Abstract: An electric propulsion system for a vertical take-off and landing (VTOL) aircraft, the electric propulsion system including an electrical motor having a stator and a rotor. The electric propulsion system may include a main shaft possessing at least one shoulder on an outer surface of the main shaft. The electric propulsion system may include a gearbox assembly comprising a sun gear that is concentrically aligned with the main shaft at least one planetary gear that interfaces with the sun gear. The electric propulsion system may include a planetary carrier, wherein a center of the planetary carrier is concentrically aligned with the main shaft. The electric propulsion system may include a propeller flange assembly that travels through the rotor, and an axial buttress positioned in the at least one shoulder located on the main shaft.

Abstract: A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gear layshafts that each support a first stage planet gear and a second stage planet gear, and a ring gear. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and the plurality of planet gear layshafts comprise an interior passage that receives one or more lubrication supply lines.

Abstract: A turbofan includes a fan, a casing positioned downstream of the fan and separating a primary flowpath from a secondary flowpath, a compressor, a combustion chamber and a turbine being arranged in the primary flowpath, the turbofan having a differential transmission coupled to the turbine, and a power supply device configured to provide additional power to the one provided by the turbine to drive the compressor.

Abstract: Aircraft turbine engine (10), comprising:—at least one first turbine rotor (22a) connected to a first turbine shaft (36) and comprising rotor blades located in a stream (V),—an annular exhaust casing (28) supporting at least one bearing (60, 62) for guiding the rotation of the first shaft and comprising arms (28a) located in the stream, downstream of the blades, and—a mechanical planetary gearbox (42) which comprises a sun gear (44), a ring gear (40) and a planet carrier (46), the gearbox being at least partially surrounded by the exhaust casing and one of the rotatable elements chosen from the sun gear and the ring gear being connected to the first shaft, characterised in that the exhaust casing carries a device (70) for recovering and discharging oil projected centrifugally by the reduction gear.

Abstract: An assembly for a turbine engine extending along an axis, includes a stator, a low-pressure compressor shaft, a low-pressure compressor comprising a rotor comprising a drum rotatably coupled to the shaft of the low-pressure compressor, and a fan comprising a disk rotatably coupled to the shaft of the low-pressure compressor. The drum has a radially internal part rotatably coupled to the shaft of the low-pressure compressor and a radially external part fixed to the radially internal part by means of detachable fixing means. A first axial retention means is configured to axially and detachably retain the disk of the fan relative to the shaft of the low-pressure compressor. A second axial retention means is configured to axially and detachably retain the radially internal part of the drum relative to the shaft of the low-pressure compressor.

Abstract: The invention concerns a planetary gear box with a flow guidance device for a planet gear lubricant stream in the planetary gear box, which is directed at least partially along a planet gear after an engagement with a sun gear, characterized by a collecting region of the flow guidance device in which the planet gear lubricant stream between the planet gear and the flow guidance device can be at least partially captured, and wherein the collecting region has an outlet region between the flow guidance device and the tooth face of the planet gear for at least a part of the planet gear lubricant stream, and an edge is arranged at the outlet region for defined constriction of the passage for the planet gear lubricant stream.

Abstract: Device for distributing oil from a rolling bearing (8) for an aircraft turbine engine, comprising: —a rolling bearing (8), —a body (5) for distributing oil, which body is configured to be mounted on a turbine engine shaft (4), said body comprising: i) a first outer cylindrical surface (5a) for mounting the inner ring (12) of the bearing, ii) a ring-shaped scoop (11) for recovering oil, iii) a ring-shaped track (26) of a dynamic seal (22), iv) a circuit (7) for lubricating the bearing and cooling the track, said circuit being formed in the body, characterised in that the ring-shaped scoop is the first scoop (11a) which supplies a first portion (7x) of the circuit with a view to cooling the track, and in that the body comprises a second ring-shaped scoop (11b) for recovering oil, which scoop supplies a second portion (7y) of the circuit with a view to lubricating the bearing.

