Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, and a gearbox. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can 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. A gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0.

Abstract: An assembly for an aircraft turbine engine, includes a fan, a speed reduction gear and an intermediate casing including an internal annular structure that houses an epicyclic gear train equipped with a planet carrier. The assembly includes a secondary retention device for the ring gear of the planet carrier, the device including: first projections that project radially inwards from the internal annular structure, each first projection having a recess that is open radially inwards, axially downwards and circumferentially in a first direction; and second projections that project radially outwards from the ring gear of the planet carrier and cooperate with the first projections in such a way that each second projection is partially accommodated in the recess of the first projection with which it is associated and downstream therefrom.

Abstract: In a strain wave gearing, in order to regulate axial-direction movement of an externally toothed gear thereof, first balls are directly interposed between a first annular end surface and a device housing, whereby the first annular end surface and the device housing are in rolling contact with one another. Similarly, second balls, are directly interposed between a second annular end surface and an output shaft, whereby the second annular end surface and the output shaft are in rolling contact with one another. No contact occurs other than rolling contact of contact portions. Additionally, pressure is applied in the axial direction to the portions that make rolling contact, and axial-direction rattling is eliminated, whereby axial-direction movement of the externally toothed gear is reliably suppressed, and generation of high thrust force is prevented.

Abstract: A fresh air module and an air conditioner are provided. The fresh air module has a housing and a fan assembly. The housing has a fresh air duct inside the housing. The fan assembly has a motor and a wind wheel disposed in the fresh air duct. The motor has a motor body and a motor shaft. The motor shaft drives the wind wheel to rotate, so as to guide airflow to flow through the fresh air duct. The motor cover is arranged on the housing and outside of the fresh air duct. A motor accommodating cavity is defined in the motor cover and accommodates the motor body. A partition member is formed between the motor accommodating cavity and the fresh air duct to separate the motor accommodating cavity from the fresh air duct. The motor shaft penetrates through the partition to connect with the wind wheel.

Abstract: Some embodiments are directed to a positive displacement pump having an eccentric piston, comprising a tube having a first end and a second end that is terminated by a cylinder secured to a delivery zone, the tube including an intake opening and a delivery opening, a drive shaft extending between the transmission zone and the tube, a piston arranged in the delivery zone and mounted in a sliding manner at the end of the shaft, being pressed against the cylinder by an elastic presser so as to prevent fluid displacement between the tube and the delivery zone when the pump is dry, and the elastic presser is provided to press the piston against the cylinder when the pump is running under load.

Abstract: A gas turbine engine includes a fan, a fan shaft coupled with the fan and arranged along an engine central axis, and a frame supporting the fan shaft. The frame defines a lateral frame stiffness (LFS). A non-rotatable flexible coupling and a rotatable flexible coupling support an epicyclic gear system. The couplings are subject to a Motion II of cantilever beam free end motion with respect to the engine central axis. The non-rotatable and the rotatable flexible couplings each have a stiffness of a common stiffness type under a common type of motion. The common stiffness type is a Stiffness B and the common type of motion is the Motion II. The Stiffness B of the rotatable flexible coupling is greater than the stiffness B of the non-rotatable flexible coupling, and a ratio of LFS/Stiffness B of the non-rotatable flexible coupling is in a range of 10-40.

Abstract: A main bearing unit for supporting the rotor shaft of a wind turbine, including a rolling bearing having an inner ring, an outer ring and a rolling element arrangement received between the outer and inner ring and a coupling arrangement which is designed to couple the rotor shaft to an output shaft of the wind turbine at least indirectly and so as to transmit torque. The rotor shaft is coupled to one of the outer and inner ring so as to transmit torque. The coupling arrangement is coupled so as to transmit torque to the one of the outer and inner ring as the rotor shaft.

