Abstract: Embodiments of the present disclosure include an oil degradation byproducts removal system. The oil degradation byproducts removal system includes a plurality of electrostatically-charged drum assemblies configured to pass through an oil flow. The oil degradation byproducts removal system is configured to be disposed within an accessory module of a turbine engine system.

Abstract: A cooling system for turbine starter lubricant includes one or more outflow transfer passages (54) extending from the turbine starter (10) to a secondary component (40). At least one heat exchange passage (56) affixed at a first end to an end of an outflow transfer passage (54) of the one or more outflow transfer passages (54), is located in the secondary component (40) having a lower interior temperature than the turbine starter (10). One or more return transfer passages (60) are affixed to a second end of the at least one heat exchange passage (56) and extend from the secondary component (40) to the turbine starter (10). Flowing a volume of starter lubricant (42) through the one or more outflow transfer passages (54), the at least one heat exchange passage (56), and the one or more return transfer passages (60) removes thermal energy from the volume of starter lubricant (42) and returns the volume of starter lubricant (42) to the turbine starter (10).

Abstract: An assembly that includes an accessory gearbox (AGB) and a tank for a liquid lubricant for a turbojet engine. The AGB includes a gear connected to parallel shafts for mechanically driving accessories. The assembly includes a housing with two compartments and a partition perpendicular to the shafts for separating the compartments, a compartment defining the accessory gearbox and a compartment defining the liquid tank. The assembly can be compact and easily manufactured.

Abstract: A gas turbine engine oil supply and scavenge apparatus includes: a stationary first frame comprising a first hub and a first outer ring interconnected by an array of radially-extending hollow first struts; a forward wet cavity defined radially inboard of the first frame, having a first rolling element bearing disposed therein; a supply line extending from the first outer ring through one of the first struts and communicating with the forward wet cavity, the supply line adapted to discharge oil to the forward wet cavity; a stationary second frame comprising a second hub and a second outer ring interconnected by an array of radially-extending hollow second struts, the second frame disposed aft of the first frame; and a scavenge path communicating with the forward wet cavity and adapted to remove oil-air mist from the forward wet cavity, the scavenge path defined at least in part by the second frame.

Abstract: A clutch assembly includes a shaft, vent plug and oil guide sleeve. The shaft includes an internal cavity, first passages for allowing oil to lubricate clutch components, and second passages for allowing excess oil to drain from the internal cavity. The vent plug has a radial passage in communication with the internal cavity for venting the cavity with an external source of air. The oil guide sleeve directs oil into the internal cavity. A method for lubricating and venting an air turbine starter includes delivering lubricating oil to an internal cavity of a clutch via an oil guide sleeve. The oil guide sleeve prevents oil from exiting the cavity through excess oil drainage passages before it lubricates the clutch components. The method also includes draining excess oil from the cavity through excess oil drainage passages so that excess oil does not substantially impede air flow through a vent plug passage.

Abstract: A generator having an integral oil tank for an auxiliary power unit (APU) is provided. A gas turbine engine has a turbine shaft extending from an aft portion to a forward portion where it is in communication with a gear box mounted thereto. The gearbox advantageously has at least one oil gravity drain passage in flow communication with a lower portion thereof and is suitable for reducing the speed of the turbine shaft by gear reduction to power an oil cooled generator attached thereto. The oil cooled generator has at least one oil gravity drain passage therein. An engine oil tank is integral with and advantageously removable from the generator and is in flow communication with each oil gravity drain passage making is suitable for gravity scavenging oil from the generator and advantageously the gearbox.

Abstract: A gas turbine oil supply system and a method for the operation of a bearing oil supply system for a gas turbine includes an oil tank 1 and a supply line 2 branching off from the oil tank 1. An electric oil pump 3 is arranged in the supply line 2. A first controllable valve 4, by which the oil flow can be recirculated into the oil tank 1 via a return line 5, is arranged downstream of the oil pump 3. If a temperature of the oil is below a predetermined value prior to turbine start-up, the oil is diverted from supplying the bearings and recirculated through the tank to heat the oil to a desired level.

