| Entries |
| Document | Title | Date |
|---|
| 20080199309 | Removable bearing arrangement for a wind turbine generator - A wind generator having removable change-out bearings includes a rotor and a stator, locking bolts configured to lock the rotor and stator, a removable bearing sub-assembly having at least one shrunk-on bearing installed, and removable mounting bolts configured to engage the bearing sub-assembly and to allow the removable bearing sub-assembly to be removed when the removable mounting bolts are removed. | 08-21-2008 |
| 20080260521 | Sealing arrangement - A sealing assembly comprises a bore in a housing, a plurality of seal rings and a shaft. The bore comprises a plurality of seats disposed at different seat radius for the seal rings. The bore comprises for each pair of adjacent seats axially inward of an inner end of the outward seat and proximate to the inward seat a chamfer extending radially inwardly over an inward axial distance. The chamfer between each pair of seats allows for the radial contraction of the seal rings upon assembly. | 10-23-2008 |
| 20080273966 | COOLANT PUMP - A coolant pump includes a housing having an internal axis; a bearing disposed on an outside surface of the housing; a shaft disposed along the internal axis of the housing, wherein the shaft is journaled by the bearing so as to be rotatable; an impeller disposed on the shaft so as to rotate with the shaft; and a seal disposed on the shaft at least partially inside of the bearing so that the bearing overlaps the seal along the internal axis of the housing, wherein the bearing has an inner diameter, the seal has an outer diameter, and the inner diameter of the bearing is greater than the outer diameter of the seal. An internal combustion engine incorporating a cooling system connected to a coolant pump in accordance with the invention is also disclosed. | 11-06-2008 |
| 20090010753 | Radiator-fan with Integral Plastic Molding Magnetic Loop for Energy Saving - The present invention pertains to a radiator-fan with integral plastic molding magnetic loop for energy saving comprising a pedestal and a blades assembly. Wherein, the pedestal has a newel for permitting an oiliness bearing and a bearing to mount therein and a PCB and a coil stator to surround it. Additionally, the blade assembly comprises a fan blade module, a plastic molding magnetic loop and an axle center disposed inside the blade module. Accordingly, the plastic molding magnetic loop substantially substitutes for the conventional rubber magnetic ring and magnetic frame unit and integrates the axle center into the fan blade module via the balance-free technique, thereby generating the integral blade assembly, which thus directly assembles with the pedestal. Therefore, the integral formation of the present invention enhances the quality and productivity, provides a higher stability of the product, and decreases the costs by streamlining components. | 01-08-2009 |
| 20090022582 | PUMP FOR PUMPING CONTAMINATED LIQUID INCLUDING SOLID MATTER - The invention relates to a pump for pumping contaminated liquid including solid matter, comprising an impeller ( | 01-22-2009 |
| 20090081027 | SEAL IN GAS TURBINE - A seal assembly for a gas turbine is arranged in grooves of a rotor heat shield having several bends. The assembly comprises four seal portions overlapping one another and extending in the axial, radial, and circumferential direction with respect to the turbine rotor. A holding means retains the radial sections of one seal portion allowing a limited movement of said seal portion independent of another seal portion. The independent movement assures contact of the individual seal portions with all mating surfaces of the rotor heat shield and improved sealing function regardless of displacements of the rotor heat shield and tolerances of turbine parts. | 03-26-2009 |
| 20090148274 | COMPACT BEARING SUPPORT - The compact squirrel-cage bearing support comprises a first end portion, a second end portion axially spaced from the first end portion, and a plurality of beams interconnecting the first end portion to the second end portion. The beams have a length that is greater than an axial spacing between the first end portion and the second end portion. | 06-11-2009 |
| 20090148275 | Laminate air seal for a gas turbine engine - A laminate air seal for a gas turbine engine includes at least one fabric layer made of fiberglass, ceramic fiber, basalt and/or carbon, and a polymeric resin that is stable at an operating temperature of the gas turbine engine. The resin may be preimpregnated into the fabric layers, or introduced into the fabric during assembly and formation of the laminate. The resin may be polyimide, bismaelimide (BMI) or cyanate ester. A particular resin selected may depend, in part, on the operating temperatures in that region of the gas turbine engine. In some embodiments, the laminate seal may include a coating to increase lubricity of the seal. In one embodiment, the laminate air seal is used to seal a gap between a pylon fairing and an exhaust nozzle of the turbine engine. | 06-11-2009 |
| 20090155059 | CENTRIFUGAL BLOWER - A centrifugal blower includes a casing, a motor fixed in the casing, a fan structure, and an anti-leakage element. The casing has a top portion having an inlet, a bottom portion, and a side wall respectively connecting the top and bottom portions and having an outlet. The fan structure disposed in the casing and driven by the motor has a body connected to the motor and blades surrounding the body and being connected to the body, and rotates about an axis in a first rotation direction. The anti-leakage element extends from at least part of an edge of the inlet to an interior of the casing, partially covers parts of the blades, and extends from neighborhood of the outlet in a second rotation direction against the first rotation direction. A range of the anti-leakage element extending to the interior of the casing is gradually reduced along the second rotation direction. | 06-18-2009 |
| 20090175717 | Multistage Turbocompressor - A dynamic compressor, in particular a turbo compressor, having an exterior housing, a compressor unit featuring a tubular housing with an outer wall and a circular cross section, wherein the compressor unit is received by a circular opening which is located in the exterior housing and has an inner wall. Two compressor elements, which are at a distance from each other, are provided between the outer wall of the tubular housing and the inner wall of the opening in which the compressor unit is received, and wherein, furthermore, a fluid supply line is provided which penetrates the exterior housing and extends between the compressor elements which are at a distance from each other. | 07-09-2009 |
| 20090202343 | TURBOCHARGER SHAFT BEARING SYSTEM - An improved bearing system is provided for use in high speed rotating machinery such as a turbocharger, wherein a turbocharger shaft is rotatably supported at opposite ends by a pair of angular contact bearings subjected to a predetermined and substantially constant thrust pre-load. The angular contact bearings are carried respectively within a pair of generally cylindrical bearing sleeves which cooperatively define an axially split bearing carrier mounted within a turbocharger housing. A spring reacts between these bearing sleeves for applying a substantially constant axial thrust pre-load transmitted by the bearing sleeves to the angular contact bearings. The mechanical spring thrust pre-load may be supplemented or substituted by an hydraulic axial thrust load attributable to oil circulated through the split bearing carrier. | 08-13-2009 |
| 20090246005 | EXHAUST GAS TURBOCHARGER FOR A MOTOR VEHICLE - The present invention relates to an exhaust gas turbocharger for a motor vehicle, comprising a turbine housing having a first area in which exhaust is carried to a turbine wheel and in which the turbine wheel is essentially situated and having a second area connected axially to the first area, such that the first area and the second area are essentially separated from one another by a separating element. It is provided that for thermal insulation, the separating element ( | 10-01-2009 |
| 20090285674 | METHOD AND APPARATUS FOR SUPPORTING ROTOR ASSEMBLIES DURING UNBALANCES - A method and apparatus for reducing dynamic loading of a gas turbine engine is provided. The gas turbine engine includes a rotor shaft assembly including a rotor shaft, a bearing assembly, a mounting race, and a support frame, the mounting race including a spherical surface. The method includes supporting the rotor shaft on the gas turbine engine support frame with the bearing assembly, the rotor shaft including a yield portion configured to permit bending of the rotor shaft during an imbalance operation. | 11-19-2009 |
| 20090304497 | GUIDE BLADE SEGMENT OF A GAS TURBINE AND METHOD FOR ITS PRODUCTION - A guide blade segment of a gas turbine, having at least one guide blade and having an inner cover band assigned to the radially inner end of the or each guide blade, is disclosed. An integral constituent part of the inner cover band of the guide blade segment is a sealing element, which serves to seal a radially inner gap between the guide blade segment and a gas turbine rotor. | 12-10-2009 |
| 20090324393 | Ceramic matrix composite turbine engine component - Aspects of the invention are directed to a gas turbine component such as a ring seal segment or combustor heat shield having a base and a plurality of walls defining a volume. The base and the walls are independently formed and are formed from ceramic matrix composite plates. The base and walls can have interconnection structures that allow for assembly. The base and walls can be coated or otherwise wrapped for connection. Locking mechanisms, such as self locking lugs, can be used for assembly. | 12-31-2009 |
| 20100008767 | SPHERICAL THRUST BEARING SYSTEM FOR TURBOCHARGERS - A turbocharger thrust bearing assembly, which maintains a constant relationship between the thrust faces, for example by use of gimbal or spherical segment geometry. Spherical geometry, while more difficult to manufacture than that of a flat thrust bearing, provides a more constant relationship between the thrust pads and thrust washers than is possible with a typical flat thrust bearing. As a consequence of this more constant relationship the thrust bearing operates with less oil flow, which ultimately may reduce vehicle emissions. | 01-14-2010 |
| 20100143100 | Jet Engine With Active-Magnetic Bearing - Jet engine ( | 06-10-2010 |
| 20100150702 | FLEXIBLE SHAFT FOR GAS TURBINE ENGINE - A shaft for a gas turbine engine is provided that includes a first shaft section, a second shaft section, a first flexible linkage, and a second flexible linkage. The first shaft section extends between a forward axial end and an aft axial end along a first axial centerline. The second shaft section extends between a forward axial end and an aft axial end along a second axial centerline. The first flexible linkage includes a bridge section connected between a first diaphragm and a second diaphragm. The first diaphragm is connected to the aft axial end of the first shaft section. The second diaphragm is connected to the forward axial end of the second shaft section. The second flexible linkage includes a diaphragm and a hub. The second flexible linkage diaphragm cantilevers radially outwardly from an inner radial end to an outer radial end, and is connected to the aft axial end of the second shaft section. The hub is connected to the outer radial end of the second flexible linkage diaphragm, and includes an engine shaft coupling connected to the hub. | 06-17-2010 |
| 20100178159 | Turbine Bucket Angel Wing Compression Seal - The present application provides an angel wing seal for a turbine bucket. The angel wing seal may include a first wing with a sinusoidally-shaped outer edge and a number of wing teeth positioned thereon. | 07-15-2010 |
| 20100226759 | BEARING APPARATUSES, SYSTEMS INCLUDING SAME, AND RELATED METHODS - A bearing apparatus is disclosed. Such a bearing apparatus may comprise a rotor including at least one bearing element mounted to the rotor and a stator including at least one bearing element mounted to the stator. At least one compliant member may be positioned between at least one selected bearing element of the at least one bearing element mounted to the rotor and the at least one bearing element mounted to the stator. Mechanical systems including such a bearing apparatus are disclosed, such as, for example, a motor for use in subterranean drilling. A method of assembling a bearing apparatus is disclosed. More specifically, a rotor and a stator each including at least one bearing element may be provided and a compressive force may be applied to the rotor and the stator to compress the bearing surfaces of the rotor and the stator against one another. Rotors and stators are disclosed. | 09-09-2010 |
| 20100247294 | METHOD AND APPARATUS FOR TURBINE INTERSTAGE SEAL RING - A seal assembly for a gas turbine engine including a seal member and an interstage seal ring including an axially forward member coupled to a first radially inward surface of a first disk and an axially aft member coupled to a second radially inward surface of a second disk, wherein the seal ring is configured to move in an axial direction while the upstream and downstream arms are coupled to the first and second disk respectively. | 09-30-2010 |
| 20100247295 | Tapered Roller Bearing - A two-row tapered roller bearing includes an outer ring ( | 09-30-2010 |
| 20100247296 | TURBOCHARGER - Turbulence of exhaust gas in a turbine impeller outlet is reduced with a simple structure to improve efficiency of a turbine. | 09-30-2010 |
| 20100284794 | Low pressure turbine rotor disk - A low pressure turbine rotor disk for a small twin spool gas turbine engine in which the rotor disk includes a forward side cavity large enough to allow for the bearing assembly that rotatably supports the rotor disk to fit within the cavity in order to shorten the axial distance between the bearings that support the inner rotor shaft on which the turbine rotor disk is secured. Minimizing the bearings spacing allows for a high critical speed for the inner rotor shaft and therefore allows for the small twin spool gas turbine engine to operate at this small scale. The turbine rotor disk also includes a plurality of axial aligned cooling air holes to allow for cooling air from the bearings to flow out from the aft end of the rotor disk. The inner surface of the cavity is an annular surface that forms a seal with knife edges extending outward from the bearing support plate also located within the cavity. The rotor disk includes an annular groove facing outward and on the rear side of the disk to allow for a tool to be inserted for removing the rotor disk from the shaft. An axial central opening in the rotor disk allows for insertion of the shaft and is formed with a bearing race abutment surface on the forward side and a nut abutment surface of the aft side used to compress the rotor disk assembly on the inner rotor shaft. | 11-11-2010 |
