Abstract: 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.

Abstract: An oil scavenge system includes a tangential scavenge scoop and a settling area adjacent thereto which separately communicate with a duct which feeds oil into an oil flow path and back to an oil sump. A shield is mounted over the settling area to at least partially shield the collecting liquid oil from interfacial shear. A multiple of apertures are located through the shield to permit oil flow through the shield and into the duct. The scavenge scoop forms a partition which separates the duct into a first portion and a second portion. The first portion processes upstream air/oil mixture that is captured by the tangential scoop while the second portion receives the oil collected in the settling area.

Abstract: The turbojet has a bearing which supports, in rotation and in thrust, a low-pressure compressor shaft of axis Z-Z of the engine. The bearing is lubricated with oil by means of two nozzles. A feed tube is fastened to the nose cone of the engine. This tube connects the low-pressure compressor shaft to the engine nose cone. A skin lines the wall of the engine nose cone, leaving a passage for the circulation of oil. A plurality of radial oil return tubes are placed between the most eccentric part of the skin relative to the Z-Z axis and the bearing, for returning the oil to the bearing. The return of the oil into the bearing is located at a distance R from the Z-Z axis larger than the radius r of the feed tube.

Abstract: The present invention relates to a method for treating an airflow, laden with oil particles, flowing in a tube (9) communicating with a rolling bearing enclosure of a gas turbine engine, wherein said airflow is made to travel into a coking box (20) associated with a heating means, in which the air is heated to a sufficient temperature to coke the oil particles contained in the airflow. Preferably, the solid residues produced by the coking are collected in the coking box (20).

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 recirculating bearing lubrication system for a gas turbine engine that comprises a housing for the engine that serves as a primary static structural support, a rotor shaft for mounting rotational components of the engine, at least two bearings for supporting the rotor shaft within the housing and an air intake for supplying engine air comprises a generally annular lubricant source mounted about the engine intake to cool lubricant for the bearings; a solenoid that seals the lubricant from air contamination during storage of the engine and unseals it upon starting the engine; a lubricant pump that circulates the lubricant; at least one lubricant spray jet that receives circulating lubricant and sprays lubricant onto the bearings; and a sump for collecting excess lubricant sprayed on the bearings.

Abstract: A deoiler 26 for separating oil from air contaminated with the oil has at least one separator for separating the oil from the air and also has a source of suction for reducing air pressure at the source of the air. In an exemplary embodiment, the deoiler 26 creates the suction at a first operating condition, but acts as a restrictor at a second operating condition. A deoiling method according to the invention creates suction at a first operating condition to reduce the air pressure at the source of the oil-contaminated air, establishes a flow restriction at a second operating condition to pressurize the air source, and encourages oil to separate from the air at both operating conditions. When used as a component of a turbine engine lubrication system 22, the source of contaminated air may be a buffered bearing compartment 16.

Abstract: A method and apparatus for cooling a fluid in a bypass gas turbine engine involves directing the fluid to the bypass duct of the engine to allow for heat exchange from the fluid to bypass air passing through the bypass air duct.

Abstract: Disclosed is a structural frame for a gas turbine engine comprising an integral fluid reservoir and air/fluid heat exchanger. A central hub includes a reservoir for storing a fluid and an outer rim circumscribes the hub. A heat exchanger is fluidly coupled to the reservoir and is in simultaneous communication with the fluid and an air stream.

Abstract: An oil scavenge system includes a tangential scavenge scoop and a settling area adjacent thereto which separately communicate with a duct which feeds oil into an oil flow path and back to an oil sump. A shield is mounted over the settling area to at least partially shield the collecting liquid oil from interfacial shear. A multiple of apertures are located through the shield to permit oil flow through the shield and into the duct. The scavenge scoop forms a partition which separates the duct into a first portion and a second portion. The first portion processes upstream air/oil mixture that is captured by the tangential scoop while the second portion receives the oil collected in the settling area.

