Class / Patent application number | Description | Number of patent applications / Date published |
415199400 | Including an axial-flow blade set | 39 |
20080260526 | COUNTER-ROTATING AXIAL-FLOW FAN - A counter-rotating axial-flow fan includes a housing that is constituted from a first divided housing unit and a second divided housing unit. Engaging members and first stopper portions are integrally formed with a first flange portion of the first divided housing unit. The first stopper portions are arranged adjacent to the engaging members. Engaged members and second stopper portions are integrally formed with a second flange portion of the second divided housing unit. The second stopper portions are arranged adjacent to the engaged members. The second stopper portions have leading ends that are abutted onto leading ends of the first stopper portions when the engaging members are completely engaged with the engaged members. Thus, damage of the first and second divided housing units is prevented when the first and second divided housing units are coupled. | 10-23-2008 |
20090129918 | Blower unit - A blower unit has a first axial fan and a second axial fan for generating a flow of cooling air passing through a heat exchanger disposed under an intake duct through which an intake air to be introduced to an engine flows. The first axial fan and the second axial fan are aligned in a substantially horizontal direction downstream of the heat exchanger with respect to the flow of air. A first rotation axis of the first axial fan and a second rotation axis of the second axial fan are perpendicular to the heat exchanger and located lower than a center of the heat exchanger. The first axial fan, which is disposed on a right side of the second axial fan, rotates in a clockwise direction and the second axial fan rotates in a counterclockwise direction when viewed from a downstream position with respect to the flow of air. | 05-21-2009 |
20090214332 | MULTISTAGE PUMP ASSEMBLY HAVING REMOVABLE CARTRIDGE - A multistage pump assembly includes a manifold having an inlet port configured to be coupled to a supply pipe and an outlet port configured to be coupled to a discharge pipe. The inlet and outlet ports define an end suction, radial outlet port configuration. The pump assembly also includes a cartridge having a sleeve and plurality of pumping stages that define a pump stack received within the sleeve. An outer chamber is defined between the pump stack and the sleeve. Each of the pumping stages includes an impeller mounted along a pump shaft that rotates about a rotation axis. The cartridge is aligned horizontally such that the rotation axis is substantially horizontal. An end plate is positioned between the manifold and the cartridge and includes at least one cartridge engagement surface supporting the cartridge. The end plate is removably coupled to the manifold. | 08-27-2009 |
20100034648 | Method of assembling a multi-stage turbine or compressor - A method is disclosed for assembling a multi-stage compressor or a multi-stage turbine for use in a gas-turbine engine. The method comprises the steps of assembling a rotor drum so as to comprise a plurality of rotor discs | 02-11-2010 |
20100166546 | APPARATUSES, SYSTEMS, AND METHODS OF GAS TURBINE ENGINE COMPONENT INTERCONNECTION - One embodiment is an apparatus comprising a first rotational gas turbine engine component including first threads; a second rotational gas turbine engine component including second threads; the first threads and the second threads being mated; and the first rotational engine component being fastened to the second rotational engine component substantially only by the first threads and the second threads being mated. Other embodiments include unique apparatuses, systems, devices, and methods relating to gas turbine engine interconnection. Further exemplary embodiments, forms, objects, features, advantages, aspects, and benefits of the present invention are included in the following description, drawings, and claims. | 07-01-2010 |
20100172750 | AIR CONDITIONING APPARATUS EQUIPPED WITH A COMPRESSOR AND A VORTEX - An air-conditioner comprises, in an accommodating structure: an axial compressor powered by a built-in motor unit which circulates air, an axial flow-straightening stator to create a static pressure in excess of atmospheric pressure by transferring the air stream obtained in a static centrifugal compressor that creates a rotational flow with the air stream being routed through an axial flow-straightener/diffuser. The flow-straightener/diffuser is internally hollow to circulate ambient air and, externally, straightens the turbulent flow into an axial flow and relieves the pressure. A transfer valve is adapted to the flow-straightener/diffuser to selectively regulate the flow of hot air with the addition of ambient air. A vortex accelerates the air stream using a turbulence effect before it enters an expansion chamber that produces cold and directs the air stream into a final air control valve under the selected temperature conditions. | 07-08-2010 |
