Abstract: A fan drive gear system for a turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a sun gear that is rotatable about an axis, a plurality of intermediate gears driven by the sun gear, and a baffle that is disposed between at least two of the plurality of intermediate gears for defining a lubricant flow path from an interface between the sun gear and at least one of the plurality of intermediate gears. The baffle includes a channel with at least one ramp portion directing lubricant.

Abstract: A gas turbine engine includes a compressor section arranged in serial flow order with a turbine section, and an electric motor assembly. The electric motor assembly has a rotor assembly that is coupled to, or integrated within, a stage of compressor rotor blades of the compressor section and a stator assembly. The stator assembly is operable with the rotor assembly to rotate the rotor assembly relative to the stator assembly and drive the stage of compressor rotor blades about the axial direction.

Abstract: A power takeoff and gearbox system of a multi-spool gas turbine engine includes a high rotor towershaft operably connected to and driven by a first spool of the gas turbine engine, a first gearbox operably connected to the high rotor towershaft, a low rotor towershaft operably connected to and driven by a second spool of the gas turbine engine, and a second gearbox operably connected to the low rotor towershaft. The high rotor towershaft is located at a first case of the gas turbine engine and the low rotor towershaft is located at a second case of the gas turbine engine axially forward of the first case.

Abstract: An aircraft turbine engine includes a low-pressure body and a high-pressure body, as well as means for drawing power on said low-pressure body, said means having a first shaft for drawing power, the radially inner end of said first shaft bearing a first bevel gear meshed with a first idler bevel wheel driven by the low-pressure body, the turbine engine further having a first annular bearing support which extends about an axis and is rigidly connected to a stator. The first bearing support includes a first cylindrical portion which extends coaxially with a second substantially cylindrical portion of the idler wheel, said first and second portions being guided one inside the other by bearings, and the idler wheel is driven by the low-pressure body by means of an annular damping piece which is independent of the first bearing support.

Abstract: Methods and systems for operating a gas turbine engine having variable geometry mechanisms are described. The method comprises detecting a failure event associated with the gas turbine engine, identifying a location of the failure event, selecting an aerodynamic load modulation schedule for the variable geometry mechanisms of the gas turbine engine as a function of the location of the failure event, and applying the aerodynamic load modulation schedule as selected to the variable geometry mechanisms during the failure event.

Abstract: A compressed air energy storage system is described, including a compressor fluidly coupled to a compressed air reservoir and an expansion train including at least a first turbine. The system further includes an electric machine aggregate configured: for converting electric power into mechanical power and driving the compressor therewith during the energy storing mode; and for converting mechanical power produced by the expansion train into electric power during the power production mode. A combustor is configured for receiving fuel and compressed air and producing combustion gas, and for supplying the combustion gas to the first turbine.

Abstract: An accessory system for a gas turbine engine having a driveshaft with an axis of rotation is provided. The accessory system includes a towershaft coupled to the driveshaft and driven by the driveshaft along a towershaft axis of rotation. The accessory system also includes a shaft including a first shaft bevel gear coupled to a towershaft bevel gear. The shaft is rotatable by the towershaft along a shaft axis of rotation and defines an air-oil separator. The shaft axis of rotation is transverse to the towershaft axis of rotation. The accessory system includes a first accessory drive shaft having a first accessory bevel gear driven by the shaft. The accessory system also includes a second accessory drive shaft having a second accessory bevel gear driven by the shaft.

Abstract: A compressed air energy storage power generation device includes an inert gas source for supplying an inert gas, an inert gas flow path system, and a flow path switching unit. The inert gas flow path system fluidly connects the gas phase portion of the high temperature heat storage unit, the gas phase portion of the low temperature heat storage unit, and the inert gas source. The flow path switching unit switches the inert gas flow path system to at least a state in which the inert gas source is in communication with both the high temperature heat storage unit and the low temperature heat storage unit and a state in which the inert gas source is blocked from both the high temperature heat storage unit and the low temperature heat storage unit.

Abstract: A gas turbine engine assembly comprising, a gearbox including a first housing that includes a first auxiliary gear drive on a first portion thereof, a second housing that includes a second auxiliary gear drive on a second portion thereof, and a third housing that includes a third auxiliary gear drive on a third portion thereof, the housings being interconnected so that the first portion of the first housing, the second portion of the second housing and the third portion of the third housing form a substantially triangular polyhedron shape, with the second portion of the second housing disposed between the first portion of the first housing and the third portion of the third housing. The first auxiliary gear drive, the second auxiliary gear drive and the third auxiliary gear drive project outwardly in mutually divergent directions.

