Abstract: A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing thermal energy equal to less than about 2% of power input into the gear system.

Abstract: A gas turbine engine comprising a nacelle and a breather duct. The breather duct provides communication between a component of the engine within the nacelle and the exterior of the nacelle and opens at an exhaust port on the external surface of the nacelle. There is a clean air outlet slot located downstream of the exhaust port and arranged to expel, in use, a sheet flow of clean air to form an aerodynamic barrier between the external surface of the nacelle and a flow of breather air expelled from the exhaust port.

Abstract: Oil sump seal pressurization apparatus for a turbine engine are disclosed. An example oil sump seal pressurization apparatus may include an oil sump comprising at least one bearing mounted therein; an oil seal operatively disposed between a non-rotating structural member of the sump and the shaft; a generally radially inwardly oriented passage arranged to supply pressurization air to the outward side of the oil seal; a generally radially outwardly oriented pathway arranged to receive at least some of the pressurization air from the passage, the pathway being at least partially defined by a generally radially outwardly extending arm disposed on the shaft, the arm rotating with the shaft; and/or a windage shield at least partially separating the passage and the pathway, the windage shield being operatively mounted to the non-rotating structural member of the sump.

Abstract: The present disclosure involves an oil scoop manifold receives and directs the oil in fore and aft directions to lubricate multiple bearing assemblies.

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 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: A device for discharging oil from an oil chamber located in a downstream part of a gas turbine engine, the device including: a mechanism discharging at least part of the oil contained in the chamber to exterior of the engine; and a drive mechanism for driving the oil, which allows passage of an air flow that assists in driving the discharge of the oil to the exterior of the engine. The drive mechanism includes: a ventilation port in the downstream part of the engine, such that the oil passes through the ventilation port; and a guide element arranged such that, after the oil has passed through the ventilation port, the oil is directed towards a downstream bleed area of the low-pressure turbine. A turbomachine can include such an oil discharge device.

Abstract: A heat exchange system for use in fluid operated equipment to provide air and working fluid heat exchanges to cool the working fluid in airstreams on a stream side of a wall. An actuator is mounted to be substantially located on a side of the wall opposite the stream side thereof having a positionable motion effector. A heat exchanger core having a plurality of passageway structures therein to enable providing the working fluid to, and removal therefrom. The heat exchanger core is mounted on the motion effector so as to be extendable and retractable thereby through the opening for selected distances into that region to be occupied by the airstreams.

Abstract: An air turbine starter assembly includes a starter turbine housing having a turbine gas flow path and a fan gas flow path, and a shaft rotatable with respect to the starter turbine housing. A plurality of turbine blades are connected to the shaft. A plurality of fan blades are also connected to the shaft.

Abstract: A turbofan gas turbine engine comprises a nacelle cowl and a core engine. A bypass duct is between an outer surface of a casing of the core engine, and an inner surface of the nacelle cowl. An air channel is in the nacelle cowl, an inlet and an outlet of the air channel being in an outer surface of the nacelle cowl. An oil cooler has at least one oil passage for oil circulation, the air cooler having a first heat exchange surface in the air channel exposed to air circulating in the air channel, the air channel having a second heat exchange surface in the bypass duct exposed to air circulating in the bypass duct. A method for cooling oil in a turbofan gas turbine engine is also provided.

Abstract: An oil supply system for a stationary turbomachine is provided. A safe operation of the turbomachine is enabled even at ambient temperatures of up to 60° C. for a plurality of hours in a novel connection arrangement of the components of the oil supply system, such as the oil tank, pump a, and heat exchanger, as well as the pipeline system, without one of the components having to be designed for a further increased operating temperature. The oil tank has two regions stacked horizontally one above the other for storing the oil. The two regions are largely or completely separated from each other by a separating element.

Abstract: Breather air, containing oil mist, is discharged from a nacelle 4 of a gas turbine engine through an exhaust port 26 at a surface 22 of the nacelle 4. Energized air, at relatively high velocity is discharged from a clean air outlet 28, and forms a barrier between the breather air and the external surface 22, so preventing contamination of the surface 22 by oil deposited from the breather air.

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: A fluid distribution system for use in a gas turbine engine includes a fan shaft, a damper, a bearing, and a pump. The damper supports the bearing, and the bearing supports the fan shaft. The pump is connected to and driven by the fan shaft. The pump is also fluidically connected to the damper.

