Abstract: A turbofan engine (20) has a fan shaft (120) coupling a fan drive gear system (60) to the fan (28). A low spool comprises a low pressure turbine (50) and a low shaft (56) coupling the low pressure turbine to the fan drive gear system. A core spool comprises a high pressure turbine (46), a compressor (44), and a core shaft (52) coupling the high pressure turbine to the core spool compressor. A first bearing (150) engages the fan shaft, the first bearing being a thrust bearing. A second bearing (160) engages the fan shaft on an opposite side of the fan drive gear system from the first bearing, the second bearing being a roller bearing. A third bearing (180) engages the low spool shaft and the fan shaft.

Abstract: A wind turbine blade bearing with a fixed ring fixed to a hub of the wind turbine and a moving ring whereto the blade is fixed by corresponding fixing elements; the bearing making it possible to avoid the collision of the blade with the wind turbine tower by providing a separation therebetween via the disposal of the blades at an angle with respect to the wind turbine hub; where the angle is given by the bearing of the blade pitch change system. The separation is achieved since a rear face of the moving ring is in contact with the blade so that a plane defined by the rear face is perpendicular to the longitudinal direction of the blade, the rear face not being perpendicular to the axis of rotation of the bearing.

Abstract: A method of immobilizing a low pressure spool assembly including maintaining a body of the locking tool in the annular gas path, attaching a securing portion of the body across an aperture defined through an annular wall delimiting the gas path; positioning a stop connected to the body of the locking tool into a rotary path of a given one of the sets of blades of the low pressure spool assembly; and rotating the high pressure spool assembly thereby biasing a blade of the given set of blades of the low pressure spool assembly against the stop, thereby immobilizing the low pressure spool assembly. A locking tool and a method of performing engine maintenance are also provided.

Abstract: A turbine is operably connected to drive a compressor, and to drive a fan through a gear drive. A number of intermediate gears connecting an output shaft of the turbine to a fan drive shaft for the fan. An oil channel collects oil thrown outwardly of the gear drive. A bearing support mounts bearings supporting the fan drive shaft. The oil channel and the bearing support each include mating faces that are bolted together by a plurality of bolts. The bolts extend through oil channel holes in the mating face of the oil channel. The oil channel holes have one dimension which closely receives the bolts and another dimension which is larger than an outer diameter of the extending portion of the bolts, such that the bolts may adjust radially within the oil channel holes.

Abstract: A reaction-type turbine according to the present invention is configured in that a portion of a rotary shaft module which penetrates through a side with an inlet portion of a housing has a diameter larger than the diameters of other portions. Thus, the pressurized area in which a working fluid applies pressure to a rotary shaft in the direction opposite to the working fluid flow direction increases, thus increasing force in the direction opposite to the working fluid flow direction. As a result, axial direction force applied to the rotary shaft in the working fluid flow direction may be reduced. Therefore, the reaction-type turbine of the present invention has the advantages of eliminating the necessity of installing a separate thrust bearing for supporting axial force in the working fluid flow direction.

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 an inner shaft extending axially along the gas turbine engine, a plurality of disks extending radially inwardly and toward the inner shaft, at least one hole in at least one of the plurality of disks, and an obstruction positioned between the inner shaft and an end of the disk having the at least one hole, such that a bore flow that flows along an axial length of the inner shaft is obstructed from flowing along the shaft by the obstruction, and forced to flow radially outward from the obstruction, through the at least one hole, and radially inward toward the inner shaft.

Abstract: A lubricating and cooling epicyclic stepdown gearing, for example in an aeroengine turbomachine, including a cylindrical casing mounted on a planet-carrier of the gearing and forming a centrifugal scoop surrounding stationary oil-delivery strips, the cylindrical casing including radial ducts feeding nozzles pointing towards zones where the planet gears mesh with outer ring(s) of the gearing.

Abstract: In at least some implementations, a fluid pump includes a drive shaft including at least one drive surface and a pumping element. The pumping element includes an opening in which a portion of the drive shaft is received so that the pumping element is driven for rotation by the drive shaft, and the opening is larger than the drive shaft to provide a clearance between the pumping element and at least part of the drive shaft. The pumping element also includes at least one engagement surface arranged to be engaged by the drive surface of the drive shaft when the drive shaft is rotated where one or both of the drive surface and the engagement surface are angled to provide a surface area of engagement between the drive surface and engagement surface that is at least 1% of the surface area of the drive surface.

Abstract: A mechanical drive system of an aircraft gas turbine engine includes a tower shaft operatively connected to first and second shafts in an accessory drive gearbox. The first shaft rotates at a rotational speed lower than the rotational speed of the tower shaft and the second shaft rotates at a rotational speed equal to or higher than the rotational speed of the tower shaft.

