Entries |
Document | Title | Date |
20080253880 | Counter-rotation drive - The mechanical counter-rotation drive according to the present invention is based on the laws of relative motion of an eccentric part of one of at least two shafts, which are constitutive parts of this drive, with respect to the plates of a determined shape whose motion is confined by pins arranged in a determined arrangement, is illustrated in FIG. | 10-16-2008 |
20090074565 | TURBINE ENGINE WITH DIFFERENTIAL GEAR DRIVEN FAN AND COMPRESSOR - A gas turbine engine ( | 03-19-2009 |
20090074566 | WIND POWER GENERATING DEVICE - A wind power generating device includes a housing, a transmission unit, at least one winding disc, at least one magnetic disc, and a rotating unit. When there are a plurality of winding discs and a plurality of magnetic discs, the winding discs and the magnetic discs are axially spaced and alternately arranged in the housing behind the transmission unit. When the magnetic discs are directly rotated by the rotating unit and the winding discs are indirectly rotated by the rotating unit via the transmission unit, magnetic bodies on the magnetic discs and windings on the winding discs are quickly moved in a relative motion to produce relatively large flux change, enabling the wind power generating device to have increased power generation capacity. | 03-19-2009 |
20090104019 | Offset drive for gas turbine engine - A gas turbine engine including a gas generator module and a reduction gearbox module. The gas generator module has an axis which extends longitudinally along a centreline of the gas generator module, and the reduction gearbox module has an axis which extending longitudinally along the centreline of the reduction gearbox and is offset from said generator axis. The reduction gearbox is driven by an intermediate shaft angled relative to the turbine output shaft. | 04-23-2009 |
20090232640 | ASSEMBLY FOR DRIVING GAS TURBINE ACCESSORIES - The invention provides an assembly for driving accessories of a gas turbine, the assembly comprising: a gearbox having a front side face and a rear side face opposite the front face and having mounted therein a first gear train made up of three toothed wheels meshing with one another, and a second gear train made up of four toothed wheels meshing with one another; a power transmission shaft that is coupled in rotation with the first and second gear trains by means of a toothed wheel pair, and that emerges from the front side face of the gearbox; and nine distinct gas turbine accessories mounted against the side faces of the gearbox, and each including a respective drive shaft that is coupled in rotation with one of the toothed wheels of the two gear trains. | 09-17-2009 |
20090290976 | Gearbox assembly - An assembly for a gas turbine engine includes an intermediate case and a gearbox. The intermediate case defines an annular transition duct. The gearbox comprises a plurality of lobes and is integrally formed with the annular transition duct. | 11-26-2009 |
20090297337 | Geared Turbine Machine For A Machine Train, Machine Train With And Gear For Geared Turbine Machine - A machine train includes a drive unit, preferably a steam turbine with axial exhaust flow, a geared turbine machine, and an additional compressor. The geared turbine machine has an integrated gear train with a drive pinion for driving turbine machine rotors via a large gear, and an output pinion of a rotational speed reduction power gear for driving the additional compressor. | 12-03-2009 |
20100061839 | SHAFT COUPLING ARRANGEMENT - A shaft coupling arrangement and a corresponding method for coupling shafts are disclosed herein. The shaft coupling arrangement includes an input shaft operable to rotate about a first axis. The shaft coupling arrangement also includes an output shaft operable to rotate about a second axis. The shaft coupling arrangement also includes a gearing arrangement operable to engage the input and output shafts together for rotation in the same angular direction at different angular speeds. In one embodiment of the invention, the gearing arrangement includes a plurality of nested bevel gears. In another embodiment of the invention, the gearing arrangement can include a single layshaft. | 03-11-2010 |
20110085890 | HARMONIZATION OF MULTIPLE GEAR TRAIN CONFIGURATIONS - A gear arrangement is disclosed herein. The gear arrangement includes a housing. The gear arrangement also includes a plurality of gears at least partially disposed in the housing and engaged with respect to one another. The gear arrangement also includes a support post mounted to the housing. The support post supports at least one of the gears. The support post has a first portion extending away from the housing and encircled by one of the gears. The support post also has a pin projecting away from the first portion. The first portion and the pin are eccentric to one another such that the first portion is centered on a first axis and the pin is centered on a second axis. The first and second axes are parallel to and spaced from one another. The gear arrangement also includes a plurality of pin apertures defined by the housing. The plurality of pin apertures are positioned about a circle and each is operable to receive the pin for adjustably positioning the first portion in one of a plurality of different positions. | 04-14-2011 |
20110142598 | Drive Train for a Wind Turbine - A drive train for a wind turbine, comprising a main bearing arrangement in the form of a single locating bearing arranged to support a main shaft. An outer raceway of the main bearing is coupled to a support structure, such as a base frame of a nacelle, via flange parts arranged on the outer raceway and the support structure, respectively. The flange parts define interfacing surfaces extending in a plane which is arranged non-parallel, preferably substantially perpendicular, to the rotational axis of the main shaft. Thereby a service friendly design is obtained, in which the main bearing and/or the main shaft can be repaired and/or replaced without having to remove the rotor from the nacelle. | 06-16-2011 |
20110176911 | ASSEMBLING TITANIUM AND STEEL PARTS BY DIFFUSION WELDING - A method of assembling together titanium parts and steel parts by diffusion welding, the method interposing two thin layers of niobium or vanadium and copper respectively between a titanium part and a steel part, evacuating the assembly of parts and interposed metal layers, and subjecting the assembly to hot isostatic compression at a temperature lying in a range 900° C. to 950° C. and at a pressure lying in a range 1000 bars to 1500 bars for about two hours. The method can be applied to fabricating turbine shafts for turbomachines. | 07-21-2011 |
20110188996 | CENTRIFUGAL PUMP - A sealless-type centrifugal pump provides a centrifugal pump that is free from leakage without using a shaft seal mechanism. The centrifugal pump includes a casing that forms a pump chamber having a liquid inflow port and an outflow port, an impeller disposed in the pump chamber and rotatably supported by a pivot bearing, and a magnetic coupling device including a driven permanent magnet built into the impeller and a driving magnet that rotationally drives the driven permanent magnet through a partition. The impeller supported in the direction of the rotation axis with respect to the casing is driven by the magnetic coupling device, and pressure is applied to liquid introduced from the direction of the rotation axis through the inflow port to send the liquid through the outflow port in a radial direction. The magnetic coupling device is disposed on a line inclined from an impeller rotating surface to the inflow port side toward the center of the rotation axis. | 08-04-2011 |
20110262268 | TURBO-MACHINE WITH BLADE WHEELS - The invention describes a turbo-machine with blade wheels, comprising a housing ( | 10-27-2011 |
20110299974 | LUBRICATING AND COOLING EPICYCLIC STEPDOWN GEARING - A lubricating and cooling epicyclic stepdown gearing, for example in an aeroengine turbomachine, including a cylindrical casing mounted on a planet-carrier of the gearing and forming a centrifugal scoop surrounding stationary oil-delivery strips, the cylindrical casing including radial ducts feeding nozzles pointing towards zones where the planet gears mesh with outer ring(s) of the gearing. | 12-08-2011 |
20110305558 | GEAR-DRIVEN TURBO COMPRESSOR - Provided is a gear-driven turbo compressor capable of increasing a natural frequency of a shaft by shortening the length of an overhang from a radial bearing to a shaft end, reducing an effort of replacing lubricant and an environmental burden by greatly reducing the amount of the lubricant, and reducing the necessity for maintenance by reducing a problem of the radial bearing caused by depleted materials of the lubricant. | 12-15-2011 |
20120020774 | ASSEMBLY BETWEEN A COMPRESSOR SHAFT TRUNNION AND A BEVEL GEAR FOR DRIVING AN ACCESSORY GEARBOX OF A TURBOMACHINE - The invention relates to an assembly between a compressor shaft trunnion and a bevel gear for driving an accessory gearbox of a turbomachine. The assembly comprises a bevel gear, a compressor shaft trunnion arranged coaxially inside the bevel gear, torque transmission means between the compressor shaft trunnion and the bevel gear, a lock nut for preventing the bevel gear from moving axially on the compressor shaft trunnion, the lock nut being suitable for being screwed onto the bevel gear and including a shoulder projecting radially outwards and suitable for coming into axial abutment firstly upstream against a stop nut screwed onto an upstream end of the compressor shaft trunnion, and secondly downstream against a bearing surface of the compressor shaft trunnion, and an anti-rotation pin for preventing the lock nut from rotating. | 01-26-2012 |
20120063887 | DOUBLE FAN FOR A HEAT EXCHANGER, IN PARTICULAR A COOLANT RADIATOR OF A MOTOR VEHICLE - The utilization of double fans for engine cooling of motor vehicles is known. Said fans generate a flow of air which then serves to cool a heat exchanger, in particular a coolant radiator for motor vehicles. The double fan is herein characterized by an optimal use of the surface of the coolant radiator that is to be cooled, so as to be able to achieve a cooling performance as high as possible. The assembly of the double fan has up to now been such that a separate electric motor is provided for each blower. The double fan ( | 03-15-2012 |