20100232954 | BYPASS DUCT OF A TURBOFAN ENGINE - In the area of the support struts and/or the aerodynamic fairings downstream of the stator vanes, the cross-section of the bypass duct of a turbofan engine is enlarged such that the pressure variations caused by the stagnation effect of the installations and reacting on the fan are reduced, enabling the fan to be operated with more efficiency and stability and finally the losses of the overall system and the fuel consumption to be reduced. The cross-sectional enlargement is accomplished by modifying the course of the wall in a limited area, actually by gradually enlarging the flow cross-section in the bypass duct in the axial and in the circumferential direction, with this enlargement being confined to the area around the leading edge of the support struts and/or the aerodynamic fairings. | 09-16-2010 |
20110164967 | AXIAL FLOW MACHINE HAVING AN ASYMMETRICAL COMPRESSOR INLET GUIDE BAFFLE - An axial flow machine having an asymmetrical air inlet and, downstream therefrom, a compressor having an inlet guide baffle composed of guide vanes is characterized in that at least some of the guide vanes of the inlet guide baffle have a vane profile and/or an angle of attack that deviate(s) from the remaining guide vanes. The inlet flow angle of the first compressor stage is hereby evened out circumferentially symmetrically. This is accomplished in that the different inlet angles resulting at various circumferential positions of the inlet guide baffle due to the asymmetry of the air inlet, are influenced by selective profiling and/or by selectively modifying the angle of incidence of individual guide vanes in such a way that a circumferentially symmetrical outflow angle from the inlet vane ring results. In this way, the circumferential distortions caused by the asymmetrical air inlet are minimized and, thus, circumferentially symmetrical inlet conditions are passed onto the first compressor stage, which results in an improved stability and an enhanced efficiency of the compressor. | 07-07-2011 |
20110223013 | Reduced Monobloc Multistage Drum of Axial Compressor - A rotor stage of an axial turbomachine compressor drum includes a symmetrical wall in rotation around the axis of rotation. The wall comprises a veil defining the general form of the drum and an annular area intended to support a row of vanes, the aforesaid area being integrally formed with the veil. This area has a particular form in that it has an exterior surface delimiting the fluid stream, which is elevated in relation to the veil. This area has a “U”-shape cross-section, of which the open part is directed towards the axis of rotation. The annular area comprises two wall parts, one upstream and one downstream, ensuring the connection with the veil and being used as stiffeners. They are preferably perpendicular to the axis of rotation or inclined in relation to the perpendicular. The junction of each upstream and downstream wall part with the central part of the support area is at the distance of the corresponding edge of the central part, so as to avoid certain stress concentrations. | 09-15-2011 |
20120014786 | WATER POWERED TURBINE AND TURBINE SYSTEMS - Disclosed herein are turbines and turbine systems that may be used to generate power and/or electricity from flowing water or may be used in various other applications such as the pumping of water. One embodiment of the disclosed turbines includes a plurality of blades that may be connected to a turbine housing by a hinge so that the blades are movable between an active state, wherein the blade is configured to contribute to the rotational movement of the turbine, and a passive state, wherein the blade is configured to minimally resist the rotation of the turbine. Turbine blades are disclosed with specific features that more efficiently capture water flow power. | 01-19-2012 |
20120087786 | Stator Structure of Turbo Molecular Pump and Method for Manufacturing the Same - The present invention discloses an improved stator structure of a turbo molecular pump and a method for manufacturing the same. The stator comprises a plurality of stator blade assemblies, and each stator blade assembly comprising an inner shroud ring, an outer shroud ring and a plurality of stator blades, wherein the inner shroud ring, the outer shroud ring and the plurality of stator blades are integrated so that the rigidity of the stator is increased and the stator is not easily to be deformed; the method for manufacturing the stator comprises the steps of: laying a raw material on a computer numerical control (CNC) lathe; proceeding an outline treatment to a shape of each stator blade assembly by a turnery process; and shaping the plurality of stator blades of each stator blade assembly with a five-axis processing machine. | 04-12-2012 |
20120128476 | NOZZLE STAGE FOR A TURBINE ENGINE - A nozzle stage for a turbine engine includes two substantially cylindrical rings, respectively an inner ring and an outer ring, with, extending between them: vanes carried by a first one of the rings; vanes carried by the second ring; and spacer-forming vanes interconnecting the two rings; the vanes of the first and second rings being arranged in alternation. | 05-24-2012 |