Abstract: Disclosed is a mechanism to exhaust refrigerant vapor resulting from operation of a thermal management system that is used to cool a thermal load by a vehicle, such as an airborne vehicle. The thermal management system includes an open circuit refrigeration system featuring a receiver configured to store a liquid refrigerant fluid, an evaporator configured to extract heat from the thermal load that contacts the evaporator, and an exhaust line, where the receiver, the evaporator, and the exhaust line are connected to provide an open refrigerant fluid flow path. Other implementations of open circuit refrigeration systems include the use of a gas receiver, a pump and an ejector are also described, as are other mechanisms to exhaust refrigerant vapor resulting from operation of the thermal management system.

Abstract: A propulsion system includes a drive shaft movable about an axis of rotation, a fan, a fan shaft that drives the fan, and a reduction device coupling the drive shaft and the fan shaft. The reduction device has first and second reduction stages and includes a sun gear, centered on the axis and driven by the drive shaft, a ring gear that is coaxial with the sun gear and that drives the fan shaft about the axis, and planet gears distributed circumferentially about the axis between the sun gear and the ring gear. Each planet gear includes a first portion meshed with the sun gear and a second portion meshed with the ring gear. A diameter of the first portion is different from a diameter of the second portion, and the first portion of the planet gears extend between the second portion of the planet gears and the fan.

Abstract: A planetary gear system includes a sun gear, a plurality of planet gears connected to a carrier and engaging with the sun gear, and a ring gear assembly including a damper housing, and a ring gear connected to the damper housing and engaging with the plurality of planet gears. The ring gear includes a geared wall having a plurality of gear teeth engaging with the plurality of planet gears, and a damper housing attachment member radially spaced outward of the geared wall and attaching the ring gear to the damper housing. A first end of the geared wall and the damper housing engage each other via a plurality of squeeze film damping members, and a second end of the geared wall is connected to the damper housing attachment member via a flexible damping wall that is configured to provide a radial damping of the second end of the geared wall.

Abstract: A turbofan engine includes a fan section that drives air along a bypass flow path in a bypass duct. An epicyclic gear system in driving engagement with the fan shaft and has a gear mesh lateral stiffness and a gear mesh transverse stiffness. A gear system input to the gear system defines a gear system input lateral stiffness and a gear system input transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness. A first performance quantity is defined as the product of a first speed squared and a first area and a second performance quantity is defined as the product of a second speed squared and a second area. A performance quantity ratio of a first performance quantity to a second performance quantity is between 0.5 and 1.5.

Abstract: An air starter for starting a turbine engine that includes a housing, a turbine member, a drive shaft, and at least one bearing assembly. The housing can define an interior where the turbine couples to the drive shaft that is rotatably supported by the least one bearing assembly. A lubricant passageway can provide lubrication to the at least one bearing assembly.

Abstract: A triple-flow turbomachine for an aircraft, including a power transmission module including a torque input connected to a turbine shaft, a first torque output of a gearbox connected to a main shaft for rotatably driving a main fan propeller, and a second torque output of a planet gear connected to a secondary shaft for rotatably driving a secondary fan propeller. The planet gear is independent of the gearbox and arranged downstream of the gearbox.

Abstract: A gas turbine engine (10) includes a compressor section, a turbine section, and an accessory gearbox (100). A turning unit (200) for the gas turbine engine includes an output assembly (204) configured to be mechanically coupled to the gas turbine engine, and an electric motor (202). The electric motor is operable to rotate, through the output assembly, one or more components of the compressor section or the turbine section at a rotational speed less than about fifty revolutions per minute during a shut-down condition of the gas turbine engine.

Abstract: An expiration date notification method uses an information terminal device that comprises a storage unit that stores an expiration date of a puncture repair liquid contained in a container; a notification condition setting unit that sets a notification period and a notification method for notifying of a replacement period of the puncture repair liquid based on the expiration date stored in the storage unit; a notifying unit that notifies of the replacement period of the puncture repair liquid; and a control unit that controls the notifying unit based on settings of the notification condition setting unit, the method comprising: after the expiration date is input into the storage unit of the information terminal device, the information terminal device notifying of the replacement period of the puncture repair liquid within a preset notification period including before and after the expiration date of the puncture repair liquid via a preset notification method.

Abstract: A drive gearbox for turbomachine equipment, the drive gearbox having a main shaft intended to be rotationally connected to a power transmission shaft of a turbomachine. The main shaft has at least one bevel gear rotationally driving at least one piece of equipment. The gearbox has gear set with cylindrical gearwheels that have an input connected to the rotational drive to the main shaft and a plurality of outputs each intended to drive a piece of equipment. The gear set extends over an angular sector and the outputs are angularly spaced apart along the angular sector.