20120087777 | GUIDING APPARATUS FOR GUIDING THE MOVEMENT OF A POOL CLEANER - A guiding apparatus ( | 04-12-2012 |
20120087778 | MACHINE UNIT LAYOUT SYSTEM - Provided is a machine unit layout system that simplifies the layout of a compressor unit and an expander unit and is extremely effective in terms of not only the reliability of the entire machine but also maintainability. Two separate compressors, a low-pressure-side compressor and a high-pressure-side compressor ( | 04-12-2012 |
20120099963 | ENGINE MOUNT SYSTEM FOR A TURBOFAN GAS TURBINE ENGINE - A gas turbine engine according to an exemplary aspect of the present invention includes a gear train defined along an engine centerline axis, and a spool along the engine centerline axis which drives the gear train, the spool includes a low stage count low pressure turbine. | 04-26-2012 |
20120107098 | GAS TURBINE ENGINE ROTOR TIE SHAFT ARRANGEMENT - Independent axial preloading of compressor and turbine disks in a gas turbine engine rotor is achieved by a dual tie shaft arrangement wherein a forward tie shaft engages forward and aft portions of a compressor hub within which the compressor disks are disposed to axially and compressively preload the compressor disks between the forward and aft portions of the compressor hub. An independent tie shaft engages an aft portion of a turbine hub within which turbine disks are disposed and an aft portion of the compressor hub to axially and compressively preload the turbine disks between the turbine and compressor hubs. | 05-03-2012 |
20120107099 | TURBO BLOWER AND HIGH SPEED ROTATING BODY USED IN SAME - The present invention relates to a turbo blower and a high speed rotation body used in the turbo blower. The turbo blower includes: i) a motor having a motor shaft; ii) a gear housing accommodating a bull gear fitted on the motor shaft and a pinion gear engaged with the bull gear; iii) a high speed rotation body that includes a rotary shaft having the pinion gear on the external circumferential surface, an impeller fitted on one end of the rotary shaft, and a rotation body housing accommodating the rotary shaft, the pinion gear, and at least one first composite bearing and partially cut off to expose the pinion gear, and is partially accommodated in the gear housing; and iv) a scroll portion covering the impeller and discharging compressed air. | 05-03-2012 |
20120107100 | RADIATOR FAN ASSEMBLY STRUCTURE AND METHOD OF FORMING - A radiator fan assembly structure has a base board with a seating surface and a stator installing surface; a stator inserting and positioning part, configured in the center of the stator installing surface of the base board; a stator set, has a silicon-steel plate, a coil and an insulate frame; and a plastic assembly seat formed integrally on the stator set, which is formed through a projection from the center of the insulate frame of the stator set. The shape of the plastic assembly seat enables it to be inserted into the stator inserting and positioning part. An axis is combined with the plastic assembly seat, with its root part fixed on the center of the plastic assembly seat. A rotor blade assembly has a wheel hub, blades, a bush, a bearing assembly and a magnet ring. The radiator fan runs smoothly and quietly. | 05-03-2012 |
20120121388 | COMBINED AXLE STRUCTURE OF A STATOR ASSEMBLY FOR A RADIATOR FAN - A combined axle structure of a stator assembly for a radiator fan, of which said radiator fan comprises: a pedestal, a stator assembly, a rotor blade unit and a reverse axle. The pedestal includes a sustaining face and a stator assembly face. The stator assembly includes silicon-steel sheet, coil and insulated frame. The insulated frame is mated with a metal bearing block, which is designed like a cup, and includes a bottom wall and a circumferential wall. The top of the circumferential wall is positioned into the insulated frame. An axle socket is set at the center of the bottom wall, allowing for insertion of the bottom of the reverse axle. An embedded locator is set centrally into the stator assembly face of the pedestal, allowing for mating with the bottom of the metal bearing block. | 05-17-2012 |
20120121389 | COMPACT AND STRENGTHENED ROTOR ASSEMBLY OF A RADIATOR FAN - A compact, strengthened rotor assembly of a radiator fan, the radiator fan having a baseplate, a stator assembly, a rotor assembly and a reverse axle. The reverse axle is erected at the center of the baseplate or stator assembly and protruded upwards. The rotor assembly has a hub with a top wall and a circumferential wall. A magnetic ring is set annularly into the circumferential wall. Several blades are set annularly onto the exterior of the circumferential wall. A metal sleeve is located at the center of the top wall and protruded downwards. A mating portion is set at the top of the metal sleeve for mating with the top wall. A holding portion is formed within the metal sleeve for assembly and positioning of a bearing, and the bearing is used for pivoting of the reverse axle. The thickness of the top wall ranges between 0.2 mm and 0.5 mm. | 05-17-2012 |
20120121390 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four (4) stages. | 05-17-2012 |
20120163959 | RISERLESS RECIRCULATION/TRANSFER PUMP AND MIXER/PRE-MELTER FOR MOLTEN METAL APPLICATIONS - A pump for processing molten metal having an enlarged tubular body which houses a centrifugal lifting pump at its bottom end. The bottom end has a curved shape that aids in the formation and sustainability of: a) a forced vortex; b) a highly forced vortex; and c) a super forced vortex, depending on the application when it which receives the ejected molten metal from the lifting pump's impeller. The lifting pump is controlled to cause the vortex to climb up the inner wall of the body up to and out of an outlet formed in the upper end of the body. A recirculation centrifugal pump is mounted coaxially to and rotates with the lifting impeller. | 06-28-2012 |
20120171017 | ANTI-ROTATION FOR THRUST WASHERS IN PLANETARY GEAR SYSTEM - A bushing for use in a planetary gear system has a cylindrical body portion defining a bore extending along a central axis to be received on a planetary gear shaft. A tab extends axially beyond a nominal body portion of the bushing and is received in a notch in a thrust washer adjacent to the bushing to prevent rotation of the thrust washer. A gear cage and an air turbine starter incorporating the bushing, along with a method of installing the bushing are also disclosed. | 07-05-2012 |
20120171018 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15. | 07-05-2012 |
20120189430 | RING GEAR MOUNTING ARRANGEMENT WITH OIL SCAVENGE SCHEME - A turbine engine includes an input shaft and a fan shaft rotatable about an axis. The fan shaft supports fan blades. An epicyclic gear train is connected between the input shaft and the fan shaft. The epicyclic gear train includes a plurality of star gears, a carrier supporting the plurality of star gears, a sun gear that meshes with the plurality of star gears and a ring gear surrounding and meshing with the plurality of star gears such that the sun gear is rotatable in a first direction and the ring gear is rotatable in a second, opposite direction. The ring gear includes first and second portions that each have an inner periphery with teeth. The first and second portions include respective recesses facing one another to provide an internal annular cavity. | 07-26-2012 |
20120213628 | GAS TURBINE ENGINE WITH GEARED ARCHITECTURE - A geared architecture with a flex mount for a fan drive gear system. | 08-23-2012 |
20120237334 | GAS TURBINE ENGINE GEAR TRAIN - An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. The star gears are supported on respective journal bearings. Each of the journal bearings includes a peripheral journal surface and each of the star gears includes a radially inner journal surface that is in contact with the peripheral journal surface of the respective journal bearing. The epicyclic gear train has a gear reduction ratio of greater than or equal to about 2.3 | 09-20-2012 |
20120237335 | GAS TURBINE ENGINE WITH GEARED ARCHITECTURE - A geared architecture with a flex mount for a fan drive gear system. | 09-20-2012 |
20120237336 | GAS TURBINE ENGINE GEAR TRAIN - An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. The star gears are supported on respective journal bearings. Each of the journal bearings includes a peripheral journal surface and each of the star gears includes a radially inner journal surface that is in contact with the peripheral journal surface of the respective journal bearing. The epicyclic gear train has a gear reduction ratio of greater than or equal to about 2.3 | 09-20-2012 |
20120243971 | EPICYCLIC GEAR TRAIN - An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. Each of the star gears is supported on a respective journal bearing. Each journal bearing includes an internal central cavity and at least one passage that extends radially from the internal cavity to a peripheral journal surface of the respective journal bearing. The epicyclic gear train has a gear reduction ratio of greater than or equal to about 2.3. | 09-27-2012 |
20120257960 | Engine Bearing Support - A turbofan engine comprises an engine case. A gaspath extends through the engine case. A fan has a circumferential array of fan blades. A fan case encircles the fan blades radially outboard of the engine case. A plurality of fan case vanes extend outward from the engine case to the fan case. A front frame assembly includes a plurality of vanes extending radially across the gaspath. A transmission couples a shaft to a fan shaft to drive the fan. A bearing assembly couples the shaft to the front frame assembly. A bearing support extends aftward and radially inward from the front frame assembly to the bearing assembly. | 10-11-2012 |
20120263578 | GAS TURBINE ENGINE FRONT CENTER BODY ARCHITECTURE - A method for servicing a gas turbine engine includes providing access from a forward section of the gas turbine engine to a gearbox contained within a bearing compartment. | 10-18-2012 |
