Class / Patent application number | Description | Number of patent applications / Date published |
415066000 | Serially spaced in working fluid flow path | 74 |
20090245998 | Fluid Flow Machine with Multi-Flow Rotor Arrangement - A fluid flow machine includes at least one casing 1 and at least one rotor drum 3 rotatable about a machine axis 4, with stator vanes 8 and rotor blades 7 being arranged in an annulus duct 2 formed between the casing 1 and the rotor drum 3 The annulus duct 2 is divided into an outer annular duct 5 and an inner annular duct 6 by at least one annular flow divider 11, in each of which rotor blades 7 and stator vanes 8 are arranged Outer rotor blades 7 | 10-01-2009 |
20100158665 | SUPERSONIC COMPRESSOR - A novel supersonic compressor is provided by the present invention. In one embodiment, the novel supersonic compressor comprises a fluid inlet, a fluid outlet, and at least two counter rotary supersonic compressor rotors, said supersonic compressor rotors being configured in series such that an output from a first supersonic compressor rotor having a first direction of rotation is directed to a second supersonic compressor rotor configured to counter-rotate with respect to the first supersonic compressor rotor. | 06-24-2010 |
20110020108 | TWO-STAGE TURBO-CHARGER ENGINE SYSTEM - A turbine housing for a high-pressure turbo-charger of a turbo-charger engine system for an internal combustion engine is provided that includes, but is not limited to a low-pressure charger opening for taking up a low-pressure turbo-charger and a high-pressure charger opening for taking up a high-pressure turbo-charger. A high-pressure exhaust opening is attached to a corresponding flange at an exhaust manifold of the engine and there is a short-cut exhaust opening with a high-pressure turbine by-pass valve area attached to a corresponding flange at the exhaust manifold. An external connection opening is attached to a muffler, a waste gate valve area being provided in the close vicinity of the external connection opening. | 01-27-2011 |
20110052371 | Multi-Component Bladed Rotor for a Turbomachine - A multipart bladed rotor ( | 03-03-2011 |
20120128464 | FAN ASSEMBLY - A fan assembly includes two fans, and a number of rigid bars. The fans are connected in series. Each of the fans includes an impeller. The impellers of the fans rotate in opposite directions. The rigid bars extend through the fans and are fixed to the fans, to counteract opposing torque forces produced by the fans. | 05-24-2012 |
20130004293 | FAN ASSEMBLY - A fan assembly includes a first fan and a second fan stacked together. Each of the first fan and the second fan includes a frame and a supporting base received in the frame. Several extending portions extend from a bottom of the frame of the first fan. A buckling block is formed on an inner side face of each of the extending portions. Several receiving portions are formed at a top of the frame of the second fan corresponding to the extending portions, respectively. A positioning groove is defined in each of the receiving portions. The buckling blocks are engagingly received in the positioning grooves. | 01-03-2013 |
20130280035 | System for the Heating and Pumping of Fluid - A fluid heating and pumping system comprising a housing that has an inlet and outlet opening as well as a plurality of turbine chambers. Each of the turbine chambers has: an inlet end, outlet end, is mounted to a driveshaft, a stator and rotor, and is constructed to create a circuitous flow path for fluid flow. Each of the rotors is: designed to move the fluid through the housing, and has a plurality of rotor vanes with each having a fin at the inlet end. The fin extends past the plane of an adjacent rotor vane to extend the circuitous flow path through the rotors. The fins, shearing plane, and outlet orifice all create thermal energy as the fluid is transferred along and between the rotor and stator vanes, through the shearing plane and between the adjacent turbine chambers as the fluid flows. | 10-24-2013 |
20130280036 | AXIALLY-SPLIT RADIAL TURBINE - An axially-split radial turbine includes a forward rotor section and an aft rotor section being mechanically and abuttingly coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split radial turbine. The axially-split radial turbine can be provided as part of a gas turbine engine. | 10-24-2013 |
20140219775 | COMPRESSION SYSTEM - Provided is a compression system including: at least one impeller; a gear train configured to the at least one impeller; a main drive shaft configured to drive the gear train; and a housing comprising an impeller container configured to house the at least one impeller and a gear train container configured to house the gear train. | 08-07-2014 |
