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 small single use gas turbine engine with a twin spool rotor shaft and a bypass fan, the rotor shafts being supported for rotation by bearings in the front and rear compartments of the engine. A portion of the bypass fan air is diverted to flow through the bearings in order to provide for cooling of the high speed bearings. Because a large amount of cooling air is required to cool the bearings, an air in tube is positioned in each of the guide vanes in the turbine section to provide for a cooling air passage leading into the rear bearings. In the front bearings, cooling air from the bypass fan is bled off from a location just upstream from the entrance to the centrifugal compressor. A fuel mist tube supplies fuel mist to the cooling air before passing through the bearings to provide extra cooling for the bearings and to provide lubrication to improve the service life of the engine.

Abstract: A jet engine with a system for recovering oil around the lubricating chamber of the rear rolling bearing of the shaft of the jet engine. The shaft is supported by a rolling bearing situated in a lubricating chamber surrounded by a single recovery chamber having a seal situated downstream from the rotor of the turbine driving the shaft.

Abstract: A sensor assembly for a gas turbine engine includes a telemetry module mounted at a rotor bearing compartment for sensing engine operational parameters and a cooling system for cooling the telemetry module separate from a rotor bearing lubricant flow.

Abstract: A flow restrictor is provided for a lubrication circulation system. The flow restrictor comprises a body configured to obstruct a flow of lubricant within the lubricant circulation system. The body has one or more through holes communicating with upstream and downstream portions of the lubrication circulation system. Each of the one or more holes has a cross-sectional area sufficiently small, and a length sufficiently long, to prevent turbulent lubricant flow therethrough at temperatures below a first predetermined reference temperature. The one or more holes have sufficient aggregate cross-sectional area to allow a desired lubricant flow rate through the body at temperatures at or above a second predetermined reference temperature.

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: In a turbo-engine system, oil is circulated by means of a positive-displacement pump directly driven by the output shaft. The pump output pressure is monitored to trigger fuel injection when the turbine reaches sufficient speed during the start-up sequence.

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 thermal management system for a gas turbine powerplant with an engine oil line and an engine fuel line incorporates a heat transfer control module that includes a reversible heat pump with a heat pump compressor for circulating working fluid in forward and reverse directions through a working fluid line of the heat pump. The heat control module also includes a first heat exchanger having a heat exchange path for the working fluid between the compressor and a heat pump expansion valve and another heat exchange path for the engine oil. A second heat exchanger has a heat exchange path for the working fluid between the compressor and the expansion valve and another heat exchange path for the engine fuel. The heat pump can be operated in forward or reverse directions depending on whether heat is to be transferred from the engine oil or the fuel to the heat pump working fluid.

Abstract: A method for treating an airflow, laden with oil, flowing in a tube communicating with a rolling bearing enclosure of a gas turbine engine, wherein the airflow is made to travel into a coking box associated with a heating mechanism, 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.

Abstract: A screw compressor (20) has a housing having first and second ports along a flow path. A male-lobed rotor has a first rotational axis. A female-lobed rotor has a second rotational axis and is enmeshed with the male-lobed rotor to define a compression path between suction and discharge locations along the flow path. The compressor has a compressor lubrication network having a lubricant outlet port (242) along a low pressure cusp (244). An unloading slide valve element (102) may be along a high pressure cusp (105).

Abstract: A gas turbine engine comprising an oil system and a gearbox, the gearbox is driven by at least one engine shaft, the oil system comprises a pump drivingly connected to the gearbox, an oil tank connected to the pump via a supply pipe and a delivery pipe connecting the pump to the engine for delivery of oil thereto, an anti-siphon pipe is connected between the tank and the delivery pipe to provide an excess oil flow to the engine characterized in that the anti-siphon pipe includes a variable flow valve for regulating the flow of oil passing therethrough such that at low engine speeds an adequate supply of oil is provided to a sight glass in the tank.

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 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.

Abstract: An exhaust-side bearing rotatably supports a rotor of a turbine. A seal air-pipe and a first air-supply pipe supply compressed air extracted from a compressor of the turbine to the exhaust-side bearing. A second air-supply pipe supplies compressed air from a supplementary air-source to the exhaust-side bearing. A control apparatus switches between the first air-supply pipe and the second air-supply pipe based on the operation state of the gas turbine.

Abstract: A heat exchange system for use in lubricating systems for aircraft turbofan engine equipment in which a lubricant is provided under pressure to spaces bounded at least in part by surfaces moving relative to one another, the heat exchange system for providing air and lubricant heat exchanges to cool the lubricant at selectively variable rates in the engine fan airstreams. A heat exchanger core is provided in a controlled air flow duct system opening at its plural entrances to the engine fan airstreams and having its outlet end opening about at the end of the fan duct nozzle.

