Class / Patent application number | Description | Number of patent applications / Date published |
060390080 | With lubricators | 64 |
20080196383 | Airframe mounted electric motor driven lubrication pump control deoil system - A system for controlling lubricant displacement from a machine during turbomachine shutdown sequence includes a motor, a pump, a control valve, and a motor control unit. The motor is selectively energized from a power bus to rotate at a rotational speed and supply a drive force to the pump. The pump, in response to the drive force, draws fluid from a fluid and supplies the fluid to the machine. The control valve is movable between at least a first position, in which the control valve fluidly communicates the pump with a lubrication fluid source, and a second position, in which the control valve fluidly communicates the pump with a gaseous fluid source. During the shutdown sequence, the motor control unit controllably energizes the motor from the power bus to thereby control its rotational speed in accordance with a schedule that will displace at least a substantial volume of lubricant in the rotating machine with fluid from the gaseous fluid source. | 08-21-2008 |
20090025363 | Vent for the lubricating oil system of a jet engine - The air exit hole of the vent line ( | 01-29-2009 |
20090077943 | Gas turbine power plant - Provided is a gas turbine power plant in which a rotor of a generator is journalled by water lubrication bearings into which a part of cooling water for cooling the generator is fed. Since the lubrication water has a viscosity lower than that of lubrication oil, it is possible to provide a gas turbine power plant with less energy loss resulting in lower power consumption for accessories, and in high power generation efficiency. | 03-26-2009 |
20090133376 | COMBINED GEARBOX BREATHER AND DRAIN MAST FOR JET AIRCRAFT ENGINE - A combined gearbox breather and drain mast is mounted to a nacelle. The combined gearbox breather and drain mast is made of a composite material and includes a body portion made of a single component with a first passage in fluid communication with a gearbox and a second passage in fluid communication with an engine component. The first passage is separate from the second passage. | 05-28-2009 |
20090199534 | OIL RECOVERY DEVICE - It comprises two bearing supports ( | 08-13-2009 |
20090235630 | NON-INTERRUPTED OIL SUPPLY FOR GAS TURBINE ENGINE - 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. | 09-24-2009 |
20090235631 | TURBOMACHINE CONTROL SYSTEM - 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. | 09-24-2009 |
20090235632 | Gas-turbine bearing oil system with improved oil return arrangement - A gas-turbine bearing oil system with an oil supply arrangement includes at least one oil pump | 09-24-2009 |
20090288384 | SYSTEM FOR REDUCING OIL CONSUMPTION IN GAS TURBINE ENGINES - A system for reducing oil usage from a sump in a gas turbine engine. Two sources of oil usage, which usage includes leakage and consumption, have been identified: (1) during idle, leakage of oil from an oil sump through seals and (2) during high-power operation, consumption of oil entrained in vent air exiting from the sump. At idle, the invention reduces pressure in the sump, to thereby increase airflow across the seals into the sump, to inhibit the oil leakage across the seals. At high power operation, the pressure reduction is terminated, but flow exiting the vent is artificially restricted. | 11-26-2009 |
20090301053 | Gas Turbine and Method of Operating a Gas Turbine - A gas turbine including at least one compressor, one combustion chamber, and at least one turbine including at least one rotor and at least one generator coupled to the at least one rotor is provided. The at least one turbine is coupled to the at least one compressor. Once the gas turbine is shut down, the at least one generator can be used as a motor in order to drive the at least one rotor for a predetermined time period following shutdown of the gas turbine and thereby effect a uniform cooling of the rotor. A method of operating a gas turbine is also provided. | 12-10-2009 |
20100058729 | Lubricant scavenge arrangement - 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 lo end being angularly spaced apart around said longitudinal axis. The scavenge arrangement is particularly suited to use on bearing chambers in gas turbine engines. | 03-11-2010 |
20100122518 | OIL SYSTEM HEATING FOR AIRCRAFT GAS TURBINES - An oil pre-heating apparatus for an aircraft gas turbine has a suction line | 05-20-2010 |
20100212281 | AUXILIARY PUMP SYSTEM FOR FAN DRIVE GEAR SYSTEM - 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. | 08-26-2010 |
