Abstract: A turbomachine engine can include a fan assembly, a pitch change mechanism, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The pitch change mechanism can be coupled to the fan assembly. The vane assembly can include a plurality of vanes. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.

Abstract: A method of assembling a gear system for a gas turbine engine according to an example of the present disclosure includes the steps of providing a unitary carrier, positioning baffles between side walls of the carrier such that an end of each of the baffles abuts a respective mount of the carrier, inserting intermediate gears through a central opening of the carrier, and then moving the intermediate gears radially outwardly into respective gear pockets of the carrier, inserting a sun gear through the central opening, moving the intermediate gears radially inwardly to engage the sun gear, coupling a shaft to the carrier, including attaching a torque frame to the carrier such that the torque frame interconnects the carrier and the shaft, placing first and second ring gear halves of a ring gear onto an outer periphery of the intermediate gears, and fixedly attaching the ring gear to an engine static structure. A gear system is also disclosed.

Abstract: A turbomachine engine can include an unducted fan assembly, an unducted vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The unducted fan assembly can include a plurality of fan blades. The unducted vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the unducted fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.

Abstract: A turbomachine engine can include a fan assembly, a pitch change mechanism, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The pitch change mechanism can be coupled to the fan assembly. The vane assembly can include a plurality of vanes. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.

Abstract: The present disclosure relates to a geared gas turbine engine for an aircraft. Example embodiments include a gas turbine engine for an aircraft including: an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan having a plurality of fan blades; and a gearbox that receives an input from the core shaft to drive the fan at a lower rotational speed than the core shaft, the gearbox having a gear ratio of around 3.4 or higher, wherein the gas turbine engine is configured such that a jet velocity ratio between a first jet velocity exiting from a bypass duct of the engine and a second jet velocity exiting from an exhaust nozzle of the engine core is within a range from around 0.75 to around 0.82.

Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.

Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.

Abstract: Systems and generating power in an organic Rankine cycle (ORC) operation to supply electrical power. In embodiments, an inlet temperature of a flow of gas from a source to an ORC unit may be determined. The source may connect to a main pipeline. The main pipeline may connect to a supply pipeline. The supply pipeline may connect to the ORC unit thereby to allow gas to flow from the source to the ORC unit. Heat from the flow of gas may cause the ORC unit to generate electrical power. The outlet temperature of the flow of the gas from the ORC unit to a return pipe may be determined. A bypass valve, positioned on a bypass pipeline connecting the supply pipeline to the return pipeline, may be adjusted to a position sufficient to maintain temperature of the flow of gas above a threshold based on the inlet and outlet temperature.

Abstract: A ring gear for an epicyclic or planetary reduction gear of a turbomachine, in particular of an aircraft, said ring gear extending about an axis X and comprising first and second coaxial annular elements and comprising, respectively, two inner annular toothing sets of different orientation, each of said toothing sets having a pitch diameter and a median plane substantially perpendicular to said axis and with an intersection point designated Y in an axial cross-section of the ring gear, said first and second annular elements further comprising, respectively, first and second radially outer annular flanges for attaching said first and second elements to each other, wherein each of said first and second flanges comprises a peripheral portion extending in a plane that is angled with respect to said axis X and that passes substantially through said intersection point Y.

Abstract: A fan drive gear system for a turbofan engine includes a geared architecture and a gear controller supporting the geared architecture and controlling rotation of the geared architecture relative a static structure.

Abstract: A gas turbine engine for an aircraft and a method of operating a gas turbine engine on an aircraft. Embodiments disclosed include a gas turbine engine for an aircraft including: an engine core has a turbine, a compressor, and a core shaft; a fan located upstream of the engine core, the fan has a plurality of fan blades; a nacelle surrounding the engine core and defining a bypass duct and bypass exhaust nozzle; and a gearbox that receives an input from the core shaft and outputs drive to the fan wherein the gas turbine engine is configured such that a jet velocity ratio of a first jet velocity exiting from the bypass exhaust nozzle to a second jet velocity exiting from an exhaust nozzle of the engine core at idle conditions is greater by a factor of 2 or more than the jet velocity ratio at maximum take-off conditions.