20120163965 | Axial Compressor - When a gas turbine is operated with inlet guide vanes (IGVs) closed during part load operation or the like, the degradation of aerodynamic performance and of reliability may potentially occur since the load on rear stage side vanes of a compressor increases. An object of the present invention is to suppress the degradation of the aerodynamic performance and of reliability of an axial compressor. | 06-28-2012 |
20150010394 | INDUCER - The present invention relates to an inducer geometry which can optimize the behavior stability of cavitation in an inducer having a plurality of blades of the same geometry. In the inducer having a plurality of blades of the same geometry, a blade loading at a tip side in a front half of a blade is larger than that in a rear half of the blade; and when a blade angle from a circumferential direction of the inducer is expressed by β | 01-08-2015 |
20150023786 | Serial Fan Device - a serial fan device including two fans linked serially is provided. Each of the two fans has a housing, a driving member and a fan wheel, the housing has an outer frame and a base, the outer frame has two openings and a guiding channel linking the two openings, the driving member is disposed on the base, and the fan wheel is rotatably coupled with the driving member. At least one of the two fans has a positioning rim on the outer frame for the base to couple therewith, and a radial buffer gap is formed between an outer periphery of the base and an inner periphery of the positioning rim. Accordingly, the radial buffer gap can largely reduce the vibration transmitted from the base to the outer frame. | 01-22-2015 |
20150125280 | ROTOR OF ROTARY MACHINE AND ROTARY MACHINE | 05-07-2015 |
415199500 | Plural serial axial-flow blade sets with intermediate stationary flow diverter(s) | 21 |
20090016876 | AXIAL TURBINE - An axial turbine includes a plurality of stages each comprising a plurality of stationary blades arranged in a row along the turbine circumferential direction and a plurality of moving blades in a row parallel to the stationary blades, each of the moving blade being disposed downstream of a respective one of the corresponding stationary blade in a flow direction of a working fluid so as to be opposed to the corresponding stationary blade. Herein, each of the stationary blades is formed so that the intersection line between the outer peripheral portion of the stationary blade constituting a stage having moving blades longer than moving blades in a preceding stage and a plane containing the central axis of the turbine, has a flow path constant diameter portion that includes at least an outlet outer peripheral portion of the stationary blade and that is parallel to the turbine central axis. | 01-15-2009 |
20090068003 | Gas Turbine Engine Systems and Related Methods Involving Vane-Blade Count Ratios Greater than Unity - Gas turbine engine systems and related methods involving vane-blade count ratios greater than unity are provided. In this regard, a representative turbine stage for a gas turbine engine includes a first set of rotatable blades operative to be positioned downstream of and adjacent to a first set of vanes, a number of blades of the first set of blades being less than a number of vanes of the first set of vanes. | 03-12-2009 |
20090081031 | Vertical vapor compressor - A vapor compressor for use with a distillation system, the compressor including a housing defining an interior volume. The housing includes an inlet and an outlet. A shaft has a first end and a second end and extends along a longitudinal axis of the housing. A first compression stage includes a first impeller and a first stator, the first impeller including a first plurality of impeller blades having a first dimension. The first stator includes a first plurality of stator blades having a second dimension. A second compression stage includes a second impeller and a second stator, the second impeller including a second plurality of impeller blades having a third dimension. The second stator includes a second plurality of stator blades having a fourth dimension. The first dimension and the third dimension are measured along corresponding portions of the first plurality of impeller blades and the second plurality of impeller blades, and the first dimension is greater than the third dimension. | 03-26-2009 |
20090263238 | DUCTED FAN WITH INLET VANES AND DESWIRL VANES - A fan apparatus includes a ducted housing with an axis of rotation including a first section and a second section. The fan apparatus further includes a first plurality of vanes being radially coupled within the first section and a second plurality of vanes being radially coupled within the second section. Additionally, the fan apparatus includes an impeller with a plurality of blades rotatably disposed within the ducted housing between the first plurality of vanes and the second plurality of vanes for rotary motion about the axis of rotation. The first plurality of vanes are stationary in a first arrangement to guide an inflow of air towards the impeller. The plurality of blades are rotary in a second arrangement to have a rotational direction substantially opposite to the inflow of air guided by the first arrangement. The second plurality of vanes are stationary in a third arrangement to diffuse an outflow of air substantially along the axis of rotation. | 10-22-2009 |