20140301827 | HOUSING OF A RADIAL COMPRESSOR - Exemplary embodiments of the present disclosure are directed to a 2-stage supercharging unit having a housing unit which integrates within it a high-pressure charger and a low-pressure charger. The rotor axes of the two chargers are vertical with respect to the housing unit, which can be screwed directly via the housing base to the side of an internal combustion engine. As a result, increased flexibility is made possible with regard to the connection of the supercharging unit to the cooler and to the internal combustion engine, whereby the structural volume of the supercharging assembly can be additionally reduced. | 10-09-2014 |
20140363272 | SERIAL AXIAL FAN - A fan includes a first motor portion, a first impeller fixed to a first rotating portion of the first motor portion, a second motor portion arranged along a central axis of the first motor portion, a second impeller fixed to a second rotating portion of the second motor portion, a tubular wind channel portion arranged to surround the first and second impellers, and support ribs arranged to join the wind channel portion to the first and second motor portions. The first impeller includes first blades arranged in a circumferential direction about the central axis and the second impeller includes second blades arranged in the circumferential direction, a rotation direction of the second impeller is opposite to a rotation direction of the first impeller. A surface of each first blade which faces the second impeller is concave. A surface of each second blade which faces the first impeller is concave. | 12-11-2014 |
20150010384 | TURBINE SEAL SYSTEM AND METHOD - A system includes a multi-stage turbine. The multi-stage turbine includes a first turbine stage with a first wheel having a plurality of first blade segments spaced circumferentially about the first wheel, a second turbine stage with a second wheel having a plurality of second blade segments spaced circumferentially about the second wheel, and an interstage seal assembly extending axially between the first and second turbine stages. The interstage seal assembly includes a first coverplate coupled to the first turbine stage. The first coverplate includes a first seal. The interstage seal assembly also includes a second coverplate coupled to the second turbine stage. The second coverplate includes a second seal. The interstage seal assembly also includes a spacer wheel extending from a rotor shaft and configured to engage with the first coverplate and the second coverplate. | 01-08-2015 |
20150050123 | SWITCHED RELUCTANCE, FULLY SUPERCONDUCTING, INTEGRATED RING TURBINE MOTOR, GENERATOR GAS TURBINE, ENGINE STAGE (SSRGTS) - A superconducting integrated ring turbine motor generator gas turbine engine stage of the present invention includes a combination of turbine vanes, rotors and blisk assemblies that prevent temperatures during operation from interfering with the extraction or control of power generation processes. The engine stage includes a ring having an evenly spaced array of aerodynamic vanes affixed on the inside or outside of the ring. The vanes are spaced apart by a nonmagnetic armature assembly spacer ring. | 02-19-2015 |
20150300264 | GEARED TURBOFAN ARCHITECTURE FOR REGIONAL JET AIRCRAFT - A gas turbine engine comprises an upstream compressor rotor and a downstream compressor rotor, each having a first stage blade row and a tip speed defined at the first stage blade row. A ratio of the tip speed of the first stage of the downstream compressor rotor to the tip speed of the first stage in the upstream compressor rotor is equal to or above about 1.18. | 10-22-2015 |
20160047304 | ULTRA HIGH OVERALL PRESSURE RATIO GAS TURBINE ENGINE - A gas turbine engine comprises a first turbine positioned upstream of a second intermediate turbine and a third turbine positioned downstream of the first and second turbines. A fan and three compressors, with an upstream one of the compressors connected to rotate with the fan rotor, and the third turbine driving the upstream compressor and the fan both through a gear reduction. A second intermediate compressor is driven by the second intermediate turbine rotor, and a third compressor downstream of the first and second compressors is driven by the first turbine rotor. | 02-18-2016 |
20160076459 | GEARED FAN WITH INNER COUNTER ROTATING COMPRESSOR - A gas turbine engine has a fan section including a fan hub supporting a plurality of fan blades for rotation relative to a fan case. A shaft is rotatable relative to the fan case about an engine center axis. A geared architecture is driven by the shaft and provides driving output to rotate the fan hub. A compressor is driven by the shaft and is positioned forward of the geared architecture. The compressor includes at least first and second stages with the first stage being positioned forward of the plurality of fan blades and the second stage being positioned aft of the plurality of fan blades. The compressor includes at least one set of vanes that rotate in a first direction about the engine center axis and at least one set of compressor blades that rotate in a second direction about the engine center axis. The second direction is opposite of the first direction. | 03-17-2016 |