Abstract: The present invention is directed to a molten metal pump comprising an elongated pumping chamber tube with a base end and an open top end. A shaft extends into the tube and rotates an impeller therein, the impeller rotates proximate the base end. The tube has a diameter at least 1.1 times the diameter of the impeller. The pumping chamber tube preferably has a length at least three times the height of the impeller. The base end includes an inlet and the top end includes a tangential outlet. Rotation of the impeller draws molten metal into the pumping chamber and creates a rotating equilibrium vortex that rises up the walls of the pumping chamber. The rotating vortex adjacent the top end exists the device cia the tangential outlet.

Abstract: An internal-combustion engine starting device includes a switch section, a motor section, a transmission mechanism section, and a pinion gear section, wherein the transmission mechanism section is configured of a planetary gear train including a pinion which is connected to the rotating shaft of the motor section, a plurality of planetary gears to which the rotation of the pinion is transmitted, and an internal gear which receives the rotation of the planetary gears; and of a machine casing in which is housed the planetary gear train, and wherein elastic bodies are each fitted between a protruding portion formed on the outer peripheral surface of the internal gear and a recessed portion in which to receive the protruding portion, and clearances are formed between the internal gear and the machine casing via the elastic bodies.

Abstract: In one exemplary embodiment, a center body support for a gas turbine engine includes a fan exit guide vane mounting ring and an outer annular wall. An aft flange extends radially outward from the outer annular wall. An inner annular wall is radially spaced from and structurally interconnected to the outer annular wall by a circumferential array of struts. A brace interconnects the aft flange to a forward portion of the outer annular wall. The aft flange includes inner and outer mounting features spaced radially apart from one another. The inner and outer mounting feature respectively receive first and second sets of fasteners. The forward portion extends in a radially outward direction from the outer annular wall. The forward portion includes a forward mounting feature that receives a third set of fasteners. The outer and forward mounting features are secured to the fan exit guide vane mounting ring respectively by the first and third sets of fasteners.

Abstract: An exhaust housing hub of a turbomachine, including a connecting wall and an inner channel wall, the connecting wall connecting the inner channel wall to inner attachment flanges, wherein a radial section of the connecting wall is curved and can be formed, as required, as a single component with the inner channel wall, the hub also including a series of ribs extending radially between the connecting wall and the inner channel wall.

Abstract: A component that is to be mounted so as to be rotatable about an axis of rotation and transmits torque along with a rotating partner includes a first serration that extends about the axis of rotation and is to mesh with the rotating partner which has an adequate second serration mating with the first serration. The first serration has a plurality of teeth which have tooth tips extending substantially in the direction of the axis of rotation and tooth valleys located between the tooth tips. The tooth tips of the first serration each have a meshing edge forming a first line, while the tooth valleys located between the teeth each define a second line. At least two adjacent second lines intersect at an imaginary point lying between the axis of rotation and the maximum circumference of the first serration, in the semicircular surface beyond the axis of rotation.

Abstract: A wind turbine rotor includes a number of blades (5) which are rotatably mounted about an axis of rotation and a number of blade supports (12) each supporting a respective blade (5). Each blade support includes a pair of legs (14) which are spaced apart along the axis of rotation. A pair of hub supports (62) support the legs (14), with the hub supports (62) also being spaced apart along the axis of rotation. The rotor further includes a pair of bearing systems (52), each bearing system being associated with one of the hub supports (62) and each bearing system rotatably supporting its associated hub support so as to allow its associated hub support to rotate about the axis of rotation. Each hub support allows the communication of forces between the blades (5), and each hub support includes at least a pair of radially extending walls (80).

Abstract: An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.

Abstract: A curvic coupling for rotational coupling is provided herein. The curvic coupling includes: plural teeth arranged in a circle and protruding from a circle plane extending in a radial direction and a circumferential direction, wherein a side surface of a tooth of the plural teeth is opposite to a side surface of another tooth of the plural teeth, and wherein the tooth is adjacent to the other tooth and is separated from the other tooth by a separating surface. The separating surface includes a flat surface lying in the circle plane, wherein the separating surface includes a central protrusion between the side surface of the tooth and the side surface of the other tooth, and wherein the protrusion protrudes from the circle plane.