Abstract: In one aspect the present subject matter is directed to a gas-electric propulsion system for an aircraft. The system may include a turbofan jet engine, an electric powered boundary layer ingestion fan that is coupled to a fuselage portion of the aircraft aft of the turbofan jet engine, and an electric generator that is electronically coupled to the turbofan jet engine and to the boundary layer ingestion fan. The electric generator converts rotational energy from the turbofan jet engine to electrical energy and provides at least a portion of the electrical energy to the boundary layer ingestion fan. In another aspect of the present subject matter, a method for propelling an aircraft via the gas-electric propulsion system is disclosed.

Abstract: A gas turbine engine assembly comprising, a gearbox including a first housing that includes a first auxiliary gear drive on a first portion thereof, a second housing that includes a second auxiliary gear drive on a second portion thereof, and a third housing that includes a third auxiliary gear drive on a third portion thereof, the housings being interconnected so that the first portion of the first housing, the second portion of the second housing and the third portion of the third housing form a substantially triangular polyhedron shape, with the second portion of the second housing disposed between the first portion of the first housing and the third portion of the third housing. The first auxiliary gear drive, the second auxiliary gear drive and the third auxiliary gear drive project outwardly in mutually divergent directions.

Abstract: A gearbox to be mounted on a turbomachine and driven by a radial drive shaft of the latter. The gearbox has a three-dimensional or sinuous shape, which can house a large quantity of equipment to be driven, without occupying a large amount of space in any dimension, since the gearbox remains close to the turbomachine and the equipment can be distributed over a large surface. The drive train of gears successively extends into several non-parallel planes and comprises an axial branch on the turbomachine and a branch forming an arc of circle around the turbomachine.

Abstract: A driveshaft vessel assembly for a gas turbine engine is disclosed. The driveshaft vessel assembly comprises a driveshaft vessel and an outlet guide vane. The driveshaft vessel includes a forward face, an aft face, and opposing side faces and is configured to house at least a portion of a radial driveshaft. The outlet guide vane includes a leading edge and a trailing edge. The length of the trailing edge is substantially equal to a length of the forward face of the driveshaft vessel such that the trailing edge of the outlet guide vane is faired into the forward face of the driveshaft vessel.

Abstract: This gearbox to be assembled to a turbomachine portion and driven by a power take-off radial shaft thereof, includes several branches, the essential advantage of which is to allow a great amount of pieces of equipment to be driven to be accommodated, without implying a significant overall size in any dimension, since the gearbox remains close to the turbomachine and the pieces of equipment can be distributed on a large surface area. The housing (5) is divided into portions (27, 28) assembled to each other at the bends, in order to reduce its manufacturing cost.

Abstract: A power generation system includes a compression unit which compresses a gas, a storage which stores the compressed gas output from the compression unit, a first expansion unit which generates first power and outputs a first exhaust gas, a heating unit which heats at least the stored gas output from the storage, a second expansion unit which generates second power and outputs a second exhaust gas, a first regenerator which performs a first heat exchange between the second exhaust gas and the stored gas output from the storage, to generate a first heat exchange gas used to generate the first power and a first regenerator gas, and a second regenerator which performs a second heat exchange between the first exhaust gas and the first regenerator gas to generate a second heat exchange gas used to generate the second power after heated at the heating unit.

Abstract: A gas turbine engine and an accessory gear box (AGB) are provided for. The gas turbine engine comprises a drive shaft, a compressor, a combustor and an exhaust turbine, where the exhaust turbine and the compressor are coaxially connected by the drive shaft. The gas turbine engine further comprises an engine casing of varying diameters circumferentially enveloping the compressor, the combustor and the exhaust turbine with a waist located between the compressor and the combustor. The gas turbine engine also includes an accessory gear box (AGB) attached to the engine casing at the waist, the AGB comprising a gear rotating on an axis extending in a transverse direction relative to that of the drive shaft.