415067000 | With initial fluid flow path to each runner | 1 |
20130315707 | STEPPED PARTING JOINT ON A TRANSMISSION HOUSING OF A FLUID MACHINE - A divisible housing of a fluid machine for a transmission to be received in the divisible housing is provided. The transmission provided for receiving in the divisible housing includes a large wheel and at least two pinion shafts which are in engagement with the large wheel. The divisible housing includes a first housing element and a second housing element which is connected to the first housing element via a parting joint. The at least two pinion shafts may be received in the parting joint. The parting joint includes a parting joint step, the at least two pinion shafts being receivable in the parting joint on both sides of the parting joint step. | 11-28-2013 |
415068000 | Coaxial runners | 57 |
20080260517 | FAN APPARATUS - A fan apparatus includes a casing and a fan unit. The casing is a hollow member having an inlet and an outlet. The fan unit has an inlet and an outlet, and includes a plurality of axial fans. The fan unit is disposed on the inside of the casing, and the inlet of the fan unit is disposed in the vicinity of the inlet of the casing. The position of the fan unit within the casing can be varied in order to alter the air flow and static pressure of the air discharged by the fan apparatus. | 10-23-2008 |
20090191045 | LOW PRESSURE TURBINE WITH COUNTER-ROTATING DRIVES FOR SINGLE SPOOL - A low pressure turbine for a gas turbine engine includes inner and outer counter-rotating rotor sets, with both said rotor sets driving a common shaft. | 07-30-2009 |
20100008757 | Ducted fan assembly for radio-controlled model - A ducted fan assembly includes a housing unit, a motor, and a propeller. The housing unit includes a duct member, and a hollow seat member disposed in the duct member. The motor is mounted to an exterior of the seat member, and includes a power cord extending through the seat member. The propeller is mounted to the motor and is driven thereby to generate an airflow that flows through the duct member and that acts on the motor. | 01-14-2010 |
20100054913 | TURBOMACHINE WITH UNDUCTED PROPELLERS - Turbomachine, comprising two external coaxial and contra-rotating unducted propellers ( | 03-04-2010 |
20100189544 | COUNTER-ROTATING AXIAL-FLOW FAN - A counter rotating axial flow fan that reduces vibration generation over a wide rotational speed range. A disk-shaped cushioning member is disposed between a circular plate portion of a first support frame main body half portion and a circular plate portion of a second support frame main body half portion. The cushioning member is compressed, with hook portions forming a plurality of engaging portions and hole portions forming a plurality of engaged portions completely engaged with each other. | 07-29-2010 |
20100303608 | Two-shaft gas turbine - A two-shaft gas turbine includes a high-pressure turbine having an annular gas-passage outlet, a low-pressure turbine having an annular gas-passage inlet, an annular intermediate duct that connects the gas-passage outlet to the gas-passage inlet, a bearing that supports a rotor of the high-pressure turbine and that is attached to a bearing case, and a plurality of struts that support the bearing case. The struts are arranged radially along the circumference of the bearing case so as to extend though the intermediate duct in a space between an outer peripheral surface of the bearing case and an inner peripheral surface of a casing wall that surrounds the intermediate duct. The intermediate duct has strut covers through which the struts extend and which function as first-stage stator blades for the low-pressure turbine. | 12-02-2010 |
20110097189 | BOUNDARY LAYER EFFECT TURBINE - Described herein are embodiments of a boundary layer effect turbine and a hydrodynamic speed reducer. Described is a boundary layer effect turbine that utilizes the phenomena of the boundary layer to drive a turbine impeller that is made of a plurality of spaced disks oriented along a rotatable shaft. As operating fluid is directed over surfaces of the plurality of disks of the boundary layer effect turbine, energy is transferred from the fluid to the disks as a result of the adhesive and viscous properties of the fluid. | 04-28-2011 |
20110129332 | AXIAL-CENTRIFUGAL COMPRESSOR HAVING SYSTEM FOR CONTROLLING PLAY - In an axial-centrifugal compressor, the rotor of which includes an impeller, axial play is controlled by a special air ventilation to the rotor, by a circuit including two parallel arms, flow rates of which are both controlled by respective veins, and moreover the temperature in one of them is changed by a heat exchanger. The ventilation air is thus controlled, both in terms of temperature and flow rate. | 06-02-2011 |