Abstract: A fuel oxygen conversion unit includes a stripping gas flowpath for a vehicle or an engine of the vehicle. The fuel oxygen conversion unit includes a stripping gas boost pump positioned in airflow communication with the stripping gas flowpath for increasing a pressure of a flow of stripping gas through the stripping gas flowpath; a contactor defining a stripping gas inlet in airflow communication with the stripping gas flowpath, a liquid fuel inlet, and a fuel/gas mixture outlet; a fuel gas separator defining a fuel/gas mixture inlet in fluid communication with the fuel/gas mixture outlet of the contactor, a stripping gas outlet, and a liquid fuel outlet; and a connection assembly mechanically coupling the stripping gas boost pump to the fuel gas separator, the connection assembly having a speed change mechanism such that the stripping gas boost pump rotates at a different rotational speed than the fuel gas separator.

Abstract: The present disclosure relates to a geared gas turbine engine for an aircraft. Example embodiments include a gas turbine engine for an aircraft including: an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan having a plurality of fan blades; and a gearbox that receives an input from the core shaft to drive the fan at a lower rotational speed than the core shaft, the gearbox having a gear ratio of around 3.4 or higher, wherein the gas turbine engine is configured such that a jet velocity ratio between a first jet velocity exiting from a bypass duct of the engine and a second jet velocity exiting from an exhaust nozzle of the engine core is within a range from around 0.75 to around 0.82.

Abstract: A gas turbine engine includes a non-rotatable flexible coupling having Stiffnesses A, B, C, D and E, which are defined herein, and at least ratio of a frame lateral stiffness FLS as follows: FLS/Stiffness A in a range of about 6.0 to about 25.0, FLS/Stiffness B in a range of about 10.0 to about 40.0, FLS/Stiffness C in a range of about 1.5 to about 7.0, FLS/Stiffness D in a range of about 0.25 to about 0.50, or FLS/Stiffness E in a range of about 6.0 to about 40.0.

Abstract: A nacelle component for a nacelle of a wind turbine, comprising a mainframe module and a power electronics module. The mainframe module and the power electronics module in each case have a length greater than a width. In the assembled state of the nacelle component, the mainframe module is oriented with its longitudinal axis parallel to a vertical plane which extends through the axis of a rotor shaft. The longitudinal axis of the power electronics module intersects the vertical plane which extends through the axis of the rotor shaft. A method for mounting such a nacelle component is also disclosed.

Abstract: A geared gas turbine engine for an aircraft includes: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan including a plurality of fan blades; and a gearbox that receives an input from the core shaft to drive the fan at a lower rotational speed than the core shaft, the gearbox having a gear ratio of around 3.6 or lower, wherein the gas turbine engine is configured such that a jet velocity ratio between a first jet velocity exiting from a bypass duct of the engine and a second jet velocity exiting from an exhaust nozzle of the engine core is within a range from around 1 to around 1.3 at cruise conditions.

Abstract: A power extraction system for a gas turbine engine may comprise a high spool transmission, a low spool transmission, and an accessory gearbox. The accessory gearbox may comprise a starter-generator, a low spool starter-generator gear, a high spool gear, and a clutch configured to selectively engage and disengage the low spool starter-generator gear and the high spool gear. The low spool starter-generator gear may be configured to transfer torque between the starter-generator and the low spool transmission for accessory power generation. The high spool gear may be configured to transfer torque to the high spool transmission for engine starting. The clutch may be controlled by a variable transmission and may allow accessories to be driven by the low spool after starting.

Abstract: Device for generating energy making use of the current of a river (2), with a self-floating paddlewheel (13) and an electric generator set (17) that is coupled to the paddlewheel (13), whereby the device (1) is provided with an immersed housing (3) with an open bottom (4) in which the paddlewheel (13) is rotatably affixed and whereby there is a unit (10) to control the flow of the river (2) at the level of the paddlewheel (13), whereby the speed of the generator set (17) is kept constant by controlling the water level (9) in the housing (3) by placing its internal space (7) under pressure and/or by controlling the aforementioned unit (10).