Abstract: A gearbox system for a rotorcraft includes a gearbox housing, an oil pump receiving bore formed into the gearbox housing and having formed therein a first opening having a first diameter and a second opening, and an oil pump positioned within the oil pump receiving bore. The second opening is bounded by a lip that extends radially into the second opening, the second opening having a second diameter that is smaller than the first diameter.

Abstract: A gas turbine engine has a compressor section and a turbine section. A secondary cooling air includes a first fluid connection to tap cooling air and pass the cooling air through a plurality of tubes, and a second fluid connection for returning air from the tubes back to at least one of the compressor and turbine for cooling. A sensor senses a condition of the cooling air downstream of the tubes and a control compares the sensed condition of the cooling air to an expected condition, and to identify a potential concern in the cooling air system should the sensed condition differ from the expected condition by more than a predetermined amount.

Abstract: A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor having a downstream end. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor, and the boost compressor passes the air back to a location to be cooled. The boost compressor is driven by a shaft in the engine through an epicyclic gear system. A speed control changes the relative speed between an input and an output to the epicyclic gear system.

Abstract: A power tool is provided which includes a housing assembly; a motor assembly disposed in the housing assembly and having an output shaft; a trigger assembly coupled to the housing assembly and configured for use in actuating the motor assembly; a spindle; and a transmission assembly transmitting rotary power between the motor assembly and the spindle. The transmission assembly comprises a star compound gear train.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed.

Abstract: A gas turbine engine for an aircraft has an engine core having a turbine, compressor, and core shaft connecting the turbine and compressor; a fan upstream the engine core, the fan having fan blades; and a gearbox. The gearbox receives an input from a core shaft and outputs drive to a fan to drive the fan at a lower rotational speed than the core shaft. The gearbox is an epicyclic gearbox and has a sun gear, planet gears, ring gear, and planet carrier on which the planet gears are mounted. The gearbox has a gear mesh stiffness between the planet gears and the ring gear and a gear mesh stiffness between the planet gears and the sun gear. The gear mesh stiffness between the planet gears and the ring gear divided by that between the planet gears and the sun gear is in the range from 0.90 to 1.28.

Abstract: A multi-stage centrifugal compressor includes: a rotary shaft that is configured to rotate around an axis; a plurality of stages of impellers that are fixed to the rotary shaft and are configured to integrally rotate to compress and deliver a fluid, which flows into the impellers from an upstream side in an axial direction, to a radial outer side; a casing including a return flow path that is configured to guide the fluid, which is compressed and delivered from an impeller on a preceding stage side, toward a radial inner side, and an introduction flow path that is connected to a downstream side of the return flow path and is configured to divert the fluid and introduce the fluid to an impeller on a succeeding stage side; and return vanes that are arranged in the return flow path while being spaced apart from each other in a circumferential direction.

Abstract: The present invention relates to an aircraft propulsion assembly comprising a turbine (15), at least one fan (10) and a mechanism for transmitting power between the turbine and the fan, characterized in that the power transmission mechanism comprises a speed reducer (20) with a motion input and a motion output, the input being in the continuation of the axis (16) of the turbine and the output connected to the fan.

Abstract: A gas turbine engine with an accessory gearbox. The accessory gearbox is rotatably coupled to the engine drive shaft. The gearbox has a gear shaft rotatable about a gear shaft axis. The gear shaft has a first end drivingly engaged to a first accessory and a second end drivingly engaged to a second accessory.

Abstract: A method for operating an internal combustion engine having a waste heat utilization device including a waste heat utilization cycle in which a valve mechanism, an evaporator, and an expander are arranged, may include adjusting the valve mechanism between an evaporator position and a bypass position via a control/regulating device as a function of at least one operating parameter of the internal combustion engine. The method may also include calculating at least one of a power and an energy generatable by the waste heat utilization device via the control/regulating device as a function of the at least one operating parameter of the internal combustion engine. The method may further include switching the expander between an active state and an inactive state via the control/regulating device as a function of the at least one of the calculated power and the calculated energy.