20120328412 | PUMP SYSTEM - A regenerative pump ( | 12-27-2012 |
20130039742 | COMPOSITE BOUNDARY LAYER TURBINE - A turbine includes a plurality of stacked disks, each disk comprising an opening in the center of the disk, which forms a central flow chamber. The turbine further includes a first disk that is coupled to a bottom of the plurality of stacked disks. The first disk does not have an opening in the center like the stacked disks. There is a plurality of disk spacers positioned between one or more of the plurality of stacked disks, thereby creating flow channels between the disks. The flow channels extend from an outside perimeter of the stacked disks to the central flow chamber. A tapered armature is coupled to the first disk and positioned within the central flow chamber, and a fluid collection unit is in communication with the outside perimeter of the stacked disks. | 02-14-2013 |
20130064645 | NON-CONTINUOUS RING SEAL - An assembly is disclosed that includes a first rotating component and a second rotating component disposed adjacent to the first rotating component. An annular slot may be defined between the first and second rotating components and may include a sealing surface. Additionally, a seal may be disposed within the annular slot and may be configured to be engaged against the sealing surface when the first and second rotating components are rotated. Moreover, the seal may form a non-continuous ring within the annular slot when the seal is engaged against the sealing surface. | 03-14-2013 |
20130149105 | TURBO-MOLECULAR PUMP - An object of the present invention is to enhance the capacity of a turbomolecular pump. | 06-13-2013 |
20130189076 | SERIES FAN ASSEMBLY STRUCTURE - A series fan assembly structure includes a first fan and a second fan mated with the first fan. The first fan includes a first frame body and at least one mating section diagonally positioned on two opposite corners of one side of the first frame body. The second fan includes a second frame body and at least one connection section diagonally positioned on two opposite corners of one side of the second frame body corresponding to the mating section. The connection section is connected with the mating section, whereby the series fan assembly structure is easy to rework and has better vibration absorption effect. | 07-25-2013 |
20130209223 | TURBOMACHINE - A turbomachine including at least one blade-row group that is arranged in the main flow path and at least two rows of blades that are adjacent to each other in the main flow direction, each row having a plurality of blades, whereby the trailing edges of the blades of the upstream row of blades and the leading edges of the blades of the downstream row of blades are arranged at an axial edge distance that decreases from the center of the main flow path in the direction of at least one main flow limiter. | 08-15-2013 |
20130209224 | TURBOMACHINE - A turbomachine including at least one blade-row group that is arranged in the main flow path and at least two rows of blades that are adjacent to each other in the main flow direction, each row having a plurality of blades ( | 08-15-2013 |
20130223983 | COUNTER ROTATING LOW PRESSURE TURBINE WITH SPLITTER GEAR SYSTEM - A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A splitter gear system couples the inner turbine 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 |
20130223984 | Multi-Stage Axial Compressor with Counter-Rotation - A multi-stage axial compressor incorporating a counter-rotational movement is provided with a series of rotors mounted along and driven by a driveshaft, and a geared counter-rotating outer casing. A planetary gear system is assembled along a static casing, which can be assembled as a forward or aft casing for the compressor. The bearings of the planetary gear system typically will be aligned concentrically with a center rotor drum assembly mounted along the single driveshaft. The counter-rotating drum assembly will be assembled over the rotor drum assembly and will be engaged by the forward and aft casings so as to provide for counter-rotation of selected ones of the rotors driven by the driveshaft of the compressor. | 08-29-2013 |
20130259643 | GEARED TURBOFAN WITH THREE TURBINES WITH FIRST TWO COUNTER-ROTATING, AND THIRD CO-ROTATING WITH THE SECOND TURBINE - 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, with the high speed spool rotating in an opposed direction to the intermediate speed spool. The fan drive turbine rotates in the same direction as the intermediate speed spool. | 10-03-2013 |