Abstract: The present invention relates to an installation for lubricating and/or cooling in an aircraft engine comprising an oil tank (3), a main feed pipe (6) feeding a main pump (1) supplying a flow in a discharge line from the main pump (7) to one or several systems (2) to be lubricated and/or cooled, wherein the installation comprises a feed pipe for an auxiliary pump (8) fitted in parallel onto the main pipe (6) and connected to an auxiliary feed pump (1A), the latter supplying a flow in a discharge line from the auxiliary pump (8A) connected by a three-way circuit on the one hand to a non-return valve (4A) directed towards the main discharge line (7), and on the other hand to a hydraulically-operated (9) recirculation valve (5), in order to divert the flow from the auxiliary feed pump (1A) into a return line (8B) directly towards the tank (3).

Abstract: A clamping assembly (2) adapted to clamp a component (4), the assembly comprising: first and second clamping members (10, 20), the first and second clamping members being movable with respect to one another in a first direction to selectively clamp the component therebetween; and a bearing element (30) positionable between the component and one of the first and second clamping members, the bearing element being configured to permit relative movement between the component and one of the first and second clamping members in a second direction.

Abstract: A turbofan engine includes a fan rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, and a fan drive gear system including a carrier for supporting a plurality of gears. A torque frame is attached to the carrier. A plurality of connectors extends between the carrier and torque frame for securing the torque frame to the carrier. A scupper captures lubricant during gear operation and directing lubricant into a space between at least one of the plurality of connectors and at least one of the torque frame and the carrier.

Abstract: An exemplary apparatus for supplying lubricant to a gear assembly in a gas turbine engine includes a valve having a valve inlet configured to be coupled to a source of lubricant. A valve outlet is configured to direct lubricant to the gear assembly. The valve is selectively controllable into a plurality of settings for varying an amount of lubricant flowing from the valve inlet to the valve outlet. A bypass is associated with the valve. The bypass has an inlet configured to receive lubricant from the source and an outlet configured to direct lubricant to the gear assembly. The bypass permits at least a selected amount of lubricant to flow to the gear assembly independent of a setting of the valve.

Abstract: An exemplary apparatus for supplying lubricant to a gear assembly in a gas turbine engine includes a valve having a valve inlet configured to be coupled to a source of lubricant. A valve outlet is configured to direct lubricant to the gear assembly. The valve is selectively controllable into a plurality of settings for varying an amount of lubricant flowing from the valve inlet to the valve outlet. A bypass is associated with the valve. The bypass has an inlet configured to receive lubricant from the source and an outlet configured to direct lubricant to the gear assembly. The bypass permits at least a selected amount of lubricant to flow to the gear assembly independent of a setting of the valve.

Abstract: In an arrangement for discharging oil-venting air (oil air) separated by a lubricating oil de-aeration system, kinetic energy of the oil-venting air (O) is increased to a static pressure which exceeds the exhaust-gas flow (A) pressure by a diffuser and the oil-venting air is then mixed with the exhaust-gas flow and discharged with the latter. The venting line (10) coming from the lubricating oil de-aeration system issues into a diffuser (13) which is integrated into the exhaust cone (9) enveloped by the exhaust-gas flow of the engine and whose oil-air outlet opening (14) is connected to the exhaust-gas flow either directly or via an attenuation chamber (18) provided in the exhaust cone. Provision is such made for discharging oil air from the engine to the atmosphere without contaminating visible engine parts and for obtaining a weight reduction due to the reduced length of the venting line.

Abstract: A lubricant system is disclosed, in particular for the supply of lubricant to a user in a gas turbine aircraft engine. The system includes a lubricant reservoir, where in the lubricant reservoir a lubricant can be set in rotation by at least one rotatable drum that is integrated into the lubricant reservoir or by at least one rotatable blade that is integrated into the lubricant reservoir, such that the lubricant, as a result of centrifugal force, comes into contact against a rotationally symmetrical wall of the lubricant reservoir, and from there can be transported toward a user. A drive system is included for the or each rotatable drum or the or each rotatable blade of the lubricant reservoir. At least one rotating lubricant separator is provided for the venting of the lubricant. The or each lubricant separator can be driven by the drive system of the or of each rotatable drum and/or of the or of each rotatable blade of the lubricant reservoir.