Abstract: The accessory gearbox (AGB) has at least one coolant passage between the AGB and the accessory for externally cooling the accessory without coolant flow inside the accessory.

Abstract: An improved passive cooling system for an aircraft APU compartment that includes a lightweight annular air-cooled oil cooler that is strategically oriented and shrouded to face its annular inlet away axially downstream from the exhaust of the APU to make it inherently fireproof to flames from the APU or any location within the APU compartment that fuel can accumulate.

Abstract: A method for assembling a gas turbine engine that includes providing a first fan assembly configured to rotate in a first rotational direction, rotatably coupling a second fan assembly to the first fan assembly, wherein the second fan assembly is configured to rotate in a second rotational direction that is opposite the first rotational direction, coupling a first shaft to the first fan assembly and to a first turbine rotor that is configured to rotate in a first rotational direction, coupling a second shaft coupled to the second fan assembly and to a second turbine rotor that is configured to rotate in a second rotational direction that is opposite the first rotational direction, and coupling a lubrication system to the gas turbine engine such that a lubrication fluid is channeled through the first shaft to lubricate at least one of the first and second fan assemblies.

Abstract: In a fluid system for a gas turbine engine, oil is supplied from an oil tank (10) by a constant displacement pump (12) to lubricate engine components (18). The oil is supplied to the components (18) via a heat exchanger (16) in which oil and fuel are placed in direct heat exchange relationship. The flow of oil to the components (18) is controlled by recirculating a proportion of the oil flow through a bypass (20). The bypass (20) regulates the flow of oil to the components (18) so that the amount of heat transferred to the fuel in the heat exchanger (16) is controlled. At low engine powers a greater proportion of the oil flows through the bypass (20) to reduce the oil flow to the components (18). This reduces the heat transferred to the fuel in the heat exchanger (16) and so prevents overheating of the fuel.

Abstract: A method and device for improved pressure balancing in a bearing chamber pressurization system for gas turbine engines employ a partition member to substantially separate first and second air-oil seals of the bearing housing.

Abstract: An electric motor thermally associated with a liquid reservoir of an aircraft engine is selectively operated to generate heat for pre-heating a liquid in a reservoir prior to engine start.

Abstract: A forced air cooling system for an APU comprising at least an oil cooler, a plenum in fluid communication with the oil cooler, and a compressor rotated by a rotating shaft of the APU such that the compressor and rotating shaft rotate at a same speed, the rotating compressor inducing a cooling air flow through the oil cooler. A method for cooling an auxiliary power unit is also provided.

Abstract: A multiple path fluid circuit comprising a fluid reservoir and a fluid pump having an inlet in fluid communication with the fluid reservoir. The fluid pump may have an outlet in fluid communication with an inlet of a fluid cooling circuit. The fluid cooling circuit may then have an outlet in fluid communication with the fluid reservoir. The outlet of the fluid pump may also be in fluid communication with an inlet of a lubrication circuit, which may be in fluid communication with a delivery system capable of supplying a fluid to a moving component or to a component in contact with the moving component. A gas turbine engine comprising a multiple path fluid circuit is also disclosed as well as a method of utilizing a multiple path fluid circuit.

Abstract: A lubrication system for an expendable gas turbine engine (20) having a rotatable shaft (26) is provided. Bearings (28) journal the shaft (26) for rotation about an axis. The system includes a vessel (46) for containing lubricating oil, a conduit (58) extending from the vessel (46) to the bearings (28), and a solenoid operated valve (70,76) in the conduit (58) and operable to only either fully open or fully closed. A control circuit (16) is provided for pulsing the solenoid (70) at a controlled rate to alternatingly (a) allow oil flow and (b) halt oil flow to the bearings (28) for a time insufficient to cause oil starvation of the bearings (28).

Abstract: A method and an apparatus for starting a gas turbine engine under various conditions are used to distribute a varying total amount of electric power to at least one of a starter, a fuel heater and an oil heater while providing fuel.