Abstract: A turbine driving a planet gear and an epicyclic gear train and including a planet pinion cage and a ring driving two propellers in rotation, is connected to the planet gear through a flexible sleeve surrounding a turbine support shaft rather than through a support shaft itself to achieve a flexible assembly with a limit stop position in contact with the shaft to limit parasite internal forces applied to the epicyclic gear train without tolerating a loose assembly or breakage of the sleeve due to a condition of the limit stop after a clearance has been eliminated.

Abstract: A coupling includes a first element having an annular projection and a second element having an annular recess. Both the first element and the second element have a common axis. A radius of the annular projection varies circumferentially around the axis to thereby define a connection profile. The annular projection is removably accommodated within the annular recess to couple the first and second elements to one another.

Abstract: A fluid pump device, in particular for a medical application, is described having a compressible pump housing and rotor, as well as with a drive shaft which runs in a sleeve and on whose end the fluid pump is arranged. In order to utilize all possibilities of a space-saving arrangement of the respective pump housing of the rotor, which is compressible per se, and as the case a bearing arrangement, the mentioned elements are displaceable to one another in the axial direction compared to an operation position. In particular these elements may be end-configured by way of an axial movement of the drive shaft after the assembly.

Abstract: A coupling to attach an impeller of a compressor to a shaft of an electric motor. The coupling has a coupling body that is attached at a first of the ends thereof to the impeller and at the opposite second end, to the motor shaft. The coupling body has a deformable section between the first and second ends of the coupling body. The deformable section is configured such that under an unbalanced loading exerted against the coupling body upon a failure of the impeller, the deformable section will permanently deform without the ultimate strength of a material forming the coupling body being exceeded and prior to a permanent deformation of the shaft. In such manner, the electric motor is protected from damage upon a failure of the impeller.

Abstract: A gas turbine engine includes a central body support that provides an inner annular wall for a core flow path. The central body support includes a first mount feature. A geared architecture interconnects a spool and a fan rotatable about an axis. A flex support interconnects the geared architecture to the central body support. The flex support includes a second mount feature that cooperates with the first mount feature for transferring torque there between. A method of disassembling a front architecture of a gas turbine engine includes the steps of accessing forward-facing fasteners that secure a central body support to a flex support, wherein the flex support includes a geared architecture supported thereon, removing the fasteners, and decoupling first and second mount features respectively provided on the central body support and the flex support.

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 turbofan engine comprises an engine case. A gaspath extends through the engine case. A fan has a circumferential array of fan blades. A fan case encircles the fan blades radially outboard of the engine case. A plurality of fan case vanes extend aftward and outward from the engine case to the fan case. A forward frame comprises a plurality of vanes radially across the gaspath. A torque box couples the fan case vanes to the forward frame. A transmission couples a shaft to a fan shaft to drive the fan. A fan bearing assembly couples a stationary forward hub structure to the fan shaft.

Abstract: A wind turbine is described. The turbine includes a hub with one or more blades that rotatably mounted on a frame and operatively coupled to a shaft. The shaft is provided at least partially internally to the frame, and a center piece from which a plurality of spokes extends substantially radially is mounted on the shaft. The hub is provided with a plurality of circumferentially arranged axial protrusions. Flexible elements are arranged to connect the spokes to the protrusions.

Abstract: An ultra high bypass ratio turbofan engine includes a variable pitch fan, a low pressure turbine, a reduction gearbox, and a plurality of outlet guide vanes. The ultra high bypass ratio turbofan engine has a bypass ratio between about 18 and about 40. The variable pitch fan and the low pressure turbine are coupled together by the reduction gearbox. The reduction gearbox reduces the speed of the variable pitch fan relative to the low pressure turbine. The plurality of outlet guide vanes are spaced aft of the variable pitch fan and are axially swept. The variable pitch fan and the low pressure turbine are configured to generate a fan pressure ratio between about 1.15 and about 1.24.

