Abstract: An apparatus to support a rotor of a turbine engine disposed upon a support surface is disclosed. The apparatus includes a housing, a rotor support bearing disposed within the housing, and a support leg in operable communication with the housing and in direct structural connection with the support surface.

Abstract: A gas turbine engine (10) comprising a first turbine (19) and a first compressor (13) mounted on a first shaft (26) and a bearing arrangement (52, 34) supporting the shaft (26), the bearing arrangement is subject to a total end load and comprises a fixed bearing (34), a load share bearing (52) and a bearing end load management system (50) that is capable of applying a variable load to the load share bearing to manage total end load between the bearings. The bearing end load management system comprises a static diaphragm (54) that defines part of a chamber (56) and that is coupled to the load share bearing whereby increased pressurization of the chamber loads the diaphragm which in turn increases the proportion of the total end load on the load share bearing.

Abstract: Systems and methods involving struts are provided. In this regard, a representative system includes a gas turbine engine defining a gas flow path. The gas turbine engine comprises a strut extending into the gas flow path. The strut has an interior operative to receive pressurized air, an outer surface, and ports communicating between the outer surface and the interior of the strut, the ports are operative to receive the pressurized air from the interior and emit the pressurized air into the gas flow path such that an effective aerodynamic length of the strut along the gas flow path is increased.

Abstract: A small twin spool gas turbine engine with a hollow inner rotor shaft having solid shaft ends and an outer rotor shaft having a cylindrical portion on the compressor end that forms a forward bearing support surface and a turbine rotor disk on the turbine end that forms a aft bearing support surface. The inner rotor shaft includes solid shaft ends that project out from the cylindrical portion of the outer shaft on one end and out from the turbine rotor disk on the other end. An inner bearing housing is secured on the solid shaft ends of the inner rotor shaft. A threaded nut on the inner rotor shafts ends provide a compressive load to the inner bearing housings which results in a tension preload to the inner rotor shaft solid ends so that the bearing assemblies for the forward and aft ends of the twin spools do not become lose from the engine operation.

Abstract: This hydraulic machine comprises a wheel supported by a shaft (5), the wheel and the shaft being able to rotate about a vertical axis (X5) while a radial hydrostatic or hydrodynamic bearing (100) is formed between, on the one hand, a radial peripheral surface (52) of the shaft and, on the other hand, an internal radial surface (102) of a member (101) that is fixed relative to the vertical axis. The bearing (100) extends between two edges (121, 122) which, in normal operation, constitute regions for the removal of a film of water formed in the bearing. At least one cavity (130) is created in the fixed member (101) and opens onto its internal radial surface (102) near a first edge (122) of the bearing. The machine comprises means (131, 132, 133) for placing the cavity (130) in fluidic communication with a volume (V1) situated outside the bearing near the second edge (121) of the bearing (100).

Abstract: A small gas turbine engine that operates at high rotational speeds and includes a rotor shaft that is supported on both ends by ball bearings. The aft end ball bearings includes an outer race mounted to the support structure in such a way that axial displacement of the outer race is allowed to prevent axial loads from damaging the ball bearing. The outer race of each bearing is supported by an O-ring to provide damping to the bearings. The O-ring is centered on the outer race, and the outer race is formed thicker than the inner race to provide for a better hoop surface. The outer race in the aft end is preloaded with a coil spring to maintain a load on the bearing during all phases of operation of the engine. The bearings are coated with a dry lubricant to eliminate the need for a liquid lubricant and its supply system.

Abstract: An apparatus to support a rotor of a turbine engine disposed upon a support surface is disclosed. The apparatus includes a housing, a rotor support bearing disposed within the housing, and a support leg in operable communication with the housing and in direct structural connection with the support surface.

Abstract: A guide vane for a gas turbine aircraft engine includes an aerodynamic shell for turning a flow of working fluid and an internal spar spaced from the aerodynamic shell by an air gap and reinforced by stiffeners.

Abstract: A bearing support structure is provided for installation in a gas turbine engine between radially inner first and second bearings adapted to rotatably support a first and a second rotor, respectively, and a radially outer engine frame. The support structure includes a first annular plate-shaped part and an arrangement for supporting the first bearing at one end thereof and a second annular plate-shaped part and an arrangement for supporting the second bearing at one end thereof. The first and second plate-shaped parts are joined together forming a one-piece unit for installation in the gas turbine engine.