Abstract: A static structure for a miniature gas turbine engine includes a forward housing, a forward cover, a diffuser housing, a diffuser, a turbine nozzle, a combustor liner, a combustor housing and an exhaust pipe with relatively uncomplicated assembly interfaces. The static structure defines airflow and lubrication passages which communicate lubricant and airflow to each shaft bearing such that an adequate measured quantity of lubricant is supplied to the bearings in response to engine speed. The airflow through the airflow passage carries the lubrication supplied to the forward bearing toward the aft bearing to further lubricate the aft hot section bearing.

Abstract: A gas turbine engine is configured to use relatively cool, low pressure air discharged from a low pressure compressor to supply buffer air to lubrication sump seals. The engine is further configured such that the lubrication sump is thermally layered by isolating relatively hot, high pressure compressor air from the sump by utilizing a warm vent mixing cavity, which is located radially between of the hot high pressure compressor air and the cool buffer air, which is located in a buffer cavity between the vent cavity and the sump.

Abstract: A turbine includes a combustion chamber with deflectors generating vortices in a secondary gas flow into the combustion chamber, thereby confining the flame front from penetrating into the cold region of the chamber under variable operating conditions, simplifying cooling of the chamber walls. The turbine further includes devices for decoupling vibrations between the high- and low-speed shafts, including a loosely mounted spline coupling the high-speed shaft to the step-down system and disk dampening means coupling the step-down system to the low-speed output shaft.

Abstract: A gas turbine engine having an oil cavity architecture and bearing placement which reduce heat rejection and oil system complexity by enclosing the reduction gearbox bearings and at least the shaft bearings supporting the high pressure shaft in the same oil cavity.

Abstract: The invention relates to a system for driving an accessory, such as a fuel pump or an oil pump in a turboengine, said system comprising an electric motor and further comprising an air turbine associated with said electric motor. Said air turbine is suitable for being fed with a flow of air taken from a compressor of said turboengine and contributing to driving the accessory. The system also includes a valve for controlling the flow of air taken from the compressor, which valve is in the closed position while the turboengine is starting.

Abstract: An oil scavenge system includes a tangential scavenge scoop and a settling area adjacent thereto which separately communicate with a duct which feeds oil into an oil flow path and back to an oil sump. A shield is mounted over the settling area to at least partially shield the collecting liquid oil from interfacial shear. A multiple of apertures are located through the shield to permit oil flow through the shield and into the duct. The scavenge scoop forms a partition which separates the duct into a first portion and a second portion. The first portion processes upstream air/oil mixture that is captured by the tangential scoop while the second portion receives the oil collected in the settling area.

Abstract: In a device for supplying secondary air in a gas turbine engine provided with an inner shaft (8) supporting a low pressure compressor and a low pressure turbine and a hollow outer shaft (7) coaxially nested with the inner shaft and supporting a high pressure compressor and a high pressure turbine, a seal air introduction passage (41, 45, 48) for introducing a part of high pressure air drawn from the high pressure compressor into a seal section provided in each of the bearing boxes is provided with a high pressure air introduction turbine (62) attached to the outer shaft in a rotationally fast manner.

Abstract: A passive cooling system for an auxiliary power unit (APU) installation on an aircraft is provided. The system is for an auxiliary power unit having at least a compressor portion of a gas turbine engine and an oil cooler contained separately within a nacelle. The system includes the auxiliary power unit housed within the nacelle of the aircraft, an engine exhaust opening defined in the aft portion of the nacelle and communicating with the gas turbine engine, at least a first air inlet duct communicating with a second opening defined in said nacelle and with said compressor portion and the oil cooler is located within a second duct communicating with an opening other than the engine exhaust opening of said nacelle and with the engine exhaust opening. Exterior cooling air and engine exhaust ejected through said engine exhaust opening entrain cooling air through said second duct to said oil cooler, and thus provide engine oil cooling. An exhaust eductor is also provided.