| 20100322758 | COMPRESSOR OF A GAS TURBINE - The invention relates to a compressor, particularly a high pressure compressor, of a gas turbine, particularly of a gas turbine aircraft engine, having at least one rotating blade ring on the rotor side, and having at least one guide blade ring on the stator side, wherein the, or each, guide blade ring is formed of a plurality of guide blade segments, and wherein each guide blade segment is formed of a plurality of individual blades. According to the invention, adjacent individual blades ( | 12-23-2010 |
| 20100329854 | SUPERCHARGER - A centrifugal supercharger is provided. One embodiment of the supercharger comprises a two-piece housing wherein a parting area is substantially aligned with a rotational axis of a drive or impeller shaft. Another embodiment comprises a sleeve, or intermediate member disposed substantially between the housing and a bearing assembly(s) located within the supercharger housing. Another embodiment comprises a disengagement device located between the supercharger impeller and the engine. The disengagement device allows selective disengagement of the impeller from the engine. This Abstract is provided for the sole purpose of complying with the Abstract requirement rules that allow a reader to quickly ascertain the subject matter of the disclosure contained therein. This Abstract is submitted with the explicit understanding that it will not be used to interpret or to limit the scope or the meaning of the claims. | 12-30-2010 |
| 20110008154 | Sealing Arrangement for Turbine Engine Having Ceramic Components - A sealing arrangement for use in a turbine engine having ceramic components. The sealing arrangement is retained in a seal gap formed between adjacent segments and is compliant to accommodate variations in the size of the seal gap as the adjacent segments move relative to one another. | 01-13-2011 |
| 20110038716 | THRUST BEARING, ESPECIALLY FOR A TURBOCHARGER - The invention relates to an axial bearing ( | 02-17-2011 |
| 20110038717 | OIL-FREE TURBOCHARGER ASSEMBLY - The present invention relates to an oil-free turbocharger assembly using an airfoil bearing that may be useful in high speed conditions. The assembly can be cooled easily. A heat-proof coating can also be easily applied to the turbo charger's rotating shaft. In one embodiment, an oil-free turbocharger assembly has a constant distance between a journal portion and a rotating shaft so that the mass of the rotating body can be minimized and the rotating body assembly can have a small moment of inertia. The turbocharger in some embodiments of the invention may be cooled by a refrigerant which improves cooling efficiency. Each part of the rotating body assembly in some embodiments may be individually treated with a heat-proof process so that productivity can be improved. | 02-17-2011 |
| 20110052375 | BEARING SYSTEM FOR ROTOR IN ROTATING MACHINES - A bearing system for a rotor in rotating machines, such as compressors, pumps, turbines, expanders, has points of bearing and sealing for the rotor each being in the form of a combined bearing and sealing formed by a stator situated within a rotating machine house and surrounding the rotor. The stator is formed with a bore, whereby an annular clearance is created between stator and rotor, and the bore is having sectional area gradually increasing in the direction of larger pressure within the rotating machine. | 03-03-2011 |
| 20110081235 | TURBINE ENGINE ALLOYS AND CRYSTALLINE ORIENTATIONS - A method is provided for engineering a single crystal cast gas turbine engine first component for cooperating with a second component. An at least local first operational stress on the first component is determined. The first operational stress has a first direction. A crystal orientation within the component or a physical configuration of the component is selected so that the first operational stress produces a desired engagement of the first component with the second component associated with either a negative Poisson's effect or high Poisson's effect in a second direction. Single crystal or highly textured iron- and nickel-base alloys enable one to use such effect in high temperature and/or corrosive environments. | 04-07-2011 |
| 20110110769 | WIND TURBINE COMPRISING A MAIN BEARING AND METHOD FOR REPLACEMENT OF THE MAIN BEARING - A wind turbine is provided comprising a rotatable main shaft having a centre axis and being at least indirectly connected to a wind turbine rotor of the turbine and a main bearing supporting the rotatable main shaft at least indirectly against a first stationary part of the turbine, wherein fastening unit are provided for fastening the rotor to the first or a second stationary part of the turbine during replacement of the main bearing and tappet unit are provided which are able to act on the main bearing and permit a movement of the main bearing relatively to the first stationary part in the direction of the centre axis. A method for replacement of a main bearing is also provided. | 05-12-2011 |
| 20110123317 | CENTRIFUGAL PUMP - A centrifugal pump includes at least one impeller (4) and at least one sealing arrangement arranged between the impeller (4) and a housing wall. The sealing arrangement seals a suction side of the impeller (4) with respect to a pressure side of the impeller (4). The sealing arrangement including a seal (12) fastened on the impeller (4) in a rotationally fixed manner. | 05-26-2011 |
| 20110135451 | GAS TURBINE - A gas turbine includes a turbine section; an annular combustor disposed upstream of the turbine section and configured to discharge a hot gas flow on an outlet side to the turbine section; an outer shell delimiting the combustor and splittable at a parting plane; a plenum enclosing the outer shell; a rotor; a turbine vane carrier encompassing the rotor; a plurality of stator vanes disposed on the vane carrier, and at least two sealing segments forming a ring, each of the at least two sealing segments having an inner edge and a head and a foot section and being movably mounted on the inner edge by the foot section to the outer shell and by the head section to the turbine vane carrier so as to mechanically connect the combustor to the turbine vane carrier. | 06-09-2011 |
| 20110135452 | Pod Drive - A propeller pod drive for a vessel has at least one driveshaft for driving a propeller, at least one radial bearing arrangement for receiving radial forces, at least one axial bearing arrangement for receiving axial forces of the driveshaft. A thrust collar is supported in axial direction on at least one side in axial direction at a guide device, and a supporting structure for arranging the at least one radial bearing arrangement and the axial bearing arrangement. The guide device has at least three, axial sliding segments arranged in a segment guide and each of which has a sliding surface in contact with the thrust collar. | 06-09-2011 |
| 20110142604 | EXHAUST-GAS TURBOCHARGER - The invention relates to an exhaust-gas turbocharger ( | 06-16-2011 |
| 20110150635 | SEAL AND SEAL ARRANGEMENT FOR CONFINING LEAKAGE FLOWS BETWEEN ADJACENT COMPONENTS OF TURBO-MACHINES AND GAS TURBINES - A seal for stemming leakage flows between adjacent components ( | 06-23-2011 |
| 20110158793 | VANE ASSEMBLY HAVING A VANE END SEAL - One embodiment of the present invention is a unique turbomachinery device, a non-limiting example of which is a gas turbine engine. Another embodiment is a unique vane assembly for a turbomachinery device. Another embodiment is a unique seal assembly for a vane of a turbomachinery device. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for turbomachinery devices, and for vane assemblies and seal assemblies for turbomachinery devices. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith. | 06-30-2011 |
| 20110176914 | Turbocharger and blade bearing ring therefor - A blade bearing ring for turbocharger application in diesel engines is described, which consists of an iron-based alloy with an austenitic basic structure having dendritic carbide precipitations. | 07-21-2011 |
| 20110182718 | CENTRIFUGAL PUMP ASSEMBLY - A centrifugal pump assembly with at least one impeller ( | 07-28-2011 |
| 20110188999 | Axial turbine for a gas turbine with limited play between blades and housing - An axial turbine for a gas turbine including a rotor blade cascade is provided. The rotor blade cascade is formed from rotor blades each including, a front edge, a blade tip, and an annular space wall that surrounds the rotor blade cascade and includes an annular space inner side, enabling the annular space wall to be arranged directly adjacent to the blade tip forming a radial gap between the covering of the blade tip and the annual space inner side. When the turbine is in operation, the area of the blade tip with the highest pressure load is disposed in the region of the front edges, and the rotor blades in the region of their front edges include a radial projection and the annular space wall includes on the annular space inner side, a peripheral radial recess that interacts with the radial projections such that a minimum is established in the direction of the main through-flow of the turbine. | 08-04-2011 |
| 20110200427 | WINDTURBINE COMPRISING A BEARING SEAL - Wind turbine provided with a bearing supporting a hub carrying rotor blades, the bearing comprising a rotational bearing race connected to the hub and a stationary bearing race, a lubrication area between the bearing races which area is confined at both ends by first seal rings sealing the gap between the rotational bearing race and stationary parts to form a lubrication barrier. At one or both ends of the lubrication area a redundant seal ring is arranged at a distance from the first seal ring in or near the gap to be sealed. | 08-18-2011 |
| 20110223009 | PUMP ASSEMBLY - A pump assembly with a rotatable rotor shaft ( | 09-15-2011 |
| 20110223010 | DEVICE FOR SEALING A BEARING HOUSING OF AN EXHAUST GAS TURBOCHARGER - A device for sealing a bearing housing, which holds lubricating oil, from which a rotor supported inside the housing of an exhaust gas turbocharger is guided into a compressor housing, loadable by a mass flow of a charger. The device includes a fixed partition with a wall extension, a sealing disk fastened on a shaft of the rotor, a separating gap arranged between the sealing disk and the wall extension, and a drip device connected to an oil-collecting channel and directs lubricating oil collected in the oil-collecting channel into an oil drain by gravity. The drip device includes a drain-off surface for lubricating oil, which has a large axial distance from a rotating sealing disk which delimits the separating gap. Lubricating oil which can penetrate into the separating gap is guided into an oil drain of the bearing housing without interacting with the sealing disk. | 09-15-2011 |
| 20110223011 | TURBOCHARGER WITH A BEARING ARRANGEMENT FOR MOUNTING A ROTOR SHAFT - A turbocharger, which is particularly suitable for a motor vehicle, includes: a rotor shaft with a turbine impeller and a compressor impeller disposed thereon. The rotor shaft has a roller bearing assembly for mounting in the housing of the turbocharger. | 09-15-2011 |
| 20110229311 | SEAL ASSEMBLY - A seal assembly comprising a first movable stator member movable between a sealing position and a non-sealing position, a second fixed stator member, the first stator member being movable relative to the second stator member, the seal assembly further comprising at least one flexure member coupled to the second stator member, and at least one biasing member coupled between the at least one flexure and the movable stator for biasing the movable stator to a non-sealing position. | 09-22-2011 |
| 20110229312 | ROLLING BEARING ASSEMBLY AND WIND TURBINE EQUIPPED THEREWITH - A rolling bearing arrangement comprising two rings arranged concentrically and at least regionally one inside the other, and a gap between the rings, such that the rings are rotatable in opposite directions about an axis at the center of the rings and perpendicular to a ring plane, wherein at least one raceway is closed on itself in a circular shape in a plane and is provided with at least one row of symmetrical rolling bodies between the rings, wherein the rolling bodies of one row are guided at generally equidistant spacings by a cage having at least one disk-shaped region is placed in continuously circumferential, groove-shaped depression in the region of the raceway of one bearing ring, and wherein the cage is shaped like a comb, comprising a plurality of spacers that are joined together along a spine region, and, between every two neighboring spacers, a respective pocket for receiving a respective rolling body. | 09-22-2011 |
| 20110236185 | INTERSTAGE SEAL - An interstage seal is provided for installation between forward and aft stage discs of a turbine section of a gas turbine engine. The seal has a forward annular portion, which extends forward to contribute to an air seal at the outer periphery of the forward stage disc, and an aft annular portion, which extends rearward to contribute to an air seal at the outer periphery of the aft stage disc. The seal has a peripheral slot into which static vane inner rails are loadable. The seal includes a first component, which provides the forward annular portion, and a second component, which provides the aft annular portion. The second component is separably connectable to the first component such that the first and second components, when connected, cooperate to form the peripheral slot. Loading the static vane inner rails into the slot prevents the second component separating from the first component. | 09-29-2011 |
| 20110236186 | WIND TURBINE AND A PITCH BEARING FOR A WIND TURBINE - A wind turbine includes a rotor having at least one wind turbine blade connected to a rotor hub through at least one blade pitch bearing. The pitch bearing includes at least one outer ring, at least one centre ring and at least one inner ring. The pitch bearing has a first rolling element arrangement between the outer ring and the centre ring, and a second rolling element arrangement between the centre ring and the inner ring, wherein at least one of the first and the second rolling element arrangements includes at least two rows of rolling elements. The at least two rows are at different axial positions in relation to a rotational axis. The play in the first row of roller elements is greater than the play in the second row of roller elements. A pitch bearing for a wind turbine is also disclosed. | 09-29-2011 |
| 20110236187 | BLOOD PUMP BEARINGS WITH SEPARATED CONTACT SURFACES - Rotary hydrodynamic blood pumps have been used to treat over a thousand patients. The Jarvik 2000 has supported a patient for seven years and uses blood immersed bearings washed by high flow to avoid excessive thrombus formation. This permits the pump to be very simple and small. Nonetheless, the present Jarvik 2000 bearings and all other mechanical blood immersed bearings of the prior art have a supporting structure that predisposes to thrombus adjacent to the bearings. The present invention provides a bearing structure that eliminates this predilection site for thrombus formation, and may provide indefinite thrombus free operation. The rotor of the preferred embodiment includes a tapered hub fabricated of wear resistant material supported by three posts at each end of the rotor, upon which the rotor rotates. Blood washes the unobstructed spaces between the posts to prevent the accumulation of a torus of thrombus that could enlarge excessively. | 09-29-2011 |