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: 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 gas turbine engine includes a fan section including a fan that is rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A bypass ratio is greater than about 11.0.

Abstract: A compound star gear system includes a sun gear rotatable about a first axis that drives a first plurality of star gears rotatable about a plurality of fixed axes. The first plurality of star gears drives a second plurality of star gears spaced axially apart from the first plurality of star gears. The second plurality of star gears drive the ring gear that in turn drives a fan drive shaft.

Abstract: A propulsion device is disclosed which is capable of lifting and/or propelling a person or an aircraft, such as a helicopter or airplane, through the air.

Abstract: A support assembly for a geared architecture includes an engine static structure. A flex support is secured to the engine static structure and includes a bellow. A support structure is operatively secured to the flex support. A geared architecture is mounted to the support structure. First members are removably secured to one of the engine static structure and the flex support and second members are removably secured to the support structure. The first and second members are circumferentially aligned with one another and spaced apart from one another during a normal operating condition. The first and second members are configured to be engageable with one another during an extreme event to limit axial movement of the geared architecture relative to the engine static structure.

Abstract: A gas turbine engine includes a housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. A shaft provides a rotational axis. A hub is operatively supported by the shaft. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively.

Abstract: A gas turbine engine includes a fan section including a fan that is rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A bypass ratio is greater than about 11.0.

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

Abstract: The present invention is a controller specifically for pumps, making the benefits of variable frequency drive (VFD) technology more accessible to pump users. The present invention incorporates pump-specific system optimization software, an industrial grade drive, and a menu-driven user interface, offering protection, reliability, and ease of use not possible with other variable frequency drives.

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 adjusting device for adjusting the rotation angle position of the rotor of a wind energy system should be improved by the invention, whereby a complicated processing of the brake disc previously used for engagement of the drive is no longer necessary, and whereby said brake disc can be flexibly arranged in an area with sufficient construction space. For this purpose, the adjusting device has at least one force transducer wheel and/or a force transducing disc which is mounted or can be mounted on a shaft (1) of the drive train which is switched downstream from the rotor, which is structured for engagement of a force transmitting means, and is designed as an independent component. The device also has a drive means for producing a drive force, and at least one force transmission means for transmitting the drive force to the force transducer wheel and/or the force transducing disc.

Abstract: A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor, with the overall pressure ratio being greater than or equal to about 35. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. A bypass ratio, which is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section, is greater than or equal to about 8.

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 axis and a speed reduction device in communication with the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A fan blade tip speed of the fan is less than 1400 fps.

Abstract: The invention concerns a pump turbine plant, comprising a turbine with a turbine impeller as well as a turbine spiral housing; a pump with a pump impeller as well as a pump spiral housing; an electrical machine, which is in a drive connection with the shaft or can be brought into said connection; a hydraulic short-circuit can be created between turbine and pump. The invention is characterised by the following features: the turbine has a higher rated power than the pump.

Abstract: A turbo-compressor train and a method for assembling a turbo-compressor train. The train includes a gas turbine engine configured to transform thermal energy into mechanical energy; a centrifugal compressor having a shaft connected to a shaft of the gas turbine engine; and a single lube pump configured to provide synthetic oil to the gas turbine engine and the centrifugal compressor. The gas turbine engine, the centrifugal compressor and the single lube pump each has only rolling bearings.

Abstract: An aircraft engine having a fan or propeller stage mounted to a planetary gearing system through a planetary gearing output drive shaft is provided with a lubricant system having a seal with lubricant delivery chamber for receiving a lubricant and a sealing surface sealing against a rotatable shaft, the rotatable shaft has a hollow interior and an opening in registration with the delivery chamber. The lubricant system has a lubricant pump in fluidical communication with and downstream of the opening.

Abstract: A gas turbine engine includes a flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system.

Abstract: A turbine engine comprises compressor and turbine sections. An epicyclic gear train includes a carrier, a sun gear and intermediate gears arranged about and intermeshing with the sun gear. The intermediate gears are supported by the carrier. A baffle includes a lubrication passage near at least one of the sun gear and intermediate gears for directing a lubricant on at least one of the sun gear and intermediate gears. A method of designing a turbine engine is also disclosed.

Abstract: A counter rotating helico-axial pump is provided, the pump comprising: (a) an inner rotor comprising a plurality of outwardly extending helico-axial impeller vanes; (b) a hollow outer rotor comprising a plurality of inwardly extending helico-axial impeller vanes; (c) a single driving device configured to drive the inner rotor or the hollow outer rotor; and (d) a force transmission coupling joining the inner rotor and the hollow outer rotor and configured to permit rotation of the inner rotor and hollow outer rotor in opposite directions; wherein at least a portion of the inner rotor is disposed within the hollow outer rotor, and wherein the inner rotor, the hollow outer rotor and the helico-axial impeller vanes define a fluid flow path, and wherein the inner rotor and hollow outer rotor are configured such that at least some of adjacent helico-axial impeller vanes are configured to rotate in opposite directions.