20120269616 | TURBINE DRIVESHAFT FOR RAM AIR TURBINE - A driveshaft for an aircraft ram air turbine includes a tubular body and a flange. The tubular body defines an axis of rotation and includes a forward portion and a frusto-conical portion located rearward of the forward portion. The flange adjoins the forward portion of the tubular body opposite the frusto-conical portion, and has a forward face and an opposite rear face. A ratio of an outer diameter of the forward portion of the tubular body to an inner diameter of the forward portion of the tubular body is in a range of approximately 1.423 to 1.425. | 10-25-2012 |
20120269617 | Cooling Fan - A cooling fan comprising a base, a lid, a fan wheel, and an auxiliary shaft assembly is disclosed. The lid is arranged above the base. The fan wheel has a shaft rotatably coupling with the base and a highest point spaced from the lid by a first gap. The auxiliary shaft assembly is arranged between a top of a hub of the fan wheel and a bottom face of the lid, with a second gap formed between the auxiliary shaft assembly and the top of the hub or between the auxiliary shaft assembly and the bottom face of the lid, wherein the second gap is smaller than the first gap. Alternatively, the auxiliary shaft assembly has a first auxiliary shaft protruding from the top of the hub and a second auxiliary shaft disposed on the bottom face of lid, with a second gap formed between the first and second auxiliary shafts smaller than the first gap. | 10-25-2012 |
20120275904 | GAS TURBINE ENGINE LUBRICATION - A turbine engine includes a fan shaft and at least one tapered bearing mounted on the fan shaft. The fan shaft includes at least one radially extending passage adjacent the at least one tapered bearing. A fan is mounted for rotation on the tapered bearing. An epicyclic gear train is coupled to drive the fan. The epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear, and a ring gear that surrounds and meshes with the star gears. Each of the star gears is supported on a respective journal bearing. The epicyclic gear train defines a gear reduction ratio of greater than or equal to about 2.3 | 11-01-2012 |
20120308362 | DUAL INPUT DRIVE AGB FOR GAS TURBINE ENGINES - A mechanical drive system of an aircraft gas turbine engine includes a tower shaft operatively connected to first and second shafts in an accessory drive gearbox. The first shaft rotates at a rotational speed lower than the rotational speed of the tower shaft and the second shaft rotates at a rotational speed equal to or higher than the rotational speed of the tower shaft. | 12-06-2012 |
20120308363 | CENTRIFUGAL PUMP APPARATUS - This centrifugal blood pump apparatus includes an impeller provided in a blood chamber, a permanent magnet provided in one surface of the impeller, and a permanent magnet provided in an inner wall of the blood chamber, for attracting the permanent magnet. A centerline of the permanent magnet is arranged at a position different from that of a centerline of a sidewall of the blood chamber such that a rotation centerline of the impeller matches the centerline of the sidewall of the blood chamber during pump operation. Therefore, high torque transmission efficiency is obtained. | 12-06-2012 |
20120315129 | Wind Turbine - A wind turbine that includes a rotor and a generator is described. The rotor includes a rotor hub that is rotatably mounted on a frame and one or more rotor blades. The generator includes a generator stator and a generator rotor with a carrying structure that carries magnetic or electromagnetic elements. One or more circumferentially arranged substantially axial protrusions that extend into the generator rotor carrying structure are attached to the rotor. Flexible couplings are arranged between one or more of the axial protrusions and the carrying structure. | 12-13-2012 |
20120315130 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the high pressure compressor section is between about 7 and about 15, and a pressure ratio across the fan section is less than or equal to 1.45. | 12-13-2012 |
20120321445 | AUTOMATIC SWING MECHANISM - An automatic swing mechanism has: a base, a lifting rod that can swing relative to the base and a driving mechanism that connects the base and the lifting rod, a flow passage that the flow can pass through is arranged in the base, and the driving mechanism comprises an impeller and a transmission mechanism. The impeller is pivotally arranged in the flow passage and can be rotated by the water passing through the flow passage. The transmission mechanism is connected between the impeller and the lifting rod to transform the rotation of the impeller to the swing of the lifting rod. The automatic swing mechanism drives the lifting rod swing by using the power of water, and the stuff arranged in the lifting rod can swing, such as handheld shower. | 12-20-2012 |
20130004297 | DUAL FAN GAS TURBINE ENGINE AND GEAR TRAIN - A gas turbine engine includes a first fan, a second fan spaced axially from the first fan, a turbine-driven fan shaft and an epicyclic gear train coupled to be driven by the turbine-driven fan shaft and coupled to drive the first fan and the second fan. The epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear, and a ring gear that surrounds and meshes with the star gears. The star gears are supported on respective journal bearings. | 01-03-2013 |
20130028712 | GAS TURBINE ENGINE SYSTEMS INVOLVING TIP FANS - Gas turbine engine systems involving tip fans are provided. In this regard, a representative gas turbine engine system includes: a multi-stage fan having a first rotatable set of blades and a second counter-rotatable set of blades, the second rotatable set of blades defining an inner fan and a tip fan and being located downstream of the first set of rotatable blades; and an epicyclic differential gear assembly operative to receive a torque input and differentially apply the torque input to the first set of blades and the second set of blades. | 01-31-2013 |
20130039745 | CENTRIFUGAL PUMP - A centrifugal pump that comprises a casing in which an impeller is arranged. The impeller has a back side that faces a back plate of the centrifugal pump, and one or more vanes for pumping the fluid. The back side of the impeller comprises a segmented scraper for scraping from the back plate material that has been deposited from the fluid. The segmented scraper comprises multiple protrusions, wherein each protrusion of the multiple protrusions is facing the back plate, and an aggregated radial extension of the protrusions equals a radius of the impeller within an interval of ±10%, ±25% or even up to ±40%. | 02-14-2013 |
20130051984 | TORQUE FRAME AND ASYMMETRIC JOURNAL BEARING FOR FAN DRIVE GEAR SYSTEM - A fan drive gear system for a gas turbine engine includes a torque frame and a journal bearing. The torque frame has an arm that extends therefrom, the journal bearing is mounted on the arm. When the fan drive gear system is in an unloaded condition an outer circumferential surface of the journal bearing is disposed at an angle so that it is non-parallel with respect to an axis of the arm. When the fan drive gear system is in a loaded condition the outer circumferential surface is disposed substantially parallel to the axis of the arm. In another aspect, the journal bearing includes a main body, a first wing, and a second wing. The first and second wings extend from the main body and are asymmetric with respect to one another. | 02-28-2013 |
20130058761 | MULTI-STAGE INTEGRALLY GEARED COMPRESSOR - A multi-stage integrally geared compressor includes a first process stage, a second process stage and a gearbox for coupling the two process stages to each other at different rotational speeds. The gearbox further couples a compressor drive shaft to the two process stages at a further rotational speed, which is different from the rotational speeds of the process stages. | 03-07-2013 |
20130071232 | RAM AIR TURBINE WITH INTEGRATED HEAT EXCHANGER - A ram air turbine system for generating electrical power in an aircraft when the system is exposed to an airstream exterior of the aircraft. The ram air turbine system includes a turbine, a housing defining an interior, a gearbox having a speed-increasing gear train, and a generator. | 03-21-2013 |
20130084164 | POWER GENERATION APPARATUS - A power generation apparatus includes an expander and a power transmission shaft that extracts a rotational driving force generated by the expander to the exterior of a housing of the expander. The housing of the expander contains a driving unit of the expander within a space enclosed by a partition wall of the housing. The power transmission shaft includes a magnetic coupling, divided between the interior and exterior of the housing of the expander through the partition wall. The rotational driving force extracted via the magnetic coupling is used as auxiliary power that supplements the power of a driving source provided separately from the expander when driving a rotating machine using the power of the driving source. A clutch mechanism and a speed variator are provided in a power transmission path that transmits the rotational driving force extracted by the power transmission shaft to the driving source. | 04-04-2013 |
20130089409 | NON-LUBRICATED ARCHITECTURE FOR A TURBOSHAFT ENGINE - A turbine engine for a helicopter, the helicopter including a main gearbox, a rotor, and a speed-reducing device housed entirely within the main gearbox of the helicopter while also being connected to the rotor, the turbine engine including a casing, a gas generator with a gas generator shaft, and a free turbine for being driven in rotation by a gas stream generated by the gas generator, the free turbine including a free turbine shaft. When the turbine engine is fastened to the gearbox of the helicopter, the free turbine shaft extends axially into the main gearbox of the helicopter to be connected directly to the speed-reducing device. | 04-11-2013 |