Abstract: A drainage system for gas turbine supporting cushions or bearings, in particular for the second supporting bearing, consisting of a central shaft (20), surrounded by a series of supporting studs (21), which result, in their turn, with connection to a container housing (22) for studs (21), a sleeve (23) for containing the second supporting bearing of the turbine and a series of pipes (24, 25), respectively for the entry and drainage of the lubrication and cooling oil; the system consists of, in addition, a series of lateral seals (26), provided in positions facing the second supporting bearing, which create a pressure difference which permits the oil to pass under pressure within the drainpipes (25) at a well sustained speed.

Abstract: A fluid scavenging system is provided for a lubrication system including a gas turbine engine having bearing compartments. A valve includes a housing with an outlet and a plurality of fluid inlets respectively in fluid communication with the bearing compartments. The valve includes a rotationally driven member arranged within the housing with the member having a plurality of ports arranged thereon each defining an arcuate slot. Each of the ports are selectively in fluid communication with one of the fluid inlets through the arcuate slot during rotation of the member for selectively permitting fluid flow between the opening of one of the fluid inlets through one of the corresponding ports in the member. A fluid pump is fluidly connected to the outlet for drawing fluid from each of the plurality of fluid compartments during fluid rotation of the member.

Abstract: The bearings of a gas turbine are supplied with a lubricant from a reservoir by a main pump, when the turbine is operating. When the turbine is shut down and rotation ceases, the main pump also shuts down. When this occurs, an auxiliary pump is placed into operation to continue to supply the bearings with the lubricant until such time as the bearings have sufficiently cooled, at which point the auxiliary pump is shut down.

Abstract: The invention recites a microturbine system comprising a housing and a turbine including a rotary element having a shaft supported by the housing and rotatable about a rotary axis. A starter wheel is coupled to the shaft and rotatable in response to a stream of high-pressure fluid flowing from a high-pressure flow path. A pump is operable to provide a supply of lubricating fluid. The engine further includes a starter valve receiving the supply of lubricating fluid and being selectively operable to provide one of the stream of high-pressure fluid to the high-pressure flow path and a stream of low-pressure fluid to a low-pressure flow path.

Abstract: A seal assembly (22) for sealing a pressurized gaseous product includes, a pair of seals (24,26) spaced axially to provide a chamber (28) therebetween, a gas seal (24) being disposed on the inboard side of the seal assembly (22) between the sealed gaseous product and the chamber (28), an inlet (38) opening to the side of the gas seal (24) exposed to the gaseous product, the inlet (38) being connected to a supply of clean gas, the chamber (38) defined between the seals (24,26) being connected to a reservoir (50), the reservoir (50) being connected back to inlet (38) via a pressure intensifier (70) and the reservoir (50) being connected to the supply of clean gas, so that additional clean gas may be supplied thereto, when pressure in the reservoir (50) falls below a predetermined minimum value.

Abstract: The invention relates to a system for driving an accessory, such as a fuel pump or an oil pump in a turboengine, said system comprising an electric motor and further comprising an air turbine associated with said electric motor. Said air turbine is suitable for being fed with a flow of air taken from a compressor of said turboengine and contributing to driving the accessory. The system also includes a valve for controlling the flow of air taken from the compressor, which valve is in the closed position while the turboengine is starting.

Abstract: A bearing housing includes inner and outer shells through which a rotor shaft may extend. A service tube is fixedly joined to the inner shell and extends through a service aperture in the outer shell. A flexible coupling sealingly joins the service tube to the outer shell at the service aperture for permitting differential thermal movement between the inner and outer shells at the service tube.