20100236213 | METHOD AND APPARATUS FOR OPERATING GAS TURBINE ENGINES - 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. | 09-23-2010 |
20100275572 | OIL LINE INSULATION SYSTEM FOR MID TURBINE FRAME - A gas turbine engine having a mid turbine frame comprising an annular outer case providing a portion of an engine casing; an interturbine duct (ITD) disposed within the outer case, the ITD including outer and inner rings radially spaced apart one from another and being interconnected by a plurality of radially extending and circumferentially spaced hollow strut fairings, the inner and outer rings co-operating to provide a portion of a hot gas path through the engine; a tube for delivering or discharging a lubricant fluid to or from a bearing housing, the tube extending radially through one of the hollow struts; and an insulation structure radially extending through one said hollow strut fairing, the insulation structure surrounding the tube and being spaced apart from the tube and from a hot internal surface of the one hollow strut fairing for shielding the tube from heat radiated from the hot internal surface of the one hollow strut fairing and for preventing the lubricant fluid from contacting the hot internal surface of said one hollow strut fairing when lubricant fluid leakage occurs. | 11-04-2010 |
20100293917 | GAS TURBINE ENGINE HAVING A NACELLE AND A BREATHER DUCT - Breather air, containing oil mist, is discharged from a nacelle | 11-25-2010 |
20110047958 | TURBINE GENERATOR SYSTEM - Provided is a turbine generator system capable of sufficiently lubricating a bearing without impeding heat transmissibility of an evaporator and a condenser. The turbine generator system comprises a turbine power generation unit including a generator and a turbine for driving the generator, an evaporator which receives heat from a heat source and supplies the working medium in a vapor phase containing a lubricant to the turbine power generation unit, a condenser which condenses the working medium which has flowed through the turbine a medium feeding pump which raises a pressure of the condensed working medium and feeds the working medium to the evaporator, and a feeding passage through which the working medium extracted from the evaporator is supplied to bearings in the turbine power generation unit. | 03-03-2011 |
20110146223 | ARRANGEMENT FOR THE DISCHARGE OF EXHAUST AIR SEPARATED FROM THE LUBRICATING OIL DE-AERATION SYSTEM OF A GAS-TURBINE ENGINE - With an arrangement for the discharge of oil-contaminated exhaust air separated from the lubricating oil de-aeration system of a gas-turbine engine and led to the atmosphere via a venting line, the venting line ( | 06-23-2011 |
20110146224 | ARRANGEMENT FOR THE DISCHARGE OF OIL-VENTING AIR ON A GAS-TURBINE ENGINE - 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 ( | 06-23-2011 |
20110203249 | TURBINE STARTER LUBRICANT COOLING - A cooling system for turbine starter lubricant includes one or more outflow transfer passages ( | 08-25-2011 |
20110239619 | COMBUSTOR AND GAS TURBINE - A combustor of the present invention includes: a plurality of nozzles which is arranged around the central axis of a combustor and of which each base end is connected to an oil supply tube; a nozzle tube base which supports the plurality of nozzles and includes an oil chamber supplying fuel to the nozzles via an oil inflow portion provided in each oil supply tube; a first guide portion which faces the center of the combustor inside the oil chamber and guides the oil remaining inside the oil chamber to the oil inflow portion; and a second guide portion which faces the base end of the combustor inside the oil chamber and guides the oil remaining inside the oil chamber to the oil inflow portion. | 10-06-2011 |
20110302903 | LUBRICATION DRIVEN GAS TURBINE ENGINE ACTUATION SYSTEM - A lubrication system for a gas turbine engine includes a variable output lubricant pump operable to supply lubricant to an actuator system. | 12-15-2011 |
20120011824 | INTEGRAL LUBRICATION TUBE AND NOZZLE COMBINATION - An assembly includes a tube fitting integrally joined with a nozzle and adapted with a plurality of passages to spray lubricating oil at components within a bearing compartment of a gas turbine engine. In another aspect, the tube fitting and the nozzle are attached to a lubrication tube such that the tube fitting and nozzle can be inserted or removed from the bearing compartment along with the lubrication tube without disassembling the bearing compartment. | 01-19-2012 |