| 20110250056 | CIRCUMFERENTIAL SEALING ARRANGEMENT - A circumferential sealing arrangement is disclosed herein. The circumferential sealing arrangement includes a seal runner operable to be fixed to a structure for concurrent rotation with the structure about an axis. The circumferential sealing arrangement also includes a housing that encircles the seal runner or is encircled by the seal runner. The circumferential sealing arrangement also includes a primary seal element at least partially disposed in the housing. The primary seal element includes a first surface cooperating with a second surface of the seal runner to form a circumferential seal between the primary seal element and the seal runner. The circumferential sealing arrangement also includes a secondary seal element positioned between the housing and the primary seal element on a first side of the primary seal element along the axis of rotation. A second side of the primary seal element along the axis of rotation opposite the first side seals against the housing. The secondary seal element generates a biasing force along the axis of rotation urging the second side against the housing. | 10-13-2011 |
| 20110255958 | SEAL MEMBER FOR HOT GAS PATH COMPONENT - A seal member for a hot gas path component in a gas turbine system is provided. The seal member includes a first seal pin, a second seal pin spaced from the first seal pin, and at least one cross-member. The at least one cross-member has a first end and a second end, and may be joined at the first end to the first seal pin and at the second end to the second seal pin. The at least one cross-member is configured to force the first and second seal pins apart when the seal member is subjected to a centrifugal force. | 10-20-2011 |
| 20110280713 | High Volume Pump having low hydrostatic head - A pump for providing high volume flows with a low hydrostatic head. The pump is particularly suited for heated fluids such as those from a solar collector and the like. | 11-17-2011 |
| 20110280714 | Two-Piece Bearing Housing For A Centrifugal Pump - A two-piece bearing housing is provided for use in centrifugal pumps having or requiring multiple chambers for enclosing or confining bearings or seals, and/or providing lubricant or coolant to the bearings and seals of the pump, the two-piece housing providing several improvements including the ability to make the two pieces from different materials, the reduction in scrap castings due to imprecision achieved in the casting process and improved structures in the housing for monitoring the lubricant chambers in the housing. | 11-17-2011 |
| 20110286836 | GEARED TURBOFAN ENGINE WITH INTEGRAL GEAR AND BEARING SUPPORTS - A gas turbine engine includes a bearing and a bearing support having a second wall extending between first and second ends and operatively supported by the bearing at a first end. An engine case is secured to the second end radially outward of the first end. A second wall integral with and extending transversely from the first wall provides a flexible support. The second wall has a flange, and a gear train component is secured to the flange. A gas turbine engine includes a support structure which supports the main rotatable structure via bearings and gear train components. The support provides both the necessary structural support for the rotor structure as well as desired flexibility for a fan drive gear system. | 11-24-2011 |
| 20110286837 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger includes an outer housing, a bearing flange connected to the outer housing by a material joint, and a turbine wheel rotatable about a rotation axis. Formfittingly connected to the bearing flange is an inner housing which is formed with a collar having at least one section in contact with an inner edge of the bearing flange in a direction of the rotation axis of the turbine wheel. | 11-24-2011 |
| 20110286838 | TURBOCHARGER HAVING FASTENING ELEMENTS FOR FASTENING VANE BEARING RINGS OF A VARIABLE TURBINE GEOMETRY VTG - A turbocharger with a variable turbine geometry device has one or two blade bearing rings. At least one or more fastening elements are provided for fastening the one or two blade bearing rings. The respective fastening element has at least one section formed with a knurl and/or at least one section formed with at least one or several notches. | 11-24-2011 |
| 20110293407 | SEAL AND AIRFOIL TIP CLEARANCE CONTROL - A turbine section includes a housing and a blade outer air seal to be mounted on the housing. A flex beam mounts the blade outer air seal onto the housing, with the flex beam being supported on the housing, but free to move relative to the housing. A pressure air chamber is formed on an opposed side of the flex beam from the blade outer air seal. A source of pressurized air is delivered into the chamber to cause the flex beam to move the blade outer air seal toward and away from a central axis of the housing. | 12-01-2011 |
| 20110293408 | SEALING APPARATUS AT THE BLADE SHAFT OF A ROTOR STAGE OF AN AXIAL TURBOMACHINE - A turbomachine is disclosed. The turbomachine includes a rotor, a plurality of blades arranged side by side on the rotor in a circumferential direction, and a plurality of sealing apparatuses each disposed on a respective blade shaft of the plurality of blades. Each of the plurality of sealing apparatuses includes first and second bottom plates protruding in a respective axial direction on the respective blade shaft and first and second bulkheads which extend in a radial direction along the respective blade shaft and form a double-walled seal in the axial direction. A respective rounded or parabolic transitional cross-section from the bottom plates to the bulkheads is provided and at least one of the bulkheads is offset with respect to a blade root edge of the respective blade shaft in a direction toward a radial longitudinal axis of the respective blade shaft. | 12-01-2011 |
| 20110293409 | METHOD OF REPAIRING A FLANGE OF A CASING - The invention relates to a method of repairing a flange of a casing for an airplane turboprop or turbojet, the flange including at least one through hole for passing a bolt for fastening equipment, the hole opening out in a face of the flange that is worn by friction against the equipment. The method consists in mounting a bearing member on the flange, the bearing member comprising a radial wall covering the worn face of the flange, said wall including a hole that comes into register with the hole in the flange and having thickness for compensating the wear of the face of the flange, said member further including an abutment for bearing against the periphery of the flange, and being fastened to the flange by adhesive. | 12-01-2011 |
| 20110311350 | TURBO MACHINE - A turbo machine includes an impeller that rotates to make gas flow, a driving device that rotationally drives the impeller, a rotary shaft that transmits a rotational driving force of the driving device to the impeller, a bearing that rotatably supports the rotary shaft, and a casing that houses at least the driving device and the rotary shaft. In addition, the casing is provided with a grease flow path to supply grease to the bearing for lubricating the bearing. | 12-22-2011 |
| 20110311351 | SHROUD FOR ROTARY ENGINE - Disclosed herein are several embodiments for shroud arrangements to be used in rotary engines using a plurality of rotors within the shroud arrangement. At least one of the rotors is not fixed to the shroud. | 12-22-2011 |
| 20110311352 | METHOD FOR CHECKING THE BEARING ALIGNMENT IN A GAS TURBINE - The disclosure refers to a method and apparatus for checking the bearing alignment of a rotor of a gas turbine or steam turbine having a rotor with a radial offset and a radial offset surface and in a bearing shell, which supports the rotor, with a radial, at least in sections, end surface, wherein the radial offset surface and the radial end surface face the free end of the rotor. The radial offset is arranged in the bearing shell and offset towards the free end of the rotor. The degree of offset in the axial direction with regard to the rotor is measured at least two different circumferential positions around the rotor periphery in order to determine the alignment of the rotor. Differences in the degree of offset at different circumferential positions are used as measurement for the bearing alignment. | 12-22-2011 |
| 20110318170 | TURBINE STAGE - A turbine stage for a turbomachine, the stage comprising a rotor wheel mounted inside a sectorized ring carried by an outer casing, and a sectorized nozzle fastened to the casing downstream from the wheel, each ring sector having a downstream end that is held bearing radially outwards against a cylindrical rail of the casing by means of the nozzle, the casing rail including an annular row of through radial notches reducing the areas for heat exchange by conduction both between the casing and the ring sectors and between the casing and the nozzle. | 12-29-2011 |
| 20120014782 | TURBOCHARGER BEARING HOUSING ASSEMBLY - An assembly for a turbocharger that includes a bearing housing with a cylindrical portion with a bore configured for receipt of a bearing, an extension that extends radially outwardly from the cylindrical portion to a base, the base configured with one or more features for securing the bearing housing to another component, a compressor fitting, a turbine fitting, and lubricant flow paths; and a fluid jacket that includes a cylindrical wall configured for placement over at least a portion of the cylindrical portion of the bearing housing where the cylindrical wall includes a recess configured to accommodate at least a portion of the extension of the bearing housing, a fluid inlet, and a fluid outlet. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed. | 01-19-2012 |
| 20120014783 | Apparatus For Non-Clogging Pumps - Improvements in the operation and maintenance of non-clogging pumps are provided which increase pump efficiencies through improved impeller design and vacuum assembly design, and which increase seal lubrication efficiencies through improved seal lubricant reservoir system design. | 01-19-2012 |
| 20120020777 | DURABLE PUMPS FOR ABRASIVES - Durable pumps for abrasives are provided. In one implementation, an example centrifugal pump or pump stage for subsurface operation has a thrust washer located inside the circumference of a close-fitting clearance seal between an impeller shroud and the diffuser. The relocation of the thrust washer allows the clearance seal to protect the thrust washer from abrasives while the thrust washer supports the impeller against the reaction forces of axial fluid flow. In one implementation, the radius or size of a thrust washer or other seal-like feature is reduced in order to increase exposure of the bottom impeller shroud to pressured fluid, thus balancing pressure at the top and bottom of the impeller to decrease friction between the impeller and the thrust washer. Reducing the radius of the thrust washer also reduces surface area of the washer subject to friction and reduces the moment arm of a braking torque on the rotating impeller, thereby reducing power loss in the pump. | 01-26-2012 |
| 20120034072 | SEAL ASSEMBLY - A seal assembly arranged adjacent to a primary flow region, the seal assembly including: first and second components; a seal arranged between the first and second components to seal a secondary flow region from the primary flow region; and a first recess portion provided in the first component and arranged adjacent to the seal and the primary flow region, the first recess portion further being arranged to receive flow from at least one of the primary flow region and the secondary flow region and shed flow to the primary flow region, wherein the first recess portion is configured to promote a first flow feature within the first recess portion, the first flow feature flowing with a portion of the first flow feature adjacent to the primary flow region and the portion of the first flow feature being shed to the primary flow region in substantially the same direction as the flow in the primary flow region. | 02-09-2012 |
| 20120034073 | ANTI-ROTATION METHOD FOR A ROLLING ELEMENT BEARING CARTRIDGE - To solve heat soak and reduced heat rejection capability problems in turbochargers with rolling element bearings (REBs), the REB cartridge is mounted to the bearing housing in a way that is not rigid, thus allows for an oil damping film, but, at the same time, the REB cartridge is held both axially, to transfer thrust loads to the bearing housing, and rotationally, so that the REB cartridge does not rotate relative to the bearing housing, using male or female features in the REB and corresponding female or male features associated with the bearing bore or the turbine face of the bearing housing closure. | 02-09-2012 |
| 20120057966 | FAN AND MANUFACTURING METHOD THEREOF - A fan includes a motor base, a bearing, an impeller, a stator and a magnetic element. The motor base has a bearing stand in a center portion thereof. The bearing is accommodated within the bearing stand. The impeller includes a metallic case, a hub, plural blades and a rotating shaft. The metallic case has a top surface and a sidewall. The hub is sheathed around the metallic case. The blades are disposed around an outer periphery of the hub. The rotating shaft is protruded from a center portion of the top surface and penetrated through the bearing stand, wherein no raised ring structure is formed in the top surface of the metallic case, and the rotating shaft and the metallic case are jointed together by a laser welding process. The magnetic element is disposed on an inner wall of the metallic case and aligned with the stator. | 03-08-2012 |
| 20120099968 | ABRASIVE ROTOR SHAFT CERAMIC COATING - An abrasive coating on a rotor shaft interacts with cantilevered vanes to form an abradable air seal in a turbine engine. The abrasive coating includes a metal bond coat, and an abrasive layer containing a plurality of abrasive grit particles in a ceramic matrix. The grit particles may be selected from cubic boron nitride (CBN), zirconia, alumina, silicon carbide, diamond and mixtures thereof. | 04-26-2012 |
| 20120099969 | DAMPER SEAL AND VANE ASSEMBLY FOR A GAS TURBINE ENGINE - One embodiment of the present invention is a vane assembly for a gas turbine engine. Another embodiment of the present invention is a damper seal that may be employed in conjunction with a vane assembly of a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods and combinations for vane assemblies and the sealing and damping thereof. Further embodiments, forms, features, aspects, benefits and advantages of the present application shall become apparent from the description and figures provided herewith. | 04-26-2012 |