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

Abstract: A manual mechanical drive to a high pressure sub assembly of a turbojet during endoscopic inspection of the high pressure turbine is provided. A coupling element suitable for coupling with an external actuator such as a crank handle is fitted on the axis of an alternator that is normally driven mechanically via the high pressure sub assembly, thereby providing a coupling suitable for driving said high pressure sub assembly.

Abstract: A gas turbine engine includes a combustor, a first turbine section in fluid communication with the combustor, a second turbine section in fluid communication with the first turbine section, and a mid-turbine frame located axially between the first turbine section and the second turbine section. An oil system includes a first oil system component that houses oil. A first connector mechanically connects the first oil system component to the mid-turbine frame.

Abstract: A turbine engine includes a shaft, a fan, at least one bearing mounted on the shaft and rotationally supporting the fan, a fan drive gear system coupled to drive the fan, a bearing compartment around the at least one bearing and a source of pressurized air in communication with a region outside of the bearing compartment.

Abstract: A device for detecting a fault in a low-pressure fuel pump of a turbojet. The pump is driven by an accessory gearbox including a gear for mechanically driving the accessories. The device measures the vibration frequencies of the accessory gearbox and detects, from among the frequencies, at least one vibration frequency of the low-pressure fuel pump. The device allows a fault in the low-pressure fuel pump to be detected as soon as it occurs.

Abstract: A gearbox for a gas turbine engine includes a housing that includes first and second housing portions interconnected by an intermediate housing portion to provide a generally U-shaped structure. Each of the first and second housing portions includes opposing first and second faces. The second faces of the first and second housing portions are adjacent to one another. First and second gear sets are respectively arranged in the first and second housing portions. A third gear set is arranged in the intermediate portion and is coupled to the first and second gear sets. Accessory drive component mounts are provided on at least three of the first and second faces of the first and second housing portions. The mounts are each configured to support an accessory drive component coupled to one of the first and second gear sets.

Abstract: A bleed system that comprises a bleed inter-compressor fluidly coupled to a low pressure port of the bleed system and configured to utilize a portion of a medium received from the low pressure port to increase the pressure of another portion of that medium. A turbine of the bleed inter-compressor is coupled to a compressor of the bleed inter-compressor and drives the compressor via a shaft, so as to regulate the pressure of the medium.

Abstract: A turbofan gas turbine engine is provided having a unique power off-take shaft and gear system. Other gas turbine engine types are also contemplated herein. Two power off-takes are provided, one each for the low pressure spool and high pressure spool. The power off-takes extend across a core flow path of the turbofan engine between the low and high pressure shafts to a fan frame of the turbofan. A drive gear is provided near the front end of the high pressure shaft, and another drive gear is provided on the low pressure shaft near the drive gear for the high pressure shaft. Both gears are located in a sump of the gas turbine engine. The power off-take shafts are coupled to the drive gears. Two power devices are coupled to the power off-take shafts and are located in the fan frame. The power devices can be electric generators or motors.

Abstract: A mounting assembly 2 for mounting a gearbox 10 to a gas turbine engine, comprising a mount ring 4 and a spigot pin 8 having a flange 22 at one end. The spigot pin 8 extends radially outwardly through a bore 14 in the mount ring 4 for engagement with a gearbox 10 and the flange 22 locates against a radially inner surface of the mount ring 4. The bore 14 supports the spigot pin 8 and dissipates forces exerted on the spigot pin 8, for example forces generated during a fan blade-off event.

Abstract: An example gas turbine engine includes, among other things, a geared architecture rotatably coupled to the fan drive shaft, and a high pressure compressor. The gas turbine engine is configured so that a core temperature at an exit of the high-pressure compressor is approximately in a range of about 1150 to about 1350 degrees Fahrenheit at take-off. The gas turbine engine is configured so that an Exhaust Velocity Ratio, defined by a ratio of a fan stream exhaust velocity to a primary stream exhaust velocity, is approximately in a range of about 0.75 to about 0.90. A Bypass Ratio of the engine is greater than about 8.0.

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

Abstract: A control system for controlling a plurality of distinct functions of a turbojet engine, each function being associated with a respective actuation device. The system includes: an electric motor adapted to supply mechanical energy to each of the actuation devices; an electronic control unit for the electric motor; and at least one switching device interposed between the motor and the actuation devices, the switching device(s) serving to distribute the mechanical energy supplied by the electric motor selectively to one of the actuation devices.