20130259644 | MULTI-STAGE CENTRIFUGAL COMPRESSOR AND RETURN CHANNELS THEREFOR - A multi-stage impeller is configured in a multi-stage centrifugal compressor by fixing and attaching a plurality of centrifugal impellers to one rotating shaft. Diffusers and return channels are provided in order downstream from each impeller. The centrifugal impellers, the diffusers and the return channel are housed within a compressor casing. The return channels have a plurality of vanes positioned at intervals from one another in a circumferential direction, and at least two stages are provided. The vane exit angles monotonically increase toward the downstream stage. | 10-03-2013 |
20130287545 | GEARED TURBOFAN WITH THREE TURBINES ALL COUNTER-ROTATING - 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 and the fan drive turbine configured to rotate in the same first direction. The intermediate speed spool rotates in an opposed, second direction. | 10-31-2013 |
20130343871 | SERIES FAN ASSEMBLY STRUCTURE - A series fan assembly structure includes a first fan frame and a second fan frame. The first fan frame has a first latch section, a second latch section, a first engagement recess, a second engagement recess, a first retainer section and a second retainer section. The second fan frame has a third latch section, a fourth latch section, a third engagement recess, a fourth engagement recess, a third retainer section and a fourth retainer section. The first and second engagement recesses are respectively connected with the third and fourth latch sections, the first and second latch sections are respectively connected with the third and fourth engagement recesses and the first and second retainer sections are respectively connected with the third and fourth retainer sections. Accordingly, the first and second fan frames can be quickly assembled and securely connected in both axial direction and radial direction. | 12-26-2013 |
20140017065 | ROTOR APPARATUS - A rotor apparatus for extracting energy from bidirectional fluid flows comprises a first rotor ( | 01-16-2014 |
20140050563 | STACKED WHEEL ASSEMBLY FOR A TURBINE SYSTEM AND METHOD OF ASSEMBLING - A stacked wheel assembly for a turbine system includes a plurality of wheels. A stud includes a forward end having a circumferential surface with at least one relatively planar portion and a first groove extending circumferentially around at least a portion of the circumferential surface. A first nut is disposed proximate a forward face of one of the plurality of wheels to receive the forward end of the stud. A resilient arcuate member is configured to fittingly reside within the first groove. A lock plate having at least one slotted region is disposed proximate an outer surface of the lock plate to fittingly engage at least one lug disposed on a forward region of the first nut for rotationally retaining the stud and a second groove is disposed within an inner surface of the lock plate to receive the resilient arcuate member for axially retaining the lock plate. | 02-20-2014 |
20140056688 | INLINE AXIAL FLOW FAN - There is disclosed an inline axial flow fan including at least first and second axial flow fans and arranged in an inline manner along an axial direction of a rotational shaft of a rotational driving apparatus. A first flow control grid is arranged in a gas discharge side of the first axial flow fan, and a second flow control grid is arranged in a gas discharge side of the second axial flow fan. The first flow control grid has a stator blade having a smooth circular arc leading edge shape matching a circular arc shape of the stator blade of the first axial flow fan and a trailing edge shape extending in parallel with a gas flow direction. The second flow control grid has a stator blade having a smooth circular arc shape matching a circular arc shape of the stator blade of the second axial flow fan. | 02-27-2014 |
20140112756 | A TWO-SPOOL DESIGN FOR A TURBOSHAFT ENGINE WITH A HIGH-PRESSURE COMPRESSOR CONNECTED TO A LOW-PRESSURE TURBINE - A turboshaft engine including a low-pressure compressor, a high-pressure compressor, a low-pressure turbine, a high-pressure turbine, and a regulator for regulating a speed of rotation of the low-pressure turbine to a speed that is substantially constant. The low-pressure turbine is coupled by a first shaft to the high-pressure compressor, while the high-pressure turbine is coupled by a second shaft to the low-pressure compressor. | 04-24-2014 |
20140119885 | TURBINE ENGINE ASSEMBLY AND METHODS OF ASSEMBLING SAME - A turbine engine assembly is provided. The turbine engine assembly includes a core gas turbine engine including a first rotatable drive shaft, a first low-pressure turbine section in serial flow communication with the gas turbine engine, a gear assembly coupled to the first low-pressure turbine section through a second rotatable drive shaft, and a second low-pressure turbine section in serial flow communication with the core gas turbine engine. The first low-pressure turbine section is configured to rotate in a first rotational direction, and the second low-pressure turbine section is configured to rotate in a second rotational direction opposite the first rotational direction. The first and second low-pressure turbine sections are spaced axially apart from each other. The turbine engine assembly also includes a fan assembly coupled to the first low-pressure turbine section through the gear assembly, and coupled to the second low-pressure turbine section through a third rotatable drive shaft. | 05-01-2014 |