Abstract: A lubrication device including a bypass valve with an inlet connected to a feed circuit, a first outlet to be connected to elements to be lubricated, and a second outlet connected to a bypass circuit. The valve includes a valve member slidable between first and second positions, and separating a cavity into first and second chambers. The first chamber is connected to the inlet. In the first position, a fluid flow passage from the first chamber to the second chamber is open, and from the first chamber to the first outlet is closed. In the second position, a fluid flow passage from the first chamber to the first outlet is open, and from the first chamber to the second outlet is closed. At least in the second position, the valve member separates the chambers in substantially leaktight manner, while the second chamber remains in fluid flow communication with the second outlet.

Abstract: An accessory box for a gas turbine engine has an input gear to be driven by an input shaft. The input gear is engaged to drive a first driven gear on one radial side of a drive axis of the input gear. The first gear drives at least a second driven gear on one radial side of the drive axis, with at least one accessory driven by one of the first and second driven gears. The second driven gear drives a bevel gear arrangement to drive a third driven gear on an opposed side of the drive axis of the input gear. The third driven gear drives at least a second accessory. The accessories are associated with a gas turbine engine.

Abstract: A thermal management system for a gas turbine engine includes a first heat exchanger that provides a first conditioned fluid, a second heat exchanger in series flow communication with the first heat exchanger and that exchanges heat with the first conditioned fluid to provide a second conditioned fluid, and a third heat exchanger in parallel flow communication with the second heat exchanger and that selectively exchanges heat with the first conditioned fluid to provide a third conditioned fluid. The second conditioned fluid and the third conditioned fluid combine to provide a mixed conditioned fluid. A first portion of the mixed conditioned fluid including a first temperature is communicated to a first engine system. A second portion of the mixed conditioned fluid including a second temperature is communicated to a second engine system. The second temperature includes a greater temperature than the first temperature.

Abstract: A gas turbine engine has a fan, first and second compressor stages, first and second turbine stages. The first turbine stage drives the second compressor stage as a high spool. The second turbine stage drives the first compressor stage as part of a low spool. A gear train drives the fan with the low spool, such that the fan and first compressor stage rotate in the same direction. The high spool operates at higher pressures than the low spool. A lubrication system is also disclosed.

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: A lubricant supply system for a gas turbine engine has a lubricant lube pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear for an associated gas turbine engine. A method and apparatus are disclosed.

Abstract: A waste heat utilization system and associated methods for preheating fuel for a turbine engine component. The turbine engine component includes at least one heat generating source. The system includes structure for applying heat from the at least one heat generating source to relatively cold fuel for the turbine engine component to preheat the fuel prior to ignition.

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 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 lubricating oil varnish mitigation system for a turbine engine. The lubricating oil varnish mitigation system may include a lubricating oil circuit with a lubricating oil therein and a hydraulic oil circuit separate from the lubricating oil circuit with a hydraulic oil therein.

Abstract: A gas turbine exhaust gas cooling system includes a conduit for a primary gas turbine exhaust gas extending from the primary gas turbine to an inlet of a desired industrial process apparatus, a work producing thermodynamic cycle in which a working fluid is heated and expanded, and at least one heat exchanger by which heat is sufficiently transferred from the primary gas turbine exhaust gas to the working fluid to produce a low temperature heating medium downstream of the heat exchanger at a predetermined temperature and energy level which are sufficient for effecting a desired industrial process.

Abstract: A gas turbine engine includes a spool, a gearbox having gearing driven by the spool, and a lubrication system. The lubrication system includes a first heat exchanger positioned in a first air flow path, a second heat exchanger positioned in a second air flow path, and a lubrication pump fluidically connected to both the first heat exchanger and the second heat exchanger. A first air fan is driven by the gearbox for inducing air flow through the first air flow path. A second air fan is driven by an electric motor for inducing air flow through the second air flow path.

Abstract: A method for starting up an aircraft turbine engine using an electric starter is provided. The aircraft turbine engine is provided with at least one hydraulic fluid circuit for lubricating the aircraft turbine engine, the aircraft turbine engine lubricating circuit is provided with a temperature-regulating section that is able to remove the heat generated by the aircraft turbine engine when the aircraft turbine engine is running, the electric starter is provided with at least one hydraulic fluid circuit for lubricating parts of the electric starter, and the lubricating circuit of the electric starter is provided with the temperature-regulating section that is able to remove the heat emitted by the electric starter when the lubricating circuit of the electric starter is operating.

Abstract: A device for cooling hot gas to be discharged from an aircraft includes a duct for leading the hot gas from a hot gas source which is connectable to the device to an outlet point, and a frame which surrounds the duct and serves for mounting the duct. The duct is formed from one or more pipe sections and has one or more cooling air inlet points which is connectable to one or more cooling air sources in order to mix the hot gas with cooling air. An outlet pipe section of the duct extends outwards beyond the aircraft outer skin to lead hot gas through and out of a flow boundary layer on the outer skin.