20130115053 | MAGNETIC DRIVE PUMP - The disclosure offers a sealless magnetic drive pump for improving the stiffness of a stationary shaft, and more particularly to, a metal magnetic drive pump with an anti-corrosion casing liner. The magnetic drive pump is used in manufacture processes related to corrosive fluid. The pump is especially used in a highly corrosive and high-temperature (up to 200° C.) condition to improve the stiffness of a front support. The stationary shaft includes a metal front support integrated with the pump casing at a pump inlet and encapsulated with a resin enclosure made of a fluoropolymer; a rear shaft seat positioned on a sealed bottom side of a containment shell for offering auxiliary support for the stationary shaft; an impeller including a channel for reducing an inlet flow velocity to offer a low NPSHr. | 05-09-2013 |
20130142626 | TANK SLOSHING ENERGY RECOVERY SYSTEM - A hydrodynamic energy recovery system for effecting mixing of gases within a headspace of a liquid-containment vessel containing a liquid enables mixing of the gases by converting energy of moving or sloshing liquid in a liquid-filled lower portion of the vessel into energy for moving the gases. The system includes (1) a hydro-driven actuator that is movably driven in response to the movement of the liquid in the vessel, (2) a mixing device driven by the actuator such that motion of the mixing device effects mixing of the gases contained in the headspace above the liquid, and (3) a motion converter for converting motion of the actuator into motion for driving the mixing device. The mixing device can be driven without the need to run electrical power within the vessel and without the transfer of motion through an external wall of the vessel. | 06-06-2013 |
20130149110 | OFF AXIS PUMP WITH INTEGRATED CHAIN AND SPROCKET ASSEMBLY - An off axis hydraulic pump for an automatic motor vehicle transmission includes an integrated chain and sprocket assembly. A first, chain drive sprocket is mounted on a shaft driven by an input to a torque converter and a second, driven chain sprocket is attached to a stub shaft which drives the pump. A multi-link chain encircles the sprockets and transfers drive torque from the torque converter input to the stub shaft. The first, chain drive sprocket is retained on the input shaft by a retainer cap which includes seals between both the shaft and a torque converter housing. The second, driven chain sprocket is retained on the stub shaft by a snap ring or similar component. | 06-13-2013 |
20130149111 | GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE FOR LOW FAN PRESSURE RATIO - A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle movable relative a fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. | 06-13-2013 |
20130149112 | GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE - A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle movable relative to a fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. | 06-13-2013 |
20130149113 | GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE FOR LOW FAN PRESSURE RATIO - A gas turbine engine includes a fan section with twenty (20) or less fan blades and a fan pressure ratio less than about 1.45. | 06-13-2013 |
20130195624 | GEARED TURBOFAN ENGINE WITH COUNTER-ROTATING SHAFTS - A mid-turbine frame is incorporated into a turbine section of a gas turbine engine intermediate a high pressure turbine and a low pressure turbine. The high pressure and low pressure turbines rotate in opposite directions. A plurality of vanes redirect the flow downstream of the high pressure turbine as it approaches the low pressure turbine. | 08-01-2013 |
20130195625 | INTEGRAL SCROLL AND GEARBOX FOR A COMPRESSOR WITH SPEED CHANGE OPTION - The volute is cast integrally with the gearbox base to allow closer radial tolerances to be used to improve efficiency. In the preferred embodiment, compressors for multi-stage compression are assembled with intercoolers and the integral volute is cast together with the impeller housing and the lower gearbox housing and the associated intercooler. Efficiency increases of 2% or more are achievable. In multistage applications, efficiency gains in the early stages are compounded in each subsequent stage. Speed changes that change center distance between bull gear and pinion are accommodated by an offset opening in the inlet and diffuser that can line up with the impeller shaft as well as an offset opening in the fluid seal despite a pinion gear change, by reorientation and remounting of those parts. | 08-01-2013 |
20130202414 | RELATIVISTIC MECHANICAL DEVICE - A mechanical device includes a prime mover, and a number of rotating masses. Each mass is rotated simultaneously around centers of rotation in two or three planes that are at right angles to each other. The device includes one or more timing devices that are synchronized. The timing devices fix the relationship of the two simultaneous input rotations. In this device, internal energy creates an internal differential that is equalized by an external acceleration of the total mass, and internal energy is transferred to the exterior. | 08-08-2013 |
20130202415 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. The engine includes a combination of quantities providing beneficial operation. | 08-08-2013 |
20130202416 | DRIVE DEVICE - [Object] To provide a drive device capable of increasing the drive precision of a movable member for generating power and capable of suppressing the generation of abraded particles. | 08-08-2013 |
20130223991 | GAS TURBINE ENGINE DRIVING MULTIPLE FANS - A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears. Each of the at least four gears extends through a drive shaft to drive an associated fan rotor. | 08-29-2013 |
20130223992 | COUNTER-ROTATING LOW PRESSURE TURBINE WITH GEAR SYSTEM MOUNTED TO TURBINE EXHAUST CASE - A gas turbine engine includes a shaft defining an axis of rotation. An inner rotor directly drives the shaft and includes an inner set of blades. An outer rotor has an outer set of blades interspersed with the inner set of blades. The outer rotor is configured to rotate in an opposite direction about the axis of rotation from the inner rotor. A gear system couples the outer rotor to the shaft and is configured to rotate the inner set of blades at a lower speed than the outer set of blades. | 08-29-2013 |
20130223993 | COUNTER-ROTATING LOW PRESSURE TURBINE WITH GEAR SYSTEM MOUNTED TO TURBINE EXHAUST CASE - A gas turbine engine includes a shaft defining an axis of rotation. An outer rotor directly drives the shaft and includes an outer set of blades. An inner rotor has an inner set of blades interspersed with the outer set of blades. The inner rotor is configured to rotate in an opposite direction about the axis of rotation from the outer rotor. A gear system couples the inner rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades. | 08-29-2013 |
20130223994 | OIL BAFFLE FOR GAS TURBINE FAN DRIVE GEAR SYSTEM - A turbine engine includes a housing supporting compressor, turbine sections, and an epicyclic gear train including a carrier. Sun gear and intermediate gears are arranged about and intermeshing with the sun gear. The intermediate gears are supported by the carrier. A baffle includes a lubrication passage near at least one of the sun gear and intermediate gears for directing a lubrication on the at least one of the sun gear and intermediate gears. | 08-29-2013 |
20130230385 | TURBINE PISTON - A torque converter includes an impeller with a plurality of impeller blades and a shell with a radial wall disposed radially outside of the blades. The converter also includes a cover fixed to the impeller shell to form a housing, and a turbine. The turbine includes a plurality of turbine blades and a shell with a radial wall disposed radially outside of the turbine blades. The turbine radial wall is arranged to frictionally engage the impeller shell radial wall. In some example embodiments, the turbine shell includes indented slots and the turbine blades include tabs disposed in the slots. In an example embodiment, the turbine blades are fixed to the turbine shell by brazing. | 09-05-2013 |
20130243579 | BARRING GEAR ASSEMBLY FOR DRIVING IN ROTATION A SHAFT OF A TURBO-ALTERNATOR GROUP - The barring gear assembly is designed to drive in rotation a shaft of a turbo-alternator group having an axis of rotation A. The barring gear assembly includes a main wheel fixed on said shaft and defining lateral sides located on either side of the axis of rotation A, a barring gear module having a support piece on which is mounted a clutch system for coupling and uncoupling a secondary shaft to and from the main wheel, the secondary shaft being driven by an auxiliary motor, and the barring gear module being positioned on one of said lateral sides (C | 09-19-2013 |
20130251511 | TORQUE FRAME BUSHING ARRANGEMENT FOR GAS TURBINE ENGINE FAN DRIVE GEAR SYSTEM - A fan drive gear system for a gas turbine engine includes a carrier that supports circumferentially arranged gears. A torque frame has circumferentially arranged fingers with each finger including a bore having a bore axis. A bushing is arranged in each bore and provides an aperture. At least one bushing has a bushing axis offset from the bore axis. A pin is disposed in the aperture and secures the carrier to the torque frame. | 09-26-2013 |
20130259648 | COMPACT GEARBOX FOR RAM AIR TURBINE OIL MANAGEMENT - A ram air turbine gearbox housing includes a housing body that has a first flange that defines a first plane and a second flange that defines a second plane that is transverse to the first plane. The housing body extends around an axis and has a first axial end and an opposite, second axial end that are each open to an internal cavity of the housing body. The housing body includes a radially-enlarged section at least partially defining an oil sump within the internal cavity of the housing body. | 10-03-2013 |
20130259649 | GAS TURBINE ENGINE FAN DRIVE GEAR SYSTEM DAMPER - A gas turbine engine includes a fan section. A turbine section is coupled to the fan section via a geared architecture. The geared architecture includes a torque frame and a flex support spaced apart from one another at a location. A gear train is supported by the torque frame. A damper is provided between the torque frame and the flex support at the location. | 10-03-2013 |