Abstract: An integral transmission for a transmission turbomachine has two gearwheels which are in mesh with a large wheel and which are each connected to a shaft that can be connected to an input and/or output unit. A housing, in which the gearwheels or the shafts connected thereto are supported and at least two partial housing units which can be connected by a main joint that extends through the support region of at least one gearwheel in mesh at least indirectly with the large wheel or of the shaft connected to the gearwheel. Accordingly, one of the two partial housing units is formed from at least three housing parts including a central housing part, which is assigned to the large wheel, and two side housing parts. The central housing part can be connected to an individual side housing part by a joint aligned at an angle to the main joint.

Abstract: A fan drive gear system for a turbofan engine includes a geared architecture and a gear controller supporting the geared architecture and controlling rotation of the geared architecture relative a static structure.

Abstract: An equipment support including at least one attachment including an output shaft, an input gear wheel, the input gear wheel being both rotated by the motor shaft at a main speed and also connected to the output shaft of the attachment in order to rotate it at a determined output speed, an input shaft, rotated by the input gear wheel at a determined input speed, and a reducer with magnetic gears, arranged between the input shaft and the output shaft, such that the input speed is different from the output speed.

Abstract: This compressor system is provided with: a driving machine having a rotary-driven first output shaft and a second shaft that is rotary driven so as to reach the same speed as the first output shaft; a working-fluid-compressing first compressor to which the rotation of the first output shaft is transmitted; a working-fluid-compressing second compressor to which the rotation of the second output shaft is transmitted; a variable-speed step-up gear for increasing the speed of the first output shaft and transmitting the increased speed to the first compressor, said step-up gear being capable of varying the increased speed; and a constant-speed step-up gear for increasing the speed of the second output shaft and transmitting the increased speed to the second compressor, said step-up gear keeping the increased speed constant.

Abstract: What is described is an aircraft engine with a compressor device and with a fan device. In the area of a compressor shaft, the compressor device is connected via an epicyclic gear to a fan shaft. A planetary web is operatively connected via bearing devices to the planetary gears. A ring gear is coupled with the fan shaft and a sun gear of the epicyclic gear is coupled with the compressor shaft, while the planetary carrier is held at the housing side in a torque-proof manner. The ring gear is connected via a flexible connection device to the fan shaft and/or the planetary carrier is connected via a flexible connection device to the housing. In the area of the connection device, movements between the ring gear and the planetary gears and/or between the planetary carrier and the housing can be at least approximately compensated in the radial and the axial direction.

Abstract: An ocean wave-crest powered electrical generator comprises a buoyant vessel anchored to the sea floor by mooring chains. The vessel defines a substantial opening at the bow leading to a paddle wheel such that ocean wave crests flow past the paddle wheel while passing through the generator thereby capturing the power of the continuous wave crests passing through the bow opening. The paddle wheel transforms energy from the breaking wave crests into kinetic energy that in turn activates an electric power generator. The wave crest electrical generator is permanently moored near the beach and allowed to rise and fall with the tide thus allowing for a continuous flow of ocean waves to be converted into power. Pumped storage provides a sustained flow of energy that is easy to regulate and this can be accomplished in combination with “energetic marinas” by constructing a reservoir on top of a near-by cliff, hill or tall building.

Abstract: A gearbox mounting link between a gas turbine engine structure and a gearbox mounting location comprises an engine attachment piece rotatably secured to the gas turbine engine structure. The engine attachment piece comprises first and second plates extending in parallel planes and separated by a gap having a gap width. A gearbox attachment piece is situated between the parallel plates, and is secured to the gearbox. A breakable primary retention fastener extends snugly through the parallel plates and the gearbox attachment piece, thereby rigidly retaining the gearbox with respect to the gas turbine engine in two degrees of freedom so long as the breakable primary retention fastener remains intact. A durable secondary retention fastener extending snugly through the parallel plates, and extends with clearance through the gearbox attachment piece via an oversized fastener passage, thereby constraining the gearbox attachment piece in the event that the breakable primary retention fastener breaks.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an engine axis with a plurality of fan blades rotatable about a fan blade axis. A geared architecture is in communication with the fan and driven by a turbine section. The fan rotates at a first speed and the turbine section rotates at a second speed different from the first speed and a fixed area fan nozzle in communication with the fan section.

