Abstract: A motor rotor includes an inner sleeve, a cylindrical permanent magnet disposed around the inner sleeve, and a resin portion formed by charging a gap between the inner sleeve and the permanent magnet with a resin. The inner sleeve includes a small diameter portion. The small diameter portion is located to face an inner peripheral surface of an end portion of the permanent magnet in an axial direction. The small diameter portion is formed to have a diameter smaller than a diameter of a portion facing an inner peripheral surface of a center portion of the permanent magnet in the axial direction.

Abstract: The present invention relates to a housing arrangement for a turbomachine, comprising a support element, which is configured to bear a shaft, and a housing, which is centered at the support element. The housing is composed of an inner housing and an outer housing fastened at the support element, the housings being connected to each other by at least one connecting strut. A press fit is provided between the support element and the inner housing, in order to center the inner housing at the support element.

Abstract: A vacuum pump and a damper for the vacuum pump are provided so as to increase vibration isolation in a twisting direction with a simple structure and prevent rupture of an O-ring and an elastic member by regulating a misalignment of flanges facing each other. Provided are a first flange and a second flange, each having a central opening, the flanges being shaped like rings opposed to each other; an O-ring and an intermediate ring that are disposed between the first flange and the second flange; O-rings disposed between the first flange and the intermediate flange and between the intermediate ring and the second flange; a plurality of elastic members that are disposed between the first flange and the second flange and are spread in the circumferential direction of central openings; and airtightness keeping means including positioning pins inserted into positioning holes sequentially provided on the first flange, the intermediate ring, and the second flange.

Abstract: A reduction gear for a turbomachine (6) extending around an axis (X-X) of rotation, comprising a ring gear (9) connected to a ring gear carrier (12), wherein the ring gear carrier (12) has, according to a section view along a plane including the axis (X-X), an internal segment (124), an external segment (126) and a ring gear support (128), extending successively from the internal shaft (122) until the ring gear support (128), the internal segment (124) extends until a radius R1 with respect to the axis (X-X), the external segment (126) forms an angle ? with the internal segment (124), the ring gear support (128) forms an angle ? with the external segment (126), and is secured to the ring gear (9) via a bolted connection accomplished at a nominal radius R2 with respect to the axis (X-X), in that the ratio R1/R2 is comprised between 0.3 and 0.7.

Abstract: An aircraft gas turbine engine has an engine core with a turbine, compressor, and core shaft connecting the turbine to the compressor, a fan upstream of the engine core; and a gearbox. The engine core has three bearings, one forward, two rearward, to support the core shaft, a minor span being the axial distance between the two rearward bearings. A first blade to bearing ratio of the minor span divided by the product of the mass, radius at mid-height, and the square of the angular velocity at cruise for a blade of the lowest pressure set may have a value in the range from 2.0×10?6 to 7.5×10?6 kg?1·rad?2·s2. A second blade to bearing ratio of the minor span divided by the product of mass and radius at mid-height for a blade of the lowest pressure set may have a value in the range from 0.8 to 6.0 kg?1.

Abstract: A turbocharger device for an internal combustion engine and a method for mounting a turbocharger device are described. The turbocharger device has a housing with a locating hole, in which a turbocharger shaft is mounted by two rolling element bearings. A rolling element bearing sleeve is situated between the two rolling element bearings. The rolling element bearing sleeve and hence the two rolling element bearings are fixed with the turbocharger shaft in the axial direction with the aid of two pins, which are introduced through a hole in the housing and are pressed into a groove in the rolling element bearing sleeve. During this process, the beveled tips of the pins slide along the chamfered outer edges of the groove as far as an end position, which fixes the axial position of the rolling element bearing sleeve.

Abstract: An aircraft gas turbine engine has an engine core having a turbine, compressor, and core shaft connecting the turbine to the compressor, the turbine being the lowest pressure turbine and having a turbine length being the distance between the roots of the most upstream turbine blade at its leading edge and of the most downstream turbine blade trailing edge, and the compressor being the lowest pressure compressor of the engine; a fan located upstream of the engine; and a gearbox receiving an input from the core shaft and outputting drive to the fan. The engine core has three bearings to support the core shaft, the three bearings having a forward bearing and two rearward bearings, with a minor span defined as the distance between the two rearward bearings, and wherein further a minor span to turbine length ratio of: minor ? ? span tu ? ? rbine ? ? length is equal to or less than 1.05.