| 20120114466 | Seal Assembly Segment Joints - The present application provides a sealing assembly for use between a first component and a second component of a rotary machine. The sealing assembly may include a first sealing segment having a first end with a first angled surface and a second sealing segment having a second end with a second angled surface. The first angled surface of the first end of the first sealing segment meets the second angled surface of the second end of the second sealing segment at a joint. | 05-10-2012 |
| 20120148388 | ANNULUS FILLER - An annulus filler for mounting to a rotor disc of a gas turbine engine and for bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler has a body portion including a lid which has a leading edge, a trailing edge and opposing side edges which connect respective ends of the leading and trailing edges. The lid defines an airflow surface for air being drawn through the engine. The annulus filler further has one or more attachment formations which, in use, connect the body portion to the rotor disc. The lid is configured such that the stiffness of the lid under compressive loading exerted on the opposing side edges by sideways blade movement is greater at the leading edge than at the trailing edge. | 06-14-2012 |
| 20120156008 | AIR CYCLE MACHINE SEAL PLATE AND SEAL LAND - An air cycle machine includes turbine and compressor housings respectively having a turbine and a compressor. An insulator seal plate is fastened between the turbine and compressor housings. The insulator seal plate includes a bore. A seal has an outer diameter that engages the bore. The seal also includes an inner diameter provided between lateral sides defining a first width. The inner diameter provides a seal and configured to engage a rotating surface. The outer diameter to the inner diameter provides a first ratio of 1.30-1.31. The inner diameter to the first width provides a second ratio of 1.59-1.61. A rotor shaft is disposed in the seal and includes knife edges extending from the rotor shaft to the seal land. The rotor shaft supports the turbine and the compressor. | 06-21-2012 |
| 20120156009 | FAN SHIELD AND BEARING HOUSING FOR AIR CYCLE MACHINE - A fan shield for an air cycle machine includes a fan shield body in the general shape of a frustum of a cone having curved sides. The curved sides define a radius of curvature and a center point of curvature that corresponds to the radius of curvature. The center point of curvature is an axial distance from a large end of the fan shield body and a radial distance from the central axis such that a ratio of the radial distance to the axial distance is between 1.160 and 1.360. A bearing housing includes a body that defines a cylindrical portion and an annular flange at one end. The annular flange includes a first attachment opening, a second attachment opening and a third attachment opening that are non-uniformly circumferentially spaced around the flange. | 06-21-2012 |
| 20120156010 | BEARING STAND COVER OF AXIAL EXHAUST TURBINE, AND AXIAL EXHAUST TURBINE - According to an embodiment, an upper-side bearing cover 50 | 06-21-2012 |
| 20120171021 | Conduit for Turbomachine and Method - A turbomachine includes a compressor having a cartridge that is configured to slide in and out of an external casing. The turbomachine further includes an electrical motor having a motor shaft configured to be connected to the compressor shaft. A conduit is configured to extend through the statoric part of the compressor or the motor, from a first magnetic bearing to the second magnetic bearing. The conduit includes conduit electrical cables provided inside the conduit and extending from a first end of the conduit to a second end of the conduit; and electrical cables connecting one of the first and second magnetic bearings to an external connector via the conduit electrical cables of the conduit. | 07-05-2012 |
| 20120183390 | PIVOT ARRANGEMENT FOR A MOTORIZED DEVICE - In the exemplary embodiment, an electric rotary fan has a fan head including a rotary motor and a fan blade, the fan blade rotated by the motor for producing an air stream. A pair of rubber bushings are each disposed between the fan head and a stand and each have a hole though the bushing and a key displaced from the hole, the holes of both bushings being coaxially aligned on a horizontal pivot axis. A pair of fasteners each pass through the associated bushing's hole to affix the fan head to the stand such that each fastener and its associated bushing cooperate to allow forced pivoting of the fan head relative to the stand the pivot about the pivot axis. The keys prevent relative pivoting between the bushings and the fan head by each engaging a mating tab hole in the fan head. | 07-19-2012 |
| 20120195741 | AXIAL BRUSH SEAL - A brush seal assembly for turbomachinery having a rotor can include a stationary seal component, a floating seal component coupled to the stationary seal component and circumferentially angled bristles arranged in a bristle pack, disposed in the floating seal component and extended axially with respect to the rotor. | 08-02-2012 |
| 20120213629 | DEVICE FOR CENTERING AND GUIDING THE ROTATION OF A TURBOMACHINE SHAFT - A device for centering and guiding rotation of a turbine engine shaft. The device includes a roller bearing and a ball bearing mounted around the shaft and carried respectively by first and second flexible annular supports, together with an oil film compression damper having a rigid annular support arranged around the roller bearing, the supports of the ball bearing and of the damper, and the roller bearing being stacked transversely, extending one around another. | 08-23-2012 |
| 20120219403 | BEARING CARRIER WITH MULTIPLE LUBRICATION SLOTS - A bearing assembly, a pump with a bearing assembly and a method of lubricating a pump bearing using a bearing assembly. The bearing assembly includes a bearing carrier and a bearing housing that are rotatably connected to one another to permit axial adjustment of the pump's impeller or other fluid-conveying apparatus, as well as variable rotational positioning of the bearing carrier relative to a pump housing. Numerous lubricant access apertures placed around the periphery of the bearing carrier facilitate lubricant passage from a connection on the bearing housing to the bearings, regardless of the rotational position of the carrier relative to the bearing housing or other pump structure. | 08-30-2012 |
| 20120251300 | JOURNAL AIR BEARING FOR SMALL SHAFT DIAMETERS - A bearing foil assembly includes a top foil, an intermediate foil, and a bump foil. The bump foil is provided with corrugations at circumferentially spaced locations. The bump foil has an end that is bent radially outwardly from a center of the foil assembly. The top foil has a bent portion extending radially outwardly and adjacent to the bent end of the bump foil. A first radius of curvature is defined to a curved portion leading into the bent portion at a first end adjacent to the bent end. A second radius of curvature is defined at an end of the bent portion on an end opposed to the bent end. A ratio of the first radius of curvature to the second radius of curvature is between 0.6 and 10. A bearing assembly, a shaft sub-assembly, an air machine, and a method of assembling a bearing into an air machine are also disclosed. | 10-04-2012 |
| 20120251301 | COMPRESSOR - A front housing configuring a scroll compressor is provided in its shaft hole with a first bearing, and the front housing rotatably supports a rotation shaft. The first bearing includes a ball bearing having a plurality of balls. First and second seal rings and are provided between an outer ring fixed to the front housing and an inner ring which abuts against an outer peripheral surface of the rotation shaft. A first seal ring disposed on the side of one side surface of the outer ring is provided such that the first seal ring is in non-contact with the inner ring, and the second seal ring disposed on the side of the other side surface of the outer ring abuts against the inner ring. | 10-04-2012 |
| 20120251302 | TURBOCHARGER WITH VARIABLE TURBINE GEOMETRY - A turbocharger ( | 10-04-2012 |
| 20120294706 | SEALING ARRANGEMENT AND GAS TURBINE ENGINE WITH THE SEALING ARRANGEMENT - At least one sealing arrangement is provided for a connecting mechanism between an inner annular member or an outer annular member and an associated segment to connect between the annular members and the segments. The sealing arrangement includes an elastic sealing member provided between the sealing surfaces, disposed linearly along a side of polygon defined around a central axis. | 11-22-2012 |
| 20120301278 | ENGINE ASSEMBLY INCLUDING TURBOCHARGER - A turbocharger includes a housing, a first rotor wheel, a second rotor wheel, a driveshaft, a first bearing and a second bearing. The housing defines a first region, a second region, an intake air inlet, an intake air outlet and an exhaust gas inlet. The first rotor wheel is located in the first region and the second rotor wheel is located in the second region. The first bearing is located on a first axial side of the first rotor wheel axially between the first and second rotor wheels and supports the driveshaft for rotation relative to the housing. The second bearing is located on a second axial side of the first rotor wheel and supports the first rotor wheel for rotation relative to the housing. | 11-29-2012 |
| 20120308365 | Turbocharger bearing system - A bearing system for a turbocharger shaft comprising a rotatable elongated cylinder with axially spaced journal bearing surfaces on the inside diameter and a thrust face on each end. A sleeve on the shaft incorporates a flange on one end that transmits thrust force to one thrust face on the elongated cylinder. A flanged collar on the opposite end of the shaft transmits thrust force to the thrust face on the opposite end of the elongated cylinder. A radially extending flange on one end of the elongated cylinder transmits thrust forces to stationary housings. | 12-06-2012 |
| 20120308366 | Bearing Assembly - A turbocharger bearing cartridge can include a bearing with an inner race, an outer race and rolling elements disposed between the inner race and the outer race; a journal bearing; and a shell that includes an interior, compressor side annular surface configured to seat the outer race of the bearing and an interior, turbine side annular surface configured to seat the journal bearing. Such a cartridge can optionally include an anti-rotation feature to limit rotation of the shell in a bore of a housing of a turbocharger and can optionally be configured to float in a bore of a housing. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed. | 12-06-2012 |
| 20120328417 | Engine bearing compartment - An engine bearing compartment is provided and includes an engine casing defining a discharge pathway for a fluid to drain from the engine bearing compartment, a shaft rotatably disposed within the engine casing to define an annulus, a housing disposed within the annulus below an elevation of the discharge pathway, an impeller rotatable with the shaft and including a centrifugal element, the impeller being disposed within the annulus at least partially below the discharge pathway elevation whereby, due to impeller rotation, the centrifugal element expels the fluid through the discharge pathway from the annulus above the discharge pathway elevation and a circuit by which fluid expelled through the discharge pathway is communicated to an interior of the housing. | 12-27-2012 |
| 20120328418 | TURBOCHARGER WITH AIR BUFFER SEAL - A turbocharger includes a turbine section, a compressor section and a bearing section. A turbine wheel and a compressor wheel are mounted on a shaft and the shaft is rotatably mounted in a bore of a housing. A lubrication system circulates lubricant through the bearing section. First and second spaced apart seals are positioned along the shaft. A recess is positioned between the first seal and the second seal to define an air buffer chamber. The air buffer chamber is provided with pressurized air to discourage lubricant leakage past the first seal. | 12-27-2012 |
| 20130004300 | SHAFT ASSEMBLY OF AN EXHAUST-GAS TURBOCHARGER - The invention relates to a shaft assembly ( | 01-03-2013 |
| 20130017067 | METHOD OF BEAM WELDING OF AN IMPELLER WITH PERFORMANCE OF TWO PASSES ON A SLOT ; IMPELLER AND TURBO MACHINE HAVING SUCH WELD CONFIGURATIONAANM Cantelli; UgoAACI FlorenceAACO ITAAGP Cantelli; Ugo Florence ITAANM Miniati; EnzoAACI FirenzeAACO ITAAGP Miniati; Enzo Firenze ITAANM Innocenti; MircoAACI FirenzeAACO ITAAGP Innocenti; Mirco Firenze IT - Systems and methods according to these exemplary embodiments provide welding techniques for impeller blades associated with impellers in centrifugal compressors. According to one exemplary embodiment, a connection area of the impeller blade has a “hammer”-shaped cross-sectional area which facilitates beam welding of the connection area to a slot in the surface or body to which the blade is to be connected. | 01-17-2013 |
| 20130017068 | AXIAL TURBINE FOR A ROTARY ATOMIZERAANM Baumann; MichaelAACI FleinAACO DEAAGP Baumann; Michael Flein DEAANM Herre; FrankAACI OberriexingenAACO DEAAGP Herre; Frank Oberriexingen DEAANM Frey; MarcusAACI Weil Der StadtAACO DEAAGP Frey; Marcus Weil Der Stadt DEAANM Seiz; BernhardAACI LauffenAACO DEAAGP Seiz; Bernhard Lauffen DEAANM Krumma; HarryAACI BonnigheimAACO DEAAGP Krumma; Harry Bonnigheim DEAANM Beyl; TimoAACI BesigheimAACO DEAAGP Beyl; Timo Besigheim DEAANM Schiffmann; JurgAACI BernAACO CHAAGP Schiffmann; Jurg Bern CHAANM Scholl; StephanAACI HerzogenbuchseeAACO CHAAGP Scholl; Stephan Herzogenbuchsee CH - A turbine rotor, e.g., for a drive turbine of a rotary atomizer, is disclosed having a rotatably supported turbine shaft with the potential for mounting an atomizer wheel, and having at least one drive turbine wheel having a plurality of turbine blades. The turbine blades of the drive turbine wheel may be impinged on during operation by a drive fluid in order to drive the turbine rotor. The drive turbine wheel may be designed for the drive fluid to axially impinge on the turbine blades. A complete drive turbine having such a turbine rotor is also disclosed, as well as a complete rotary atomizer and individual exemplary components of the drive turbine. | 01-17-2013 |
| 20130094943 | UNDUCTED FAN FOR TURBINE ENGINE - An unducted fan of variable-pitch blades including roots engaged from outside in respective radial housings of an annular rotor element and guided to turn about their respective axes by pairs of rolling bearings, one of which is carried by an annular segment of a cylindrical skirt mounted in a groove of the annular body and by a locknut screwed onto the cylindrical skit. The bearing is covered externally by a ring including outer dog-clutch teeth co-operating with inner dog-clutch teeth of the housing to hold the ring axially in the housing. A blocking mechanism is engaged between the teeth of the housing and the teeth of the ring preventing the ring from turning and preventing the ring from being withdrawn axially from the housing. | 04-18-2013 |