20120060463 | Oil Varnish Mitigation Systems - The present application provides 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. | 03-15-2012 |
20120233977 | ROTATING FLUID PUMPING SYSTEM - A mechanism such as a rotor of an open rotor gas turbine engine comprises a rotor assembly | 09-20-2012 |
20130097990 | ROTARY OIL DEGRADATION BYPRODUCTS REMOVAL SYSTEM - 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. | 04-25-2013 |
20130205745 | LUBRICATING DEVICE HAVING A BYPASS VALVE - 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. | 08-15-2013 |
20130213001 | OIL SUPPLY SYSTEM FOR A STATIONARY TURBOMACHINE - 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. | 08-22-2013 |
20130247538 | OIL DISCHARGE DEVICE AND TURBOMACHINE COMPRISING SUCH A DEVICE - 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. | 09-26-2013 |
20130283757 | MITIGATING VORTEX PUMPING EFFECT UPSTREAM OF OIL SEAL - 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. | 10-31-2013 |
20130283758 | Oil Scoop Manifold - The present disclosure involves an oil scoop manifold receives and directs the oil in fore and aft directions to lubricate multiple bearing assemblies. | 10-31-2013 |
20130291514 | GAS TURBINE ENGINE OIL TANK - A gas turbine engine includes an engine static structure housing that includes a compressor section and a turbine section. A core nacelle encloses the engine static structure to provide a core compartment. An oil tank is arranged in the core compartment and is axially aligned with the compressor section. Fan and core nacelles define an annular bypass flow path. The core nacelle provides a core compartment and includes an opening into the core compartment. The oil tank is arranged in the core compartment and includes a portion aligned with the opening that is exposed to the bypass flow path. The engine static structure is supported relative to a fan case by a radial structure. The oil tank is mounted to the engine static structure. An oil fill tube is mounted to the fan case and is fluidly connected to the oil tank. | 11-07-2013 |
20130318939 | LUBRICATION ARRANGEMENT FOR A GAS TURBINE ENGINE GEAR ASSEMBLY - 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. | 12-05-2013 |
20130318940 | LUBRICATION ARRANGEMENT FOR A GAS TURBINE ENGINE GEAR ASSEMBLY - 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. | 12-05-2013 |
20140026534 | OIL SUPPLY SYSTEM FOR AN AIRCRAFT ENGINE - In an oil supply system for an aircraft engine, including at least one oil circuit, into which an oil tank having a closing valve associated with the outlet opening of the oil tank into a suction line, an oil pump and at least one consumer to be supplied with oil by means of a pressure line are integrated, a negative pressure relief line having a shut-off valve incorporated is connected to the suction line, said negative pressure relief line for ensuring pressure relief in the suction line being connectable after shutdown of the engine to the pressure line or to the ambient air. Via a volume flow limiter designed as a diaphragm and alternatively incorporated into said negative pressure relief line, the suction line can also be connected permanently to the pressure line. A negative pressure occurring in the suction line after shutdown of the engine when the closing valve is closed and the plastic deformation of the suction line as well as a reduction of the pump suction capacity are thus avoided. | 01-30-2014 |
20140075916 | METHOD AND DEVICE FOR SUPPLYING A LUBRICANT - A device and method feeding turbomachines with lubricant, the turbomachine including a first set of bearings and a second set of bearings. Both the first and the second sets of bearings are fed with lubricant, and the second set of bearings operate at a temperature higher than the first set. The second set of bearings is fed with lubricant at a temperature higher than the first set. | 03-20-2014 |
20140083076 | Gas Turbine Engine With Geared Turbofan and Oil Thermal Management System - 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. | 03-27-2014 |
20140090355 | REDUCED TRIM FLOW GAS TURBINE ENGINE OIL SYSTEM - A disclosed lubrication system for a gas turbine engine includes a primary passage defining a flow path for lubricant to a gas turbine engine and a bypass passage defining a flow path for lubricant around the gas turbine engine. The lubrication system further includes a primary lubrication pump including a reduced total flow capacity of lubricant with a reduced bypass lubricant flow relative to the total overall flow capacity. | 04-03-2014 |