Abstract: Disclosed is a micro gas turbine having a compact structure. The micro gas turbine includes a turbine wheel, a tie shaft connected, at one end thereof, to the turbine wheel, a compressor wheel spaced from the turbine wheel and mounted to the tie shaft, a thrust rotor spaced from the compressor wheel and fixed to an end of the tie shaft, a thrust collar provided on a portion of an outer surface of the thrust rotor, and a sub journal bearing provided between the thrust collar and the compressor wheel.

Abstract: A method for servicing a gas turbine engine includes disassembling a bearing compartment, providing access from a forward side of the gas turbine engine to a gearbox contained within said bearing compartment. The gas turbine engine provides a core flow path that extends from the forward side aftward in a core flow direction. The method includes servicing a component located within the bearing compartment. A method for servicing a gas turbine engine includes providing access from a forward side of a front center body assembly, and servicing a component located within a bearing compartment aft of the front center body assembly. The gas turbine engine includes a seal package located aft of a bearing package. A front wall is mounted to the front center body support and is removable from a front center body support to access at least one of the gearbox, the bearing package and the seal package.

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

Abstract: An energy recovery apparatus includes a fixed frame, a shaft, an impeller vane, and an energy transfer unit. A fluid stream exits the host device along a flow axis. The fixed frame defining a longitudinal axis mounts the host device. The shaft is rotatably mounted to the fixed frame parallel to the longitudinal axis. The impeller vane is connected to the shaft to cause rotation when the fluid stream of the host device strikes the impeller vane. The energy transfer unit is linked to the shaft to transfer energy from the energy recovery apparatus when the shaft rotates thereby recovering energy from the fluid stream. A geologic heat exchange system includes at least one conduit in thermal contact with the geologic environment. A coolant distribution system is in fluid communication with the conduit such that heat exchange with the geologic environment occurs.

Abstract: A gas turbine engine includes a very high speed low-pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for a higher pressure turbine is at a ratio between about 0.5 and about 1.5. In addition, the lower pressure turbine is mounted with a first bearing mounted in a mid-turbine frame, and a second bearing mounted within a turbine exhaust case.

Abstract: A vehicle transmission consisting of two or more fixed displacement hydraulic pumps mounted on a common shaft (input) which provide the fluid to drive one or more fixed displacement hydraulic motors on a second common shaft (output) and a means of selectively activating and deactivating the pumps and motors to change the rotational speed of the second shaft with respect to the first shaft. The two shafts are connected by a selectable one way clutch to allow the hydraulic elements to be bypassed under certain operating conditions. Variations include the use of a reduction gear driving the input shaft and a two or more speed mechanical transmission on the output shaft. A hydraulic reservoir and accumulator are provided for energy storage and to accomplish instantaneous torque control. When used to provide hydraulic regenerative braking, the roles of pumps and motors are reversed.

Abstract: A micro gas turbine has a compressor and a turbine, the rotors of which are arranged on a common driveshaft. The aim of the described system is to provide a lightweight and inexpensive micro gas turbine. This is achieved in that the driveshaft is mounted using at least two rolling bearings, one of which is arranged in the vicinity of the compressor rotor and one of which is arranged in the vicinity of the turbine rotor. The drive shaft is designed in a hollow manner, the inner hollow space of the driveshaft being filled with an evaporable coolant.

Abstract: A mixed flow fan assembly uses induced reverse ambient air flow through the in-line motor enclosure for motor cooling, motor segregation from primary exhaust contamination, and augmentation of volumetric flow rate. Induced ambient airflow through openings in and/or around the base of the fan housing balances low pressure around the fan wheel and the inlet cone to inhibit primary exhaust recirculation and increase volumetric flow rate. Straightening vanes downstream of the fan wheel are used to axially reorient radial and tangential velocity components of primary effluent flow. Airfoil impeller blades have a scalloped and/or perforated single-thickness trailing edge to attenuate fan noise.

Abstract: A turbomachine for use as a compressor has a tubular housing centered on an axis, a rotor at least generally centered on the axis in the housing, and bearings supporting the rotor in the housing for rotation about the axis. The rotor is formed by a small-diameter shaft extending along and centered on the axis, formed with at least one mounting collar, and carried by the bearings, and by a plurality of annular disks fitted axially together and formed with radially outwardly extending vanes. At least one of the disks is fitted with and secured to the mounting collar.