Abstract: The invention relates to an inter-turbine casing (1) comprising: an inner shell (10), an outer shell (20), and an assembly of arms (2) extending radially between the timer (10) and outer (20) shells; and an assembly of splitter blades (30) positioned between the arms (2), each splitter blade (30) comprising an inner platform (33) and an outer platform (36). The inner shell (10) comprises at least one inner groove (11) for slidably receiving one or more inter platforms (33). The outer shell (20) comprises at least one outer groove (21) for slidably receiving one or more outer platforms (36). The inter-turbine casing further comprises locking means (4, 5) for locking the splitter blades (30) in the inner (11) and outer (21) grooves. The splitter blades are arranged using multiple tenons (39) that extend in corresponding ribs (12, 22).

Abstract: Provided is a linear compressor. The linear compressor includes a piston, a cylinder, and a bearing inflow passage. The bearing inflow passage includes a first bearing inflow passage extending inward from an outer circumferential surface of the cylinder in the radial direction and a second bearing inflow passage extending from the first bearing inflow passage to an inner circumferential surface of the cylinder. The second bearing inflow passage extends from the inner circumferential surface of the cylinder in a circumferential direction.

Abstract: A unitary fan inlet case and bearing support structure for a gas turbine engine includes an annular body having a radially inward ring connected to a radially outward ring via a plurality of struts. A platform protrudes radially inward from the radially inward ring. The platform includes a radially outward facing surface and a radially inward facing surface. The annular body is a single unitary structure.

Abstract: What is illustrated and described is a pump assembly (1) for a pump, particularly for a miniature pump, with an electric motor (2) and with a housing unit (3), wherein the electric motor (2) has a motor shaft (5) passing freely through a motor housing of the electric motor (2) and the motor housing is connected to the housing unit (3), and wherein the motor shaft (5) is supported in the motor housing with an axial shaft play. According to the invention, at least one stabilizing element (6, 13, 14, 16) arranged outside of the motor housing is provided in order to reduce or eliminate the axial play of the motor shaft (5), with an axial compressive force or axial tensile force acting on the motor shaft (3) being applied by the stabilizing element (6, 13, 14, 16) to the motor shaft (5).

Abstract: In a first aspect, a method of lowering a wind turbine blade assembly comprising a wind turbine blade and a pitch bearing from a wind turbine hub is provided. The method of lowering a wind turbine blade assembly comprises positioning the wind turbine blade in a substantially horizontal position, holding the wind turbine blade in the substantially horizontal position with a crane, removing the blade assembly from the hub and lowering the blade assembly with the crane. In a further aspect, a method of disassembling a pitch bearing from a wind turbine hub using a tool having a socket wrench is provided. In yet a further aspect, tool for connecting or disconnecting a wind turbine blade assembly to or from a hub of a wind turbine is provided.

Abstract: A pump bearing retainer (1), for a wet-running pump, includes a radially inner section (3) including an inner section surface (9) for a press-fit contact with an essentially cylinder-shaped radial outer surface (29) of a pump bearing (13). A radially outer section (7) includes an annular or essentially conical-shaped outer section surface (17) with a cone angle (?1) equal to or larger than 45°. An intermediate section (5) extends from the inner section (3) to the outer section (7). The intermediate section (5) includes an essentially conical-shaped intermediate section surface (15) with a cone angle (?2) smaller than 45°. A longitudinal cross-section area (A) of the inner section (3) is smaller than a longitudinal cross-section area (B) of the intermediate section (5).

Abstract: An airfoil material loss control structure is provided. This structure includes at least one fuse zone that, during impact from a foreign object, fail before the surrounding structure. In a further aspect, a rotary machine is provided. This rotary machine includes a ducted fan gas turbine engine including a composite airfoil with at least one fuse zone.

Abstract: A gas turbine engine comprises a gearbox comprising a sun gear, an annulus gear, a plurality of planet gears and a carrier. Each planet gear is rotatably mounted in the carrier by a bearing. The sun gear meshes with the planet gears and the planet gears mesh with the annulus gear. The sun gear, the planet gears and the annulus gear comprise helical gear teeth. The annulus gear is secured to a surrounding structure by a radially extending member. A face of the flange nearest the middle of the annulus gear is axially spaced from the middle of the annulus gear by a first distance. The reference diameter of the annulus gear is radially spaced from a point at which the radially extending member is secured to the surrounding structure by a second distance. The ratio of first distance to second distance is between and including 0.5 and 1.2 such that misalignment between the annulus gear and the planet gears is reduced to minimise vibrations, noise, stress and wear of the gearbox.