| 20130115057 | MID-TURBINE BEARING SUPPORT - 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. | 05-09-2013 |
| 20130115058 | Stator Seal Structure In Uniaxial Screw Pump - There is provided a stator seal structure in a uniaxial eccentric screw pump by which the abrasion resistance of sealing mechanisms is improved and the pumped fluid can be prevented from stagnating in the sealing mechanisms. The stator seal structure is provided with a pair of sealing mechanisms for sealing between a housing and an intake side end portion, and between the housing and a discharge side end portion of the stator. The pair of sealing mechanisms is provided with ring-shaped secured rings respectively secured to the housing. The secured rings are respectively attached with elastic bodies for ensuring contact pressures between the sliding seal surface of the stator and the sliding seal surface of the secured rings with the elastic forces of the elastic bodies and for sealing between the secured rings and the housing. | 05-09-2013 |
| 20130129488 | FOIL BEARING SUPPORTED MOTOR-DRIVEN BLOWER - A high-speed blower designed to move and circulate dry process gas includes an axial or mixed-flow compressor driven by a brushless permanent magnet synchronous motor utilizing a remotely mounted variable frequency drive. The blower uses foil gas bearings which enable high-speed, low-power loss, and oil-free operation. The blower comprises an outer blower housing and an inner blower housing defining an annular cavity therebetween. A cooling flow of process gas may be leaked through the inner blower housing to cool the internal operational components of the blower, including the motor and the bearings, and to capture heat therefrom, which can be added to the process gas flow moving through the blower. Diffuser vanes and flow-straightening vanes are provided on the outer surface of the inner blower housing to improve the fluid dynamics of the process gas flow through the blower and heat transfer from the inner blower housing. | 05-23-2013 |
| 20130149116 | BEARING HOUSING OF AN EXHAUST-GAS TURBOCHARGER - A bearing housing ( | 06-13-2013 |
| 20130156552 | COST EFFECTIVE HIGH THRUST CAPACITY TURBOCHARGER ASSEMBLY - An assembly for a turbocharger and methods for creating the same are disclosed. Such assembly for a turbocharger includes a bearing housing having first and second bore ends, a housing cavity, and a bearing assembly disposed within the housing cavity. The bearing assembly includes an annular rotating journal positioned at the first bore end and first and second angular contact bearings positioned at the second bore end, where the first and second angular contact bearings resist axial loads in opposite directions. The bearing housing and bearing assembly are configured to receive a shaft and together dampen axial and radial loads in all directions from the shaft. | 06-20-2013 |
| 20130156553 | HONEYCOMB SEAL AND METHOD - A seal for a turbo machine is provided. The seal includes a plurality of honeycomb cells, at least one circumferential groove within the plurality of honeycomb cells, and at least one swirl brake within the at least one groove. | 06-20-2013 |
| 20130170960 | TURBINE ASSEMBLY AND METHOD FOR REDUCING FLUID FLOW BETWEEN TURBINE COMPONENTS - According to one aspect of the invention, a turbine assembly includes a stator and a rotor adjacent to the stator. The turbine assembly also includes a passage formed in a member coupled to the rotor to form a fluid curtain between the rotor and stator, wherein the fluid curtain reduces a flow between the stator and rotor. | 07-04-2013 |
| 20130170961 | LOW EMISSION DRY GAS SEAL SYSTEM FOR COMPRESSORS - Systems and methods according to these exemplary embodiments provide sealing mechanisms for centrifugal compressors. A sealing mechanism includes first, second and third dry gas seals arranged in series. Each seal receives its own sealing gas and has its own venting mechanism. Sealing gas pressures remain low enough that a dedicated compressor for supplying the sealing gases is not needed. Additionally, the risk of process gas being released into the atmosphere in case of seal failure is limited. | 07-04-2013 |
| 20130183144 | BEARING HOUSING OF AN EXHAUST-GAS TURBOCHARGER - A bearing housing ( | 07-18-2013 |
| 20130189083 | FAN - A fan includes an outer casing having an air inlet and an air outlet, and an impeller housing located within the casing. An impeller is provided within the impeller housing for generating an air flow along a path extending from the air inlet to the air outlet through the impeller housing. A motor for driving the impeller is located within a motor housing connected to the impeller housing. A foam annular seal is located between the impeller housing and a seat to inhibit the leakage of air between the impeller housing and the casing. A plurality of resilient supports is provided between the impeller housing and the seat to reduce the load on the annular seal. | 07-25-2013 |
| 20130189084 | ARRANGEMENT, A SEALING ASSEMBLY, A CASING FLANGE AND A SPACER FOR SEALING THE PROPELLER SHAFT OF A MARINE VESSEL - A propeller shaft of a marine vessel is supported by bearing means within a stern tube or frame. The stern tube or frame has an aft end provided with a sealing assembly for sealing the propeller shaft. The sealing assembly and the stern tube or frame have at least one leakage monitor line for monitoring the condition of the sealing assembly. The at least one leakage monitor line is provided with a circumferentially extending channel section. | 07-25-2013 |
| 20130195631 | SPIRAL-GROOVED THRUST BEARING - A thrust-bearing ( | 08-01-2013 |
| 20130195632 | WIND TURBINE WITH BEARING SUPPORT - In order to provide a wind turbine generator with a shaft and a bearing system which bearing system, e.g., using less material or using material which is relatively cheaper or which is not needed to have the same strength in comparison with some other solutions, there is disclosed a wind turbine generator with a bearing system including a lockable connection comprising a bearing surface and a support surface which surfaces are engaged when the lockable connection is locked and where forces from the shaft are transferred via the bearing and into the support through the bearing surface and wherein a support angle of the support surface, relatively to a shaft plane formed by rotating the shaft around a first axis, which first axis is perpendicular to the centre axis and which first axis is comprised in a vertical plane, is ranging from and including 5 degrees to and including 70 degrees. | 08-01-2013 |
| 20130223997 | BEARING ASSEMBLY - A bearing assembly that includes a first bearing, a second bearing, a spring and a sleeve. The spring applies a preload to each of the bearings, and the sleeve surrounds the spring and the bearings. The sleeve includes an end portion that extends axially beyond the first bearing. The end portion includes a step down in the outer diameter that defines a seat for an o-ring. | 08-29-2013 |
| 20130230386 | Diffuser Seal for Geared Turbofan or Turboprop Engines - A diffuser seal for an aft end of a high pressure compressor of a gas turbine engine is disclosed. The diffuser seal includes a flow guide carrier coupled to the diffuser case. The flow guide carrier is also coupled to a static seal. The static seal engages a rotary seal and permits air flow through the static and rotary seals in the aft direction. The flow guide carrier is also coupled to a fairing and a fairing/hub support. The flow guide carrier supports the fairing in a spaced-apart position with respect to the rear hub so that air flowing through the static and rotary seals passes between a forward surface of the fairing and the rear hub. The fairing/hub support extends forward from the flow guide support and engages an aft surface of the fairing thereby limiting movement of the rear hub and fairing in the aft direction. This design helps to prevent parts or debris from piercing the rear hub and entering the high pressure turbine in the even of a fan blade-out or fan blade-off event. | 09-05-2013 |
| 20130230387 | PROPELLER BLADE SEAL POSITIONING GAUGE - The propeller blade seal positioning gauge provides for precisely marking the position(s) of the circumferential seal(s) about the blade shank of a controllable pitch propeller prior to propeller reassembly. The gauge includes an elongate arm having a stop extending from one end normal thereto. The distal portion of the arm is inwardly offset toward the spanwise axis of the blade to place the distal portion of the arm adjacent the blade shank. One or more marker notches are formed in either or both edges of the arm, their locations being precisely determined according to the specific propeller type. The stop is placed upon the butt of the blade and the tip of an appropriate marker is placed in the appropriate notch of the gauge. The device is then rotated about the blade shank to mark a circumferential ring about the shank to indicate the precise position of the seal. | 09-05-2013 |
| 20130230388 | COMPRESSOR - A compressor having a stator vane assembly having an inner ring and a seal carrier secured thereto, the seal carrier having two opposite seal carrier end faces and the inner ring having two inner ring end faces which face said seal carrier end faces and are received between said seal carrier end faces with an axial gap therebetween, at least one clamping element bearing axially with a first clamping element end face against the inner ring and with a second clamping element end face against the seal carrier and being axially resiliently clamped between the inner ring and the seal carrier. A compressor with a clamping element for radial clamping is also provided. | 09-05-2013 |
| 20130236297 | PUMP - Pump, in particular a canned motor pump, to deliver liquids in water carrying domestic appliances and such like, which comprises a stator, a rotor and a drive shaft non-rotatably coupled to an impeller disposed in a pump compartment which is rotatably arranged inside a motor casing via bearing means wherein seal means are fitted on a first face end of the motor casing to seal said casing off against the pump compartment, wherein the bearing and seal means arranged on the first face end of the motor casing are in the form of a seal-bearing combination which comprises an axial bushing section for sliding arrangement on the drive shaft, a radial closing section to cover up the motor casing and at least one flexible seal element formed to said axial bushing section and/or said radial closing section. | 09-12-2013 |
| 20130243581 | Bearing housing shroud - A turbocharger including a turbine wheel having a hub-to-tip ratio of no more than 60% and blades with a high turning angle, a turbine housing forming an inwardly spiraling primary-scroll passageway that significantly converges to produce highly accelerated airflow into the turbine at high circumferential angles, and a two-sided parallel compressor. The compressor and turbine each produce substantially no axial force, allowing the use of minimal axial thrust bearings. The bearing housing forms a shroud for the internal side of the compressor wheel. | 09-19-2013 |
| 20130259659 | Knife Edge Seal for Gas Turbine Engine - A seal for a gas turbine engine and a gas turbine engine employing such a seal are disclosed. More specifically, the engine includes a knife edge seal which is better able to withstand the extremely high temperatures and mechanical loads to which gas turbine engine components are increasingly subjected. By moving the knife edge seal to the aft hub and cantilevering its angle off of vertical, thermal and mechanical loads are balanced and thus thermal mechanical fatigue life is improved while low cycle fatigue is maintained. | 10-03-2013 |
| 20130259660 | AXIAL NON-C0NTACT SEAL - A gas turbine engine has a turbine section and an air moving section upstream of the turbine section. A seal is between a static surface and a rotating surface in at least one of the turbine section and air moving section. The seal includes a seal shoe which is biased at least in part by a spring force, with the spring force created by cuts formed to provide a gap to allow arms associated with the seal to provide the spring force. The movement of the shoe is along a direction having at least a component parallel to an axis of rotation of the gas turbine engine. In addition, an axially moving non-contact seal is claimed. | 10-03-2013 |
| 20130259661 | SEALING STRUCTURE FOR TURBOCHARGER HOUSING - Bolt holes | 10-03-2013 |
| 20130266425 | EXHAUST GAS TURBOCHARGER - An exhaust gas turbocharger ( | 10-10-2013 |
| 20130272853 | COMPRESSOR - A compressor is provided with a substantially tubular compressor casing, a substantially circular lid that is provided inside an inner periphery of the compressor casing so as to close off an end surface of the compressor casing, a space that is enclosed by the lid and an inner circumferential surface of the compressor casing so as to accommodate a blade, and seal member that is provided in a circumferential direction on the space side of an outer circumferential surface of the lid, wherein a slit part is provided on the lid, radially inside the outer circumferential surface, where the seal member is provided, so as to extend in the axial direction from the space side of the lid. | 10-17-2013 |
| 20130272854 | BEARING ARRANGEMENT FOR A TURBOCHARGER, AND TURBOCHARGER - A bearing arrangement for a turbocharger, including a bearing housing-which extends in an axial direction, an anti-friction bearing, situated within the bearing housing, having an outer bearing ring and a number of rolling bodies and an axially extending shaft which is rotatably mounted within the bearing housing. It is provided that the shaft includes a rolling body raceway for guiding the rolling bodies. Moreover, the invention relates to a turbocharger having such a bearing arrangement. A bearing arrangement of this type allows the secure mounting of a shaft in a turbocharger with simple assembly and low costs. | 10-17-2013 |
| 20130280047 | Stator Seal for Turbine Rub Avoidance - A stator seal for a turbine assembly includes a seal base securable to a turbine stator and including an annular inner surface, and an abradable coating disposed on the annular inner surface. The abradable coating and the annular inner surface have a predefined cross-sectional profile including a transient operation section that facilitates axial expansion and a steady state operation section that facilitates a tighter clearance. | 10-24-2013 |
| 20130287551 | SEPARABLE SEAL ASSEMBLY FOR A GAS TURBINE ENGINE - A seal assembly for sealing a rotatable shaft in a gas turbine engine, wherein the shaft includes sections of greater shaft diameter located both forward and aft of the seal shaft coupling point is provided. The seal assembly includes a first semi-annular segment with a first end, a second end, and a plurality of seal teeth, where the first and second ends each include an overlap joint. The seal assembly also includes a second semi-annular segment with a first end, a second end, and a plurality of seal teeth, where the first and second ends each include an overlap joint. The first end of the second segment is coupled to the first end of the first segment, and the second end of the second segment is coupled to the second end of the first segment. | 10-31-2013 |
