/or third sub-controllers may receive control signals from the controller via a communication bus.

Systems and methods of monitoring lubrication of a gear assembly during operation of a machine provide for receiving at a control system, a signal from a sensor indicative of a value obtained by the sensor for an electrical property of a circuit crossing the gear assembly operably coupled to the machine, ascertaining whether the value for the electrical property corresponds to a warning level for a condition of the lubricant film, and outputting a control command when the value for the electrical property corresponds to the warning level for the condition of the lubricant film.

Lubrication systems of an aircraft engine and associated methods are provided. The lubrication system includes a chamber having a fluid inlet for receiving lubricating fluid into the chamber, and a fluid outlet for draining the lubricating fluid from the chamber. The fluid outlet is disposed on a wall defining part of the chamber. A rotor is disposed inside the chamber and interacts with the lubricating fluid inside the chamber. The rotor is rotatable in a rotation direction about a rotation axis. A perforated baffle is disposed in the chamber for interacting with the lubricating fluid inside the chamber. The perforated baffle includes a base attached to the wall of the chamber. The base of the perforated baffle is disposed at an angular position preceding the fluid outlet relative to the rotation direction of the rotor.