Abstract: An aircraft comprising a fuselage and a propulsion assembly, the propulsion assembly comprising at least one fan rotor located at the rear of the fuselage in the extension thereof along a longitudinal axis, and a nacelle forming a fairing of the at least one fan rotor into which a flow of air passes. The aircraft also comprises a plurality of radial stator arms mounted upstream of the at least one fan rotor and extending between the fuselage and the nacelle, the radial arms comprising blowing means configured for blowing, into the environment of a trailing edge of the radial arms, an additional air flow adding to the airflow in the extension of the trailing edge.

Abstract: A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section via a primary flowpath and a turbine section fluidly connected to the combustor via the primary flowpath. Also included is a cascading cooling system having a first inlet connected to a first compressor bleed, a second inlet connected to a second compressor bleed downstream of the first compressor bleed, and a third inlet connected to a third compressor bleed downstream of the second compressor bleed. The cascading cooling system includes at least one heat exchanger configured to incrementally generate cooling air for at least one of an aft compressor stage and a foremost turbine stage relative to fluid flow through the turbine section.

Abstract: A system for stimulating oil or gas production from a wellbore includes a hydraulic fracturing pump unit having one or more hydraulic fracturing pumps driven by one or more electrical fracturing motors, a variable frequency drive (VFD) controlling the electrical fracturing motors, a fracturing pump blower unit driven by a blower motor, and a fracturing pump lubrication unit having a lubrication pump driven by a lubrication motor and a cooling fan driven by a cooling motor. The system may further include a blender unit and a hydration unit. A system control unit may control the operational parameters of the system.

Abstract: A gas turbine engine includes: an engine core with a turbine, compressor, and core shaft; a fan upstream the engine core; a gearbox that can receive an input from the core shaft and output drive to a fan shaft to drive the fan at a lower rotational speed than the core shaft. A fan-gearbox axial distance is greater than or equal to 0.35 m. The fan shaft has: (i) a radial bending stiffness ratio of a radial bending stiffness of the fan shaft at the fan input to a radial bending stiffness of the fan shaft at the gearbox output that is greater than or equal to 6.0×10?3; and/or (ii) a tilt stiffness ratio of a tilt stiffness of the fan shaft at the fan input to a tilt stiffness of the fan shaft at the gearbox output that is greater than or equal to 2.5×10?2.

Abstract: An engine for an aircraft includes 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; a fan shaft; a gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft so as to drive the fan at a lower rotational speed than the core shaft, the gearbox being an epicyclic gearbox having a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted; and a gearbox support arranged to mount the gearbox within the engine. The fan shaft, core shaft, gearbox and the gearbox support together may form a transmission.

Abstract: A geared turbofan engine that has a planetary gearbox which couples a fan shaft and a turbine shaft to each other. The planetary gearbox includes a sun gear that is driven by the turbine shaft. The turbine shaft and the sun gear form a spline shaft connection that is lubricated with oil. Sealing means are provided, sealing off the oil in the toothing area of the spline shaft connection. The sealing means have an elastic sealing ring that has a variable diameter and is springing outwards, and that is arranged inside a groove extending in the circumferential direction of the turbine shaft, wherein the sealing ring abuts at an inner circumferential surface of the sun gear with its radially outer circumferential surface. In further aspects, the invention relates to a method for mounting a planetary gearbox on a turbine shaft and to a spline arrangement.

Abstract: A turbofan engine includes a first spool including a first turbine, a second spool including a second turbine, and a fan. A fan drive gear system drives the fan. A first tower shaft engages the first spool, and a second tower shaft engages the second spool. A superposition gear system includes intermediate gears engaged to the sun gear and supported in a carrier and a ring gear circumscribing the intermediate gears. The first tower shaft drives the sun gear. A main oil pump is driven by the carrier and supplies oil to the fan drive gear system. An auxiliary oil pump supplies oil to the fan drive gear system and is driven by a ring gear shaft coupled to the ring gear. A shuttle valve selectively allows oil to be supplied to the fan drive gear system by one of the main oil pump and the auxiliary oil pump.

Abstract: A gas turbine engine for an aircraft has an engine core having a turbine, compressor, and core shaft connecting the turbine and compressor; a fan upstream the engine core, the fan having fan blades; and a gearbox. The gearbox receives an input from a core shaft and outputs drive to a fan to drive the fan at a lower rotational speed than the core shaft. The gearbox is an epicyclic gearbox and has a sun gear, planet gears, ring gear, and planet carrier on which the planet gears are mounted. The gearbox has a gear mesh stiffness between the planet gears and the ring gear and a gear mesh stiffness between the planet gears and the sun gear. The gear mesh stiffness between the planet gears and the ring gear divided by that between the planet gears and the sun gear is in the range from 0.90 to 1.28.