Abstract: A lubrication system for a heavy duty gas turbine includes a bearing lubrication assembly coupled to the bearing and an oil and vapor extraction assembly disposed in a cavity defined by a bell mouth hood in an air inlet duct. A high volume vacuum blower is coupled to the oil and vapor extraction assembly to provide a relative negative pressure. An oil and vapor separator is disposed downstream from the high volume vacuum blower. The lubrication system also includes a control subsystem that maintains a cavity pressure lower than an air inlet pressure.

Abstract: A support assembly for a geared architecture includes an engine static structure. A flex support is secured to the engine static structure and includes a bellow. A support structure is operatively secured to the flex support. A geared architecture is mounted to the support structure. First members are removably secured to one of the engine static structure and the flex support and second members are removably secured to the support structure. The first and second members are circumferentially aligned with one another and spaced apart from one another during a normal operating condition. The first and second members are configured to be engageable with one another during an extreme event to limit axial movement of the geared architecture relative to the engine static structure.

Abstract: A case comprises a radially inner case hub, a radially outer case section with an outer wall, a plurality of circumferentially distributed struts extending radially between the inner hub and the outer case section, and a lubricant scavenge passage disposed circumferentially apart from a bottom dead center (BDC) position of the case. The lubricant scavenge passage includes an inner scavenge section extending radially through a first one of the plurality of struts.

Abstract: A lubrication system includes a control subsystem operable to selectively communicate lubricant from a reserve lubrication subsystem under a pressure to supplement lubricant from a main lubrication subsystem in response to identification of a prolonged reduced-G condition. A gas turbine engine includes a main lubrication subsystem in communication with a geared architecture; a reserve lubrication subsystem in communication with the geared architecture; and a control subsystem operable to selectively communicate lubricant from the reserve lubrication subsystem under a pressure in response to identification of a prolonged reduced-G condition.

Abstract: A bi-directional auxiliary lubrication system which allows lubricant to be supplied to moving engine components after a loss of lubricant pressure from a main lubricant tank is disclosed. In a gas turbine engine, the lubrication system may siphon compressed air from a compressor to draw lubricant from a reserve lubricant tank and deliver that lubricant to the engine components. The same conduits used by the lubrication during normal operations are utilized in an opposite direction to provide the flow of lubricant from the reserve lubricant tank during such auxiliary or low-lubricant-pressure operations.

Abstract: A lubrication system for a gas turbine engine including at least one porous element located in a cavity containing at least one rotating component receiving a flow of the lubricant, the porous element being located across a path taken by a portion of the lubricant expelled from the at least one respective rotating component such that the portion of the lubricant circulates therethrough, the at least one porous element being made of a material resistant to a temperature of the lubricant, the at least one porous element reducing a velocity of the portion of the lubricant circulating therethrough.

Abstract: Gas turbine engines systems and methods involving oil flow management are provided. In this regard, a oil pressure analysis system for a gas turbine engine is operative to: receive information corresponding to measured oil pressure and rotational speed during a start up of the engine; correlate the information into data sets, each of the data sets containing a measured oil pressure and a corresponding rotational speed; and determine whether the oil flow valve is functioning properly based on the information contained in the data sets.

Abstract: A system for removing oil from a bearing compartment has a port connected to an end wall of the compartment through which the oil exits the compartment, a scavenge scoop connected to the port for collecting the oil, and a separation device connected to the scavenge scoop for creating an oil collection region.

Abstract: A lubrication system for a fan drive gear system includes a lubricant supply and a collection conduit for drawing lubricant from within the lubricant supply. The collection conduit includes a first opening and a second opening for withdrawing lubricant and supplying lubricant to a pump. During normal operation lubricant may be drawn through both first and second openings. During negative G operating conditions a fitting at the second opening blocks the second opening to prevent air from being drawn into the lubricant system and communicated to the pump.

Abstract: A lubrication system for use with a gas turbine engine includes a first reservoir for containing a lubricant. The first reservoir includes a first discharge passage through which the lubricant is flowable in a first direction. A second reservoir contains the lubricant. The second reservoir includes a second discharge passage through which the lubricant is flowable in a second direction. The first direction is generally opposite to the second direction. A first pump pumps the lubricant from the first reservoir. A second pump pumps the lubricant from the second reservoir. A manifold distributes the lubricant to a component. The lubricant from the first pump and the second pump flows into the manifold and exits the manifold through a manifold discharge.