Abstract: A joining device including a clevis and a connecting member is disclosed. The connecting member includes a through hole which is housed between a first and a second lug of the clevis. These lugs respectively have a first clevis hole and a second clevis hole. The device further includes a shear pin system passing through each of the holes and includes a threaded end collaborating with a nut system which abuts against the second lug. The shear pin system includes a widened portion passing through the first hole and forming a shoulder situated between the two lugs. The member is situated away from the first lug. A first side of the member is pressed against the shoulder and a second side of the member is pressed against the second lug.

Abstract: A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a single point load structure and a plurality of struts. The single point load structure combines the first load and the second load into a combined load. The plurality of struts is connected to the single point load structure and transfers the combined load from the single point load structure to the mount.

Abstract: Gas turbine engine systems involving rotatable annular supports are provided. In this regard, a representative support assembly for a gas turbine engine includes: a rotatable member having a first end located about a first annulus; and a stationary member located about a second annulus; the first end of the rotatable member being rotatably coupled with the stationary member, with at least a portion of the first annulus being coextensive with at least a portion of the second annulus, the first end being operative to rotate locally with respect to a corresponding portion of the stationary member.

Abstract: A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a load transfer unit, a torque box rotatably positioned within the load transfer unit, and a plurality of struts. The load transfer unit has a first locking element and combines the first load and the second load into a combined load. The torque box has a second locking element that is engagable with the first locking element of the load transfer unit. The plurality of struts are connected between the torque box and the mount, and transfer the combined load from the torque box to the mount. The first locking element and the second locking element are at least one of a rib or a groove.

Abstract: In a method for reducing noise generated in a turbo engine with cascades, and a stator-rotor arrangement, in which hydrodynamic pressure fluctuations occurring on the cascades are reduced by varying the surface circulation of at least one section of at least one stator. A structure is provided on one or more stators, influencing the surface circulation of at least one section of the stator.

Abstract: A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a plurality of inverted panels and a plurality of struts. The inverted panels convert the first and second loads to a shear flow. The struts are connected to the inverted panels and transfer the shear flow to the mount.

Abstract: A structural turbine engine casing is disclosed. The casing includes a central hub, at least one intermediate shroud, and an external ring, which are concentric, the external ring and the intermediate shroud being connected via links, the intermediate shroud and the central hub being connected by a series of radially fastened hollow arms. The series of arms includes at least one main arm and at least one secondary arm, each main arm being arranged in the continuation of a link and having a mass which is greater than that of a secondary arm arranged at a distance from the links.

Abstract: An expandable mid-turbine frame assembly includes a first bearing cone, a second bearing cone and a mid-turbine frame. The mid-turbine frame assembly connects to a gas turbine engine casing and transfers a first load from a first bearing and a second load from a second bearing towards the engine casing. The first bearing cone transfers the first load from the first bearing. The second bearing cone transfers the second load from the second bearing. The mid-turbine frame is connected to the first and second bearing cones and includes segments. Each segment includes a pre-stressed support for equilibrating the first and second loads.

Abstract: The thrust bearing housing comprises two opposite annular end members and a cone member extending between the two end members. The cone member is connected to each end member at a circular junction, each circular junction having a medial line which borders a respective end of a virtual conical plane. At least a major portion of the cone member is provided inside the virtual conical plane.

Abstract: A method of reducing gas turbine engine distortion includes coupling a core gas turbine engine to a power turbine, coupling the power turbine to a thrust bearing support assembly through a frusto-conically shaped structural support such that the net axial thrust of the coupled core gas turbine engine and power turbine reacts through the thrust bearing support assembly at engine centerline to facilitate minimizing distortion of the core gas turbine engine casing, and supporting the thrust bearing support assembly such that all of the remaining thrust generated by the core gas turbine engine and the power turbine is reacted to ground.

Abstract: A method of assembly of a turbomachine that includes a first module and a second module with a second shaft assembled by a bearing, the bearing including an outer ring shrink-fitted inside a journal integral with the first module and an inner ring integral with the second shaft. The second module is assembled on the first module by engagement of the second shaft, with the inner ring, inside the journal. The method includes a step of inserting the second module in the first module up to a determined distance such that the first and second modules are only partially assembled. The second shaft is centered with respect to the journal, the centering being controlled on the basis of measuring distance deviations with respect to a reference on the journal. The journal is expanded by heating its outer surface. After the step of expanding, the second module is displaced inside the first module so as to complete the assembly. This displacement step is started based on a predetermined temperature.

Abstract: A bearing system includes a first bearing ring, a second bearing ring spaced radially outwards from the first bearing ring, and a bearing cage between the first bearing ring and the second bearing ring. The bearing cage includes a circumferential outer side, a circumferential inner side, and a plurality of circumferentially spaced retainer portions between an axially forward end and an axially trailing end. Roller elements are located in the plurality of retainer portions of the bearing cage. At least one fluid nozzle is axially spaced from the bearing cage for dispensing a fluid to the roller elements.