Abstract: A gas turbine engine including high and low pressure shafts, an electromechanical device having a rotor and a stator coupled such that the rotor is rotatable with respect to the stator, the rotor having a device gear secured thereto, the device being secured to a support structure in a bearing housing forming part of a bearing assembly supporting a portion of the low pressure shaft extending in proximity of the high pressure shaft and of the shaft gear, and a coupling idle gear secured for rotation about a stationary gear support mounted in the bearing housing, the idle gear being in toothed engagement with the shaft gear and with the device gear. An electromechanical device assembly for a gas turbine engine and a method of operating an electromechanical device are also provided.

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 flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system.

Abstract: A compression system may include a compressor having first and second sides separated by a division wall, first and second shafts, and first and second radial bearings. The first and second shafts may be axially connected to each other at respective first ends via a rotor portion of an intermediate radial bearing. The rotor portion may include a plurality of laminations stacked between first and second plates fastened to each other. The first radial bearing may be disposed on a first side of the intermediate radial bearing and may be proximate a second end of the first shaft. The first radial bearing may be configured to support the first shaft. The second radial bearing may be disposed on a second side of the intermediate radial bearing and may be proximate a second end of the second shaft. The second radial bearing may be configured to support the second shaft.

Abstract: An example turbomachine geared architecture support assembly includes a subpart having a more compliant portion and a less compliant portion.

Abstract: A water pump for a vehicle, may include a first shaft fixed to a pulley to be rotated thereby, a second shaft fixed to an impeller for pumping, and clutch that is disposed between the first shaft and the second shaft to selectively connect the first and second shafts to transfer a rotation torque of the first shaft to the second shaft.

Abstract: A disclosed gear assembly support for a gas turbine engine includes a first portion configured for attachment to a case of the gas turbine engine and a second portion configured for supporting a gear assembly. The support further includes a snap portion defining a fit within the case. The snap portion includes a tunable feature for adjusting a fit within the case. A torque reacting portion of the support transfers torque from the second portion to the first portion separate from the snap portion and include separately tunable features fore adjusting the snap fit independent of the torque transfer portions.

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: Turbine engine (1), especially for aircraft, comprising a power gear box shaft (30), a turbine shaft (28), and a connecting part (38) of annular shape by which one end of the power gear box shaft (30) and one end of the turbine shaft (28) are connected in a rotationally fixed manner, the turbine engine also including a structural housing (3) and a guide bearing (44) for guiding the connecting part (38) relative to the housing (3), the guide bearing (44) being mounted between the connecting part (38) and the housing (3) and comprising an external ring (48) mounted on the housing (3), an internal ring (46) mounted on the connecting part (38) and at least one rolling element (50a, 50b) configured in order to enable the external ring (48) to roll around the internal ring (46), characterised in that the guide bearing (44) is configured in order to form a ball joint link (R) enabling a relative angular displacement of its external ring with respect to its internal ring.

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 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 power transmission system for increasing the rotational speed from a rotor of a wind turbine comprises a main shaft configured to be driven by the rotor, a support structure, and a gearbox. The support structure includes at least one bearing supporting the main shaft for rotation about the main axis, with no other degrees of freedom between the main shaft and support structure. The gearbox includes a gearbox housing rigidly coupled to the support structure and a gearbox input member coupled to the main shaft. The gearbox housing supports the gearbox input member for rotation about the main axis without any other degrees of freedom, and the gearbox input member is coupled to the main shaft with translational degrees of freedom in all directions and rotational degrees of freedom about axes perpendicular to the main axis.

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: An epicyclic gear train includes planetary gears rotatably mounted on spindles supported by an annular carrier and including axially spaced apart forward and aft sets of output teeth extending radially outwardly from a planetary gear hub and axially spaced apart forward and aft roller bearings disposed between planetary gears and spindles. The forward and aft roller bearings are axially aligned with or adjacent to spaced apart forward set of output teeth and input gear respectively. A ring gear meshes with forward set of output teeth and an external gear meshes with aft set of output teeth. An input gear fixedly attached to hub aft of aft set of output teeth and engaged with a sun gear. The output teeth, input gear, ring gear, external gear, and sun gear may all be helical. A turbofan gas turbine engine may include counter-rotatable first and second fan stages driven by a low pressure turbine through the gear train.