20140126994 | RADIAL GAS EXPANDER - This radial gas expander is provided with a rotating shaft, an impeller which is fixed to the rotating shaft, and a casing by which the rotating shaft is supported in a rotatable manner and in which an introduction channel introducing fluid to the impeller is formed. The introduction channel includes a nozzle blade which guides fluid flowing into the impeller and a support member which is provided in the upstream side of the nozzle blade and which supports wall surfaces of the introduction channel, wherein the wall surfaces are mutually opposed, and the support member has a wing shape in a cross-sectional view. | 05-08-2014 |
20140147249 | GAS TURBINE ENGINE ROTOR DRAIN FEATURE - An assembly for a gas turbine engine includes a rotor formed by a drum and a hub. The drum has a generally conically shaped inner surface that defines a flow path along a first cavity. The hub is connected to the drum and has a conically shaped inner surface that defines a flow path along a second cavity. | 05-29-2014 |
20140241856 | 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. | 08-28-2014 |
20140255154 | REACTION-TYPE TURBINE - A reaction-type turbine according to the present invention is configured in that a portion of a rotary shaft module which penetrates through a side with an inlet portion of a housing has a diameter larger than the diameters of other portions. Thus, the pressurized area in which a working fluid applies pressure to a rotary shaft in the direction opposite to the working fluid flow direction increases, thus increasing force in the direction opposite to the working fluid flow direction. As a result, axial direction force applied to the rotary shaft in the working fluid flow direction may be reduced. Therefore, the reaction-type turbine of the present invention has the advantages of eliminating the necessity of installing a separate thrust bearing for supporting axial force in the working fluid flow direction. | 09-11-2014 |
20140271125 | STEAM TURBINE - A steam turbine | 09-18-2014 |
20140321975 | WIND TURBINE - The invention relates to a wind power station ( | 10-30-2014 |
20150037136 | Overhung Turbine and Generator System With Turbine Cartridge - A turbine-generator device for use in electricity generation using heat from industrial processes, renewable energy sources and other sources. The generator may be cooled by introducing into the gap between the rotor and stator liquid that is vaporized or atomized prior to introduction, which liquid is condensed from gases exhausted from the turbine. The turbine has a universal design and so may be relatively easily modified for use in connection with generators having a rated power output in the range of 50 KW to 5 MW. Such modifications are achieved, in part, through use of a modular turbine cartridge built up of discrete rotor and stator plates sized for the desired application with turbine brush seals chosen to accommodate radial rotor movements from the supported generator. The cartridge may be installed and removed from the turbine relatively easily for maintenance or rebuilding. The rotor housing is designed to be relatively easily machined to dimensions that meet desired operating parameters. | 02-05-2015 |
20150125262 | SERIES FAN ASSEMBLING STRUCTURE - A series fan assembling structure includes a connection assembly, a first fan and a second fan. The connection assembly has a first connection member having a first end face and a second end face opposite to the first end face. A second connection member is disposed at an upper end of the first connection member to outward horizontally extend from the first end face. A third connection member is disposed at a lower end of the first connection member to outward horizontally extend from the second end face. A passage is formed at the centers of the first and second end faces. The first fan is mated with the first end face of the first connection member and horizontally connected with the second connection member. The second fan is mated with the second end face of the first connection member and horizontally connected with the third connection member. | 05-07-2015 |
20150291276 | UNDUCTED THRUST PRODUCING SYSTEM ARCHITECTURE - An unducted thrust producing system has a rotating element with an axis of rotation and a stationary element. The rotating element includes a plurality of blades, and the stationary element has a plurality of vanes configured to impart a change in tangential velocity of the working fluid opposite to that imparted by the rotating element acted upon by the rotating element. The system includes an inlet forward of the rotating element and the stationary element. | 10-15-2015 |