Abstract: A rotary machine system includes: a rotary machine including a gas seal portion; a gas seal device connected to the rotary machine and that supplies a seal gas to the gas seal portion; a pressure sensor that detects a pressure of the seal gas; a vent portion that discharges the seal gas discharged from the gas seal portion; and a vent pressure sensor that detects a pressure in the vent portion. The rotary machine includes: a casing through which a working fluid flows; a rotatable rotary shaft that passes; and the gas seal portion provided between the casing and the rotary shaft and that seals the working fluid by the seal gas having a pressure higher than a pressure of the working fluid in the casing. The gas seal device includes: a pressure regulating valve; and a control part that controls the pressure regulating valve.

Abstract: A housing for retention of the outer race of a bearing of a gas turbine engine includes an arrangement of spring fingers that yields a lightweight housing capable of withstanding very high radial loads combined with very high torsional windup and axial thrust load. Controlled circumferential gaps on both sides of each spring finger limit the deflection and self-arrest the distortion of the housing. The spring fingers define at least one side edge that extends at an angle relative to the axial direction. An axial gap is created on the aft end by a portion of the spring finger beam structure that opposes an axial face of the housing and limits the axial distortion. A radial gap created between interface hardware of the housing and the inner retention housing also acts to retain the spring finger housing under load in a radial direction.

Abstract: A method of suppressing shaft vibration of a turbocharger capable of being driven by a motor includes: a specific-vibration-state determination step of determining whether a rotor shaft of the turbocharger is in a specific vibration state in which a magnitude of shaft vibration of the rotor shaft is, or is likely to be, greater than a predetermined magnitude; an excited state determination step of determining whether the motor is in an excited state in which an exciting voltage is applied to the motor; and a vibration suppression execution step of applying the exciting voltage to the motor if it is determined that the rotor shaft is in the specific vibration state in the specific-vibration-state determination step and it is determined that the motor is not in the excited state in the excited state determination step.

Abstract: A method for continuously removing water vapor from a carrier gas is disclosed. This method includes, first, causing direct contact of the carrier gas with a liquid mixture in a separation chamber, the carrier gas condensing at a lower temperature than the water vapor. A combination of chemical effects cause the water vapor to condense, complex, or both condense and complex with the liquid mixture.

Abstract: A planetary drive assembly includes a first housing that is coupled a top end of a stanchion. A drive unit is rotatably positioned in the first housing. A plurality of wind propellers is coupled to the drive unit thereby facilitating the wind propellers to rotate the drive unit. A planetary driven unit is rotatably positioned in the first housing. The planetary driven unit is in mechanical communication with the drive unit such that the drive unit rotates the planetary driven unit when the wind propellers rotate the drive unit. The planetary driven unit is mechanically discrete from the first housing. Thus, the planetary driven unit inhibits the first housing from being exposed to rotational torque. The planetary driven unit is coupled to a generator thereby facilitating the wind propellers to rotate the generator.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, a shaft including at least one bearing, a speed change device in communication with the shaft, a first lubrication system in communication with the at least one bearing and a second lubrication system in communication with the speed change device.

Abstract: A turbocharger bearing assembly of a split turbocharger for an engine is disclosed in which key rotational parts are rotatably supported by a pair of spaced apart bearings located in a bore of a tubular bearing housing forming part of a bearing assembly. The rotational parts of the turbocharger bearing assembly are balanced as a unit before the turbocharger bearing assembly is assembled to a cylinder block of the engine by insertion into a bore formed in the cylinder block.

Abstract: An electric motor includes a stator and a rotor. The stator includes a motor housing with an open end and an end cover mounted to the open end. The rotor includes a rotor shaft that extends through the end cover. The end cover includes a bearing that supports the rotor shaft. The rotor shaft and motor housing are made of an electrically conductive material and are electrically connected with each other. The motor housing, end cover, bearing and rotor shaft cooperatively form an electromagnetic shield suppressing electromagnetic interference generated by the motor. Optionally, the rotor shaft drives a coaxial worm shaft of a gearbox by an insulating member, which further suppresses electromagnetic interference.