Abstract: An assembly includes a gas turbine engine, a compartment wall, and a gutter system. The gas turbine engine has a spool connected to a fan shaft via a gear system. The compartment wall is positioned radially outward from the gear system. The gutter system is positioned radially outward from the gear system for capturing lubricating liquid slung from the gear system and positioned radially inward of the compartment wall. The gutter system includes a gutter and a flow passage fluidically connected to the gutter. The flow passage has a plurality of holes that allow the lubricating liquid to pass through the flow passage into a space between the flow passage and the compartment wall.

Abstract: An auxiliary power unit (APU) is provided and configured to be mounted in an APU compartment that defines an inlet opening. The APU includes a power section having components lubricated with oil; an intake duct coupled to the inlet opening and the power section and configured to direct a first portion of air flow through the inlet opening into the power section; an oil cooler coupled to the power section and configured to cool the oil of the power unit; a cooling duct coupled to the oil cooler and the intake opening; an inlet door mounted at the inlet opening and configured to open and close the inlet opening, the inlet door further configured to be positioned in at least a first open position and a second open position; and a thermal management system configured to adjust the inlet door between the first open position and the second open position based on one or more operating temperatures within the APU.

Abstract: An oil recovery device is disclosed. The oil recovery device includes two bearing supports mounted on an inter-turbine casing, a first bearing and a second bearing mounted on the bearing supports, a low-pressure turbine journal mounted rotating with respect to the inter-turbine casing, a fixed ferrule, and an oil passage provided in the low-pressure turbine journal making it possible to discharge the oil inside the fixed ferrule. The ferrule is preferentially widened from the end at which the oil is discharged.

Abstract: Gas turbine engine systems involving I-beam struts are provided. In this regard, a representative strut assembly for a gas turbine engine includes a first I-beam strut having first and second flanges spaced from each other and interconnected by a web, the first strut exhibiting a twist along a length of the web.

Abstract: A pump system for lubricating a bearing in a gear system includes an auxiliary pump connected to the gear system. The auxiliary pump is fluidically connected to the bearing through an auxiliary supply passage and to a reservoir through an auxiliary scavenge passage. An auxiliary valve is fluidically connected to the auxiliary supply passage for transferring liquid from the auxiliary pump to the bearing when a pressure in the auxiliary supply passage downstream of the auxiliary valve is less than a particular threshold and for transferring liquid from the auxiliary pump to the reservoir when the pressure in the auxiliary supply passage downstream of the auxiliary valve is greater than the particular threshold. A method for circulating liquid is also included.

Abstract: The present invention provides an air-oil separator comprising a first region having a mixture of air and oil, a second region wherein separation of at least some of the oil from the air-oil mixture occurs and at least one multi-directional injector plug located on a rotating component in flow communication with the first region and the second region, the multi-directional injector plug having a discharge head that is oriented such that at least a part of the air-oil mixture discharged therefrom has a component of velocity that is tangential to the direction of rotation of the rotating component.

Abstract: A gas-turbine bearing oil system with an oil supply arrangement includes at least one oil pump 5 supplying oil from an oil tank 1 to the bearing chambers 2, 3, 4 and at least one scavenge pump unit 6 returning oil from the bearing chambers 2, 3, 4 to the oil tank 1 At least one additional electric scavenge pump 7 is used to return oil from at least one bearing chamber 2, 3, 4 to the oil tank 1.

Abstract: A gas-turbine plant including a fuel system coupled to combustion chambers of a gas-turbine engine; the fuel system including fuel pipelines and a device for controlling fuel to the combustion chambers, a lubrication system for friction units of the gas-turbine engine and actuating units; the lubrication system including a lubrication loop for the friction units of the gas-turbine engine and a lubrication loop for the actuating units, each lubrication loop having a fuel-oil cooling heat-exchanger, a supply pump and an oil tank; wherein a first fuel pipeline of the fuel pipelines connects the device to the fuel-oil cooling heat-exchanger of the lubrication loop of the actuating units and the fuel heater, and a second fuel pipeline of the pipelines connects the device to the fuel-oil cooling heat-exchanger of the lubrication loop of the gas-turbine engine and the fuel heater.