Abstract: A hydraulic fracturing system includes a plurality of pumps positioned at a wellsite and configured to pressurize a fracturing fluid, a distribution system fluidly coupled to receive and consolidate fracturing fluid from the plurality of pumps for injection into a wellhead. The hydraulic fracturing system further includes a control system, which includes a plurality of sensing devices configured to measure one or more parameters of the plurality of pumps and the distribution system, one or more processing device configured to receive and analyze the one or more parameters measured by the plurality of sensing devices and generate control instructions based at least in part on the one or more parameters, and one or more control device configured 110 to receive the control instructions and control one or more aspects of the plurality of pumps or the distribution system based on the control instructions.

Abstract: Compressor stage with a stator-side intake connection piece via which medium which is to be compressed can be introduced into the compressor stage in the region of the compressor stage, with a stator-side inflow channel via which the medium to be compressed can be conveyed in direction of a rotor-side impeller proceeding from the intake connection piece, wherein the impeller has a radially inner hub, a radially outer cover disk and impeller blades extending between the hub and the cover disk, wherein a plus measuring point and a minus measuring point are provided at the compressor stage for measuring the effective pressure at the compressor stage, and wherein the minus measuring point is positioned upstream of the impeller outside of the stator-side inflow channel in an annular gap which branches off from the inflow channel.

Abstract: A gas turbine engine includes a fan, a compressor section, and a turbine section configured to drive the compressor section and the fan. A buffer system is configured to communicate a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and an ejector that selectively augments the first bleed air supply to prepare the buffer supply air for communication to the portion of the gas turbine engine. A method and a buffer system are also disclosed.

Abstract: An air turbine starter device comprises a rotor arranged in a cavity of a housing, a first manifold having a cavity with a port operative to direct compressed air to the rotor, a second manifold having a cavity with a port operative to direct compressed air to the rotor, wherein the first manifold is larger than the second manifold.

Abstract: A blower assembly is configured to deliver a flow of breathable gas at a continuously positive pressure with respect to ambient air pressure to a patient interface in communication with an entrance to a patient's airways including at least an entrance of the patient's nares, while the patient is sleeping, to ameliorate sleep disordered breathing. The blower assembly includes a motor having a shaft that extends from opposite sides of the motor. The blower assembly also includes an impeller and a circuit board. The impeller is attached to the shaft on a first side of the motor and is structured to rotate in close proximity to a volute wall. The circuit board is configured to control power supplied to the motor and is configured to disable the motor when the impeller is closer than a predetermined distance from the volute wall.

Abstract: A system for stimulating oil or gas production from a wellbore includes a hydraulic fracturing pump unit having one or more hydraulic fracturing pumps driven by one or more electrical fracturing motors, a variable frequency drive (VFD) controlling the electrical fracturing motors, a fracturing pump blower unit driven by a blower motor, and a fracturing pump lubrication unit having a lubrication pump driven by a lubrication motor and a cooling fan driven by a cooling motor. The system may further include a blender unit and a hydration unit. A system control unit may control the operational parameters of the system.

Abstract: Systems and methods are disclosed for manipulating the noise and vibration of a switched reluctance machine (SRM). By use of vibration sensors and real-time optimization methods, the noise and vibration profile of an SRM and associated load may be modified to meet one or more control objectives, such as torque ripple mitigation (TRM), harmonic spectrum shaping, and/or efficiency improvement.

Abstract: An integral transmission; comprising a driving gear connected to a driving shaft for co-joint rotation, a large gear engaging with the driving gear, a first driven gear engaging with the large gear, and at least one additional driven gear which engages with the driving gear; wherein an axis of rotation of the driving gear and an axis of rotation of the first driven gear engaging with the large gear are arranged in a plane of alignment, an axis of rotation of the large gear is offset in the vertical direction with respect to the plane of alignment, and an axis of rotation of the at least one additional driven gear engaging with the driving gear is located in the plane of alignment. A geared compressor system; comprising the integral transmission and a drive unit.