Abstract: An aircraft (1) having a rotary wing (2) and turboshaft engines (11, 12, 13) for driving said rotary wing (2). The aircraft then includes two main engines (11, 12) that are identical, each capable of operating at at least one specific rating associated with a main power (maxTOP, OEIcont), and a secondary engine (13) capable of operating at at least one specific rating by delivering secondary power (maxTOP?, OEIcont?) proportional to the corresponding main power (maxTOP, OEIcont) in application of a coefficient of proportionality (k) less than or equal to 0.5, said aircraft having a control system (20) for driving the rotary wing by causing each main engine (11, 12) to operate continuously throughout a flight, and by using the secondary engine (13) as a supplement during at least one predetermined specific stage of flight.

Abstract: The invention relates to a device comprising at least one vertical pump (3) and at least one associated turbine (4) for transporting, over a level difference, a heat-transfer fluid brought to a high temperature, wherein the device further comprises a device for mechanically coupling the turbine (4) with the pump (3), comprising a gearbox (21) with a gimbal coupling (41) located on the turbine (4) side, allowing the mechanical energy produced by the turbine (4) to be reused to actuate the pump (3).

Abstract: Methods of moving a rotating device of a wind turbine during transportation or standstill are provided. The methods include securing at least one auxiliary device to a position and connecting the device to one or more shafts of the rotating device at transportation or standstill. The auxiliary device is able to store, generate and/or convert energy during transportation, transferring energy continuously from at least one auxiliary device to one or more shafts of the rotating device during transportation or standstill, and moving one or more shafts of the rotating device continuously or discontinuously from a position to another. Also provided is a nacelle for a wind turbine, an auxiliary device, a control system for controlling moving of a rotating device of a wind turbine nacelle during transportation of the nacelle and use thereof.

Abstract: A supercharger transmission includes a first chamber having timing gears operatively disposed therein. A second chamber has transmission gears operatively disposed therein. An oil fill level is defined in the second chamber. A bearing retention wall is disposed between the first chamber and the second chamber. The bearing retention wall includes a return port to allow fluid communication between the first chamber and the second chamber. The return port is an aperture defined in the bearing retention wall below the oil fill level. The bearing retention wall also includes a crosstalk port to allow fluid communication between the first chamber and the second chamber. The crosstalk port is an aperture defined in the bearing retention wall above the oil fill level.

Abstract: A buffer air pump provides pressurized cooling air for cooling components of the gas turbine engine. The buffer air pump is supported on and/or within an accessory gearbox and draws bypass air in through an inlet manifold. An impeller supported within a scroll housing pressurizes the incoming bypass air and directs the pressurized air through passages to a component requiring cooling. The buffer air pump draws in relatively cool air from the bypass flow, pressurizes the air with the impeller and sends the air through conduits and passages within the gas turbine engine to the component that requires cooling such as a bearing assembly.

Abstract: An example turbomachine geared architecture support assembly includes a subpart having a more compliant portion and a less compliant portion. The less compliant portion includes a stop that limits axial movement of a geared architecture within a turbomachine.

Abstract: A fan includes a frame, rotor supported by this frame and having a central hub and a number of blades and a drive mechanism for rotatably driving the rotor, in addition to a ring to which the end zones of the blades are connected. The ring is assembled from two part-rings of the same form which each include a circular strip of sheet material, the free ends of which are mutually connected to form the outer surface of a truncated cone, and a third part-ring which mutually connects the inner edges of the first two part-rings. The end zones of the blades are connected to the third part-ring. The ring has a diameter of more than about 1.50 m. The number of blades amounts to at least eight. The blades are hollow and include a framework structure which is provided with a skin connected thereto.

Abstract: A gas turbine engine includes a fan, a speed reduction device driving the fan and a lubrication system for lubricating components across a rotation gap. The lubrication system includes a lubricant input. A stationary first bearing receives lubricant from the lubricant input and has a first race in which lubricant flows and a second race. A second bearing for rotation is within the first bearing including a first opening in registration with the first race such that lubricant may flow from the first race through the first opening into a first conduit. There is a rotating carrier for supporting at least one planetary gear. The second bearing extends from the rotating carrier about an axis. A first spray bar is disposed on the carrier. The second bearing has a second opening in registration with the second race and a second conduit for passing lubricant to the spray bar.