Abstract: A mechanism such as a rotor of an open rotor gas turbine engine comprises a rotor assembly 100 rotatable about a rotational axis A. The rotor assembly 100 has a fluid pathway 110 including a pump 114 carried by the first rotor assembly 100 for driving fluid along the fluid pathway 110. The fluid may be oil for lubricating components of the mechanism. The fluid is collected by an annular channel-shaped collector 111 and pumped through surface coolers 116 to an outlet pipe 119. From the pipe 119 the fluid migrates along a path 500 under centrifugal force, returning to the collector 111.

Abstract: A thermal management system and method for a miniature gas turbine engine includes a forward cover having a filter portion along an axis of rotation of a gas turbine engine, a first lubrication passage and a second lubrication passage.

Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.

Abstract: A gas turbine has a rear bearing chamber 2 including a bearing arrangement 1. A vent valve 14 vents the bearing chamber 2 as a function of relative pressure of the bearing chamber.

Abstract: A twin fan turbomachine with two contrarotating fans, one upstream and one downstream, driven by two contrarotating coaxial shafts each of which connects one fan impeller to at least one low-pressure turbine impeller located downstream, the downstream fan impeller being connected by its downstream part to its drive shaft.

Abstract: A nose cone of a turbomachine, such as an aircraft engine, is heated to prevent ice formation. The nose cone is configured as a conical shell positioned concentrically over an inner shell with a space therebetween. Spiral spacers in the space provide distributed passages through which heated lubricating oil flows. A system for separating entrained air from the lubricating oil as part of this mechanism is disclosed.

Abstract: An oil scavenge system includes a scavenge pipe which extends forward into a relatively long and narrow compartment area of a rear bearing compartment of a gas turbine engine with aggressive core size constraints. The scavenger pipe communicates collected oil to a scavenger pump to return oil to the oil sump and evacuate the oil before flooding of the seals may occur.

Abstract: A heat exchange system for use in operating equipment having a plurality of subsystems in each of which one of a plurality of working fluids is utilized to provide selected operations with there being an air and working fluid heat exchanger providing controlled cooling to cool at least one of the plurality of working fluids in its corresponding subsystem. In addition, a coupling heat exchanger is also provided connected to two of the subsystems to pass there working fluids therethrough, including the subsystem with the air and working fluid heat exchanger, to allow one of the connected subsystems to aid in cooling the other.

Abstract: A method for assembling a turbine engine to facilitate reducing an operating temperature of a lubrication fluid during engine operation, the gas turbine engine including a fan assembly, a booster downstream from the fan assembly, and a splitter circumscribing the booster. The method includes coupling a radially inner wall and a radially outer wall at a leading edge to form a splitter body, and coupling an inner support structure within the splitter body such that a cooling circuit is defined between at least a portion of the inner support structure and the inner and outer walls, said cooling circuit configured to circulate lubrication fluid therethrough such that as a temperature of the lubrication fluid is reduced and a temperature of at least a portion of the inner and outer walls is increased.

Abstract: A single oil nozzle unit is mounted in a bearing compartment of a gas turbine engine for providing multiple individual jets for the individual bearing components in the bearing compartment.

Abstract: A lubrication scavenge system is disclosed herein. The lubrication scavenge system includes a sump housing substantially encircling a structure disposed for rotation about an axis. The sump housing has an inwardly-facing surface extending at least partially about the axis in a spiral path. The spiral path increases in radial distance from the axis in the direction of rotation of the structure, in a plane perpendicular to the axis. The spiral path extends 360°.

Abstract: A turbomachine control system comprising an auxiliary hydraulic circuit with an auxiliary hydraulic pump, at least one hydraulic actuator, and at least one servo-valve, the auxiliary pump powering the actuator via the servo-valve. The auxiliary hydraulic circuit is connected in parallel with the main fuel or lubricating oil circuit of the turbomachine. Said auxiliary pump is driven by an electric motor.

Abstract: A method of providing a standby lubrication for an engine in the event of the failure of a main lubrication system of this engine, in which the failure is detected and, in response to the detection of this failure, at least one portion of a fuel fluid of the engine is tapped off to lubricate at least one element of the engine. A standby lubrication device includes a device for detecting a failure of a main lubrication system, a device for tapping off at least a portion of a fuel fluid of the engine in order to direct it to at least one element of the engine intended to be lubricated, and a controller connected to the tapping and detection devices, in order to carry out the standby lubrication method.

Abstract: The present invention relates to an overall monitoring method allowing to calculate the autonomy of a lubrication system of an airplane engine and also allowing the diagnosis and prognosis of a plurality of problems and breakdowns of the engine and of its lubrication system by means of measurements taken by sensors arranged in said lubrication system, the method comprising the step of calculating the status of the lubrication system at a given moment and calculating its evolution over time in order to determine the remaining lifetime before a breakdown.