Abstract: Conventionally, turbocharger bearing housings are cast, and then oil passageways are drilled or bored into the casting. As a result, bores are limited to straight lines extending from drill access points. Greater design flexibility is provided by pre-staging in a mold a collection of metal pipes which will define one or more of oil, air and water galleries, and then casting a bearing housing around the pipes. This provides almost unlimited freedom in shaping and locating the oil bores and other features.

Abstract: A rotor assembly for a wind turbine comprises a hub, a blade provided with a blade root portion and a strengthener for the blade root portion. The strengthener comprises a supporting part that strengthens the blade root portion and the supporting part comprises a supporting portion to temporarily support the blade. The supporting portion is made in one piece with the supporting part. The rotor assembly also comprises a number of first fasteners and second fasteners to fasten the blade root portion to the hub. The second fasteners are adapted to fasten the supporting part of the strengthener to the blade root portion when the latter is not fastened to the hub.

Abstract: A method for removing a twin-spool turbine including a front fan, a HP module with a HP rotor, and a LP turbine module, an intermediate casing including a support bearing for the HP rotor, the HP rotor being retained in the bearing by a link nut, the method including inserting a tool for unscrewing the link nut after having released access to the link nut, and preheating the link nut before starting the unscrewing tool.

Abstract: Various “contactless” bearing mechanisms including hydrodynamic and magnetic bearings are provided for a rotary pump as alternatives to mechanical contact bearings. In one embodiment, a pump apparatus includes a pump housing defining a pumping chamber. The housing has a spindle extending into the pumping chamber. A spindle magnet assembly includes first and second magnets disposed within the spindle. The first and second magnets are arranged proximate each other with their respective magnetic vectors opposing each other. The lack of mechanical contact bearings enables longer life pump operation and less damage to working fluids such as blood.

Abstract: A method for coating a pump component (23, 31), in particular, a part of an axial piston pump (7), having the steps of providing a blank of the component (23, 31), providing at least one recess in the blank, filling a powdery coating material into the associated recess, melting the coating material under a protective gas atmosphere and material-removing processing of the blank to form at least one sliding and/or bearing surface (6) from the coating.

Abstract: An exemplary method of controlling fluid flow in a ram air turbine assembly, includes redirecting flow moving in an axial direction against the surface of a drive shaft to flow moving in a radial direction away from the drive shaft to limit flow of the fluid from a hydraulic pump to a generator.

Abstract: This invention relates to a cross-flow wave making pump comprising an impeller shell forming a water intake and a water outlet, an impeller assembly pivotally connected to two ends of the impeller shell, and a motor used for driving the impeller assembly; wherein, the impeller assembly comprises an impeller used for driving a liquid flow, a first turntable and a second turntable respectively fixed at two ends of the impeller, wherein the first turntable is provided with a shaft rotatably mounted in the impeller shell, the second turntable is provided with a cavity used for receiving a rotor shaft of the motor. The embodiments of the present invention can provide a sufficient liquid-circulation in a container, and significantly reduce the dead zone where the liquid flows extremely slowly.

Abstract: The invention concerns a gas turbine engine component (27) comprising an outer ring (21), an inner ring (20), a plurality of circumferentially spaced elements (22) extending between the inner ring (20) and the outer ring (21), wherein an annular load transfer structure (23) extends circumferentially along an inner side of the inner ring (20) and also inwards in a radial direction of the component (27). The first portion (23a), at least along a part of the circumference, is inclined in the radial direction in relation to a second portion (23b), wherein the two inclined portions (23a, 23b) are connected in a connection zone (26) between the inclined portions (23a, 23b), and wherein a radial and/or axial position of the connection zone (26) varies along the circumference such that the radial/axial position of the connection zone in a location that circumferentially corresponds to a first element (22a), i.e.

Abstract: Disclosed is a low-cost composite-type vacuum pump having a strength capable of withstanding high loads and using a cylindrical rotor formed from a fiber-reinforced plastic material. Having a turbo-molecular pump section (14) and a thread groove pump section (15), the composite vacuum pump is formed by press-fitting a joint portion (20a) of a rotor (17) of the turbo-molecular pump section (14) into the upper end section of a cylindrical rotor (21) formed from the fiber-reinforced plastic material of the thread groove pump section (15).