Abstract: A shaft coupling is disclosed herein. The shaft coupling includes a tubular portion extending along a central axis. The tubular portion has a maximum inner diameter. The shaft coupling also includes a first set of internal splines positioned in the tubular portion. The shaft coupling also includes a dam rising above the maximum inner diameter in the tubular portion. The dam is spaced from the first set of internal splines along the central axis. The shaft coupling also includes at least one aperture for receiving lubricant for the first set of internal splines. The at least one aperture extends through the tubular portion along an aperture axis transverse to the central axis. A cross-sectional area of the at least one aperture decreases along at least part of the aperture axis. In another feature, the shaft coupling can include a passageway extending through the dam.

Abstract: A system for supplying lube oil to a gas turbine includes an auxiliary lube oil skid and an auxiliary lube oil pump. A first fluid connection to supply piping of a main lube oil system is downstream from the auxiliary lube oil pump. A second fluid connection to return piping of the main lube oil system is upstream from the auxiliary lube oil pump. A method for supplying lube oil to a gas turbine includes connecting an auxiliary lube oil pump to supply piping of a main lube oil system, connecting the auxiliary lube oil pump to return piping of the main lube oil system, and operating the auxiliary lube oil pump to supply lube oil to the supply piping.

Abstract: A tank includes a tank discharge passageway at least partially within a tank body. A segmented anti-back flow structure is mounted adjacent to the tank body and the tank discharge passageway.

Abstract: A turbine engine case defines a centerline and a gaspath within the engine case. A fan is coupled to a fan shaft. A transmission couples the shaft to the fan shaft to drive the fan and comprises a gear system. A gutter system is positioned to capture lubricating fluid slung from the gear system. The gutter system includes a gutter extending partially circumferentially about the centerline having a first circumferential end edge. An inlet channel has an inlet at the gutter first circumferential end edge and locally radially outboard of the gutter. At least one vane is spaced apart from the gutter first circumferential end edge.

Abstract: A gas turbine engine oil system has an air-oil separator for removing air from an air/oil mixture. A breather tube is connected to an exhaust of the air-oil separator for receiving hot air removed from the air/oil mixture in the air-oil separator. The gas turbine engine oil separator exhaust is directed in a cooled oil collector to cause the oil mist remaining in the air at the exit from the engine air-oil separator to condensate. The oil condensate is returned back into the engine oil system.

Abstract: A first turbocharger comprises a first center housing and a first return passage. A second turbocharger comprises a second center housing and a second return passage. The first return passage joins the second return passage at a junction. The length of the second return passage from the second center housing to the junction is longer than that of the first return passage from the first center housing to the junction. A bellows-shaped vibration absorption portion is provided at the second return passage. The first return passage comprises a first upstream return passage and a first downstream return passage, and the first upstream and downstream return passages are connected to each other via the flexible hose.

Abstract: An assembly for holding a fluid includes an auxiliary reservoir inside a main reservoir. The auxiliary reservoir includes an auxiliary reservoir shell with a fill passage at or near its bottom. The auxiliary reservoir shell also has a vent passage at or near its top. The fill passage and the vent passage fluidically connect the auxiliary reservoir to the main reservoir. A fluid inlet is located inside the main reservoir and outside of the auxiliary reservoir. A fluid outlet located inside the auxiliary reservoir between the fill passage and the vent passage.

Abstract: An oil supply system for a gas turbine engine with a centrifugal air/oil separator in fluid communication with the scavenge system to receive the used oil mixture and extract oil and air therefrom, a supply pump in serial connection with the main oil outlet of the separator and in fluid communication with the bearing cavities to deliver the oil thereto, an oil tank in fluid communication with the overflow oil outlet of the separator, and at least one make-up pump having an inlet in fluid communication with the tank and having an outlet in fluid communication with the scavenge system.

Abstract: A lubrication system includes a bearing compartment. A main reservoir is fluidly connected to the bearing compartment by a main supply passage. A main pump is arranged in the main supply passage configured to provide fluid from the main reservoir to the bearing compartment during a positive gravity condition. A secondary supply passage fluidly connects the main reservoir to at least one segment of the main supply passage, thereby providing fluid from the main reservoir to the bearing compartment during a negative gravity condition. A method of supplying a bearing compartment with fluid includes pumping a fluid from a main reservoir to a bearing compartment through a main supply passage during a positive gravity condition, and providing fluid from the main reservoir to the bearing compartment through a secondary supply passage, fluidly connected to at least one segment of the main supply passage, in response to a negative gravity condition.