| 20130287552 | SPRING BIASED SEALING METHOD FOR AN ACTUATING SHAFT - The propensity for gas and soot leakage around a shaft, which extends through a bore which connects volumes of differing pressures, e.g., a turbocharger turbine housing and the ambient air, is minimized with the addition of a pair of seal rings axially biased by a spring to provide a continuous gas and soot seal. The spring may bias the seal rings apart from each other or towards each other. | 10-31-2013 |
| 20130294896 | METHOD AND SYSTEM OF INCREASING WEAR RESISTANCE OF A PART OF A ROTATING MECHANISM EXPOSED TO FLUID FLOW THERETHROUGH - A method of increasing wear resistance of one or more part(s) of a rotating mechanism includes manufacturing the one or more part(s) with a portion thereof configured to be exposed to wear during fluid flow associated with the rotating mechanism having a dimension different from that of a desired dimension, applying a protective coating of an aluminum bronze alloy to the portion through welding deposition, and mechanically treating the protective coating. The method also includes applying one or more layer(s) of solid-alloy over the protective coating through electro-erosion deposition, and continuing the mechanical treatment of the protective coating and/or the one or more layer(s) of solid-alloy after the solid-alloy deposition to obtain the desired dimension of the portion. | 11-07-2013 |
| 20130302149 | HERMETIC COMPRESSOR - A hermetic compressor includes: a crank shaft rotated by using an axial direction as a rotational axis; a stator rotating the crank shaft; a first bearing penetrated by the crank shaft and rotatably coupled to one side of the crank shaft based on the stator to support one side of the crank shaft when the crank shaft is rotated; a support part having one side provided at the stator and the other side disposed to be adjacent to the other side of the crank shaft, based on the stator; and a second bearing coupled to the other side of the support part and supporting the other side of the crank shaft. | 11-14-2013 |
| 20130309072 | BEARING SPACER AND HOUSING - An exemplary center housing rotating assembly includes a turbine wheel ( | 11-21-2013 |
| 20130323029 | SEGMENTED SEAL WITH SHIP LAP ENDS - A segment for a knife edge seal includes an arcuate segment with a first end with a first end surface and a second end with a second end surface. The first end surface and the second end surface are complementary and overlapping when the first end surface and the second end surface interface with ends of adjacent segments. | 12-05-2013 |
| 20130323030 | BEARING ARRANGEMENT FOR A RECIPROCATING COMPRESSOR - The arrangement of the present invention is applied to a compressor which comprises a bearing hub housing a crankshaft and presenting at least a first and a second bearing portion, spaced apart by a circumferential recess. The crankshaft presents at least a first and a second support portion, spaced apart by a circumferential recess, which is offset from the circumferential recess of the bearing hub. At least one of the bearing portions and support portions has an axial extension superior to that required for radially bearing the crankshaft, the first and second bearing portions defining, with the first and second support portions, respectively, a first and a second radial bearing regions having the axial extensions required for a radial bearing for the crankshaft, presenting lower loss by viscous friction. | 12-05-2013 |
| 20140023489 | SEAL ASSEMBLY AND GAS TURBINE HAVING THE SAME - In a seal assembly which is inserted into a space, the space being defined by a pair of concave portions provided on side surfaces of transition piece outlet flanges, including: a seal body in which a seal portion, which contacts each of side surfaces of a downstream side of combustion gas flowing through the transition piece of side surfaces which face each other in each of the pair of concave portions, is formed, and an elastic body which presses the seal body toward the downstream side, wherein the seal body includes a seal plate and a side plate, and the elastic body includes a seal plate contacting portion and an elastic portion. | 01-23-2014 |
| 20140030070 | CABIN AIR COMPRESSOR HOUSING - A cabin air compressor housing for a cabin air compressor assembly includes a compressor volute configured to direct a compressed flow to a compressor outlet. The cabin air compressor housing also includes a journal bearing support having a journal bearing bore. The cabin air compressor housing further includes an interior portion between the compressor volute and the journal bearing support. The interior portion includes a plurality of cooling airflow holes having a ratio of a diameter of the journal bearing bore to a diameter of one of the cooling airflow holes between 3.64 and 4.52. | 01-30-2014 |
| 20140044527 | ABRASIVE THERMAL COATING - A protective coating for a surface exposed to hot gas flow comprises a thermal layer, a conducting layer and an abrasive layer. The thermal layer comprises alumina having a sufficient amount of impurities to lower the thermal layer thermal conductivity. The layer is formed from a powder having a thermal conductivity no more than 10 BTU in/hr ft | 02-13-2014 |
| 20140056698 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger ( | 02-27-2014 |
| 20140064935 | FAN BLADE PLATFORM FLAP SEAL - A seal for sealing a gap between adjacent first and second components, includes a first portion for attaching to the first component and a second portion extending at an angle from the first portion, the second portion having a top extending therealong that is flat in an uninstalled position, a thickened portion beneath the top and a hinge wherein the thickened portion is disposed between the hinge and an end of the top. | 03-06-2014 |
| 20140064936 | REINFORCED SEAL FOR ROTARY SHAFTS - A seal for sealing a space between a housing and a rotatable shaft disposed within the housing includes an annular, elastomeric seal body disposeable about the shaft. The body has a central axis, an outer portion disposeable within a housing recess, and an inner portion with a lip engageable with the shaft. At least a portion of the seal body is configured to bendingly deflect when fluid pressure exerted on the body exceeds a predetermined value such that at least a section of the body inner portion displaces radially outwardly to permit fluid flow between the shaft and the seal body. A rigid support member is disposed within the body outer portion so as to be located at least partially within the housing recess and is configured to reduce bending deflection of the body inner portion so as to prevent disengagement of the body from the recess. | 03-06-2014 |
| 20140072414 | APPARATUSES AND METHODS FOR A PUMP - A pump having a pump chamber and an impeller which rotates therein has an inlet leading into the pump chamber and an outlet leading out of the pump chamber, the pump having a pump motor having a rotor. The rotor and the impeller are connected to each other, the impeller being supported in an axial direction towards the inlet and an axial support being provided therefor against an axial bearing. In this instance, the axial bearing is located on a rotation axis of the rotor and includes a centrally supported concave bearing shell in which a convex-curved bearing projection of the impeller is in abutment. | 03-13-2014 |
| 20140086731 | BEARING UNIT FOR A TURBOCHARGER - A bearing unit for a turbocharger, including a bearing housing extending in an axial direction and also including a bearing cartridge arranged within the bearing housing, wherein between the outer circumference of the bearing cartridge and the bearing housing there is formed an intermediate space with an oil film, and wherein the bearing housing has a supply bore formed for the supply of oil to the oil film. The bearing cartridge includes a rolling bearing, the outer cartridge ring of which is mounted in a freely rotatable manner in the oil film. A bearing unit for a turbocharger, the bearing cartridge of which includes a rolling bearing, the bearing outer ring of which is mounted in a freely rotatable manner in the oil film. By means of bearing units of such design, it is possible to ensure the secure mounting of a shaft even without a separate twist prevention device. | 03-27-2014 |
| 20140119898 | BEARING DEVICE FOR TURBOCHARGER - It is intended, with respect to a first floating bush bearing disposed on a compressor housing side and a second floating bush bearing disposed on a turbine housing side, to improve oscillation stability when a turbine rotor revolves at a high speed, reduce the number of parts, and facilitate processing and assemblability. Provided are a bearing housing ( | 05-01-2014 |
| 20140127005 | METHOD FOR PRODUCING A COMPONENT, COMPONENT AND TURBOMACHINE HAVING A COMPONENT - A method for manufacturing a metallic component especially configured and designed for a turbomachine includes a) for a precision-casting process, a wax model with a wax structure is produced, subsequently b) the tip of the wax structure is thermally and/or mechanically treated such that a region with an undercut is formed on the wax structure, subsequently c) the metallic component is manufactured from the wax model in the precision-casting process, with a component structural element with an undercut forming on a surface of the component, and d) the component structural element is provided at least partially with a ceramic coating, a plastic-containing coating, in particular a fibre composite layer and/or a plastic component. | 05-08-2014 |
| 20140140823 | HYBRID GAS TURBINE BEARING SUPPORT - A hybrid radial gas turbine engine component comprises an inner hub portion joined to an outer ring portion. The inner hub portion is a first alloy and operates at temperatures less than 1200° F. The outer ring portion is a second alloy and is designed to withstand extended periods at temperatures greater than 1200° F. | 05-22-2014 |
| 20140140824 | OIL SYSTEM BEARING COMPARTMENT ARCHITECTURE FOR GAS TURBINE ENGINE - A gas turbine engine with a geared architecture includes a multiple of bearing compartments and at least one carbon seal that seals at least one side of each of the multiple of bearing compartments. | 05-22-2014 |
| 20140147256 | COMPRESSOR HOUSING AND EXHAUST TURBINE SUPERCHARGER - A compressor housing is provided with a shroud member, which surrounds a compressor impeller, and a sealing member. The shroud member has a facing surface that is located at a position on a radially outside of the compressor impeller on an inner circumferential surface of the shroud member. The sealing member is provided on the facing surface. The sealing member is formed from a cylindrical material that has free-cutting property to the compressor impeller. The sealing member is press-fitted into the facing surface of the shroud member. | 05-29-2014 |
| 20140154058 | ROTATING ASSEMBLIES OF TURBOMACHINERY, FOIL JOURNAL BEARING ASSEMBLIES THEREOF, AND METHODS FOR PRODUCING JOURNALS OF THE FOIL JOURNAL BEARING ASSEMBLIES - A rotating assembly of turbomachinery is provided. The rotating assembly includes a plurality of components mounted on a rotatable shaft within a housing of the turbomachinery and at least one foil journal bearing assembly for mounting the rotatable shaft to the housing. The foil journal bearing assembly includes an annular bearing carrier mounted to the housing. An annular bearing sleeve is disposed within the annular bearing carrier and attached thereto. The annular bearing sleeve is lined with a plurality of foils. A journal is mounted to the rotatable shaft. The journal has an outer surface engaging the foils. The journal is configured to at least one of the following: resist operational deflection thereof and reduce the effects of misalignment. A method for producing the journal of the foil journal bearing assembly is also provided. | 06-05-2014 |
| 20140154059 | TURBINE NOZZLE BAFFLE - An embodiment of the present invention is a turbine nozzle baffle including an annular box structure. The turbine nozzle baffle includes a first diaphragm, a second diaphragm, and a static portion of a rotating seal that form a one-piece annular box structure. The first diaphragm extends from an inner diameter of the box structure to an outer diameter of the box structure to form a first axial side. The second diaphragm includes a first portion and a second portion. The first portion extends from the inner diameter to the outer diameter to form a second axial side. The second portion extends toward the first axial side to form the outer diameter. The second diaphragm connects to the first diaphragm at the outer diameter. The static portion of the rotating seal faces radially inward at the inner diameter between the first axial side and the second axial side. | 06-05-2014 |
| 20140154060 | TURBOMACHINE SEAL ASSEMBLY AND METHOD OF SEALING A ROTOR REGION OF A TURBOMACHINE - A turbomachine seal assembly includes a rotor disposed about an axial centerline, the rotor having an outer surface. Also included is a stationary component extending circumferentially about the rotor. Further included is at least one primary annular seal ring operably coupled to the stationary component and extending radially inwardly to close proximity with the outer surface of the rotor. Yet further included is a secondary annular seal ring operably coupled to the stationary component and integrally formed with the at least one primary annular seal ring, the secondary annular seal ring extending radially inwardly to close proximity with the outer surface of the rotor. | 06-05-2014 |
| 20140169951 | COMPRESSOR MOTOR HOUSING AND METHOD OF MANUFACTURING - A compressor motor housing includes an aft region having a radially inner surface defining an inner diameter and a radially outer surface defining an outer diameter. Also included is an O-ring groove extending around at least a portion of the aft region within the radially outer surface, the O-ring groove. The O-ring groove includes a groove width, a groove depth and a groove diameter, wherein a width ratio defined by the groove width in relation to the groove diameter ranges from about 0.0257 to about 0.0272. The O-ring groove also includes an axially forward face, an axially aft face and a circumferential face disposed radially outwardly from the radially inner surface. The compressor motor housing further includes an O-ring seal simultaneously disposed in contact with the axially forward face, the axially aft face and the circumferential face. | 06-19-2014 |
| 20140169952 | DIRECT-DRIVE WIND TURBINE - A direct driven wind turbine and a main bearing used in such a wind turbine is provided. A rotor of the wind turbine is directly connected with a rotating drive train of the wind turbine, the rotating drive train is directly connected with a rotor of an electrical generator of the wind turbine. The rotating drive train is connected with a stationary part of the wind turbine via at least one bearing, which allows the rotation of the drive train in relation to the stationary part. The at least one bearing is a plain bearing and the bearing is a tapered bearing, which comprises at least one conical shaped sliding surface. | 06-19-2014 |