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

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

Abstract: A turbine engine is disclosed herein. The turbine engine includes a starter/generator operable to deliver rotational power in a first mode of operation and to generate electrical power in a second mode of operation. The turbine engine also includes an accessory gear box mechanically coupled to the starter/generator. The turbine engine also includes a shaft mechanically coupled to the accessory gear box such that the accessory gear box is operably disposed between the shaft and the starter/generator. The turbine engine also includes a clutch operably disposed between the accessory gear box and the starter generator. The clutch is operable to slip in and out of full engagement in response to a first predetermined level of torque between the starter/generator and the accessory gear box.

Abstract: The method and apparatus for in-flight relighting of a turbofan engine involve in one aspect selectively controlling an accessory drag load on one or more windmilling rotors to permit control of the windmill speed to an optimum value for relight conditions.

Abstract: A hybrid propulsive technique includes providing at least some first thrust associated with a flow of a working fluid through at least a portion of an at least one axial flow jet engine. The hybrid propulsive technique includes extracting energy from the working fluid that is at least partially converted into electrical power, and converting at least a portion of the electrical power to torque. The hybrid propulsive technique further includes rotating an at least one independently rotatable propeller/fan of at least one rotatable propeller/fan assembly at least partially responsive to the converting the at least a portion of the electrical power to torque, wherein the rotating of the at least one independently rotatable propeller/fan of the at least one rotatable propeller/fan assembly is arranged to produce at least some second thrust.

Abstract: An intermediate casing for a gas-turbine engine has an outer ring (3), an inner ring (1) and an intermediate ring (2) mutually supported by mutually aligned outer and inner supporting struts (4, 5). A radial drive shaft (6), positioned through inner and outer supporting struts (4.1, 5.1) aligned at a 6-o? clock position, connects to an auxiliary gear drive (7). Four additional outer supporting struts (5.2, 5.3, 5.4, 5.5) are spaced apart 72°. A mounting bracket connects to the outer ring at a side facing an aircraft fuselage in areas of two of the additional outer supporting struts. The arrangement of supporting struts and type of mounting bracket attachment, saves weight, improves flow in the bypass duct and increase maintenance and installation access at the bottom side of the engine to nearly 144°.

Abstract: An assembly for driving accessories of a gas turbine is provided. The assembly includes: a gearbox having a front side face and a rear side face opposite the front face and having mounted therein a first gear train made up of three toothed wheels meshing with one another, and a second gear train made up of four toothed wheels meshing with one another; a power transmission shaft that is coupled in rotation with the first and second gear trains by a toothed wheel pair, and that emerges from the front side face of the gearbox; and nine distinct gas turbine accessories mounted against the side faces of the gearbox, and each including a respective drive shaft that is coupled in rotation with one of the toothed wheels of the two gear trains.

Abstract: An accessory gear box configured to be mounted on a fan casing of a turbojet engine, including: an input shaft; a plurality of accessory drive shafts; and a compartment forming an interface with an accessory arranged on the housing of the accessory gear box at a site of the accessory, the interface compartment including an inlet and an outlet configured to allow air to circulate inside the compartment, to insulate the accessory gear box from heat generated by the accessories.

Abstract: An example method of allocating power within a gas turbine engine includes driving an off-take power delivery assembly using a first amount of power from a spool, the first amount of power corresponding to an off-take power requirement of a gas turbine engine; and driving the spool of the gas turbine engine using a second amount of power, wherein a ratio of the first amount of power to the second amount of power is greater than or equal to 0.009.

Abstract: A gas turbine engine (10) comprises a diffuser (14) and a nozzle (16) affixed to an annular housing (12), a bearing assembly including first and second bearings (24,26) mounted on a support tube (28) affixed at one end (28a) in cantilever fashion to a radially inner portion (16c) of the nozzle, a compressor (18) and a turbine (20) affixed to axially spaced apart ends of a shaft (22) rotatably mounted in the bearings, and an annular combustor (32) disposed between the compressor and turbine and concentric to the shaft. The diffuser is adjustably attached to the housing external threads (14e) on an outer annular surface of the diffuser and received in internal threads (12e) in an internal annular surface of the housing. An electric generator (42) is disposed radially inward of the annular combustor axially between the diffuser and nozzle. A fuel slinger (30), affixed to the shaft, receives fuel from an air/fuel annulus (88) defined by a stator (44) and a rotor (46) of the generator.