Abstract: A passive cooling system for an auxiliary power unit (APU) installation on an aircraft is provided. The system is for an auxiliary power unit having at least a compressor portion of a gas turbine engine and an oil cooler contained separately within a nacelle. The system includes the auxiliary power unit housed within the nacelle of the aircraft, an engine exhaust opening defined in the aft portion of the nacelle and communicating with the gas turbine engine, at least a first air inlet duct communicating with a second opening defined in said nacelle and with said compressor portion and the oil cooler is located within a second duct communicating with an opening other than the engine exhaust opening of said nacelle and with the engine exhaust opening. Exterior cooling air and engine exhaust ejected through said engine exhaust opening entrain cooling air through said second duct to said oil cooler, and thus provide engine oil cooling. An exhaust eductor is also provided.

Abstract: A fluid flow system for a gas turbine engine provides combustion fuel to a main pump and an actuator pump significantly reducing heat generation at low flow demand, while regulating actuator flow temperature at high flow demand. Fuel flow from the actuator pump in excess of the actuators needs is directed through an actuator minimum pressure valve and into a thermal bypass valve (TBV.) Depending upon the temperature of the fuel, the TBV determines the path of the excess actuator pump fluid flow. The TBV divides the fuel flow between being recirculated to the actuator pump inlet and the main pump output flow path to the engine fuel input conduit. The engine actuators are thereby assured of receiving flow which preclude freezing of water entrained in the fuel. When there is minimal concern with the possibility of freezing water entrained in the fuel, the TBV passes a greater percentage of fuel through to join together in the engine fuel input conduit.

Abstract: Air captured from the tips of a compressor of a gas turbine engine is diverted from the engine core and can be collected for auxiliary uses. Gas path separation can be achieved using part-span shrouded compressor blades or using blade tip cut-outs conforming to an airflow dividing annular shroud. In a preferred application for the present invention, the gas turbine engine is the auxiliary power unit of an aircraft. This permits compressed air generation for Auxiliary Power Unit oil cooling and for compartment pressurization without loosing significant mass flow to the engine core, while eliminating the need to provide a separate active cooling system such as an engine driven fan.

Abstract: This invention relates to a gas-turbine engine which is provided in the turbine interior with a bearing chamber for a turbine shaft, the bearing chamber being sealed by sealing elements, and with a scavenge line for the lubricating oil which is supplied to the bearing chamber, in particular is sprayed onto the bearing(s) arranged therein. In accordance with the present invention, the single scavenge line, which is connected to a suitable lubricating-oil collecting compartment, features such an ample cross-section and the sealing elements have such a high sealing effect that the pressure in the bearing chamber is essentially equal to the pressure in the lubricating-oil-collecting compartment and maximally half the pressure in the turbine interior.

Abstract: Provided is a device for supplying seal air to the bearings of a gas turbine engine which allows the seal pressure to be kept even between the front and rear gear boxes without complicating the passages for supplying the seal air to the bearing boxes. Sealing air drawn from a part of high pressure compressor is conducted through passages defined between the inner periphery of the rotors of the high pressure compressor and a high pressure turbine and the outer periphery of the outer shaft, and is distributed to the front and rear bearing boxes. By appropriately providing narrowed parts in these passages, seal air is evenly distributed between the front and rear bearing boxes. Thus, even in case of a failure of one of the oil seals, any concentrated leakage of the lubricating oil can be avoided.

Abstract: A breather outlet 10 for discharging a liquid dispersion therefrom comprising an outlet pipe 12 wherein the breather outlet 10 further comprises an electromagnetic wave generator 14 so that, in use, electromagnetic waves produced by the wave generator 14 impart sufficient electromagnetic energy to the liquid dispersion to evaporate at least a portion thereof.

Abstract: A breather outlet 10 for discharging a liquid dispersion therefrom comprising an outlet pipe 12 wherein the breather outlet 10 further comprises an electromagnetic wave generator 14 so that, in use, electromagnetic waves produced by the wave generator 14 impart sufficient electromagnetic energy to the liquid dispersion to evaporate at least a portion thereof.