| 20140178182 | ARRANGEMENT HAVING A SEAL, SEAL, AND TURBOCOMPRESSOR - An arrangement having an annular seal extending about a machine axis, and a vessel for sealing an L-shaped gap extending along a circumferential direction between a main vessel body and a cover is provided. A radial section of the gap extends in the radial direction and circumferential direction, and an axial segment extends in the axial direction and the circumferential direction. A sealing chamber is provided in the region where the radial segment and the axial segment intersect, the chamber expanded radially and axially relative to the adjacent gap segments. A seal is disposed in the sealing chamber, and a greater pressure is present in the radial segment than in the axial segment, the pressure differential sealed by means of the seal. The seal includes a support ring disposed radially inward made of a first material, and a jacket element made of a second material. | 06-26-2014 |
| 20140186160 | SLIDER SEAL - An assembly for a gas turbine engine includes a component, a seal element, and a seal cap. The component defines a pocket adapted to accept the seal element and the pocket allows for sliding movement of the component relative to the seal element. The seal cap overlying the pocket and the seal element. | 07-03-2014 |
| 20140186161 | SEAL PLATE - A seal plate for an air cycle machine includes a substantially disk-shaped body having a first side configured to be coupled to a compressor housing of the air cycle machine and a second side configured to be coupled to a turbine housing of the air cycle machine. The seal plate also includes a timing pin slot configured to align the first side of the seal plate with the compressor housing. The seal plate further includes a plurality of fastener holes distributed radially in an asymmetric pattern. The plurality of fastener holes includes an alignment fastener hole configured to align the second side of the seal plate with the turbine housing. An angular offset between the alignment fastener hole and the timing pin slot is about 38.45 degrees. | 07-03-2014 |
| 20140186162 | ROTATION MECHANISM FOR GAS EXHAUST PUMP, MANUFACTURING METHOD OF THE SAME, GAS EXHAUST PUMP HAVING ROTATION MECHANISM, AND MANUFACTURING METHOD OF THE SAME - In a gas exhaust pump, there is provided a rotation mechanism that can ensure safe rotation and can greatly reduce the usage of a seal gas. A rotation mechanism of the present invention is formed of a rotating shaft and a seal housing. Between the rotating shaft and the seal housing, there is provided a predetermined gap. On at least one of an outer surface of the rotating shaft and an inner surface of the seal housing, there is provided a PFA film. As to a PFA film on a surface of at least one of the rotating shaft and the seal housing, after coating with PFA the wall surface of the rotation mechanism member defining at least the gap, followed by melting and remelting processes, the PFA film is formed to have a high smoothness on its free surface. | 07-03-2014 |
| 20140193243 | SEAL ASSEMBLY FOR TURBINE SYSTEM - The disclosure includes a sealing assembly for a turbine system. In one embodiment, the sealing assembly is for a turbine having a rotor blade and a stator nozzle. The sealing assembly includes a pair of oppositely facing seal teeth including concave surfaces. The pair of oppositely facing seal teeth are positioned on one of the rotor blade and the stator nozzle, and are for sealingly engaging the other of the rotor blade and the stator nozzle during operation of the turbine. | 07-10-2014 |
| 20140193244 | BEARING HOUSING OF AN EXHAUST-GAS TURBOCHARGER - A bearing housing ( | 07-10-2014 |
| 20140193245 | TURBO ENGINE COMPRISING A DAMPING FLUID FILM FOR DAMPING A GUIDE BEARING OF A SHAFT OF THE TURBO ENGINE AND METHOD OF ADJUSTING THE THICKNESS OF SUCH A DAMPING FLUID FILM - A turbine engine including a casing, a turbine engine shaft extending axially, a guide bearing for guiding the turbine engine shaft in the casing, the guide bearing including an inner circumferential ring rigidly connected to the turbine engine shaft, an outer circumferential ring fitted in a housing of the casing, and gripping rolling members, and a damping cavity configured to receive a damping fluid to form a damping fluid film for damping the guide bearing, the cavity being delimited radially between an outer surface of the outer ring and an inner surface of the housing. The outer surface of the outer ring and the inner surface of the housing are conical surfaces. | 07-10-2014 |
| 20140199162 | Positive Displacement Pump Including Detectable Composite Non-Metallic Components - A positive displacement pump is disclosed which includes a case that defines a pump cavity. A shaft and rotor, which are detachably connected together, are also included wherein the rotor is disposed within the pump cavity and the shaft passes through an opening in the proximal end of the case. The distal end of the shaft, in addition to being connected to the rotor, is also coupled to a fastener that couples a cover plate over the distal end of the shaft and over at least part of the base portion of the rotor. The opening in the proximal side of the case through which the shaft passes also accommodates a seal assembly. Access to the seal assembly is easily made by removing the head from the case and removing the rotor from the shaft. The seal assembly can be changed or serviced without removal of the shaft. | 07-17-2014 |
| 20140205440 | COMPLIANT PLATE SEALS FOR ROTARY MACHINES - A seal assembly for rotary machine is provided. The seal assembly includes multiple compliant plates disposed between a stationary component and a rotary component of the rotary machine, and coupled circumferentially along the stationary component. Each compliant plate comprises a tip configured to be disposed facing the rotary component, and at least one plate slot extending from the stationary component towards the rotary component. The seal assembly also includes at least one annular resistance member configured to be coupled to the stationary component and disposed in the at least one plate slot in the compliant plates and one or more rotor slots or grooves located circumferentially on a surface of the rotary component proximate the tip of each of the plurality of compliant plates. | 07-24-2014 |
| 20140205441 | SEAL ASSEMBLY INCLUDING GROOVES IN A RADIALLY OUTWARDLY FACING SIDE OF A PLATFORM IN A GAS TURBINE ENGINE - A seal assembly between a disc cavity and a turbine section hot gas path includes a stationary vane assembly and a rotating blade assembly downstream from the vane assembly and including a plurality of blades that are supported on a platform and rotate with a turbine rotor and the platform during operation of the engine. The platform includes a radially outwardly facing first surface, a radially inwardly facing second surface, a third surface, and a plurality of grooves extending into the third surface. The grooves are arranged such that a space is defined between adjacent grooves. During operation of the engine, the grooves guide purge air out of the disc cavity toward the hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path. | 07-24-2014 |
| 20140205442 | SEALING DEVICE FOR A TURBOMACHINE TURBINE NOZZLE - A sealing device for a nozzle of a turbomachine turbine including a turbine rotor. The turbine nozzle includes at least one inner annular platform. The turbine rotor includes a downstream spoiler disposed substantially axially. The sealing device includes at least one sealing sheet disposed, radially, between the inner face of the inner platform and the downstream spoiler of the rotor of the turbine so as to form an overlap clearance. | 07-24-2014 |
| 20140205443 | SEAL ASSEMBLY INCLUDING GROOVES IN AN AFT FACING SIDE OF A PLATFORM IN A GAS TURBINE ENGINE - A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a stationary vane assembly and a rotating blade assembly axially upstream from the vane assembly. A platform of the blade assembly has a radially outwardly facing first surface, an axially downstream facing second surface defining an aft plane, and a plurality of grooves extending into the second surface such that the grooves are recessed from the aft plane The grooves are arranged such that a circumferential space is defined between adjacent grooves During operation of the engine, the grooves impart a circumferential velocity component to purge air flowing out of a disc cavity through the grooves to guide the purge air toward a hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path. | 07-24-2014 |
| 20140212278 | TURBINE HOUSING - A turbine housing comprises an exhaust port flange, a turbine discharge flange, a crossover flange, and a bearing support ring. The exhaust port flange is configured for mechanically coupling the turbine housing to a mating structure providing a source of working fluid. The turbine discharge flange is configured for mechanically coupling the turbine housing to an exhaust system. The crossover flange is configured for mechanically coupling the turbine housing to a crossover duct. The bearing support ring is configured for mechanically supporting a bearing, on which a turbine output shaft is supported. The turbine housing defines an inlet plenum, a turbine shroud, and a discharge vent. The exhaust port flange defines an inlet port configured to provide fluid communication between the inlet plenum and the source of working fluid. The turbine shroud defines a fluid expansion flow path for expansion of the stream of working fluid. | 07-31-2014 |
| 20140255163 | VEHICULAR FLUID POWER TRANSMITTING DEVICE - A vehicular fluid power transmitting device has a pump impeller, a turbine runner, damper device, an annular set member and a bearing assembly. The pump impeller has a pump shell. The damper device is provided between a drive source and the pump shell in an axial direction of an output shaft, and has a damper input member that is connected to the drive source, and a damper output member that is connected to the pump shell. The damper output member is connected to the annular set member that is fixed to the pump shell. The damper input member is relatively rotatably supported via the bearing assembly by the annular set member. | 09-11-2014 |
| 20140255164 | Pump Fittings and Methods for Their Manufacture - A pump fitting has an inlet adaptor ( | 09-11-2014 |
| 20140255165 | CENTRIFUGAL PUMP FOR FLUIDS CONTAINING SOLID MATERIALS, AND GAP SEAL - The proposed rotary pump for transporting liquids containing solids is composed of a pump housing ( | 09-11-2014 |
| 20140255166 | ENERGY-STORING AND POWER-GENERATING SYSTEM AND METHOD FOR A VERTICAL-AXIS WIND GENERATOR - The energy-storing and power-generating system comprises an energy-storing system and a power-generating system. The energy-storing system comprises a high pressure gas generator, a water storage apparatus and a water turbine. The high pressure gas generator comprises at least one sealed high pressure gas tank ( | 09-11-2014 |
| 20140271141 | PUMP SEALING SYSTEM WITH THROTTLE BUSHING - A sealing arrangement is disclosed for a rotating shaft. A mechanical seal and a throttle bushing are mounted in a pump casing having a process fluid chamber and an end region. A shaft is rotatably mounted in the pump casing. The seal has a stationary portion mounted to the pump casing, and a rotatable portion mounted to the shaft. A throttle bushing surrounds the shaft and is connected to the casing. The throttle bushing has an inner surface that provides a fluid passageway between the inner surface of the throttle bushing and the shaft. The throttle bushing is spaced along the shaft at an axial distance from the mechanical seal, thus forming a barrier fluid space. The mechanical seal separates the barrier fluid space from the process fluid chamber. Barrier fluid migrates past the throttle busing inner surface, lubricates the pump bearings and gears, and is collected for reuse. | 09-18-2014 |
| 20140286760 | SEAL ASSEMBLY INCLUDING GROOVES IN AN INNER SHROUD IN A GAS TURBINE ENGINE - A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a rotating blade assembly having a plurality of blades that rotate with a turbine rotor during operation of the engine, and a stationary vane assembly having a plurality of vanes and an inner shroud. The inner shroud includes a radially outwardly facing first surface, a radially inwardly facing second surface, and a plurality of grooves extending into the second surface. The grooves are arranged such that a space having a component in a circumferential direction is defined between adjacent grooves. During operation of the engine, the grooves guide purge air out of the disc cavity toward the hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path. | 09-25-2014 |
| 20140314551 | BEARING HOUSING OF AN EXHAUST-GAS TURBOCHARGER - A bearing housing ( | 10-23-2014 |
| 20140334919 | STEAM TURBINE BEARING SUPPORT STRUCTURE AND STEAM TURBINE THEREOF - In a foundation in which both ends of a turbine rotor are arranged in the foundation and are freely rotatably supported by bearings, there are provided rectangular notches extending over a prescribed vertical depth from the top face of a wall surface on the casing side of a concrete section, having prescribed width and horizontal depth; bearing support members formed with an extension are laid in these notches; the bearings are installed on these extensions. | 11-13-2014 |
| 20140341720 | SEAL SYSTEM INCLUDING ANGULAR FEATURES FOR ROTARY MACHINE COMPONENTS - Systems and devices configured to seal interfaces/gaps between stationary components of turbines and manipulate a flow of coolant about portions of the turbine during turbine operation are disclosed. In one embodiment, a seal element includes: a first surface shaped to be oriented toward a pressurized cavity of the turbine; a second surface oriented substantially opposite the first surface and shaped to sealingly engage a contact surface of the static components; and a first set of angular features disposed in the second surface, the first set of angular features fluidly connecting the pressurized cavity and the flowpath of the turbine. | 11-20-2014 |
| 20140348642 | CONJOINED GAS TURBINE INTERFACE SEAL - A device including a conjoined laminate interface seal shaped for reducing inter-seal gap (e.g., an angled gap, an ‘L’-shaped gap, etc.) leakage in gas turbines is disclosed. In one embodiment, a seal device for a gas turbine includes: a first flange shaped to be disposed within a first slot of a first arcuate component and a first adjacent slot of a second arcuate component; a conjoined layer connected to a first surface of the first flange, the first surface configured to face a working fluid flow of the gas turbine; and a second flange shaped to be disposed within a second slot of the first arcuate component and a second adjacent slot of the second arcuate component, the second flange including a second surface connected to the conjoined layer. | 11-27-2014 |