20150354361 | ROTOR ASSEMBLY AND METHOD OF MANUFACTURING THEREOF - A rotor assembly is provided. The rotor assembly includes a rotor shaft and at least one blisk integrally formed with the rotor shaft. The at least one blisk includes an inner rim extending circumferentially about the rotor shaft, and a plurality of blades extending radially outward from the inner rim, wherein the rotor shaft and the at least one blisk are defined from a single billet of material. | 12-10-2015 |
20150369250 | TURBINE APPARATUS WITH COUNTER-ROTATING BLADES - A turbine apparatus has a main shaft, a first set of blades mounted to the main shaft, a second set of blades, and a barrel affixed to a periphery of the second set of blades. The barrel is rotatably mounted independent of a rotation of the main shaft. The barrel and the second set of blades rotates in a direction opposite to the direction of rotation of the first set of blades and the main shaft. A third set of blades is mounted to the main shaft such that the second set of blades is interposed between the first and third sets of blades. An outer shell extends over and an outer surface of the barrel such that the barrel is rotatable interior of the outer shell. | 12-24-2015 |
20160076444 | MULTI-FAN ENGINE WITH AN ENHANCED POWER TRANSMISSION - A multi-fan engine including a gas turbine engine, a casing and fans encased by geared rings, which connect with the geared rings of an adjacent fan(s) such that the rotation of one fan rotates the other fans. Intermediate gears may prove the connection between adjacent geared rings, wherein the intermediate gears are retracted by linear actuators to disengage the intermediate gears from the geared rings and thereby disengage the fans from each other. The multi-fan engine may be mounted flush to the fuselage of an aircraft invention to capture into the fans boundary layer airflow moving over the skin of the fuselage. | 03-17-2016 |
20160115815 | TURBINE ASSEMBLY - The invention relates to a turbine in which a bypass-passage extends through a base member of a stationary vane to join seal cavities of adjacent rotating blade rows so that seal flow passing between a casing and shrouds of the rotating blades at least partially bypasses the turbine main flow passage. | 04-28-2016 |
20160146101 | GAS TURBINE WITH PLURALITY OF TIE RODS AND METHOD OF ASSEMBLING THE SAME - Disclosed herein is a gas turbine with a plurality of tie rods. The gas turbine includes a compressor section having a plurality of compressor-side rotor disks, a turbine section having a plurality of turbine-side rotor disks arranged downstream of the compressor-side rotor disks, a first tie rod penetrating central portions of the rotor disks provided in the compressor section to press the compressor-side rotor disks against each other, a plurality of second tie rods penetrating vicinities of edges of the rotor disks provided in the turbine section to press the turbine-side rotor disks against each other, and a torque transfer member coupled to the first and second tie rods so as to transfer rotational torque generated by the turbine section to the compressor section. | 05-26-2016 |
20160160647 | TURBINE ENGINE ASSEMBLY AND METHOD OF MANUFACTURING - A turbine engine assembly is provided. The assembly includes a low-pressure turbine assembly including a first turbine section configured to rotate in a first rotational direction at a first rotational speed, and a second turbine section configured to rotate in a second rotational direction at a second rotational speed. The second rotational direction is opposite the first rotational direction and the second rotational speed is lower than the first rotational speed. The assembly also includes a first drive shaft coupled to the first turbine section, and a fan assembly including a first fan section coupled to the first drive shaft such that the first fan section rotates in the first rotational direction at the first rotational speed, and a second fan section coupled to the second turbine section such that the second fan section rotates in the second rotational direction at the second rotational speed. | 06-09-2016 |
20160186762 | HOUSING DEVICE FOR A COMPRESSOR STAGE OF A COMPRESSOR DEVICE THAT IS EMBODIED WITH MULTIPLE STAGES AND METHOD FOR MANUFACTURING A HOUSING DEVICE - A housing device for a compressor stage of a compressor device of an aircraft engine that is embodied in a multi-stage design, including a flange area for connection to at least one housing device of another compressor stage that is adjacent in the axial direction. The housing device has a rotor area that during operation of the housing device directly acts together with the rotor blades of a rotor device in the radial direction of the compressor device. Further, the housing device has at least one reception area that is provided for receiving guide blades of a stator device. At least one part of the housing device is made of a sheet metal part. What is further described is a method for manufacturing such a housing device, with at least one part of the housing device being manufactured by means of a forming process. | 06-30-2016 |