20140144120 | Lubrication Cut-Off at High Speed - A mechanical system has a component to be lubricated that requires greater lubrication at lower speed conditions than would be required at higher speed conditions. A lubricant tower is biased to a position allowing a greater flow of lubrication to the component at lower speed conditions, then moved to a position at higher speed conditions where there is a lesser flow of lubrication. | 05-29-2014 |
20140144121 | GAS TURBINE ENGINE WITH BEARING OIL LEAK RECUPERATION SYSTEM - A gas turbine engine having an annular gas path between a radially outer wall and a radially inner wall, leading successively across at least one compressor stage, a combustor section, and at least one turbine stage, a hollow shaft having an internal surface with an oil trap formed therein, and at least one oil recuperation orifice extending out across the hollow shaft from the oil trap; and a bearing cavity formed within the radially inner wall, having at least one bearing therein rotatably supporting the hollow shaft of the gas turbine engine, at least two bearing seals enclosing the at least one bearing in the bearing cavity and separating the bearing cavity from associated buffer air entry points, at least a first one of said buffer air entry points being exposed to the at least one oil recuperation orifice outside the hollow shaft. | 05-29-2014 |
20140150400 | FLUID SYSTEM WITH GRAVITY CONTROLLED VALVE - A fluid system for use with a gas turbine engine includes a reservoir having a reservoir inlet and a reservoir outlet and includes a supply assembly positioned in the reservoir. The supply assembly includes a first passage, a second passage, and a valve disc. The first and second passages are fluidically connected to the reservoir outlet. The valve disc is positioned in the first passage. The valve disc is pivotable about an axis and is weighted to have a center of gravity offset from the axis. | 06-05-2014 |
20140157750 | TURBO-COMPRESSOR TRAIN WITH ROLLING BEARINGS AND RELATED ASSEMBLY METHOD - A turbo-compressor train and a method for assembling a turbo-compressor train. The train includes a gas turbine engine configured to transform thermal energy into mechanical energy; a centrifugal compressor having a shaft connected to a shaft of the gas turbine engine; and a single lube pump configured to provide synthetic oil to the gas turbine engine and the centrifugal compressor. The gas turbine engine, the centrifugal compressor and the single lube pump each has only rolling bearings. | 06-12-2014 |
20140165530 | Bi-Directional Auxiliary Lubrication System - 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. | 06-19-2014 |
20140260176 | LUBE TUBE EXPANSION AND TORQUE RETAINING DEVICE - A bearing lubrication tube for an APU is mounted on a bearing to permit expansion and contraction of the tube along its length while preventing rotational movement of the tube. The bearing lubrication tube is held by a bracket attached to a flange outside the engine. The bracket includes a double hex ring with the outer hex ring engaging the bracket and an inner hex ring engaging the tube to prevent rotation of the tube. A cover on the bracket maintains the double hex ring in position. | 09-18-2014 |
20140331639 | Turbomachine Lubrication System with an Anti-Siphon Valve for Windmilling - The present application relates an oil feed system for a turbomachine having a tank designed to contain a volume of oil, a pump designed to suck the oil from the tank and discharge it to at least one device on the turbomachine, and an anti-siphon valve designed to prevent the flow of oil to the device or devices. The anti-siphon valve is located upstream of the pump and is designed to allow the flow of oil when the speed of the pump becomes higher than a speed R1. The present application also relates to a turbojet fitted with a fan and two anti-siphon valves designed to open at different rotational speeds of the first pump. | 11-13-2014 |
20140345246 | GAS TURBINE ENGINE SUMP PRESSURIZATION SYSTEM - A sump pressurization system for a gas turbine engine comprises a first hollow shaft and a second hollow shaft disposed within the first hollow shaft and defining a cavity therebetween. Each of the first and second hollow shafts has a common axis of rotation. Also included is a source of pressurized air to pressurize the cavity and a plurality of hollow tubes disposed in the cavity. The tubes are oriented perpendicular to the axis of rotation and are connected to and rotatable with the first hollow shaft. A plurality of apertures in the second hollow shaft are in fluid communication with the tubes, such that pressurized air flowing through the tubes passes through the apertures into the interior of the second hollow shaft. | 11-27-2014 |