Abstract: An automatic transmission pump assembly includes a torque converter housing and pinion that rotate about a first axis, an idler engaged with the pinion, a gear engaged with the idler, shaft secured to the gear, and a pump rotor secured to the shaft and that rotates about a second axis offset from the first axis.

Abstract: A wind turbine electrical generator can provide wind powered portable or stationary electrical power at a user site or application without the need of utility services. The wind turbine electrical generator incorporates tunneling and multiplying available wind via funneling to produce more power at a wind turbine driven generator. The generator is portable and is mounted on a utility size trailer frame suitable for permanent anchoring or can moved about as needed. The generator is complete, needing only an electrical connection to the user's intended application.

Abstract: An exemplary turbine engine assembly includes a first shaft that is rotatably driven by a second shaft of a gas turbine engine, a compressor hub driven by the second shaft, the compressor hub within a compressor section of the gas turbine engine, an epicyclic gear train that is driven by the first shaft, and a common attachment point that secures the first shaft and the compressor hub to the second shaft.

Abstract: Method and gas turbine system having a reduced footprint. The gas turbine system includes a gas turbine configured to produce energy and having a gas turbine shaft; an auxiliary equipment attached to the gas turbine; an overhung shaft of the auxiliary equipment being configured to be attached to the gas turbine shaft; a flexible joint configured to be provided between the shaft of the auxiliary equipment and the gas turbine shaft; and a bearing system having at least two bearing units provided at a first end of the shaft of the auxiliary equipment next to the flexible joint. A second end of the shaft of the auxiliary equipment is free of bearings.

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 axis and a speed reduction device in communication with the fan. The speed reduction device includes a planetary fan drive gear system with a planet gear ratio of at least 2.5. A fan blade tip speed of the fan is less than 1400 fps.

Abstract: A gas turbine engine includes a compressor having first annular connection structure at a forward end portion of an air inlet housing of the compressor. The gas turbine engine may also include intake ducting having second annular connection structure adjacent a central passage of the intake ducting. The first annular connection structure and the second annular connection structure may form at least part of an interface between the air inlet housing and the intake ducting during operation of the gas turbine engine. The first and second annular connection structures may have shapes allowing the first annular connection structure to be moved through and beyond the second annular connection structure in a forward direction, the forward direction being opposite a direction of compressed air flow in the compressor during operation.

Abstract: The invention relates to a pump, in particular a centrifugal pump (1), with a pump housing (2), wherein a motor shaft (5), which is connected to a pump impeller (6) arranged in the pump housing (2), extends through a shaft passage (4) in a rear wall (3) of the pump housing (2) and is mounted in the rear wall (3) by means a mechanical seal arrangement (8). In order to ensure a high accuracy of fit of a seal seat even over a long service life, the seal seat (9) of the mechanical seal arrangement (8) is formed in a ring-shaped protector (10) that is made from a corrosion-resistant material and is fixedly arranged in the shaft passage (4) of the rear wall (3).

Abstract: A vacuum pump has a rotor mounted on a rotor shaft and provided with pump active components cooperating with opposite stationary pump active components, fastening element for securing the rotor on the rotor shaft, and a safety element provided in addition to the fastening element for preventing rotation of the rotor and the rotor shaft relative to each other.

Abstract: An isothermal turbo-compressor-condenser-expander arrangement includes heat-transferring blades that are mounted on, or surround, individual conduits to promote air exchange and heat transfer. In operation, the open framework rotates in free air to promote heat exchange. The assembly includes a first plurality of spokes extending radially outwardly from a first central hub to an outer perimeter with first radial conduits that transport refrigerant under centrifugal force and compression from the hub to the outer perimeter. The first radial conduits include heat exchanging blades. A second plurality of spokes extend radially outwardly from a second central hub that each includes a second thermally-insulated conduit that transports refrigerant from the outer perimeter to the second central hub. Axial conduits extend axially at the outer perimeter. At least some of the axial conduits include an axial blade in thermal communication with the conduit that promotes heat exchange radially.

Abstract: In a water pump, a reinforcement rib is integrally installed on either an outer surface or an inner surface of a flange wall of a pulley and radially extended toward an outer direction from a center side at which one end section of a drive shaft is coupled.

Abstract: A turbine engine case defines a centerline and a gaspath within the engine case. A fan is coupled to a fan shaft. A transmission couples the shaft to the fan shaft to drive the fan and comprises a gear system. A gutter system is positioned to capture lubricating fluid slung from the gear system. The gutter system includes a gutter extending partially circumferentially about the centerline having a first circumferential end edge. An inlet channel has an inlet at the gutter first circumferential end edge and locally radially outboard of the gutter. At least one vane is spaced apart from the gutter first circumferential end edge.