20160201495 | GAS TURBINE AND MOUNTING METHOD | 07-14-2016 |
20160201496 | GAS TURBINE AND MOUNTING METHOD | 07-14-2016 |
20160201606 | LOW WEIGHT LARGE FAN GAS TURBINE ENGINE | 07-14-2016 |
20180023482 | TURBINE SHAFT POWER TAKE-OFF | 01-25-2018 |
415069000 | One runner support surrounds another | 11 |
20100135770 | MID TURBINE FRAME SYSTEM FOR GAS TURBINE ENGINE - A gas turbine engine mid turbine frame having an inner case supporting at least one bearing and at least three spokes extending radially outwardly to an outer case, the mid turbine frame having an interturbine duct extending through the mid turbine frame, the interturbine duct spaced axially closer to an upstream turbine disc than a bearing supporting structure of the mid turbine frame and mounted axially slidingly relative to the bearing supporting structure to substantially isolate the bearing supporting structure from axial loads, for example such as disc loads incurred in the unlikely event a turbine disc shaft shears within the engine. | 06-03-2010 |
20160017797 | TURBOFAN AIRCRAFT ENGINE - A turbofan aircraft engine having a primary duct (C), including a combustion chamber (BK), a first turbine (HT) disposed downstream of the combustion chamber, a compressor (HC) disposed upstream of the combustion chamber and coupled (W | 01-21-2016 |
20160025003 | Turbofan Engine Bearing and Gearbox Arrangement - A turbofan engine ( | 01-28-2016 |
20160032827 | Turbofan Engine Bearing and Gearbox Arrangement - A turbofan engine ( | 02-04-2016 |
20160053679 | GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES - A turbine section of a gas turbine engine according to an example of the present disclosure includes, among other things, a fan drive turbine section and a second turbine section. The fan drive turbine section has a first exit area at a first exit point and is configured to rotate at a first speed. The second turbine section has a second exit area at a second exit point and is configured to rotate at a second speed, which is faster than the first speed. | 02-25-2016 |
20160061107 | Low Pressure Shaft - A low pressure shaft is provided for interconnecting a fan or low pressure compressor of a gas turbine engine with a low pressure turbine of the engine. The shaft has an aft section whose diameter expands progressively with distance along the rearward direction of the engine. The shaft further has an annular joint portion at the rear end of the aft section for joining the shaft to a drive arm of the low pressure turbine. The rate of expansion of the diameter of the aft section decreases with distance along the rearward direction of the engine. | 03-03-2016 |
20160069260 | COMPRESSOR SYSTEM - In a gas turbine engine, the booster compressor is driven by both the low pressure or fan shaft and high pressure shaft through a differential gear arrangement. The rotational speed of the booster compressor is intermediate between the speed of the fan and the speed of the high pressure compressor. | 03-10-2016 |
20160069297 | GEARED TURBINE ENGINE WITH O-DUCT AND THRUST REVERSER - A geared turbofan engine is provided that includes a first rotor, a second rotor and a gear train that are arranged along an axis within a casing. The first rotor is connected to and driven by the second rotor through the gear train. The casing includes a nozzle, a bifurcation, a thrust reverser and a flowpath. The flowpath extends axially to the nozzle and circumferentially between opposing surfaces of the bifurcation. | 03-10-2016 |
20160102607 | Compressor of Axial Turbine Engine with Contra-Rotating Rotor - The present application relates to an axial turbine engine with a turbine, a low-pressure compressor, and a fan. The turbine drives the compressor and the fan via a plurality of epicyclic reducing gears. The rotor of the compressor includes upstream a disc with a row of vanes and downstream a drum with a plurality of rows of vanes. The disc and the drum are connected to different parts of the epicyclic reducing gears, so as to be counter-rotating. The turbine engine includes a row of stator vanes arranged between two rows of rotor blades of the drum of the compressor, so as to straighten the flow and improve the efficiency. The turbine engine includes at least two epicyclic reducing gears, so that the vane rows of the drum turn faster than that downstream, which itself turns faster than the fan. | 04-14-2016 |
20160177725 | FIXED COAXIAL SHAFT FOR A HYDRAULIC UNIT | 06-23-2016 |
20160186656 | TRUNNION FOR HIGH-PRESSURE TURBINE, AND TURBOJET ENGINE INCLUDING SUCH A TRUNNION - The invention relates to a trunnion ( | 06-30-2016 |