Abstract: An example turbomachine geared architecture support assembly includes a subpart having a more compliant portion and a less compliant portion.

Abstract: A gas turbine engine includes a central body support that provides an inner annular wall for a core flow path. The central body support includes a first mount feature. A geared architecture interconnects a spool and a fan rotatable about an axis. A flex support interconnects the geared architecture to the central body support. The flex support includes a second mount feature that cooperates with the first mount feature for transferring torque there between. A method of disassembling a front architecture of a gas turbine engine includes the steps of accessing forward-facing fasteners that secure a central body support to a flex support, wherein the flex support includes a geared architecture supported thereon, removing the fasteners, and decoupling first and second mount features respectively provided on the central body support and the flex support.

Abstract: A pumping device ensures that the fluid materials such as water and liquid are transmitted from one area to another area. The pumping device includes an outer flexible pipe forming an enclosed volume between a first suction area and a destination area, which has a flexible shaft through winch the rotational motion from the said pumping device is transferred and at least one impeller to which rotational motion is transferred through this flexible shaft and multiple centering components ensuring that the flexible shaft is centered and/or bedded inside the outer flexible pipe.

Abstract: A device for driving an auxiliary unit, in particular a high-pressure pump, includes a rotatably supported drive shaft of an internal combustion engine, wherein the drive shaft and a unit shaft of the auxiliary unit are operatively connected to each other by a coupling. The unit shaft has a first bearing on the side facing away from the coupling, and the coupling is a second bearing for the unit shaft. The device provides a low-cost, acoustically inconspicuous, tolerance-insensitive coupling solution for connecting, for example, a high-pressure pump camshaft to an available intake or exhaust camshaft.

Abstract: A three journal bearing supported shaft with a link between two of the bearings may allow for longer spacing between the wheels supported by the shaft. The flexible shaft may move one bending critical speed below the minimum operating speed of the shaft and the next bending critical speed above the maximum operating speed of the shaft, thus extending the speed range significantly. A tie rod may be used as the link in the shaft.

Abstract: A method for servicing a gas turbine engine includes providing access from a forward section of the gas turbine engine to a gearbox contained within a bearing compartment. A gas turbine is also disclosed in which a bearing package is mounted to a front center body support and a low spool. A front wall is removable from the front center body support to provide access to the gearbox.

Abstract: A gas turbine engine includes a central body support that provides an inner annular wall for a core flow path. The central body support includes first splines. A geared architecture interconnects a spool and a fan rotatable about an axis. A flex support interconnects the geared architecture to the central body support. The flex support includes second splines that intermesh with the first splines for transferring torque there between.

Abstract: A geared architecture with a flex mount for a Fan Drive Gear System defined by a transverse stiffness relationship.

Abstract: A geared architecture with a flex mount for a Fan Drive Gear System defined by a lateral stiffness relationship.

Abstract: A gas turbine engine includes a central body support that provides an inner annular wall for a core flow path. The central body support includes first splines. A geared architecture interconnects a spool and a fan rotatable about an axis. A flex support interconnects the geared architecture to the central body support. The flex support includes second splines that intermesh with the first splines for transferring torque there between.

Abstract: A gearbox for a wind turbine, comprising a first planetary gear set; and a second planetary gear set having the same transmission ratio as the first planetary gear set; and, a load splitter to split the torque between the first planetary gear set and the second planetary gear set, wherein the load splitter is adapted to provide slip for absorbing deviations in the rotational position between the first planetary gear set and the second planetary gear set; and, wherein the first planetary gear set and the second planetary gear set are coupled in a split load arrangement for transmitting torque from a rotor shaft to a high speed shaft.

Abstract: A method and apparatus for reducing dynamic loading of a gas turbine engine is provided. The gas turbine engine includes a rotor shaft assembly including a rotor shaft, a bearing assembly, a mounting race, and a support frame, the mounting race including a spherical surface. The method includes supporting the rotor shaft on the gas turbine engine support frame with the bearing assembly, the rotor shaft including a yield portion configured to permit bending of the rotor shaft during an imbalance operation.