20100047065 | BLADE STRUCTURE OF GAS TURBINE - To reduce secondary flow loss and to improved turbine efficiency, a section located radially outward of a border section | 02-25-2010 |
20100054931 | SERIAL AXIAL FAN - A serial axial fan includes first and second axial fans. The first axial fan preferably includes a first motor portion, a first impeller, and a first housing. The second axial fan preferably includes a second motor portion, a second impeller, and a second housing. In the first impeller, an angle defined by a rotational plane of the first impeller with a chord of each blade of the first impeller on an imaginary cylindrical surface centered about a central axis increases as the radius of the imaginary cylindrical surface increases. | 03-04-2010 |
20100119364 | Stator - rotor assemblies having surface features for enhanced containment of gas flow, and related processes - A stator-rotor assembly which includes at least one interface region between the stator and rotor is described. At least one stator or rotor surface in the interface region includes a pattern of concavities. The concavities restrict gas flow through a gap between the stator and the rotor. Various turbomachines which can contain such a stator-rotor assembly are also described. The disclosure also discusses methods to restrict gas flow through gaps in a stator-rotor assembly, utilizing the concavities. | 05-13-2010 |
20100310361 | WIND TURBINE WITH TWO SUCCESSIVE PROPELLERS - A wind turbine comprises a tubular casing having an inlet opening, an outlet opening, an outer surface generating a pressure decrease, an inner surface presenting a convergent section joined to the inlet opening, a divergent section joined to the outlet opening and to the convergent section by a throat, and a propeller mounted rotating with respect to the tubular casing in proximity to the throat. It is coupled to a first generating machine. It comprises another propeller mounted rotating with respect to the tubular casing, placed upstream from the first propeller in the convergent section. | 12-09-2010 |
20120003085 | COMPRESSOR CASING WITH OPTIMIZED CAVITIES - The invention relates to a compressor for a turbine engine including a casing ( | 01-05-2012 |
20120148390 | Turbo Molecular Pump with Improved Blade Structures - The present invention discloses a turbo molecular pump with improved blade structures. The turbo molecular pump comprises a rotor and a stator, wherein the rotor includes five rotor blade assemblies and the stator includes five stator blade assemblies, and wherein the blade number and the blade angle of each rotor blade assembly and stator blade assembly are adjusted to optimization, so as to enhance the pumping speed and the stability of the turbo molecular pump as well as to reduce the difficulty for manufacturing the turbo molecular pump. | 06-14-2012 |
20120201663 | TURBOMACHINE FLOW PATH HAVING CIRCUMFERENTIALLY VARYING OUTER PERIPHERY - A turbomachine includes an annular flow path section between a plurality of radially extending stator blades and a plurality of radially extending rotor blades. At least a portion of the flow path section has a circumferentially varying outer periphery. | 08-09-2012 |
20120275912 | AXIAL COMPRESSOR WITH ARRANGEMENT FOR BLEEDING AIR FROM VARIABLE STATOR VANE STAGES - A compressor includes: a compressor spool rotatable about an axis carrying axially-spaced-apart blade rows of compressor blades; a casing surrounding the compressor blades, the casing carrying a liner assembly defining a boundary of a primary compressor flowpath; and a plurality of axially-spaced-apart stator rows of stator vanes carried by the liner assembly, the stator rows alternating axially with the blade rows. At least some of the stator rows are variable stator rows, the stator vanes of which are mounted on trunnions passing through the casing, and are pivotable relative to the casing. An actuator arm is coupled to each trunnions, outside the casing. At least one first bleed slot passes through the liner structure between axially adjacent first and second ones of the variable stator rows; and a first flow path defined by the casing communicates with the first bleed slot and with the exterior of the casing. | 11-01-2012 |
20140064946 | GAS TURBINE ENGINE COMPRESSOR UNDERCUT SPACER - A gas turbine engine compressor spacer ( | 03-06-2014 |
20140234095 | AEROFOIL FOR AXIAL-FLOW MACHINE - An aerofoil, such as a vane, for an axial flow machine, the aerofoil having first and second ends and opposing pressure and suction surfaces extending between said first and second ends in a span-wise direction. A first portion of the span of the aerofoil towards the first end the aerofoil has a location of greatest camber which is closer to a trailing edge than a leading edge of the aerofoil. In a further portion of the aerofoil span the camber is either uniform between the leading and trailing edges or else a location of greatest camber is closer to the leading edge than the trailing edge. In the first portion of the span of the aerofoil the pressure and/or suction surface may turn to a greater extent towards the trailing edge than towards the leading edge of the aerofoil. | 08-21-2014 |