Abstract: A fan impeller structure and a manufacturing method thereof. The fan impeller structure includes a hub and multiple securing sections. The hub has a top section, an annular section and multiple recesses. The annular section axially extends from a circumference of the top section. The annular section and the top section together define a receiving space. The recesses are formed at a junction between the top section and the annular section. The securing sections are disposed in the receiving space and formed oppositely between the recesses. The manufacturing method of the fan impeller structure enables the manufacturing process to be simplified. Moreover, by using the securing sections, magnetic members can be quickly connected with and secured to inner circumference of the hub to save working time.

Abstract: A flow-based power generating plant with a turbine, which can be acted on by a fluid flow and having a plurality of blades that extend from a blade base to a blade tip and are fastened by the blade base to a rotating rotor. The action of the fluid flow can cause the blades to twist elastically around an axis which extends through the blade base, in such a way that the pitch of the blades can be increased.

Abstract: A turbofan engine (20; 300; 400) comprises a fan (28), a fan drive gear system (60), a fan shaft (120) coupling the fan drive gear system to the fan, a low spool, an intermediate spool, and a core spool. The low spool engages at least three main bearings of which at least two are non-thrust bearings and at least one is a thrust bearing. The fan shaft engages at least two bearings (148, 150). The core spool engages at least two bearings (250, 260). The intermediate spool engages at least two of said bearings (220, 200, 230; 220, 200, 230-2; 200, 220, 230-3).

Abstract: An electronically-controlled turbocharger (ECT) includes a rotor (of an electric motor) on the shaft of the turbomachine. There are a variety of embodiments for securing the rotor onto the shaft including, but not limited to: having a taper on both the shaft on the rotor and using a nut engaging with threads in the shaft to put the two tapers together; a press fit; splines and grooves also using a nut; and a shoulder on the shaft that the rotor abuts when a nut is engaged with threads on the shaft. To accommodate these retaining features, the diameter of the shaft is greater near the turbine end of the shaft. A first bearing installed on the shaft near the turbine end of the shaft has a larger inside diameter than a second bearing installed on the other side of the rotor.

Abstract: A turbocharger assembly includes a compressor assembly, a turbine wheel, a shaft, a bearing assembly, and a cooling gas conduit. The compressor assembly includes a compressor impeller. The compressor impeller includes an outermost impeller edge and has a maximum cross-sectional dimension at the outermost impeller edge. The shaft interconnects the compressor impeller and the turbine wheel. The bearing assembly surrounds at least a portion of the shaft. The cooling gas conduit is disposed in fluid communication with the compressor assembly and the bearing assembly. At least a portion of the cooling gas conduit is disposed adjacent the outermost impeller edge such that the cooling gas conduit is configured to receive a portion of intake gases flowing along the outermost impeller edge and guide the portion of the intake gases toward the bearing assembly to cool the bearing assembly.

Abstract: A gas turbine engine includes a bearing structure mounted to the front center body case structure to rotationally support a shaft driven by a geared architecture. A bearing compartment passage structure is in communication with the bearing structure through a front center body case structure.

Abstract: A ball bearing system for use with engine turbochargers dampens axial and radial thrust loads of a turbocharger and enhances performance and longevity. The system includes a bearing carrier with an aperture to house a shaft having a compressor wheel affixed to a first end of the shaft and a turbine wheel affixed to a second end of the shaft, the bearing carrier being able to house a plurality of bearings in contact with the shaft, an outer housing member connected to the shaft to enclose the bearing carrier, and a first O-ring and a second O-ring both disposed within grooves around the outer surface area of the bearing carrier, each O-ring also in contact with a corresponding groove in the interior of the outer housing member. The O-rings dampen the axial and radial loads of the rotating shaft of the turbocharger.

Abstract: A gas turbine engine includes a gas turbine engine internal compartment structure having an integral passageway. Wiring is routed through the integral passageway of the gas turbine engine internal compartment structure.

Abstract: A mounting system for mounting a blade to a rotor body includes a pitch control mechanism including an anchor and a pitch change rod extending radially outwardly from the anchor to join to a base of the blade. The anchor and the rod are rotatable about the longitudinal axis of the rod to vary the blade pitch. The pitch control mechanism further includes a torque-transmitting formation between the blade and the anchor such that pitch-varying torque can be transmitted to the blade through the torque-transmitting formation while allowing relative radial movement between the blade and the anchor. The system includes a primary bearing formation, which transmits blade centrifugal loads to the rotor body while accommodating variation of the blade pitch, and secondary bearing formation, which transmits pitch change mechanism centrifugal loads to the rotor body while accommodating rotation of the anchor and the rod during variation of the blade pitch.