20130259650 | GEARED TURBOFAN WITH THREE TURBINES WITH FIRST TWO CO-ROTATING AND THIRD ROTATING IN AN OPPOSED DIRECTION - A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool rotating in the same direction as the intermediate speed spool. The fan drive turbine rotates in an opposed direction as the intermediate speed spool. | 10-03-2013 |
20130259651 | DIFFERENTIAL GEARED ARCHITECTURE FOR GAS TURBINE ENGINE - A gas turbine engine includes first and second shafts rotatable about a common axis. A first turbine section is supported on the first shaft. Second compressor and turbine sections are supported on the second shaft. The gas turbine engine includes a fan, a first compressor section, and a differential gear train that couples the fan and the first compressor section to the first shaft. | 10-03-2013 |
20130259652 | GEARED ARCHITECTURE WITH INDUCER FOR GAS TURBINE ENGINE - A gas turbine engine includes first and second shafts rotatable about a common axis. A first turbine section is supported on the first shaft. Second compressor and turbine sections are supported on the second shaft. The gas turbine engine includes a fan. A first compressor section is arranged in an axial flow relationship with the second compressor and the first and second turbines. A geared architecture operatively connects the first shaft and the fan. An inducer operative couples to the gear train. | 10-03-2013 |
20130259653 | GEARED TURBOFAN ENGINE WITH POWER DENSITY RANGE - A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in a second direction opposed to the first direction. | 10-03-2013 |
20130259654 | GEARED ARCHITECTURE WITH SPEED CHANGE DEVICE FOR GAS TURBINE ENGINE - A gas turbine engine includes first and second shafts rotatable about a common axis. The gas turbine engine includes a fan, and first and second gear trains interconnected to one another and coupling the first shaft to fan. | 10-03-2013 |
20130259655 | GAS TURBINE ENGINE FAN DRIVE GEAR SYSTEM DAMPER - A gas turbine engine includes a fan section. A turbine section is coupled to the fan section via a geared architecture. The geared architecture includes a torque frame and a flex support spaced apart from one another at a location. A gear train is supported by the torque frame. A damper is provided between the torque frame and the flex support at the location. | 10-03-2013 |
20130259656 | Gas Turbine and Gas Turbine Power Facilities - Disclosed is a gas turbine and a gas turbine power facility which flexibly accommodate changes in layout of devices and in user's needs. | 10-03-2013 |
20130266421 | TIE SHAFT ARRANGEMENT FOR TURBOMACHINE - A turbomachine includes a tie shaft extending along an axis. Multiple rotors are mounted on the tie shaft. First and second clamping members are secured to the tie shaft and exert a clamping load between the rotors and clamping members at multiple interfaces. The clamping load at one of the interfaces includes a radial clamping load of greater than 5% of a total design clamping load at the one interface. In one example, one of the clamping members is provided by a hub including a first leg extending between first and second opposing ends. The first end provides a flange configured to be supported by the tie shaft. The second end includes first and second hub surfaces respectively extending in radial and axial directions. The first leg is inclined between 15° and 75° relative to the axial direction. | 10-10-2013 |
20130294893 | ACTUATION SYSTEM FOR A PROPULSIVE UNIT OF AN AIRPLANE - The invention relates to an actuation system ( | 11-07-2013 |
20130315714 | METHOD FOR PULLING A BEARING BODY OFF THE ROTOR OF A GAS TURBINE AND TUBULAR SHAFT EXTENSION - A method is provided for pulling a bearing body off the rotor of a gas turbine having a casing, while the casing is closed. The method includes fixing a shaft extension on the relevant end of the rotor. In order to free the bearing body of the weight of the rotor, the method involves supporting the rotor and/or holding the rotor. The method further includes fitting sliding elements between the bearing body and the rotor, and moving the bearing body axially along the machine axis onto the shaft extension. | 11-28-2013 |
20130323024 | FUEL PUMP - A fuel pump includes a pump cover on one side of a housing, a cover end portion on the other side of the housing, a stator inside the housing, a rotor inside the stator, a shaft rotatable with the rotor, an impeller rotatable with the shaft to pressurize fuel inside the housing, a bearing portion provided in the cover end portion on its center axis to slidably support an end part of the shaft, and a relief valve capable of reducing a fuel pressure inside the housing. The cover end portion has an end surface located on its side opposite from the pump cover, and the relief valve includes a valve seat located on an opposite side of the end surface of the cover end portion from the pump cover. | 12-05-2013 |
20130336770 | Turbine - Disclosed is a turbine for a machine for projecting abrasive for the surface treatment of objects. The turbine includes a first flange and a second flange, at least one blade element provided with a guide surface for receiving, guiding and projecting the abrasive, and a mounting system for releasable mounting of the blade element on the flanges. The mounting system includes a support element arranged between the blade element and the flanges and configured for a releasable mounting on the flanges and for supporting the blade element. | 12-19-2013 |
20140003912 | BEARING SUPPORT FOR A TURBOCHARGER | 01-02-2014 |
20140003913 | INFINITELY ADJUSTABLE COOLANT PUMP | 01-02-2014 |
20140023486 | TIE SHAFT FOR GAS TURBINE ENGINE AND FLOW FORMING METHOD FOR MANUFACTURING SAME - A method is disclosed for manufacturing a tie shaft for aero or land based gas turbine engine. The method includes flow forming a tie shaft preform to produce a tie shaft. In one example, the tie shaft includes a nickel alloy cylindrical wall having a length to diameter ratio of at least 6:1, wherein the diameter is an average outer diameter. The wall includes a minimum effective strain of 0.3 in/in (7.6 mm/mm), and a grain size is in the range of G4 to G16 per ASTM E112. The wall includes a roll formed threaded surface having a thread roughness of less than 1260 μin (32 microns). | 01-23-2014 |
20140037432 | CONTROLLABLE COOLANT PUMP - A coolant pump for a coolant circuit of an internal combustion engine, the coolant pump having a pump housing in which is mounted a drivable shaft, to one end of which is attached an impeller-which has vanes extending into a suction chamber and is connected to a cover plate. Fluid can be drawn into the suction chamber through an intake port of the pump housing by joint rotation of the impeller and the cover plate and can be conveyed by the vanes into the pump housing. A guide plate, which is axially displaceable by an actuation unit, is disposed between the impeller and the cover plate. The guide plate has a contour corresponding to the impeller and a collar oriented toward the impeller. The coolant pump is characterized in that the guide plate has at least one opening. | 02-06-2014 |
20140064930 | Turbine Engine Transmission Gutter - A turbine engine case defines a centerline and a gaspath within the engine case. A fan is coupled to a fan shaft. A transmission couples the shaft to the fan shaft to drive the fan and comprises a gear system. A gutter system is positioned to capture lubricating fluid slung from the gear system. The gutter system includes a gutter extending partially circumferentially about the centerline having a first circumferential end edge. An inlet channel has an inlet at the gutter first circumferential end edge and locally radially outboard of the gutter. At least one vane is spaced apart from the gutter first circumferential end edge. | 03-06-2014 |
20140064931 | WATER PUMP - In a water pump, a reinforcement rib is integrally installed on either an outer surface or an inner surface of a flange wall of a pulley and radially extended toward an outer direction from a center side at which one end section of a drive shaft is coupled. | 03-06-2014 |
20140064932 | GAS TURBINE ENGINE FAN DRIVE GEAR SYSTEM DAMPER - A gas turbine engine includes a fan section. A turbine section is coupled to the fan section via a geared architecture. The geared architecture includes a torque frame and a flex support spaced apart from one another at a location. A gear train is supported by the torque frame. A viscous damper is provided between the torque frame and the flex support at the location. | 03-06-2014 |
20140072408 | VACUUM PUMP - A vacuum pump has a rotor mounted on a rotor shaft and provided with pump active components cooperating with opposite stationary pump active components, fastening element for securing the rotor on the rotor shaft, and a safety element provided in addition to the fastening element for preventing rotation of the rotor and the rotor shaft relative to each other. | 03-13-2014 |
20140072409 | PUMP AND PROTECTOR FOR PUMP - The invention relates to a pump, in particular a centrifugal pump ( | 03-13-2014 |
20140093357 | GAS TURBINE SYSTEM AND CORRESPONDING METHOD FOR ASSEMBLING - Method and gas turbine system having a reduced footprint. The gas turbine system includes a gas turbine configured to produce energy and having a gas turbine shaft; an auxiliary equipment attached to the gas turbine; an overhung shaft of the auxiliary equipment being configured to be attached to the gas turbine shaft; a flexible joint configured to be provided between the shaft of the auxiliary equipment and the gas turbine shaft; and a bearing system having at least two bearing units provided at a first end of the shaft of the auxiliary equipment next to the flexible joint. A second end of the shaft of the auxiliary equipment is free of bearings. | 04-03-2014 |
20140105728 | HYDRAULIC PUMP CONFIGURATION FOR AUTOMATIC TRANSMISSION - An automatic transmission pump assembly includes a torque converter housing and pinion that rotate about a first axis, an idler engaged with the pinion, a gear engaged with the idler, shaft secured to the gear, and a pump rotor secured to the shaft and that rotates about a second axis offset from the first axis. | 04-17-2014 |