20140345247 | Tank and Method for Manufacturing Same - The present invention relates to a method for manufacturing a tank ( | 11-27-2014 |
20140360152 | OIL TANK MOUNT WITH YOKE - An engine has an oil tank mounted to an engine wall with clevis ears formed on both the oil tank and a mount bracket. A link connects the mount bracket clevis ears to the oil tank clevis ears. The link has a spherical bearing which is mounted in the oil tank clevis ears. This provides a connection allowing movement between the link and the oil tank clevis ears. The link is a yoke having arms positioned outwardly of the mount bracket clevis ears securing the oil tank to the mount bracket. | 12-11-2014 |
20140360153 | GAS TURBINE ENGINE THERMAL MANAGEMENT SYSTEM - A gas turbine engine according to an exemplary embodiment of this disclosure, among other possible things includes a fan. A geared architecture is configured for driving the fan. A turbine section is configured for driving the geared architecture. A thermal management system that includes a first fluid circuit and a second fluid circuit that manage heat generated in at least a portion of the gas turbine engine. A first heat exchanger is incorporated into each of the first fluid circuit and the second fluid circuit. A second heat exchanger is incorporated into the first fluid circuit. A valve controls an amount of a first fluid that is communicated to the first heat exchanger and the second heat exchanger. A controller is configured to control a positioning of the valve. The amount of the first fluid communicated to the first heat exchanger is based on a first characteristic of a second fluid and the amount of the first fluid communicated to the second heat exchanger is based on a second characteristic of the second fluid. A method and a system are also disclosed. | 12-11-2014 |
20150052872 | THERMAL ISOLATING SERVICE TUBES AND ASSEMBLIES THEREOF FOR GAS TURBINE ENGINES - Thermal isolating service tubes and assemblies thereof for gas turbine engines are provided. The thermal isolating service tube comprises an inner tubular member defining a fluid passage and at least one outer tubular member disposed about the inner tubular member. A spacing volume is defined between at least the inner tubular member and an adjacent outer tubular member. The thermal isolating service tube comprises a unitary structure and has at least one portion with a curved configuration, a non-circular cross-sectional shape, or both. | 02-26-2015 |
20150052873 | TORQUE CONNECTOR LUBRICATION SCUPPERS - 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, a fan drive gear system including a carrier for supporting a plurality of gears, and a scupper capturing lubricant during gear operation and directing lubricant into the carrier. A fan drive gear system is also disclosed. | 02-26-2015 |
20150075132 | ARRANGEMENT FOR A TANK BETWEEN A NACELLE COWLING AND A TURBOMACHINE - The invention proposes an arrangement of a tank of lubrication liquid for an aircraft turbomachine ( | 03-19-2015 |
20150089918 | GAS TURBINE LUBRICATION SYSTEMS - A casing for a fan drive gear system includes a cast body with an upper and a lower portion. The cast body defines an oil inlet and an oil outlet arranged below the oil outlet. An integrally cast oil channel extends between the inlet and outlet for conveying oil from the upper portion of the cast body portion to the lower portion of the cast body for providing a supply of lubrication to the gear system when oil pools in an upper portion of an auxiliary oil reservoir during negative-G flight events. | 04-02-2015 |
20150308351 | FUNDAMENTAL GEAR SYSTEM ARCHITECTURE - A fan drive gear system for a gas turbine engine according to an exemplary embodiment of this disclosure, among other possible things includes a gear system that provides a speed reduction between a fan drive turbine and a fan. A lubrication system configures to provide lubricant to the gear system and to remove thermal energy produced by the gear system. The lubrication system includes a capacity for removing thermal energy greater than zero and less than about 2% of power input into the gear system during operation of the engine. There is a second turbine rotor. A gas turbine engine is also disclosed. | 10-29-2015 |
20150361810 | FLUID COLLECTION GUTTER FOR A GEARED TURBINE ENGINE - A turbine engine system includes a gutter and a gear train with an axial centerline. The gutter is disposed radially outside of the axial centerline. The gutter includes an inner surface and a channel that receives fluid directed out of the gear train. The inner surface at least partially defines a bore in which the gear train is arranged. The channel extends radially into the gutter from the inner surface, and circumferentially to a channel outlet. The bore has a cross-sectional bore area, and the channel has a cross-sectional channel area that is substantially equal to or less than about two percent of the bore area. | 12-17-2015 |