Abstract: An auxiliary power unit has a gas turbine engine, a generator, and a gear box. A mount bracket is mechanically attached to the gear box. The bracket is for connecting to a plurality of struts. The struts are for connecting to an aircraft housing. A shield box is formed of a flame resistant rigid material. The shield box encloses the mount bracket to provide flame protection to the mechanical attachment.

Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool, the intermediate speed spool, and the fan drive turbine configured to rotate in the same first direction.

Abstract: A turbine engine for aircraft includes a gas generator as well as to a receiver driven by a power turbine, and to an electric power generator, the rotor of which centered on a rotor axis distinct from the longitudinal axis, is driven into rotation by the power turbine, via a mechanical gear transmission, including a toothed drive wheel centered on the axis. Further the receiver includes a first propeller driven by a free power turbine and the toothed drive wheel is attached on an outer case of this power turbine.

Abstract: With an engine for aircraft with high electric power demand, the power of the low-pressure shaft (7) operating in a lower speed range is transmitted to the high-pressure shaft (6) by an electromagnetic clutch (10). In the clutch element (14) on the side of the low-pressure shaft a frequency-controllable rotary field is generated, which drives a magnet (13) connected to the high-pressure shaft.

Abstract: An assembly and method for providing buffer air and/or ventilation air within a gas turbine engine, the assembly includes an accessory gearbox and a centrifugal compressor. The accessory gearbox is connected to a driven shaft of the gas turbine engine. The centrifugal compressor is driven by the accessory gearbox during operation of the gas turbine engine to receive and compress a bleed air to produce the buffer air and/or the ventilation air. The buffer air and/or the ventilation air is communicated within the gas turbine engine.

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

Abstract: An accessory system for a gas turbine engine includes a main case which defines an accessory gearbox axis. A cover is removably mountable to the main case and a first gear set at least partially within the cover along a first accessory axis transverse to the accessory gearbox axis.

Abstract: An accessory system for a gas turbine engine includes an accessory gearbox which defines an accessory gearbox axis. A crossover gear set generally along the accessory gearbox axis interconnects a first gear set and a second gear set.

Abstract: An accessory gearbox for a gas turbine engine has a main gearbox housing for receiving a plurality of gears to drive a plurality of accessories. An input shaft has a first bevel gear at an outer end, and extends inwardly to transmit rotation to the plurality of gears. A tower shaft has a second bevel gear engaging the first bevel gear to in turn drive the input shaft. A tower shaft houses is fixed to the main gearbox housing. A method of removing a tower shaft is also disclosed.

Abstract: An accessory system for a gas turbine engine includes an accessory gearbox which defines an accessory gearbox axis and includes first and second sides. A first geartrain includes one or more shafts rotatable about axes perpendicular to the first side of the accessory gearbox and a second geartrain includes one or more shafts rotatable about axes perpendicular to the second side of the accessory gearbox. A driven gear set defines an input axis and drives first geartrain and the second geartrain about corresponding first and second drive axes parallel to the input axis.

Abstract: Devices and methods for supporting an accessory (32) in a gas turbine engine (10) are disclosed. The accessory (32) may have an interface (36) for coupling to a shaft (24) of the gas turbine engine (10). The device may comprise a first support (38) configured to support a first portion (34) of the accessory (32) proximal the interface (36) and a second support (40) configured to support a second portion (35) of the accessory (32) distal from the interface (36). The second support (40) may be configured to provide a lower resistance to relative displacement between the accessory (32) and structure (42) of the engine (10) than does the first support (34).

Abstract: A disclosed gas turbine engine includes a core engine defined about an engine centerline axis, the core engine including a compressor section driven through a shaft by a turbine section. A core nacelle surrounds the core engine and a fan nacelle is mounted at least partially around the core nacelle to define a fan bypass flow path for a bypass airflow. A fan section disposed within the fan nacelle is driven by the turbine section of the core engine through a geared architecture. An engine pylon supports the core nacelle and the fan nacelle. A towershaft is driven by the shaft of the core engine and drives a generator mounted within the core nacelle. The generator powers an electric motor mounted within the engine pylon. The electric motor drives a plurality of accessory components that are also mounted within the engine pylon.