Abstract: A gas turbine engine comprises a fan, a compressor, a combustor, and a fan drive turbine rotor. The fan drive turbine drives the fan through a gear reduction. The gear reduction includes at least two double helical gears in meshed engagement. Each of the at least two double helical gears are disposed to rotate about respective axes, and each have a first plurality of gear teeth axially spaced from a second plurality of gear teeth by a spacer. Each of the first plurality of gear teeth has a first end facing the spacer and each of the second plurality of gear teeth has a first end facing the spacer. Each first end of the first plurality of gear teeth is circumferentially offset from each first end of the second plurality of gear teeth. A method is also disclosed.

Abstract: A fan drive gear system for a gas turbine engine includes a torque frame and a journal bearing. The torque frame has an arm that extends therefrom, the journal bearing is mounted on the arm. When the fan drive gear system is in an unloaded condition an outer circumferential surface of the journal bearing is disposed at an angle so that it is non-parallel with respect to an axis of the arm. When the fan drive gear system is in a loaded condition the outer circumferential surface is disposed substantially parallel to the axis of the arm. In another aspect, the journal bearing includes a main body, a first wing, and a second wing. The first and second wings extend from the main body and are asymmetric with respect to one another.

Abstract: An example turbomachine thrust balancing system includes a member coupled in rotation with a turbine for transferring rotational power therefrom. A load carrying device rotatably supports the member. The load carrying device is configured to counteract substantially all of the thrust load generated by the turbine.

Abstract: A turbine engine assembly includes a turbine engine case, a gearbox and a plurality of mounts connecting the gearbox to the case. Each of the mounts includes a linkage and a fuse joint. The linkage extends towards the case substantially in a first direction. The fuse joint is configured to substantially prevent movement between the gearbox and the case when the fuse joint is subject to loading less than a threshold, and to permit a constrained movement between the gearbox and the case when the loading is greater than the threshold. The fuse joint of a first of the mounts has a different configuration than the fuse joint of a second of the mounts.

Abstract: The described embodiments relate generally to improving performance characteristics of a low profile fan. More specifically configurations having sloped fan blade edges are disclosed. By applying a gradual slope to each of the fan blades, performance of the fan can be increased without risking contact or rubbing between the fan blades and a fan housing. In some embodiments, the sloped fan blades can be configured to prevent contact when bearings of the fan include a certain amount of tilt play.

Abstract: A gear arrangement is disclosed herein. The gear arrangement includes a housing. The gear arrangement also includes a plurality of gears at least partially disposed in the housing and engaged with respect to one another. The gear arrangement also includes a support post mounted to the housing. The support post supports at least one of the gears. The support post has a first portion extending away from the housing and encircled by one of the gears. The support post also has a pin projecting away from the first portion. The first portion and the pin are eccentric to one another such that the first portion is centered on a first axis and the pin is centered on a second axis. The first and second axes are parallel to and spaced from one another. The gear arrangement also includes a plurality of pin apertures defined by the housing.

Abstract: A cranking pad assembly for a gearbox of a turbomachine including a cranking pad shaft rotatably secured in a gearbox housing and engageable with a gearbox drivetrain when urged inwardly into the gearbox housing. The cranking pad shaft includes an interface for a cranking tool. An interlock pin retains the cranking tool at the cranking pad shaft and a disconnect spring is operably connected to the gearbox housing to bias the cranking pad shaft outwardly from the gearbox housing.

Abstract: A turbine engine includes a fan section including a plurality of fan blades, a turbine section, and an epicyclic gear train coupled between the turbine section and the fan section for providing a speed reduction between turbine section and the fan section. The epicyclic gear train includes a plurality of intermediate gears. A carrier supports the plurality of intermediate gears. A sun gear meshes with the plurality of intermediate gears and a ring gear surrounding and meshing with the plurality of intermediate gears. The ring gear includes first and second portions that each have an inner periphery with teeth. The first and second portions of the ring gear have an outer circumferential surface opposite the teeth that provides a first thickness, a second thickness greater than the first thickness and axially inward from the first thickness, and a flange extending radially away from the axis. An epicyclic gear train for a turbine engine and method of designing an epicyclic gear train are also disclosed.