Abstract: A lubrication system is provided for delivering a lubricant to a plurality of nozzles. The lubrication system includes a reservoir for the lubricant; a pump fluidly coupled to the reservoir and configured to remove a flow of the lubricant from the reservoir; a lubrication sensor positioned between the pump and the plurality of nozzles and configured to detect a blockage in the plurality of nozzles and to generate a blockage signal when the blockage is detected; and an indicator coupled to the lubrication sensor and configured to generate a warning based on the blockage signal from the lubrication sensor.

Abstract: An oil supply system for a gearbox in a gas turbine engine includes a holding container which holds a quantity of oil to be delivered to a pump. The holding container includes a flexible barrier.

Abstract: A turbocharger includes a housing, a first rotor wheel, a second rotor wheel, a driveshaft, a first bearing and a second bearing. The housing defines a first region, a second region, an intake air inlet, an intake air outlet and an exhaust gas inlet. The first rotor wheel is located in the first region and the second rotor wheel is located in the second region. The first bearing is located on a first axial side of the first rotor wheel axially between the first and second rotor wheels and supports the driveshaft for rotation relative to the housing. The second bearing is located on a second axial side of the first rotor wheel and supports the first rotor wheel for rotation relative to the housing.

Abstract: A turbine generator system includes a turbine power generation unit including a generator and a turbine for driving the generator. The turbine generator system also includes an evaporator, a condenser, a medium feeding pump, a circulating pump, and a feeding passage. The evaporator receives heat from a heat source and supplies a working medium in a vapor phase containing a lubricant to the turbine power generation unit. The condenser condenses the working medium which has flowed through the turbine. The medium feeding pump raises a pressure of the condensed working medium and feeds the working medium to the evaporator, and the working medium extracted from the evaporator is supplied through the feeding passage to bearings in the turbine power generation unit.

Abstract: Disclosed are articles, lubrication systems, and methods that sequester lubricant viscosity modifiers via adsorption of the viscosity modifier molecules onto a molecular sieve material at lubricant temperatures below a threshold temperature and release of the viscosity modifier molecules from the molecular sieve material at lubricant temperatures at about the threshold temperature so that the viscosity modifier molecules are in the lubricant at temperatures from about the threshold temperature and higher. In this way, the viscosity modifier molecules are removed from the lubricant at temperatures where the lubricant has sufficient viscosity but released into the lubricant when they can useful increase the lubricant viscosity because it otherwise would be too low.

Abstract: A support assembly for a geared architecture includes an engine static structure. A flex support is secured to the engine static structure and includes a bellow. A support structure is operatively secured to the flex support. A geared architecture is mounted to the support structure. First members are removably secured to one of the engine static structure and the flex support and second members are removably secured to the support structure. The first and second members are circumferentially aligned with one another and spaced apart from one another during a normal operating condition. The first and second members are configured to be engageable with one another during an extreme event to limit axial movement of the geared architecture relative to the engine static structure.

Abstract: There is disclosed a lubricant scavenge arrangement provided on a chamber having an outer wall and configured to house a lubricated rotative component for rotation about an axis. The scavenge arrangement comprises: a substantially elongate channel provided in a substantially arcuate region of the wall, the channel being open to the chamber over substantially its entire length between an inlet end and an outlet end, said inlet end and said outlet end being angularly spaced apart around said longitudinal axis. The scavenge arrangement is particularly suited to use on bearing chambers in gas turbine engines.

Abstract: An oil scavenge system of a gas turbine engine in accordance with one embodiment of the present invention, comprises a housing defined about an axis of rotation, the housing confining an air/oil mixture in motion within the housing and defining an oil scavenge area below the axis of rotation. The housing further includes an outlet at a low location of the housing. A churning damper is supported within the housing and is located in the oil scavenge area. The churning damper includes at least one plate, allowing the air/oil mixture in motion to pass over or through the plate only in a peripheral area of the at least one plate to cause flow energy dissipation.