| 20140348643 | SEMI-PERMEABLE MEDIA SEALING AN ACTUATING SHAFT - To impede soot leakage around a shaft which extends through a bore connecting volumes of differing pressures, e.g., a turbocharger turbine housing and the ambient air, a soot seal is provided to capture particulate matter while allowing the passage of gas. | 11-27-2014 |
| 20140356140 | CENTRIFUGAL COMPRESSOR HAVING A BEARING ASSEMBLY - Embodiments of the present disclosure are directed towards an annular bearing retainer ring comprising a first axial surface, wherein the first axial surface is planar, and a second axial surface, wherein the second axial surface is non-planar. | 12-04-2014 |
| 20140356141 | GEARED TURBOFAN ENGINE WITH INTEGRAL GEAR AND BEARING SUPPORTS - A gas turbine engine includes a bearing. A bearing support includes a first wall that extends between the first and second ends and is operatively supported by the bearing at a first end. An engine case is secured to the second end radially outward of the first end. A flexible support is provided by a second wall integral with and extending transversely from the first wall. The second wall has a first flange and a gear train component is secured to the first flange. | 12-04-2014 |
| 20140369819 | METHOD FOR MANUFACTURING ANTI-ROTATION RING OF SCROLL TYPE COMPRESSOR AND ANTI-ROTATION MECHANISM OF THE SCROLL TYPE COMPRESSOR - In a method for manufacturing an anti-rotation ring of a scroll type compressor, wherein the anti-rotation ring is provided in an anti-rotation mechanism for preventing a movable scroll from rotation on its own axis and made of a metal, the steps of the method include drawing a steel plate into a first intermediate body having a bottomed cylindrical shape, punching the bottom of the first intermediate body thereby to make a second intermediate body and ring forming the second intermediate body. | 12-18-2014 |
| 20140369820 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger ( | 12-18-2014 |
| 20140377057 | SEALING DEVICE - A sealing device in which coming off from the housing is suppressed with a simple structure even when the housing is made of resin. A case | 12-25-2014 |
| 20150010392 | Modular Water Pump - A water pump apparatus is provided having a plurality of modular components, which allows for construction of various configurations of the water pump apparatus depending on specific vehicle requirements. The water pump apparatus modular components include a pump housing with a fluid chamber formed therein, a bearing housing for attachment to the pump housing, and a thermostat housing for connecting to the bearing housing and the pump housing. A method for forming modular components for assembling a water pump apparatus for use in an internal combustion engine is also provided. | 01-08-2015 |
| 20150050130 | SEALING DEVICE BETWEEN TWO AXISYMMETRIC COAXIAL PARTS - A sealing device between two axisymmetric coaxial parts, includes an elastic segment, two holding elements located on each side of the annular segment, an annular spacer arranged between the two holding elements, wherein the annular spacer has a notch around its peripheral rim; the annular elastic segment has a hooking element at each of its free ends, adapted to cooperate with the notch of the annular spacer, and to hold the elastic segment in a pre-holding position by elastic return force. | 02-19-2015 |
| 20150098805 | INSULATING SEAL PLATE FOR AN AIR CYCLE MACHINE - A seal assembly of an air cycle machine includes a seal plate with an outer diameter. A bore extends axially through a center of the seal plate and a seal land is disposed at least partially within the bore. The seal land includes an inner diameter and a minimum ratio between the inner diameter of the seal land and the outer diameter of the seal plate is approximately 0.1985. | 04-09-2015 |
| 20150125276 | BEARING HOLDING STRUCTURE - A bearing holding structure includes a base and at least one bearing. The base includes a bearing cup, which is axially extended from a center of the base and defines a receiving space therein. The bearing is fitted in the receiving space of the bearing cup and has a shaft hole. At least one groove is provided on one or both of an inner surface of the bearing cup and an outer surface of the bearing; and the groove is communicable with the receiving space of the bearing cup. The groove is filled with a meltable filler, which is melted by laser welding to fixedly connect the bearing and the bearing cup to one another, such that the bearing is not brought by a rotary shaft to rotate and slide in the bearing cup, enabling the bearing and the bearing cup to have prolonged service life. | 05-07-2015 |
| 20150125277 | BEARING SYSTEM FOR A TURBOCHARGER WITH AN INTERNAL ELECTRIC MOTOR - A turbocharger bearing system comprising a shaft ( | 05-07-2015 |
| 20150125278 | Seal configuration for a turbo machine - The present invention relates to a seal configuration ( | 05-07-2015 |
| 20150330253 | BEARING HOUSING OF AN EXHAUST-GAS TURBOCHARGER - A bearing housing ( | 11-19-2015 |
| 20150337851 | SEALING DEVICE AND ROTATING MACHINE - Provided is a sealing device that has a seal rotary body and a seal stationary body disposed with a clearance in a radial direction with respect to an outer circumferential surface of the seal rotary body, and that suppresses the flow of a fluid between the seal rotary body and the seal stationary body. The seal stationary body has a plurality of holes in an inner surface facing the outer circumferential surface of the seal rotary body, and grooves in a circumferential direction of the inner surface. The seal rotary body has first protrusions that protrude toward the grooves. | 11-26-2015 |
| 20150337852 | Turbine Sealing System - A system for reducing leakage between static and rotating components within a turbine includes a static structure that is disposed radially outward from a tip of a rotating component. The static structure includes a seal assembly slot formed therein. A seal assembly includes a support block that is disposed within the seal assembly slot. A sealing material is disposed along a bottom portion of the support block and a tip slot is formed within the sealing material. The support block includes a forward portion that is slideably engaged with a forward inner surface of the seal assembly slot and an aft portion that is slideably engaged with an aft inner surface of the seal assembly slot. The system further includes a spring that extends axially between an aft wall of the seal assembly slot and an aft wall of the support block. | 11-26-2015 |
| 20150369249 | COMPRESSOR - A compressor comprises a casing, a bundle which is housed inside the casing, and an inner roller which is provided at a front of the bundle in the inserting direction and rolls on an inner circumferential surface of the casing, a sealing surface protruded from the inner circumferential surface toward an inner circumferential side of the casing in a radial direction, a recess which is provided on the inner circumferential surface and in which the inner roller is settled when the bundle is housed inside the casing, a sealing member provided on an outer circumferential surface of the bundle and abutting on the sealing surface of the casing when the bundle is housed inside the casing. An extension part extending the sealing surface to a front side thereof in the insertion direction of the bundle is provided in the inner circumferential surface of the casing. | 12-24-2015 |
| 20150377039 | COATED GAS TURBINE ENGINE COMPONENTS - A gas turbine engine component may include a coating adapted to protect the component during use. The coating may be applied by sintering metallic particles to form a metallic matrix fused to the component. | 12-31-2015 |
| 20160003087 | EDGE TREATMENT FOR GAS TURBINE ENGINE COMPONENT - A gas turbine engine component according to an exemplary aspect of the present disclosure includes, among other things, a body having a first outer face meeting a second outer face at an intersection, the body having a plurality of apertures extending from an opening in the first outer face to an opening on the second outer face; and a coating filling at least a portion of the plurality of apertures. | 01-07-2016 |
| 20160010653 | SHAFTLESS FAN STRUCTURE | 01-14-2016 |
| 20160024953 | Fluid Flow Machine - A fluid flow machine, in particular turbocompressor, with a housing, having a rotor mounted in the housing, and with a dry gas seal for sealing the rotor relative to the housing. The housing at least one recess or bore for a gaseous medium is introduced, via which the gaseous medium for temperature-controlling the dry gas seal can be conducted in the direction of the same. The gaseous medium can be directly conducted into a gas space formed between the housing and the dry gas seal via the or each recess or bore. Additionally or alternatively, the or each recess or bore receives a guide tube for the gaseous medium. | 01-28-2016 |
| 20160032745 | TURBINE INCLUDING PACKING DEVICE AND METHOD OF ASSEMBLING THE SAME, AND SEALING ASSEMBLY - A turbine includes a rotor shaft having a plurality of rotating blades mounted on the rotor shaft, a bearing assembly rotatably supporting the rotor shaft, a casing forming a passage of a fluid and to include a space in which the rotating blades are disposed so that thermal energy of the fluid is converted into mechanical energy by rotation, a foundation fixedly supporting the bearing assembly, and a packing device installed in the rotor shaft for sealing between the casing and the rotor shaft and supported by the foundation. The casing comprises a connection unit extended toward the packing device and fixed to the casing so that a location of the connection unit is relatively changed with respect to the packing device. Accordingly, there is an advantage in that the leakage of a fluid is reduced because a clearance between the packing device and the rotor shaft is reduced. | 02-04-2016 |
| 20160032840 | SHIELD FOR ARRANGING BETWEEN A BEARING AND A ROTATING SEAL ELEMENT - An assembly is provided that includes a shaft, a bearing, a stator seal element, a rotor seal element and a shield. The shaft extends along an axis. The bearing supports the shaft and receives lubrication fluid. The stator seal element circumscribes the shaft. The rotor seal element is mounted on the shaft axially between the bearing and the stator seal element. The rotor seal element forms a seal with the stator seal element. The shield substantially prevents the lubrication fluid from traveling axially away from the bearing onto the rotor seal element. | 02-04-2016 |
| 20160040554 | REAR BEARING SLEEVE FOR GAS TURBINE AUXILIARY POWER UNIT - The presently disclosed embodiments utilize a rear bearing sleeve interposed between an inner surface of an exhaust housing of a gas turbine auxiliary power unit and the rear roller bearing supporting a turbine within the exhaust housing. In some embodiments, the rear bearing sleeve includes a lubricant supply channel formed in an outer surface thereof for receipt of a supply of lubricant, and at least one lubricant supply opening between the outer surface and an inner surface thereof, the inner surface of the bearing sleeve forming an outer race of the rear roller bearing. The at least one lubricant supply opening supplies the lubricant to a gap between the rear roller bearing and the rear bearing sleeve for formation of a squeeze film viscous damper therebetween. | 02-11-2016 |
| 20160053746 | A HUB AND BEARING SYSTEM AND A TURBINE COMPRISING THE HUB AND BEARING SYSTEM - A bearing system supports a plurality of turbine blades; each blade being rotatable about a pitch axis relative to a bearing system hub. The hub, comprising a plurality of static frames having a conical structure including two or more legs with openings therebetween, is connected to a main shaft of the turbine. Dynamic frames include a conical structure and two or more legs with openings therebetween. Legs of the static frame pass through openings between the legs of the corresponding dynamic frame, and legs of the dynamic frame pass through openings between legs of the corresponding static frame. Each dynamic frame is connected to one of the blades and is rotationally mounted to the corresponding static frame by a first bearing unit and a second bearing unit, distally arranged along the pitch axis from the first bearing unit. A central hub portion interconnects first shaft sections of the static frames. | 02-25-2016 |
| 20160084098 | SEALING STRUCTURE AND TURBINE - A sealing structure according to the embodiment includes a first cylinder, a second cylinder, an intermediate cylinder, a first sealing part, and a second sealing part. The first cylinder forms a flow passage of a working fluid of a turbine therein. The second cylinder is disposed at one end of the first cylinder and downstream from the flow passage. The intermediate cylinder is disposed between the first and second cylinders. The first sealing part is disposed at one of a first region between the first cylinder and the intermediate cylinder and a second region between the second cylinder and the intermediate cylinder, and follows a positional displacement in a radial direction. The second sealing part is disposed at the other of the first and second regions, and follows a positional displacement in an axial direction. | 03-24-2016 |
| 20160123391 | TILTING-PAD BEARING AND TURBO COMPRESSOR - The tilting-pad bearing includes: a plurality of tilting pads arranged around a rotary shaft; a housing including a lubricating oil-supplying hole provided at a position facing a gap formed between the tilting pads disposed next to each other; and a pair of side plates disposed so that the tilting pads are interposed therebetween. The tilting pad is provided with an internal flow passageway through which lubricating oil flow. The internal flow passageway includes a first inflow opening, a second inflow opening, and a discharge opening. | 05-05-2016 |
| 20160169242 | DYNAMIC PRESSURE BEARING APPARATUS AND FAN | 06-16-2016 |
| 20160177784 | TURBOMACHINE WITH AXIAL STOP MEMBER | 06-23-2016 |
| 20160186568 | Turbocharger With a Radial-Axial Turbine Wheel - A turbocharger has a shaft with a rotational axis, a radial/axial turbine wheel which is arranged in a turbine housing and which is connected to the shaft in a non-rotatable manner, and a bearing housing which adjoins the turbine housing and which contains a lateral wall facing the turbine housing. A sub-region of the lateral wall of the bearing housing forms a sub-region of the rear wall of the turbine housing. The sub-region of the bearing housing has two sub-sections, one of which runs diagonally to the rotational axis in an inflow direction of an exhaust gas flow conducted into the turbine housing and the second of which runs in a radial direction relative to the rotational axis of the shaft and parallel to the rear wall of the turbine wheel. The two sub-sections are connected to each other via an exhaust gas flow separation edge of the bearing housing. | 06-30-2016 |
| 20190145320 | SEAL SEGMENT AND ROTARY MACHINE | 05-16-2019 |