20140105729 | WIND TURBINE ELECTRICAL GENERATOR - A wind turbine electrical generator can provide wind powered portable or stationary electrical power at a user site or application without the need of utility services. The wind turbine electrical generator incorporates tunneling and multiplying available wind via funneling to produce more power at a wind turbine driven generator. The generator is portable and is mounted on a utility size trailer frame suitable for permanent anchoring or can moved about as needed. The generator is complete, needing only an electrical connection to the user's intended application. | 04-17-2014 |
20140112763 | TURBOMACHINE FOR COMPRESSING A FLUID - A turbomachine for use as a compressor has a tubular housing centered on an axis, a rotor at least generally centered on the axis in the housing, and bearings supporting the rotor in the housing for rotation about the axis. The rotor is formed by a small-diameter shaft extending along and centered on the axis, formed with at least one mounting collar, and carried by the bearings, and by a plurality of annular disks fitted axially together and formed with radially outwardly extending vanes. At least one of the disks is fitted with and secured to the mounting collar. | 04-24-2014 |
20140119892 | Mixed Flow Fan Assembly - A mixed flow fan assembly uses induced reverse ambient air flow through the in-line motor enclosure for motor cooling, motor segregation from primary exhaust contamination, and augmentation of volumetric flow rate. Induced ambient airflow through openings in and/or around the base of the fan housing balances low pressure around the fan wheel and the inlet cone to inhibit primary exhaust recirculation and increase volumetric flow rate. Straightening vanes downstream of the fan wheel are used to axially reorient radial and tangential velocity components of primary effluent flow. Airfoil impeller blades have a scalloped and/or perforated single-thickness trailing edge to attenuate fan noise. | 05-01-2014 |
20140126999 | High Efficiency Hydro-mechanical Vehicle Transmission - A vehicle transmission consisting of two or more fixed displacement hydraulic pumps mounted on a common shaft (input) which provide the fluid to drive one or more fixed displacement hydraulic motors on a second common shaft (output) and a means of selectively activating and deactivating the pumps and motors to change the rotational speed of the second shaft with respect to the first shaft. The two shafts are connected by a selectable one way clutch to allow the hydraulic elements to be bypassed under certain operating conditions. Variations include the use of a reduction gear driving the input shaft and a two or more speed mechanical transmission on the output shaft. A hydraulic reservoir and accumulator are provided for energy storage and to accomplish instantaneous torque control. When used to provide hydraulic regenerative braking, the roles of pumps and motors are reversed. | 05-08-2014 |
20140133965 | METHOD AND APPARATUS FOR ENERGY RECOVERY FROM FLUID FLOWS - An energy recovery apparatus includes a fixed frame, a shaft, an impeller vane, and an energy transfer unit. A fluid stream exits the host device along a flow axis. The fixed frame defining a longitudinal axis mounts the host device. The shaft is rotatably mounted to the fixed frame parallel to the longitudinal axis. The impeller vane is connected to the shaft to cause rotation when the fluid stream of the host device strikes the impeller vane. The energy transfer unit is linked to the shaft to transfer energy from the energy recovery apparatus when the shaft rotates thereby recovering energy from the fluid stream. A geologic heat exchange system includes at least one conduit in thermal contact with the geologic environment. A coolant distribution system is in fluid communication with the conduit such that heat exchange with the geologic environment occurs. | 05-15-2014 |
20140140817 | MICRO GAS TURBINE HAVING COMPACT STRUCTURE - Disclosed is a micro gas turbine having a compact structure. The micro gas turbine includes a turbine wheel, a tie shaft connected, at one end thereof, to the turbine wheel, a compressor wheel spaced from the turbine wheel and mounted to the tie shaft, a thrust rotor spaced from the compressor wheel and fixed to an end of the tie shaft, a thrust collar provided on a portion of an outer surface of the thrust rotor, and a sub journal bearing provided between the thrust collar and the compressor wheel. | 05-22-2014 |
20140147253 | COUNTER ROTATING HELICO-AXIAL PUMP - A counter rotating helico-axial pump is provided, the pump comprising: (a) an inner rotor comprising a plurality of outwardly extending helico-axial impeller vanes; (b) a hollow outer rotor comprising a plurality of inwardly extending helico-axial impeller vanes; (c) a single driving device configured to drive the inner rotor or the hollow outer rotor; and (d) a force transmission coupling joining the inner rotor and the hollow outer rotor and configured to permit rotation of the inner rotor and hollow outer rotor in opposite directions; wherein at least a portion of the inner rotor is disposed within the hollow outer rotor, and wherein the inner rotor, the hollow outer rotor and the helico-axial impeller vanes define a fluid flow path, and wherein the inner rotor and hollow outer rotor are configured such that at least some of adjacent helico-axial impeller vanes are configured to rotate in opposite directions. | 05-29-2014 |
20140154054 | OIL BAFFLE FOR GAS TURBINE FAN DRIVE GEAR SYSTEM - A turbine engine comprises compressor and turbine sections. An epicyclic gear train includes a carrier, a sun gear and intermediate gears arranged about and intermeshing with the sun gear. The intermediate gears are supported by the carrier. A baffle includes a lubrication passage near at least one of the sun gear and intermediate gears for directing a lubricant on at least one of the sun gear and intermediate gears. A method of designing a turbine engine is also disclosed. | 06-05-2014 |
20140161591 | LUBRICANT SYSTEM - An aircraft engine having a fan or propeller stage mounted to a planetary gearing system through a planetary gearing output drive shaft is provided with a lubricant system having a seal with lubricant delivery chamber for receiving a lubricant and a sealing surface sealing against a rotatable shaft, the rotatable shaft has a hollow interior and an opening in registration with the delivery chamber. The lubricant system has a lubricant pump in fluidical communication with and downstream of the opening. | 06-12-2014 |
20140219784 | PROPULSION DEVICE - A propulsion device is disclosed which is capable of lifting and/or propelling a person or an aircraft, such as a helicopter or airplane, through the air. | 08-07-2014 |
20140241861 | FLUID PUMP WITH SHAFT DRIVEN PUMPING ELEMENT - In at least some implementations, a fluid pump includes a drive shaft including at least one drive surface and a pumping element. The pumping element includes an opening in which a portion of the drive shaft is received so that the pumping element is driven for rotation by the drive shaft, and the opening is larger than the drive shaft to provide a clearance between the pumping element and at least part of the drive shaft. The pumping element also includes at least one engagement surface arranged to be engaged by the drive surface of the drive shaft when the drive shaft is rotated where one or both of the drive surface and the engagement surface are angled to provide a surface area of engagement between the drive surface and engagement surface that is at least 1% of the surface area of the drive surface. | 08-28-2014 |
20140255162 | Adjustable Floating Oil Channel for Gas Turbine Engine Gear Drive - A turbine is operably connected to drive a compressor, and to drive a fan through a gear drive. A number of intermediate gears connecting an output shaft of the turbine to a fan drive shaft for the fan. An oil channel collects oil thrown outwardly of the gear drive. A bearing support mounts bearings supporting the fan drive shaft. The oil channel and the bearing support each include mating faces that are bolted together by a plurality of bolts. The bolts extend through oil channel holes in the mating face of the oil channel. The oil channel holes have one dimension which closely receives the bolts and another dimension which is larger than an outer diameter of the extending portion of the bolts, such that the bolts may adjust radially within the oil channel holes. | 09-11-2014 |
20140271135 | Turbofan Engine Bearing and Gearbox Arrangement - A turbofan engine ( | 09-18-2014 |
20140286754 | Elongated Geared Turbofan With High Bypass Ratio - A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (D | 09-25-2014 |
20140321983 | MOBILE ROTARY DRIVE FOR A ROTOR OF A WIND POWER PLANT - The invention relates to a mobile rotary drive for a wind rotor of a wind power plant having a frame comprising a drive wheel for driving a segment of a rotor shaft of the wind power plant and a drive set which drives the drive wheel in rotation as a drive pinion, wherein the drive wheel is a friction wheel and interacts with a pressing device in such a way that the pressing device generates a force which presses the friction wheel onto the segment with the result that the friction wheel can apply a drive torque to the segment through friction, wherein a torque support for supporting an opposing torque to the drive torque generated by the friction wheel is also provided. Thanks to the friction wheel drive, there is no need for specific pre-equipping of the wind power plant. The invention makes available a mobile rotary drive which can be transported from one wind power plant to another. | 10-30-2014 |
20140341715 | ROTARY MACHINE INCLUDING A MACHINE ROTOR WITH A COMPOSITE IMPELLER PORTION AND A METAL SHAFT PORTION - A rotary machine includes a machine stator and a machine rotor rotatable relative to the machine stator and having a metal shaft portion, a composite impeller portion, and at least a first metal ring portion securing the composite impeller portion to the metal shaft portion, the metal ring portion having a first interface with the composite impeller portion and a second interface with the metal shaft portion. | 11-20-2014 |