Abstract: A turbofan engine (20) comprises a fan (28). A fan drive gear system (60) is configured to drive the fan. 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. An intermediate spool comprises an intermediate pressure turbine (48), a compressor (42), and an intermediate spool shaft (54) coupling the intermediate pressure turbine to the intermediate spool compressor. A combustor (45) is between a core spool compressor (44) and a high pressure turbine (46). A first (160) main bearing engages a static support (164; 164?) and a forward hub (236) of the intermediate spool. A second (162) main bearing engages the low shaft and the forward hub.

Abstract: The present disclosure relates generally a system for preventing relative rotation between three components. The three components include tabs and slots such that at least one first tab and at least one second tab on one component is disposed within at least one slot formed in the other two components to prevent relative rotation between any two of the three components.

Abstract: A method for assembling a turbofan engine (20) comprises coupling a bearing assembly (176) and a shaft (420) as a unit to a bearing support (453). A transmission (46) and the fan shaft (132) are installed to a front frame assembly (172). The bearing assembly and shaft are installed as a unit so that the shaft engages a central gear (52) of the transmission and the bearing support engages the front frame assembly.

Abstract: Gas turbine engines including multi-axis accessory gearboxes of mechanical drive systems are provided. The gearbox comprises a housing, a drive shaft, bevel pinion and drive shaft bevel gears, and a side bevel gear set operable to directly at least one side accessory device. Housing is disposed about a towershaft operatively coupled to main engine shaft and operable to rotate about a first axis. Drive shaft is skewed to main shaft and operable to rotate about a second axis that intersects the first axis at a first angle. Bevel pinion gear is mounted on the towershaft. Drive shaft bevel gear is mounted on the drive shaft. Side bevel gear set comprises an input gear meshing with one or more side bevel gears each having a side bevel gear axis at a second angle to the first axis and independently positionable relative to input gear. Second angle is independent of other angles.

Abstract: The invention relates to a method for mounting a rotor blade with a rotor blade shell and an internal space defined by the rotor blade shell, by at least one rotor blade clamp being applied around the outside of the rotor blade shell, by means of which at least one clamping force is exerted from the outside to the rotor blade shell, directed into the internal space by at least one expansion device being introduced into the internal space, by the expansion device inside the internal space being moved into at least one segment of the rotor blade around which the at least one rotor blade clamp is applied, by the at least one expansion device being expanded inside the at least one segment until at least one outwardly-acting counteracting force is exerted from the inside on the rotor blade shell.

Abstract: A structure improvement of a pump casing with a Polyfluoroalkoxy (PFA) liner which improves manufacturing efficiency, reduces manufacturing cost and improves yield strength, more particular to keep the stiffness of the shaft support and improve yield of the pump casing. The metal pump casing with the PFA liner used for handling corrosive liquids includes a suction casing with PFA liner, and a volute casing with PFA liner for accommodating an impeller. The volute casing also collects and then ejects the liquid through a discharge. The suction casing with the PFA liner and the volute casing with the PFA liner are separately formed as two workpieces by injection molding process and then assembled to form the pump casing so as to reduce the residual stress applied in the PFA liner.

Abstract: Disclosed herein are a shaft assembly having a dry well and a gearbox incorporating the shaft assembly. The shaft assembly may include a housing having an opening and a lubricant reservoir. A tubular member may be fixed in the opening and extend above a surface of lubricant that collects in the lubricant reservoir during operation. At least one sealing member may be positioned between the tubular member and an inner wall defining the opening. A solid shaft may extend through the tubular member and have an outer diameter that is smaller than an inner diameter of the tubular member, thereby defining a dry well between the solid shaft and the tubular member. A bearing mount may be arranged about the tubular member and may be removably connected to a gear associated with the solid shaft. A method of assembling a gearbox incorporating the shaft assembly is also disclosed.

Abstract: A gas turbine engine includes a fan shaft arranged along an engine central axis, a frame supporting the fan shaft, a gear system rotatably coupled with the fan shaft, and a flexible coupling at least partially supporting the gear system. The flexible coupling defines, with respect to the engine central axis, a torsional stiffness TS and a lateral stiffness LS such that a ratio of TS/LS is greater than or equal to about 2.0 to reduce loads on the gear system from misalignment of the gear system with respect to the engine central axis.