Abstract: The invention relates to a system (2) for deicing an aircraft turbine engine inlet cone (4) comprising air-diffusing means (18) intended to equip the inlet cone of the turbine engine so as to deliver hot air thereto. According to the invention, it also comprises a circuit (20) for removing pressurizing air from at least one bearing enclosure of the turbine engine, this circuit communicating with the air-diffusing means in order to be able to supply the latter with hot air.

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

Abstract: 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: A fuel delivery system for a gas turbine engine that delivers fuel to a combustor of the engine and lubricates bearings of the engine with fuel, comprising: a tank for storing the fuel; a pump for delivering a continuous flow of fuel from the tank to the combustor by way of a combustor inlet stream and the engine bearings by way of a bearing lubrication stream; a pressurized container for storing fuel lubrication additive under pressure; and a flow valve for controlling flow of fuel lubrication additive that flows from the pressurized container into the bearing lubrication inlet stream to mix with the fuel delivered to the engine bearings.

Abstract: A method and system for controlling fuel in a gas turbine engine including a fuel supply system channeling fuel to a combustor are provided. The system includes a first heat exchanger configured to transfer heat between a working fluid and a first cooling medium. The system also includes a second heat exchanger in series flow communication with the first heat exchanger wherein the second heat exchanger is configured to transfer heat between the working fluid and a second cooling medium. The system further includes a modulating valve configured to control the flow of at least one of the first and the second cooling media to maintain a temperature of the first or second cooling medium substantially equal to a predetermined limit.

Abstract: 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.

Abstract: In a device for supplying secondary air in a gas turbine engine provided with an inner shaft (8) and a hollow outer shaft (7) coaxially nested with each other, a seal air introduction passage (71, 85, 88) is defined inside the engine for introducing a part of high pressure air drawn from a high pressure compressor into a seal section provided in each of the bearing boxes for supporting the inner and outer shafts; and a swirl air cooling turbine (59) is provided in the seal air introduction passage and attached to a part attached to the outer shaft in a rotationally fast manner. The swirl air cooling turbine (59) is formed around a section of the outer shaft intermediate between the high pressure compressor and the high pressure turbine, the swirl air cooling turbine including a spiral flow path extending in a substantially cylindrical plane coaxial with the outer shaft.

Abstract: 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.

Abstract: The pump system extracts motive power from oil in the pressurized oil circuit to power a scavenge pump mounted on a scavenge oil circuit.

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: 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 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 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.

Abstract: A method for assembling a gas turbine engine is provided. The method includes coupling a high-pressure compressor to a high-pressure turbine using a first shaft, coupling a fan assembly to a low-pressure turbine using a second shaft, and coupling a differential squeeze film damper assembly between the first and second shafts.

Abstract: It comprises two bearing supports (19) and (23) mounted on an inter-turbine casing (25), a first and a second bearing (2, 4) mounted on said bearing supports, a low-pressure turbine journal (20) mounted rotating with respect to the inter-turbine casing (25), a fixed ferrule (48) and an oil passage (44) provided in the low-pressure turbine journal (20) making it possible to discharge the oil inside the fixed ferrule (48). The ferrule is preferentially widened from the end at which the oil is discharged.

Abstract: Oil system components for a turbine engine are used to provide a vacuum system for a fuel stabilization unit (FSU). A vacuum system pulls oxygen and other contaminants from fuel into a vacuum chamber within the FSU. The vacuum system pumps the discharge through a vacuum outlet in the FSU toward a vacuum pump. Due to the quality of vacuum required, a two-stage vacuum pump is used. A first stage vacuum pump is an oil system scavenge pump for the turbine engine and the second stage vacuum is provided by a second stage vacuum pump. The discharge flows from the vacuum chamber through to the second stage vacuum pump and is then added to the oil supply. The oil and discharge mixture is sent through an oil system de-oiler and a de-aerator to clean the oil supply prior to pumping the oil back through the oil system.

Abstract: A system and method for precisely controlling lubricant supply flow to one or more rotating machines in an aircraft includes a motor, a pump, and a motor control unit. The motor is coupled to receive motor speed commands and, in response to the commands, rotates at the commanded motor speed and supplies a drive force to the pump. The pump, upon receipt of the drive force, draws lubricant from a lubricant source and supplies it to a rotating machine. The motor control unit determines a scheduled lubricant supply pressure based at least in part on lubricant temperature, rotating machine rotational speed, and one or more aircraft operating conditions, and to supplies the motor speed commands to the motor that cause the pump to supply lubricant at the scheduled lubricant supply pressure.

Abstract: A centrifugal air/oil separation system communicates with bearing cavities of the engine and substantially isolates separated oil from contacting the gearbox.