20140348640 | THRUST EFFICIENT TURBOFAN ENGINE - A turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in ambient air. A power turbine converts the gas stream flow into shaft power. The power turbine rotates at a first rotational speed. A speed reduction device is driven by the power turbine. A propulsor section includes a fan driven by the power turbine through the speed reduction device at a second speed lower than the first speed for generating propulsive thrust as a mass flow rate of air through a bypass flow path. The fan includes a tip diameter greater than about fifty (50) inches and an Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine is less than about 0.30 at a take-off condition. | 11-27-2014 |
20150023784 | ROTATION DRIVE DEVICE - Provided is a rotation drive device including a shaft member extending in a first direction, and a rotating object configured to allow the shaft member to be inserted in the rotating object, and configured to rotate around an axis of rotation extending in the first direction relative to the shaft member. Opposite ends of the shaft member are fixedly joined to respective inner surfaces of a first partition wall and a second partition wall located on the opposite sides in the first direction of the rotating object. | 01-22-2015 |
20150030437 | Fan Device and Electronic Device Thereof - A fan device and an electronic device thereof are disclosed. The fan device is disposed in a casing of the electronic device and adjacent to a board of the casing, wherein the board has a first state and a second state. The fan device includes a plurality of fan blades, a shaft, and a ball. The shaft is connected to the plurality of fan blades and allows the plurality of fan blades rotating with the shaft, wherein at least one end of the shaft has a ball accommodating portion and an opening. The ball is disposed in the ball accommodating portion and limited by the opening for not separate from the ball accommodating portion. When the board is in the first state, a gap is between the ball and the casing. When the board is in the second state, the board and the ball touch each other. | 01-29-2015 |
20150050126 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger ( | 02-19-2015 |
20150098802 | SHROUDED TURBINE BLISK AND METHOD OF MANUFACTURING SAME - Shrouded turbine blisks and methods of manufacturing same are provided. A shrouded turbine blisk includes a central disk portion including an axis of rotation, an inner rim, a plurality of airfoils that extends radially outwardly from the inner rim; and a shroud integrally coupled to each of the plurality of airfoils. The shroud includes a plurality of circumferentially-arranged arcuate shroud segments defined at least in part by gaps positioned between adjacent shroud segments. The central disk portion, the inner rim, the plurality of airfoils, and the shroud are defined from a single billet of blisk material. | 04-09-2015 |
20150110605 | MARINE CURRENT POWER GENERATION DEVICE - In one embodiment, a marine current power generation device has rotary blades, rotating shaft, power generator, guide bearings, thrust collars and thrust bearings. The guide bearing has a second slide surface being slidable relative to the first slide surface of the rotating shaft. The thrust bearing has a fourth slide surface being slidable relative to the third slide surface of the rotary plate of the thrust collar. The materials of the first and third slide surfaces include ferrous materials, stainless materials, Ti, Ti alloy, Co, or Co alloy. The materials of the second and fourth slide surfaces include a resin material filled with a first fibrous member and a second fibrous member. The second fibrous member is smaller than the first fibrous member. | 04-23-2015 |
20150125269 | COUPLING OF SHAFTS USING VARIABLE-PROFILE SPLINES - A device for coupling two shafts by a gear mechanism includes a coupling part ending one of the two shafts. The coupling part is fitted concentrically into a complementary coupling part ending the other shaft. Splines of the coupling part have a constant profile along a median zone of the coupling part and which, in a first zone in continuation of the median zone, has a smaller thickness, between flanks of a spline, than a maximum thickness of the same spline in the median zone. Splines of the coupling part continue, beyond the first zone, as far as a centering zone on the same side as the first zone. The splines and the spline bottoms have, in the coupling zone between the centering zone and the first zone, a profile that continuously couples the splines and the spline bottoms to the surface of the centering zone. | 05-07-2015 |
20150300256 | MULTIPLE BEARING STACK RETENTION - An arrangement of concentric, independently rotating shafts for a rotating gear train system is disclosed. The arrangement may include an inner shaft, the inner shaft operatively couplet to a rotating element, and an outer shaft, the outer shaft concentric with the inner shaft and arranged radially outward from the inner shaft. The arrangement may further include a first bearing stack, the first bearing stack arranged radially outward from the inner shaft and including at least one preloaded ball bearing and a second bearing stack, the second bearing stack arranged radially outward from the outer shaft and comprising at least one ball bearing. The arrangement may include a bearing stack retainer, the bearing stack retainer mating with the first and second bearing stacks to hold the first and second bearing stacks in position with respect to the inner and outer shafts and the bearing stack retainer coupled with and rotating with the outer shaft. | 10-22-2015 |
20150361829 | FLUID COLLECTION GUTTER FOR A GEARED TURBINE ENGINE - A turbine engine system includes a gutter and a gear train with an axial centerline. The gutter is disposed radially outside of the axial centerline. The gutter at least partially circumscribes the gear train, and includes an inner surface and a channel. The channel receives fluid directed out of the gear train. The channel extends radially into the gutter from the inner surface to a channel end, and circumferentially to a channel outlet. At least a portion of the channel has a cross-sectional channel geometry that tapers axially as the channel extends radially towards the channel end. | 12-17-2015 |
20150381224 | WIRELESS COMMUNICATION SYSTEM AND METHOD - A marine propulsor comprises: a stationary part and a movable part which is movable relative to the stationary part; and a wireless communication system, comprising at least one transmitter which is disposed in the movable part and is configured to transmit an electromagnetic data signal and at least one receiver which is disposed in the stationary part and is configured to receive the electromagnetic data signal. The wireless communication system includes a diversity scheme for mitigating multipath distortion of the electromagnetic data signal between the at least one transmitter and the at least one receiver. | 12-31-2015 |
20160003098 | Compartment Shielding - A gas turbine engine having an engine axis and method of manufacturing the same is disclosed. The gas turbine engine may comprise a fan configured to drive air, a low pressure compressor section having a core flow path and configured to draw in and compress air flowing along the core flow path, a spool configured to drive the fan, and geared architecture configured to adjust the fan speed. The gas turbine engine may also include a housing defining a compartment that encloses the geared architecture. The housing is disposed between the core flow path and the axis, and includes a shielded mid-section that is in thermal communication with the core flow path of the low pressure compressor section. The shielded mid-section includes an outer layer and an insulator adjacent to the outer layer. | 01-07-2016 |
20160024957 | GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE - A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, a first compressor section including three (3) or more stages, a second compressor section including between eight (8) and thirteen (13) stages, and a first turbine section operable for driving the first compressor section, the first turbine section including between three (3) and six (6) stages, a second turbine section operable for driving the second compressor section, and a gear train defined along an engine centerline axis. One of the first turbine section and the second turbine section is operable to drive the fan section through the gear train. | 01-28-2016 |
20160024958 | GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE - A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, a low spool that includes a low pressure compressor section, the low pressure compressor section including three (3) or more stages, and a high spool including a high pressure compressor section. The high pressure compressor section includes between eight to thirteen (8-13) stages. A gear train is defined along an engine axis. The low spool is operable to drive the fan section through the gear train. | 01-28-2016 |
20160024965 | Geared Architecture Turbofan Engine Thermal Management System and Method - A method of sizing a heat exchanger for a geared architecture gas turbine engine includes sizing a minimum frontal area of at least one heat exchanger located in communication with a fan bypass airflow such that a ratio of waste heat area to horsepower generation characteristic area is between 1.6 to 8.75. | 01-28-2016 |
20160032755 | V-SHAPED GEARBOX FOR DRIVING TURBOMACHINE EQUIPMENT - A gearbox for driving equipment of a turbomachine, including a substantially V-shaped box having two arms joined together by a joining part, the arms containing gear trains joined together at the joining part, and an attachment to the turbomachine. The attachment include a mechanism for insetting and/or for attaching the joining part and a suspension device of the arms. | 02-04-2016 |
20160032828 | GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE - A gas turbine engine including a core nacelle defined about an engine axis. A fan nacelle is mounted at least partially around the core nacelle to define a fan bypass airflow path for a fan bypass airflow. A gear train is defined along an engine axis. The gear train defines a gear reduction ratio of greater than or equal to about 2.3. A spool along the engine axis drives the gear train. The spool includes a downstream turbine having six or fewer stages. A fan is driven through the gear train by the downstream turbine. A pressure ratio across the fan is less than about 1.45. A fan variable area nozzle is axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. | 02-04-2016 |