Abstract: A method for determining volumes of working fluids used in fluid operated systems that would be present at selected temperatures in working fluid reservoirs provided in those fluid operated systems based on measured volumes of the working fluids present in the reservoirs at measured temperatures, systems volumes and densities of the working fluids at the selected and measured temperatures.

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: The present invention relates to a method for calculating the oil consumption and autonomy associated with the lubrication system of an airplane engine during flights, preferably a turbine engine, on the basis of the measurement of the oil level in the tank of said lubrication system, allowing to manage the refills and maintenance and to detect either abnormal consumption or insufficient autonomy, characterized by at least one of the following methods: comparing different engines of the airplane and possibly a reference value, the engines used for said comparison being in more or less identical condition, in order to detect abnormal oil consumption; taking into account one or more interference effects that affect said oil level in the tank, these being linked at least to the thermal expansion in the tank, to the “gulping” and to the attitude and acceleration, in order to deduce the modification to the oil level due to a decrease in the total quantity of oil available as a result of said interference effect

Abstract: An internal combustion engine includes a crankcase which accommodates cylinders, having at least one exhaust turbocharger and having an oil circuit containing at least one oil pump, in which engine oil is siphoned by at least one oil pump and delivered to the cylinders for lubrication, and in which the or each exhaust turbocharger is coupled to the oil circuit such that siphoned engine oil can be distributed to bearings of the respective turbocharger via an inlet line leading to the respective exhaust turbocharger and can then be expelled from the bearings of the respective exhaust turbocharger in the direction of an oil sump via an outlet line leading away from the respective exhaust turbocharger. The respective outlet line of the respective exhaust turbocharger is assigned a pressure limiting device, with the aid of which a vacuum prevailing at the bearings of the respective exhaust turbocharger can be limited.

Abstract: A lubricant scoop is disclosed herein. The lubricant scoop comprises an annular body encircling a central axis. The annular body is operable to rotate about the central axis in a first direction. The lubricant scoop also comprises a plurality of lubricant passageways defined in the annular body. Each of the plurality of passageways extends radially inward toward the central axis from respective entry ports to respective exit ports. The lubricant scoop also comprises an entry plenum defined in the annular body. The entry plenum is upstream of and fluidly communicates with each of the plurality of passageways. The entry plenum has an upstream opening operable to receive lubricant from a lubricant spray nozzle.

Abstract: Dynamically-lubricated bearings and methods of dynamically lubricating bearings, including bearings used in gas turbine engines. Such a bearing includes an inner race having an inner race groove, an outer race having an outer race groove that opposes the inner race groove, rolling elements disposed between the inner and outer races and in rolling contact with the inner and outer race grooves, and a cage disposed between the inner and outer races to maintain separation between the rolling elements. A lubricant is introduced into a cavity between the inner and outer races, and rotation of the inner race relative to the outer race causes air to enter pockets of the cage that contain the rolling elements, which in turn causes the lubricant to exit the cavity of the bearing.

Abstract: Dynamically-lubricated bearings and methods of dynamically lubricating bearings, including bearings used in gas turbine engines. Such a bearing includes an inner race having an inner race groove between a pair of inner race cage lands, an outer race having an outer race groove between a pair of outer race cage lands and opposes the inner race groove, rolling elements disposed between the inner and outer races and in rolling contact with the inner and outer race grooves, and a cage disposed between the inner and outer races to maintain separation between the rolling elements. A lubricant is introduced into a cavity between the inner and outer races, and rotation of the inner race relative to the outer race causes the lubricant to exit the cavity through recessed surface features in at least one of the inner and outer race cage lands.

Abstract: An assembly for capturing lubricating liquid from a fan drive gear system of a gas turbine engine includes a gutter and an auxiliary reservoir. The gutter is positioned radially outward from a centerline axis of the gear system for capturing lubricating liquid slung from the gear system. The auxiliary reservoir is fluidically connected to the gutter for receiving and storing the lubricating liquid from the gutter. A portion of the auxiliary reservoir and a portion of the gutter have a same radial distance from the centerline axis of the gear system.

Abstract: Disclosed is a device for preserving fluid systems, for example of a fuel system and an oil system of a turbine engine, with at least one drive for driving at least one fuel pump and at least one oil pump, wherein a valve arrangement is provided, which makes transfer-pumping a fluid between the fluid systems possible, an engine having such a device as well as a method for triggering such a device or for preserving fluid systems.