Abstract: A cooling fan for cooling a heat source includes a frame (10), a stator (20) mounted in the frame, a rotor (30) rotatably attached in the frame, a cover (40) fixed on the frame, and a pair of bearings (50, 60) received in the cover and the frame respectively. The rotor includes an impeller and a shaft (36) inserted through the impeller, wherein the shaft has an upper portion being received in one of the pair of bearings in the cover, and a lower portion being received in another one of the pair of bearing in the frame; thus, a vibration of the shaft can be prevented by supports of the pair of bearings, and the rotor is able to maintain a stable rotation, as the cooling fan is in a high speed operation.

Abstract: A bearing mounting system for use in a gas turbine engine having a low pressure turbine supported on a low pressure shaft through a support rotor comprises a low pressure turbine case, a forward bearing and an aft bearing, and a forward support structure and an aft support structure. The low pressure turbine case surrounds the low pressure turbine. The forward bearing and the aft bearing are positioned on the low pressure shaft to straddle the support rotor. The forward support structure and the aft support structure connect the forward bearing and the aft bearing, respectively, to the low pressure turbine case. The low pressure shaft extends axially between the forward bearing and the aft bearing. In one embodiment, the turbine comprises a plurality of adjacent rotor disks, and the support rotor comprises a conical support connecting one of the rotor disks with the shaft.

Abstract: The present invention relates to a support structure and a method for assembling a support structure in a turbine or compressor engine for rotatably supporting a rotor member in a stator member. The support structure includes an inner ring, an outer ring and a plurality of struts which extend radially between the inner ring and the outer ring. The inner ring has integrated portions projecting in the direction of the struts and forming end connections for the struts. The integrated end connecting portions of the inner ring are together with the ring made by a metal alloy having initially oversized cross sectional dimensions relative to the cross sectional dimensions of corresponding strut, followed by working at least one lateral surface for removing material. The purpose is to achieve final dimensions and position to conform to the cross sectional dimensions and correct position of each corresponding strut.

Abstract: Gas turbine engines and related systems involving offset hub struts are provided. In this regard, a representative bearing assembly for a gas turbine engine includes: a bearing operative to support a rotatable shaft; an annular hub positioned about the bearing; and an annular array of struts extending radially outwardly from the hub, at least two of the struts being positioned in different planes, the planes being oriented transversely with respect to the rotatable shaft. The method of assembling the struts by mounting first and second pluralities of struts, each plurality in a common plane, between the hub and the turbine exhaust case, with the second plurality of struts longitudinally offset from the first plurality of struts.

Abstract: A retention system for a fan in a gas turbine engine includes a shaft that is rotatable relative to a bearing support structure about an axis. The retention system includes fore and aft bearings that rotatably support the shaft, with the fore and aft bearings being spaced apart from each other in a direction along the axis. A machined spring reacts between the bearing support structure and the fore bearing to provide a desired axial preload.

Abstract: A sequential stiffness support is provided for a bearing assembly to improve vibration characteristics of a gas turbine engine and to provide a variable structural stiffness to the support to minimize unbalance load transmissibility. In one embodiment, and by way of example only, the sequential stiffness support includes an inner ring, an outer ring, and means for coupling the inner ring and the outer ring. The sequential stiffness support is configured to provide a first stiffness support at a first engine speed and a second stiffness support at speeds greater than the first engine speed. Methods of manufacturing the sequential stiffness support are also provided.

Abstract: In a turbofan gas turbine engine, a fan shaft is rotatably mounted and radially supported by a bearing in a bearing support structure supported from a fixed engine structure by radially frangible bolts and radially extending spokes. The radially inner ends of the radially extending spokes are mounted on a common member that engages the bearing support structure. The radially outer ends of the radially extending spokes are mounted on a fixed engine structure located radially outwardly of the bearing support structure. The radially extending spokes are held in tension and include a super elastic material to exert a radially inward restoring force on the bearing support structure, subsequent to any radial excursion of at least part of the fan shaft relative to an engine rotational axis (X) following any fracture of the frangible bolts.

Abstract: Component parts for a mixing assembly adapted to be used with clean in place techniques. The component parts may include an impeller assembly, an adjustable hub assembly, and a steady bearing assembly. The bearing assembly may include a supporting structure having a fitting and a plurality of legs extending from the fitting and securely engaging the vessel, and a guide bearing bore adapted to receive a shaft, wherein the guide bearing is adapted to be removably engaged from the supporting structure and wherein the guide bearing is removable from the supporting structure shaft without necessitating removal or lifting of the shaft.