20160040601 | TRANSVERSE MOUNTED ACCESSORY GEARBOX - An accessory gear box for a gas turbine engine having a drive shaft with a rotational axis and a tower shaft coupled to the drive shaft is provided. The accessory gear box includes a first plurality of gears arranged, which extend along a first axis substantially parallel to the rotational axis of the drive shaft. The accessory gear box includes a second plurality of gears, which extend along a second axis. The accessory gear box includes a first shaft, with one of the first plurality of gears coupled to the first shaft, and one of the second plurality of gears coupled to a second shaft. The one of the second plurality of gears coupled to the first shaft includes a first engagement surface and a second engagement surface, and the second engagement surface is coupled to another one of the second plurality of gears to drive the second shaft. | 02-11-2016 |
20160047268 | GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a spool along an engine axis which drives a gear train, the spool including a low stage count low pressure turbine. | 02-18-2016 |
20160061057 | LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE - According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension D that is based on a dimension of the fan blades. Each fan blade has a leading edge. An inlet portion is situated forward of the fan. A length of the inlet portion has a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion. A dimensional relationship of L/D is between about 0.2 and 0.45. | 03-03-2016 |
20160069624 | Direct-Drive System For Cooling System Fans, Exhaust Blowers And Pumps - The present invention is directed to a load bearing direct-drive system and a variable process control system for efficiently managing the operation of fans in a cooling system such as a wet-cooling tower, air-cooled heat exchanger (ACHE), HVAC system, blowers and centrifugal blowers, mechanical towers or chiller systems. In one embodiment, the load bearing direct-drive system comprises a load bearing torque multiplier device having an output rotatable shaft connected to a fan, and a load bearing motor comprising a rotatable shaft that drives the load bearing torque multiplier device. | 03-10-2016 |
20160083062 | PROPULSION SYSTEM HAVING COUNTER-ROTATING IMPELLERS - A marine propulsion system includes a housing configured to be coupled to, or within, a marine vessel hull. At least one pair of counter-rotating impellers is disposed within the housing such that the rotation occurs in a plane generally parallel to the surface of the water. A moveable output nozzle is coupled to the rear portion of the housing and can move to facilitate controlling the direction of travel of the vessel. | 03-24-2016 |
20160097330 | GAS TURBINE ARCHITECTURE - A geared architecture for a gas turbine comprising an output shaft for connection with a fan, an input shaft and a gearbox connecting the input shaft with the output shaft. The gearbox has a forward planet carrier plate supported by a forward radially fixed bearing structure and a rearward planet carrier plate supported by a rearward radially fixed bearing structure. By supporting the carrier plates on radially fixed bearing structures the planet carriers can rotate about their own axis to lower vibration and mesh forces within the gearbox. | 04-07-2016 |
20160097331 | GAS TURBINE ARCHITECTURE - A geared architecture for a gas turbine comprising an output shaft for connection with a fan, an input shaft and a gearbox connecting the input shaft with the output shaft. The gearbox has a forward planet carrier plate supported by a forward radially fixed bearing structure and a rearward planet carrier plate supported by a rearward radially fixed bearing structure. By supporting the carrier plates on radially fixed bearing structures the planet carriers can rotate about their own axis to lower vibration and mesh forces within the gearbox. | 04-07-2016 |
20160107754 | SINGLE STAGE ENGINE BLEED - An environmental control system is provided. The environmental control system may receive pressurized air from a single supply line. A pressure regulating turbomachine may be located within the supply line. A motor-generator may be coupled to the pressure regulating turbomachine. In response to a pressure in the supply line being less than a desired pressure in the environmental control system, the motor-generator may supply energy to the pressure regulating turbomachine, causing the pressure regulating turbomachine to function as a compressor. In response to a pressure in the supply line being greater than a desired pressure in the environmental control system, the pressure regulating turbomachine may function as a turbine and supply energy to the motor-generator. | 04-21-2016 |
20160123149 | ROTARY MACHINE SYSTEM - A rotary machine system ( | 05-05-2016 |
20160123223 | SPEED REDUCED DRIVEN TURBOCHARGER - Disclosed is a speed reduced driven turbocharger that utilizes a step-down roller that is coupled to a turbo shaft with a traction interface. Either a flat or a shaped traction interface can be used. The step-down roller mechanically actuates either a mechanical or hydraulic transmission, or can be mechanically coupled to an electric motor/generator. | 05-05-2016 |
20160138425 | TURBOFAN ENGINE FRONT SECTION - A front section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a fan hub. The fan hub includes a hub diameter supporting a plurality of fan blades including a tip diameter. A transitional entrance passage is configured to communicate flow between the fan section and a compressor section. The transitional entrance passage includes an inlet disposed at an inlet diameter and an outlet to the compressor section disposed at an outlet diameter. A method of designing a gas turbine engine is also disclosed. | 05-19-2016 |
20160138474 | LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE - A gas turbine engine according to an example of the present disclosure includes, among other things, a fan and a turbine section having a fan drive turbine rotor, and a compressor rotor. A gear reduction effects a reduction in a speed of the fan relative to an input speed from the fan drive turbine rotor. The compressor rotor has a number of compressor blades in at least half of a plurality of blade rows of the compressor rotor. The blades are configured to operate at least some of the time at a rotational speed. The number of compressor blades in the at least half of the blade rows and the rotational speed is such that the following formula holds true for each row of the at least half of the blade rows of the compressor rotor: (the number of blades×the rotational speed)/60 s≧about 5500 Hz. | 05-19-2016 |
20160138477 | THREE SPOOL GEARED TURBOFAN WITH LOW PRESSURE COMPRESSOR DRIVE GEAR SYSTEM - A turbofan engine includes a fan rotatable about an axis and a compressor section including a high pressure compressor and a low pressure compressor. A turbine section includes a high pressure turbine, an intermediate turbine and a fan drive turbine. The high pressure turbine is coupled to drive the high pressure compressor. A fan drive gear system is driven by the fan drive turbine for driving the fan and a compressor drive gear system is driven by the intermediate turbine for driving the low pressure compressor. | 05-19-2016 |
20160138478 | GAS TURBINE ENGINE - A gas turbine engine is disclosed comprising a shaft driven by a turbine, the turbine directly driving a lower speed compressor via a shaft and driving a higher speed compressor via the shaft and a multiplier power gearbox. The gearbox comprises a ring gear, a plurality of planet gears and planet carrier and a sun gear. The input from the turbine to the gearbox is to the carrier and the output from the gearbox to drive the higher speed compressor is from the sun gear or the ring gear. | 05-19-2016 |
20160138603 | SPLIT AXIAL-CENTRIFUGAL COMPRESSOR - A gas turbine engine including a compressor, a turbine, and a variable-ratio unit is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The variable-ratio unit is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor. | 05-19-2016 |
20160146102 | GEARED ARCHITECTURE GAS TURBINE ENGINE WITH OIL SCAVENGE - A gas turbine engine includes a geared architecture with a multiple of intermediate gears, and a baffle with an oil scavenge scoop adjacent to each of the multiple of intermediate gears. A geared architecture and method are also disclosed. | 05-26-2016 |
20160153310 | Three Spool Turbofan Engine With Low Noise Intermediate Turbine Rotor | 06-02-2016 |
20160153426 | BEARING AND GEAR UNIT FOR WIND TURBINES | 06-02-2016 |
20160160670 | VANE ASSEMBLY OF A GAS TURBINE ENGINE - A first stage vane array of a high pressure turbine that may be for a geared turbofan engine includes a plurality of airfoils circumferentially spaced from one-another and orientated about an engine axis. Each airfoil has a leading edge and a trailing edge with the trailing edge being circumferentially separated by the next adjacent trailing edge by a pitch distance. The leading a trailing edges of each one of the plurality of airfoils are axially separated by an axial chord length. A pitch-to-chord ratio of the pitch distance over the axial chord length is equal to or greater than 1.7. | 06-09-2016 |
20160169235 | VISCOUS FAN DRIVE SYSTEMS WITH FAN DRIVE SLIP FEEDBACK | 06-16-2016 |
20160177774 | LOW NOISE TURBINE FOR GEARED GAS TURBINE ENGINE | 06-23-2016 |
20160195012 | TURBOMACHINE PROVIDED WITH AN ASSEMBLY FOR CONTROLLING THE PITCH VARIATION OF A PROPELLER | 07-07-2016 |
20160195021 | LOW NOISE COMPRESSOR AND TURBINE FOR GEARED TURBOFAN ENGINE | 07-07-2016 |
20160201569 | EXHAUST NOZZLE ARRANGEMENT FOR GEARED TURBOFAN | 07-14-2016 |
20160201570 | EXHAUST NOZZLE ARRANGEMENT FOR GEARED TURBOFAN | 07-14-2016 |
20160252170 | TORQUE CONVERTER DRIVE CONNECTION | 09-01-2016 |
20170233049 | PROPULSION UNIT | 08-17-2017 |