Abstract: A system and associated method for protecting during a shutdown a turbine having a turbine shaft and a compressor driven by the turbine shaft. The system include a first lubrication system, a second lubrication system, and a control system. The first lubrication system is configured to provide lubrication to the compressor. The second lubrication system is configured to provide lubrication to the turbine. The control system monitors the rotation of the turbine shaft in response to a shutdown request and causes the first and second lubrication systems to provide lubrication to the turbine and compressor until and after the turbine shaft stops rotating. The control system causes the first lubrication system to provide lubrication for a first predetermined period of time after the turbine shaft stops rotating. The control system causes the second lubrication system provides lubrication for a second predetermined period of time after the turbine shaft stops rotating.

Abstract: A sump evacuation system for a gas turbine facilitates reducing oil leakage from bearing assembly sumps in a cost-effective and reliable manner. The engine includes at least one bearing assembly housed within a sump pressurization cavity. The sump evacuation system includes a sump pressurization cavity, a sump oil cavity, an air/oil separator, and an air pump. The bearing assembly and the sump oil cavity are coupled in flow communication with the sump pressurization cavity, and the air/oil separator is coupled in flow communication with the sump oil cavity. Furthermore, the air pump is coupled in flow communication with the air/oil separator.

Abstract: A sump evacuation system for a gas turbine facilitates reducing oil leakage from bearing assembly sumps in a cost-effective and reliable manner. The engine includes at least one bearing assembly housed within a sump pressurization cavity. The sump evacuation system includes a sump pressurization cavity, a sump oil cavity, an air/oil separator, and an air pump. The bearing assembly and the sump oil cavity are coupled in flow communication with the sump pressurization cavity, and the air/oil separator is coupled in flow communication with the sump oil cavity. Furthermore, the air pump is coupled in flow communication with the air/oil separator.

Abstract: An apparatus for use in the bearing compartment of a gas turbine engine includes a first conduit and a second conduit. The first conduit defines inner and outer surfaces between an inlet end and an outlet end. The second conduit defines inner and outer surfaces between an inlet end and an outlet end. At least a portion of the second conduit is substantially coaxial with and enclosed by at least a portion of the first conduit. One of the first conduit or the second conduit is a lubricant feed to the bearing compartment. The other of the first conduit and the second conduit is the air vent from the bearing compartment.

Abstract: A fuel control system for an engine, having a pump operable to supply an output flow of fuel, engine fuel flow regulation means operable to regulate the pump output flow, and pump control means operable to vary an output rate of the pump according to an operational condition of the engine fuel flow regulation means.

Abstract: The invention is embodied in a closed-cycle lubrication oil system used during turbine start-up to provide both lift oil and hydraulic oil from one system using a single variable volume pump that supplies fluid at a high pressure for lift oil requirements. The pump discharge pressure is reduced, through a pressure regulating/reducing valve, down to hydraulic system demands. During steady-state gas turbine operation, the system provides only a flow of hydraulic oil to position the inlet guide vanes and gas valves as required by the gas turbine controls logic. During gas turbine shut-down, the system again meets both lift oil and hydraulic oil requirements. A second pump is advantageously incorporated in the preferred embodiments of the system to provide 100% redundancy in providing either lift or hydraulic oil.

Abstract: The present invention relates to a gas turbine generator plant in which, by forming auxiliary equipment, comprising a starter, a lubricating oil device, a control oil device, and a lubricating oil main tank, into a unit, this may be disposed within a building in a unitary manner with a generator and a gas turbine unit.

Abstract: A buffer seal arrangement is provided for improved buffer sealing of oil sump seals in gas turbine engines. The buffer seal arrangement includes a three section labyrinth seal. Disposed between the first and second section is a buffer air supply annulus for delivering pressurized air from the engine to said first and second sections of the seal. Oil drains are disposed between said second and third sections and adjacent the third section. The first section has four knife seals, and the second and third sections have three knife seals. Rig testing has shown that this buffer seal arrangement can prevent the leakage of oil into the gas path of the gas turbine engine.