20140271160 | VACUUM PUMP - A vacuum pump comprises an exhaust portion having a plurality of rotating blade portions arranged in multiple stages, each of the rotating blade portions having a plurality of rotor blades, and a plurality of stationary blade portions arranged between the rotating blade portions, in which outer circumferential rims are supported via spacers, each of the stationary blade portions having a plurality of stator blades. In at least one stationary blade portion among the plurality of stationary blade portions, a blade height on the inner circumferential side of the plurality of stator blades provided in the stationary blade portion is set to be smaller than a blade height on the outer circumferential side, and the stationary blade portion is supported by the spacers in such a manner that the inner circumferential side of the stationary blade portion is floated up toward an intake port side. | 09-18-2014 |
20140341726 | BLOOD PUMP WITH SEPARATE MIXED-FLOW AND AXIAL-FLOW IMPELLER STAGES AND MULTI-STAGE STATORS - A pump for a fluid which can be blood has a stator housing and a rotor hub with leading and trailing portions and an intermediate portion disposed therebetween. At least one impeller blade at the leading portion drives circumferential and axial components of a flow into a pump annulus or intermediate pathway portion. At least one stator blade extends radially inward from the stator housing within the intermediate pathway portion and is configured to reduce a circumferential component of the flow. | 11-20-2014 |
20150063992 | STEAM TURBINE - A steam turbine | 03-05-2015 |
20160047305 | MULTI-STAGE AXIAL COMPRESSOR ARRANGEMENT - A multi-stage axial compressor arrangement is disclosed that uses a compressor speed reducer to rotate the moving blades in the forward stages of the compressor at a slower rotational speed than the moving blades in the mid stages and the aft stages of the compressor. Slowing the rotational speed of the moving blades in the forward stages in relation to the blades in the mid stages and the aft stages, enables the multi-stage axial compressor to deliver a high airflow rate while overcoming excessive attachment stresses that is typically experienced in the large rotating blades of the forward stages of the compressor. | 02-18-2016 |
20160061205 | AXIAL COMPRESSOR WITH TANDEM BLADES - Axial compressor with tandem blades consists of a compressor stage ( | 03-03-2016 |
20160177723 | TURBINE AIRFOIL WITH OPTIMIZED AIRFOIL ELEMENT ANGLES | 06-23-2016 |
20160186591 | FLOWPATH BOUNDARY AND ROTOR ASSEMBLIES IN GAS TURBINES - A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a first axial section of an inner boundary of the flowpath; a second rotor wheel supporting a second rotor blade having a platform that defines a second axial section of the inner boundary of the flowpath; and an annulus filler that includes an outboard surface that defines at least part of a third axial section of the inner boundary of the flowpath occurring between the first axial section and the second axial section of the inner boundary of the flowpath. The first rotor wheel may include an axial connector for axially engaging a mating surface formed on a radially innermost face of the first rotor blade and a mating surface formed on a radially innermost face of the annulus filler. | 06-30-2016 |
415199600 | And radial-flow blade set in series therewith | 2 |
20090155064 | SYSTEM, METHOD AND APPARATUS FOR TWO-PHASE HOMOGENIZING STAGE FOR CENTRIFUGAL PUMP ASSEMBLY - A two-phase, homogenizing or mixing stage for a centrifugal pump assembly homogenizes the fluids being circulated therethrough. The mixing stage produces high shut-in head pressure and a very high maximum flow rate. The mixing stage has a diffuser with fixed diffuser vanes that extend radially or tangentially at acute angles. The vanes may be curved in both the axial and radial directions to force fluids impinging thereon to have a radially inward component to create turbulence. The turbulence mixes and homogenizes the gas and liquid fluids to improve the overall performance of centrifugal pump assemblies that operate in two-phase fluids. The mixing stage also has an impeller adjacent the diffuser. The impeller vanes likewise extend radially and tangentially therefrom at acute angles and may be curved. | 06-18-2009 |
20150139788 | COMPRESSOR ARRANGEMENT - A compressor arrangement has a common shaft, an axial compressor having at least a single-stage, and a radial compressor having at least single-stage. Assemblies of the, or each, axial compressor stage on the rotor side and assemblies of the, or each, radial compressor stage on the rotor side are attached to a common shaft ( | 05-21-2015 |