Abstract: Provided is a gear-driven turbo compressor capable of increasing a natural frequency of a shaft by shortening the length of an overhang from a radial bearing to a shaft end, reducing an effort of replacing lubricant and an environmental burden by greatly reducing the amount of the lubricant, and reducing the necessity for maintenance by reducing a problem of the radial bearing caused by depleted materials of the lubricant. The gear-driven turbo compressor includes: a gas bearing 32 which is in communication with a compressed gas compressed by an impeller 16 and rotatably supports both ends of a pinion shaft 13; and an inner gas seal 34 which is positioned between the gas bearing and a thrust collar, maintains the gas bearing to be compressed by the compressed gas, and prevents intrusion of lubricant for gears due to the compressed gas.

Abstract: A gas turbine engine includes a fan section. A turbine section is coupled to the fan section via a geared architecture. The geared architecture includes a torque frame and a flex support spaced apart from one another at a location. A gear train is supported by the torque frame. A viscous damper is provided between the torque frame and the flex support at the location.

Abstract: A run-of-the-river or ocean current turbine may comprise a hatch and a slanted block having protector ribs for directing water flow to a waterwheel. The hatch may be controlled by a plurality of Transgear™ gear assemblies for varying the amount of water flow to the waterwheel from extreme drought to flood conditions so that the waterwheel may turn at rated speeds and within a predetermined range. The Transgear gear assemblies may comprise an accumulator for accumulating a rough and a fine tuned waterwheel speed. The Transgear assemblies may comprise embodiments of power take-off switches for, for example, bi-directional or clockwise and counterclockwise waterwheel shaft rotation. The turbine may be aligned for top-feed, side-feed or bottom feed of water and may comprise a tail wing or first and second turbines facing in opposite directions to capture high and low tidal flow.

Abstract: A mechanical arrangement for an engine having two propeller stages, including: a first epicyclic gear stage including a sun gear, a planet gear, a planet carrier and an annulus, wherein the sun gear is driven by a shaft of the engine, the planet carrier is stationary and thereby permits static structure to be located there through, and the annulus outputs torque and/or drive; a second epicyclic gear stage including a second sun gear, a second planet gear, a second planet carrier and a second annulus, wherein the second sun gear is driven by the annulus of the first epicyclic gear stage and is annular to accommodate the static structure, the second planet carrier includes the output to one of the propeller stages and the second annulus includes the output to the other of the propeller stages; wherein the static structure provides mounting for static components on one or both sides of each epicyclic gear stage.

Abstract: A gas turbine engine includes a fan shaft and a support which supports the fan shaft. The support defines a support lateral stiffness. A gear system drives the fan shaft. A flexible support at least partially supports the gear system, and defines a flexible support lateral stiffness with respect to the support lateral stiffness. An input to the gear system defines an input lateral stiffness with respect to the support lateral stiffness. A method of designing a gas turbine engine is also disclosed.

Abstract: In one exemplary embodiment, a gas turbine engine includes a fan, a speed reduction device driving the fan, and a lubrication system for lubricating components across a rotation gap. The lubrication system includes a lubricant input. A stationary first bearing receives lubricant from the lubricant input and has a first race in which lubricant flows. A second bearing for rotation is within the first bearing. The second bearing has a first opening in registration with said first race such that lubricant may flow from the first race through the first opening into a first conduit. The first bearing also has a second race into which lubricant flows. The second bearing has a second opening in registration with the second race such that lubricant may flow from the second race through the second opening into a second conduit. The first and second conduits deliver lubricant to distinct locations.

Abstract: A gas turbine engine includes a fan section including a fan rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a planetary fan drive gear system with a planet gear ratio of at least 2.5. A bypass ratio is greater than about 11.0.

Abstract: A gear transmission having at least one gear wheel stage, wherein at least one of the gear wheels is fastened coaxially on a hollow shaft that is rotatably mounted in a transmission housing via at least two shaft bearings. An outside-radial stage offset is formed on the hollow shaft as a seat for a broad rim gear wheel that approaches the plant radially on the inside.