Abstract: A compact bearing support operable for supporting and damping movement of a bearing assembly. The bearing support includes a plurality of flexible elements engaging the bearing assembly in a plurality of locations.

Abstract: A guide vane for a gas turbine aircraft engine includes an aerodynamic shell for turning a flow of working fluid and an internal spar spaced from the aerodynamic shell by an air gap and reinforced by stiffeners.

Abstract: A turbine section of an engine that includes a shaft, a plurality of blades extending radially relative to the shaft, a bearing assembly, a flowpath housing, and a shroud is provided. The bearing assembly is mounted to the shaft adjacent to the plurality of blades. The flowpath housing is coupled to the bearing assembly and includes an inner cylinder, an outer cylinder, and a strut. The inner and outer cylinders each include a strut attachment point between which the strut is coupled, and the outer cylinder includes an outer surface. The shroud is disposed concentric to the outer cylinder and has an inner surface including a groove formed therein that is substantially aligned with the outer cylinder strut attachment point. The groove has a depth that provides and maintains a gap between the outer cylinder outer surface and the shroud inner surface when the flowpath housing is exposed to heat and the strut radially expands.

Abstract: A windmill 10 includes a frame 11 and a rotor 12 provided rotatively around the vertical shaft center. The rotor includes bosses 23, 24 located above and below, plural transversal blades 25 extending radially from the bosses, longitudinal blades 26 held by the front edges of the transversal blades 25 of both above and below bosses. The frame includes bearing 19, 20 supporting the bosses 23, 24 of the rotor rotatively around the vertical shaft center, spokes 17 provided radially supporting the bearing, and legs 15 holding the spoke 17 away from the ground. In the lower bearing 20, a generator connected to the boss 24 of the rotor 12 is accommodated.

Abstract: A recuperator and turbine support adapter for securing a recuperator to a combustor case is provided. The recuperator and turbine support adapter comprises an outer strutted body, an inner strutted body and a thermal spring. The thermal spring allows for thermal expansion of the recuperator and turbine support adapter while alleviating any stress or fatigue damage to the adapter. Each of the outer strutted bodies further comprises an outer ring and an inner ring connected by a plurality of struts. The recuperator and turbine support adapter also provides a means of directing the flow of cold compressed air to the recuperator and the return of the recuperator heated air to the combustor/turbine module.

Abstract: A structural turbine exhaust case of a gas turbine engine, comprises inner and outer case portions; a bearing housing connected to the inner case portion for supporting a main spool of the gas turbine engine; and a plurality of airfoils extending between the inner and outer case portions, airfoils structurally connecting the inner case portion to the outer case portion.

Abstract: A bearing support for a rotor of an aircraft turbine engine which includes a front bearing and a front bearing support and bearing strut for securely attaching the front bearing, to the aircraft turbine engine support structure, wherein the front bearing support and bearing strut are integral with the aircraft turbine engine support structure.

Abstract: To further isolate imbalances in a rotating structure such as a gas turbine engine, an effective length between two bearings may exceed an actual length. This may be achieved via one or more tapering bearing supports associated with at least one of the bearings.

Abstract: The invention relates to a turbine installation, especially a steam turbine installation. The inventive turbine installation comprises at least two partial turbines, each of the partial turbines having a rotor disk that extends along the main axis. Said rotor disks are rigidly interlinked to a shafting. At least one of the partial turbines has an inner housing that concentrically encloses the rotor disk and that is mounted so as to be axially displaceable in a bearing area. To allow for an axial displacement a push element transmits the axial force and is linked with the inner housing. In order to allow the inner housing to be axially displaced as easily as possible, the bearing area has a bearing device with a static friction and/or sliding friction that is so low that the axial misplacement that spontaneously occurs when the static friction is overcome during displacement of the inner housing is smaller 2 mm.

Abstract: An impeller for a magnetic-drive centrifugal pump includes a core for supporting a magnetic assembly of magnets. An inner barrier covers at least part of the magnets. The inner barrier hermetically isolates the magnetic assembly within the impeller. For example, in one embodiment the inner barrier may be sealed or hermetically connected to the core at one or more seams. An outer barrier overlies the inner barrier.

Abstract: A method of assembling a gas turbine engine includes coupling an inner engine casing to an outer engine casing such that an annular flow path is defined therebetween, coupling a plurality of circumferentially-spaced support struts between the inner and outer casings, and coupling a plurality of circumferentially-spaced outlet guide vanes within the flow path upstream from the support struts, such that a first circumferential spacing is defined between a first guide vane and a second guide vane, and a second circumferential spacing is defined between the second guide vane and a third guide vane. The guide vanes are arranged such that the second guide vane is between the first and third guide vanes and the second circumferential spacing is different from the first circumferential spacing.