Abstract: A small gas turbine engine with a compressor, a combustor, and a turbine located downstream of the combustor. The compressor and turbine are supported on a rotary shaft, and a main bearing is support on the rotary shaft, the main bearing being located in a hot zone of the combustor. The main bearing includes cooling air passages within the races to provide cooling for the bearing. A cooling air is diverted from the compressor and passed through the bearing cooling passages for cooling the bearing, and then the cooling air is directed into the combustor. The cooling air is also passed through a guide nozzle before being passed through the bearing to cool both the guide nozzle and the bearing. A swirl cup injector is sued to deliver the compressed air from the compressor and the cooling air from the bearing into the combustor, the swirl cup injector also acting to draw the cooling air through the bearing.

Abstract: The invention relates to an air-oil heat exchanger located at the inner shroud of the secondary duct of a turbojet. In characteristic manner, it comprises an oil circuit placed inside the separator nose and fins placed outside the top wall of the separator nose, between the leading edge of the separator nose and the outlet guide vanes.

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 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.

Abstract: A system and method for controlling the rotational speed of a gas turbine engine in an aircraft includes appropriate devices and processes for determining a pressure of lubricant supplied to the turbine engine, and for determining a maneuver state of the aircraft. The rotational speed of the gas turbine engine is controlled based at least partially on the determined pressure and the determined maneuver state. Thus, if the aircraft is in a maneuver state that may cause a reduction or loss of lubricant to the gas turbine engine, the rotational speed of the gas turbine engine can be reduced to a magnitude sufficient to increase turbomachine tolerance to the reduced or no lubricant flow.

Abstract: A two-stage turbofan system for use in a gas turbine engine comprises a first-stage fan shaft, a second-stage fan shaft, a stationary torque tube and a gear system. The second-stage fan shaft connects with a drive shaft in the gas turbine engine such that the second-stage fan shaft is driven at the speed of the drive shaft. The stationary torque tube is connected with a fan case in the gas turbine engine. The gear system is connected to the second-stage fan shaft and the torque tube. The first-stage fan shaft extends from the gear system such that the first-stage fan shaft is driven at a speed reduced from that of the drive shaft.

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: 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.

Abstract: The air exit hole of the vent line (6) connected to a venting apparatus for the lubricating oil system of a jet engine is arranged behind the nozzle throat (2) on the periphery of the exiting engine jet (4). The exit hole is tangentially arranged on the periphery of the engine jet, or slightly enters the rim area of the engine jet. The vent line extends under the protection of an aerodynamically shaped fairing (5, 11). This arrangement of the air exit, while being simply designed, cost-effective and weight-saving, provides for clean, invisible discharge of air from the oil venting apparatus.

Abstract: A thermal management system for a gas turbine engine includes a cooling airflow which enters through an air filter portion of a forward cover for filtration of particulate which may result in FOD to a rotational system of the engine. Filtered cooling airflow flows along a rotor shaft over and through a forward bearing, over and through a permanent magnet generator, then over and through an aft bearing to provide thermal management. Commensurate therewith, the cooling airflow atomizes and communicates a lubricant to the bearings. From the aft bearing, the cooling airflow merges with a primary airflow path from an intake which generally surrounds the forward cover.

Abstract: A method for assembling a gas turbine engine 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, and coupling a lubrication system to the gas turbine engine such that a lubrication fluid is channeled through at least a portion of the second fan assembly.

Abstract: A gas turbine engine is provided with an oil cooler which receives cooling air from a turbo fan. At times when the turbo fan is operating at lower speeds, the volume of cooling air is also lowered. At such times, a supplemental airflow is provided over heat exchangers in the oil cooler. The supplemental airflow includes a supplemental airflow fan and valve for selectively controlling the supplemental airflow over the heat exchangers.

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 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 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: A method facilitates assembling a gas turbine engine that includes an oil supply and scavenge system, wherein the oil supply and scavenge system includes at least one sump cavity that includes a first scavenge port and a second scavenge port, a first oil pump and a second oil pump such that the first oil pump is in flow communication with and receives scavenge oil from the first scavenge port and the second oil pump is in flow communication with and receives scavenge oil from the second scavenge port. In addition, an oil supply source is coupled in flow communication with the first and second oil pumps.

Abstract: The invention relates to a standby lubrication method for an engine 1 in the event of the failure of a main lubrication system 2 of this engine 1, in which said failure is detected and, in response to the detection of this failure, at least one portion of a fuel fluid of the engine 1 is tapped off to lubricate at least one element of the engine 1. The invention also relates to a standby lubrication device 6 for an engine 1 comprising a main lubrication system 2, said standby lubrication device 6 comprising means for detecting a failure of the main lubrication system 2, means 12 for tapping off at least a portion of a fuel fluid of the engine 1 in order to direct it to at least one element of the engine 1 intended to be lubricated, and control means 15 capable of being connected to said tapping and detection means 12, in order to carry out the standby lubrication method.