Abstract: Provided is a uni-axial multi-stage radial gas expander which has a high degree of reliability and which can sufficiently cope with the conditions of a high pressure and a high pressure ratio. Two or more radial gas expander sections (11A, 11B) formed of two-or-more-stage impeller vanes (14a to 14h) arranged between bearings (21a, 21b) on a rotor shaft (13) consisting of a single shaft are housed in a signal casing (10).

Abstract: An oil-retaining bearing fan device includes a fan base seat, at least one oil-retaining bearing and at least one magnetic member. The oil-retaining bearing is disposed in a bearing hole of the fan base seat. The oil-retaining bearing has at least one receiving hole for receiving the magnetic member therein. The magnetic member serves to apply a magnetic attraction force to a shaft of the fan device to make the shaft quickly restore to its optimal operation position so as to reduce wear and lower the noises and vibration of the fan device in operation. Therefore, the lifetime of the fan device can be prolonged.

Abstract: A bearing assembly for a gas turbine engine includes a bearing, an outer assembly disposed about an axis and having an angled perimeter, and an inner assembly supporting the bearing and having a surface angled to slide against and attach to the angled perimeter as the bearing is aligned with the axis.

Abstract: A prestressing device extending about an axis between a first plane that is substantially perpendicular to the axis and a second plane that is substantially parallel to the first plane and axially offset relative to the latter. The device includes a first annular body extending in the first plane, and a first series of at least three tabs, each of which is connected to the first body and extending in an essentially radial direction, each of the tabs of the first series including a planar surface extending in the second plane. This arrangement ensures surface contact between the parts of the elements to be subjected to prestressing. The device can be used for example for a rotor, and for example for a rotor of an unducted propeller for a turbine engine.

Abstract: A bearing system for a turbocharger rotor assembly that includes an elongated bearing carrier with anti-friction bearings on each end carried in a stationary housing. The elongated bearing carrier is supported within the housing by axially spaced elastomeric bands in grooves in the outside diameter of the bearing carrier that cooperate with grooves in the bore of the stationary housing within which the elastomeric bands are seated to carry the axial thrust of the rotor assembly in both axial directions.

Abstract: An exemplary center housing rotating assembly includes a turbine wheel; a compressor wheel; a center housing (510) that includes a through bore (515), extending from a compressor end to a turbine end along a bore axis; a bearing assembly (530) positioned in the bore where the bearing assembly includes an outer race (532) that includes keyways (535, 535?) extending from an axial end, the keyways radially inset from an outer diameter of the outer race; and a plate (570) attached to the center housing where the plate includes extending keys (578, 578?), each of the keys (578, 578?) being received by a respective one of the keyways (535, 535?) to restrict rotation of the bearing assembly in the bore. Various other exemplary devices, systems, methods, etc., are also disclosed.

Abstract: A shaft cap to connect between a shaft and a tie rod on a rotative assembly includes a circular portion with a central opening for connecting to the tie rod; a conical portion extending out from the circular portion at a slope; and a pilot around the outer edge of the conical portion. The pilot includes an outer lip to connect to an end of the shaft, an inner portion to connect to the inner circumference of the shaft and an undercut portion between the outer lip and the inner portion.

Abstract: In an aluminum turbocharger bearing housing, there is a potential for wear of the bearing housing at the interface with the journal bearing system. With a protective hard anodized surface, the wear resistance and resistance to chemical attack of the bearing housing can be improved so that an aluminum bearing housing can have the life of a cast iron bearing housing, at greatly reduced weight.

Abstract: An aircraft engine including a fan having a center of mass, a low-pressure shaft that couples the fan directly to a low-pressure turbine of the aircraft engine, and a bearing arrangement for mounting the low-pressure shaft, where the bearing arrangement has at least two front bearings for mounting the low-pressure shaft, a first front bearing and a second front bearing, with the first front bearing being arranged in the axial direction in front of the second front bearing. It has been provided that the first front bearing is arranged substantially in the same plane, extending perpendicular to the longitudinal axis of the aircraft engine, as the center of mass of the fan.