Abstract: An arrangement for the releasable fastening of struts serving as bearing carriers for the rotor of an aeronautical gas turbine to the casing structure of the aeronautical gas turbine, with stop faces, arranged in the circumferential direction and in the axial direction of the rotor of the gas turbine, at that end of the strut which faces away and acts as a connection head, the stop faces being assigned matching stop faces on the casing structure of the aeronautical gas turbine, and with a screw connection, inclined at an angle, between the casing structure and the connection head of the strut, for the purpose of the positive and non-positive retention of the strut on the casing structure.

Abstract: A turbomachine frame member including an annular inner hub and a concentric annular outer casing that is spaced radially outwardly from the inner hub to define an annular flow passageway. A plurality of substantially radially-extending, circumferentially-spaced struts interconnect the inner hub and outer casing. The struts are connected to the outer casing by respective pairs of connecting bolts that pass through the outer casing and into the struts to engage barrel nuts.

Abstract: A turbomachine frame member including an annular inner hub and a concentric annular outer casing that is spaced radially outwardly from the inner hub to define an annular flow passageway. A plurality of substantially radially-extending, circumferentially-spaced struts interconnect the inner hub and outer casing. The struts are connected to the outer casing by respective pairs of connecting bolts that pass through the outer casing and into the struts to engage barrel nuts.

Abstract: A casing (12) for a steam turbine section has a housing (14) installed therein for a bearing supporting a rotor for buckets. A housing support structure (10) includes a pair of horizontally extending struts (T1-T2) extending from a side (18) of the casing to the housing and a second pair of struts (T3, not shown) extending from the opposite side of the casing to the housing. The struts are in fluid communication with the interior of the housing and the atmosphere and both support the housing within the casing and vent the interior of the housing. Vertical struts (T4-T6) also extend between the casing and the housing. A foundation plate (20) is installed beneath the casing, and a pair of gibs (28) are installed on opposite sides of the casing along the longitudinal centerline thereof to strengthen the casing and prevent tilting of components within the casing when a vacuum within the casing is present.

Abstract: A method for installing an expandable stiffener includes providing an assembly including a first sidewall and a second sidewall connected at a leading and trailing edge such that a cavity is defined therebetween, forming an opening extending through the first sidewall and the second sidewall, inserting a first expandable sleeve through the assembly opening such that the sleeve extends between the first and second strut sidewalls, and coupling the sleeve to the first and second sidewalls.

Abstract: A gas turbine engine having an exhaust casing that includes a plurality of fairings that shield struts that are affixed to and extend between concentric rings. Each fairing has a moveable tail section that is adjusted during turbine operation to change the angle of attack of the exhaust gases to minimize vortex shedding and the corresponding vibrations that result.

Abstract: The inner barrel of a turbine has a plurality of holes for receiving compressor discharge air and flowing such air within the inner barrel. A plurality of replaceable nozzles having internal bores of different diameters are selectively screw threaded into the openings of the inner barrel body enabling, with different diameters, a variation in the flow of compressor discharge air entering the inner barrel.

Abstract: An outer shape of a section in the longitudinal direction at a leading edge of the strut is an aerofoil whose thickness is gradually increased along a flow direction of the combustion gas to prevent reduction of turbine efficiency caused by a shock wave generated at the strut of the exhaust diffuser.

Abstract: A thermal turbomachine, an axial flow gas turbine (10) in particular, includes a rotor (16), which at its exit side is supported on a bearing (15), which is situated on a bearing saddle (14) within an annular inner part (11) of an exhaust casing, the bearing saddle (14) being supported on a foundation of the machine by means of a spring support (25). In such a turbomachine, the stiffness of the bearing support is improved or restored by attaching the bearing saddle (14) to the inner part (11) of the exhaust casing by a spring-loaded bolted connection (19, . . . .,22).

Abstract: An annular hanger for supporting an annular wall element from a gas turbine engine annular outer casing is circumscribed about a centerline extending in opposite first and second axial directions and has an annular first hook extending in the first axial direction from said body section and an annular second hook extending in the second axial direction. One of the hooks has circumferentially spaced apart tabs extending equal axial lengths from the body section and corresponding notches circumferentially disposed between a corresponding adjacent pair of the tabs. The annular hanger is used to support at least in part a wall element from the outer casing as part of a bayonet mount. The bayonet mount further includes a bayonet slot on one of the casing and the wall element and the hanger tabs are received within the bayonet slot.