20150361811 | MULTI-CIRCUIT LUBRICATION SYSTEM FOR A TURBINE ENGINE - A turbine engine system includes a first lubricant circuit, a second lubricant circuit, a plurality of engine stages and a shaft. The first lubricant circuit includes a first turbine engine component that is fluidly coupled with a first lubricant heat exchanger. The first turbine engine component includes a gear train, which connects a first of the engine stages to a second of the engine stages. The second lubricant circuit includes a second turbine engine component that is fluidly coupled with a second lubricant heat exchanger. The second lubricant circuit is fluidly coupled with the first lubricant circuit, and the second turbine engine component includes a bearing. The shaft is supported by the bearing, and connected to one of the engine stages. | 12-17-2015 |
20160003090 | FAN DRIVE GEAR SYSTEM SPLINE OIL LUBRICATION SCHEME - An input coupling for a fan drive gear system includes features for maintaining lubricant within a splined interface. The fan drive gear system includes a gear rotatable about an axis that includes an inner spline. The input coupling includes an outer spline engaged to the inner spline of the gear. The input coupling includes an aft oil dam for maintaining lubricant within an interface between the outer spline and the inner spline. | 01-07-2016 |
20160010550 | MANIFOLD FOR GAS TURBINE | 01-14-2016 |
20160024968 | AIR OIL COOLER AIRFLOW AUGMENTATION SYSTEM - 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. | 01-28-2016 |
20160032770 | GEARED GAS TURBINE ENGINE WITH OIL DEAERATOR AND AIR REMOVAL - A gas turbine engine has a fan drive turbine for driving a gear reduction. The gear reduction drives a fan rotor. A lubrication system supplies oil to the gear reduction, and includes a lubricant pump to supply an air/oil mixture to an inlet of a deaerator. The deaerator includes a separator for separating oil and air, delivering separated air to an air outlet, and delivering separated oil back into an oil tank. The separated oil is first delivered into a pipe outwardly of the oil tank, and then into a location beneath a minimum oil level in the tank. Air within the oil tank moves outwardly through an air exit into the deaerator. A method of designing a gas turbine engine is also disclosed. | 02-04-2016 |
20160108819 | Fuel/Oil Manifold - A single, unitary fuel/oil manifold for a gas turbine engine is provided which comprises one or more interfaces for mounting various fuel system and lubricating system components directly to the fuel/oil manifold. The fuel/oil manifold also defines fluid passages for transferring fuel or lubricant from one component to another component. Packing numerous fuel system and lubricating system components within the fuel/oil manifold reduces cost and weight and simplifies maintenance. | 04-21-2016 |
20160201791 | EPICYCLIC REDUCTION GEAR WITH FLUID TRANSFER PIPES, AND PROPELLER TURBOMACHINE FOR AN AIRCRAFT WITH SUCH A REDUCTION GEAR | 07-14-2016 |
20160376922 | DE-OILER AND A METHOD OF USING THE SAME - A de-oiler for separating oil from an air/oil mixture comprises a housing, and a rotatable porous element accommodated within the housing. The housing has a first axial face and a second, opposite, axial face, the first axial face being separated from the second axial face by an axial length. | 12-29-2016 |
20160376988 | WINDMILL AND NEGATIVE-G OIL SYSTEM FOR GEARED TURBOFAN ENGINES - A lubrication system for a gear system of a geared turbofan engine, the lubrication system includes an upper strut including an upper sump. A lower strut includes a lower sump. The upper strut and the lower strut support a gear system. A conduit extends from the upper sump within the upper strut to the lower sump within the lower strut. A lubricant collector receives lubricant exhausted from the gear system and directing the received lubricant into one of the lower sump and the upper sump. A pump in communication with the conduit for drawing lubricant from at least one of the lower sump and the upper sump and communicates lubricant to a lubricant inlet of the gear system. The pump draws lubricant from the lower sump when operating within a positive g-force environment and draws lubricant from the upper sump when operating within a negative g-force environment. A geared turbofan engine is also disclosed. | 12-29-2016 |