Entries |
Document | Title | Date |
20080199310 | Axial flow turbine - An axial flow turbine provided with a stage composed of a turbine nozzle and a turbine rotor blade arranged in an axial flow direction. Both end portions of a nozzle blade of the turbine nozzle are supported by a diaphragm inner ring and a diaphragm outer ring, and a flow passage is formed to have its diameter expanded from an upstream stage to a downstream stage. In such axial flow turbine, trailing edges at ends of the nozzle blade supported by the diaphragm inner ring and the diaphragm outer ring are curved as a curvature to an outlet side, and an intermediate portion between the trailing edges is formed to be straight. | 08-21-2008 |
20080232957 | WIND TURBINE WITH MIXERS AND EJECTORS - A Mixer/Ejector Wind Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. In the preferred embodiment, Applicants' MEWT incorporates advanced flow mixing technology, single and multi-stage ejector technology, aircraft and propulsion aerodynamics and noise abatement technologies in a unique manner to fluid-dynamically improve the operational effectiveness and efficiency of wind turbines, so that its operating efficiency routinely exceeds the Betz limit. Applicants' preferred MEWT embodiment comprises: an aerodynamically contoured turbine shroud with an inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer/ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass wind flow. The MEWT can produce three or more time the power of its un-shrouded counterparts for the same frontal area, and can increase the productivity of wind farms by a factor of two or more. The same MEWT is safer and quieter providing improved wind turbine options for populated areas. | 09-25-2008 |
20080267771 | Gas turbine with a guide vane - A guide vane for a gas turbine with a vane base body which is of single-piece design and comprises a profiled vane blade extending between a vane root and a cover plate and also the vane root formed integrally with the vane blade and the cover plate formed integrally with the vane blade, is intended, in a relatively simple way to be able to be matched to the individual conditions of use with especially little outlay on apparatus and logistics. For this purpose, according to the invention, a flow-routing body with an advance guide blade that is connected upstream of the vane blade as seen in the direction of flow of the working medium of the gas turbine is joined to the vane base body. | 10-30-2008 |
20080267772 | AEROFOIL MEMBERS FOR A TURBOMACHINE - A circumferential row of aerofoil members span an annular duct for carrying a flow of compressible fluid. The duct is centred on the axis of a turbomachine. Pressure and suction surfaces of neighbouring aerofoil members bound respective sectoral passages which receive the flow of compressible fluid. The row comprises at least one radial endwall to which the tangent to the trailing edge of each aerofoil member at midspan is substantially orthogonal. Each aerofoil member has reverse compound lean. Each aerofoil member further has a leading edge which has a position at the endwall which is upstream of its position at midspan. | 10-30-2008 |
20080279679 | Multivane segment mounting arrangement for a gas turbine - A mounting arrangement ( | 11-13-2008 |
20090035129 | Vane air-cooling system for automatic transmission torque converter - A cooling system is provided for automatic transmission torque converter assemblies having a housing shell and flex plate. The cooling system includes a housing cover having opposing exterior and interior surfaces that define a wall portion and a preferably circular base portion. The base portion is configured to attach to the flex plate, preferably by one or more stud members, to be rotated thereby. The wall portion extends from a periphery of the base portion and is configured to attach to the housing shell. The cooling system also includes a plurality of vane members positioned along the outer periphery of the base portion. The vane members are configured to increase convective dissipation of heat from the torque converter assembly to surrounding ambient air by increasing the heat transfer coefficient and surface area. Optimally, the vanes have a turbine fin configuration, but may alternatively have curved fin or a straight-fin configuration. | 02-05-2009 |
20090035130 | SHAPE OF GAS PASSAGE IN AXIAL-FLOW GAS TURBINE ENGINE - An axial-flow gas turbine engine includes a plurality of inlet guide vanes (V) which are radially disposed in an annular gas passage defined between an inner peripheral wall (Ch) and an outer peripheral wall (Ct) of a turbine. The inner peripheral wall (Ch) of the gas passage includes inner peripheral concave portions (Cc | 02-05-2009 |
20090087308 | WIND TURBINE WITH MIXERS AND EJECTORS - A Mixer/Ejector Wind Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. In the preferred embodiment, Applicants' MEWT incorporates advanced flow mixing technology, single and multi-stage ejector technology, aircraft and propulsion aerodynamics and noise abatement technologies in a unique manner to fluid-dynamically improve the operational effectiveness and efficiency of wind turbines, so that its operating efficiency routinely exceeds the Betz limit. Applicants' preferred MEWT embodiment comprises: an aerodynamically contoured turbine shroud with an inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer/ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass wind flow. The MEWT can produce three or more time the power of its un-shrouded counterparts for the same frontal area, and can increase the productivity of wind farms by a factor of two or more. The same MEWT is safer and quieter providing improved wind turbine options for populated areas. | 04-02-2009 |
20090110549 | GAS TURBINES HAVING FLEXIBLE CHORDAL HINGE SEALS - Gas turbine systems having flexible chordal hinge seals are provided. According to an embodiment, a turbine system comprises: a nozzle segment comprising a stator vane extending between an inner band segment and an outer band segment; an inner support ring adjacent to the inner band segment; and an inner chordal hinge seal in operable communication with the nozzle segment, the inner chordal hinge seal comprising a flexible inner rail extending inwardly from the inner band segment, the inner rail having a projection for sealingly engaging the inner support ring. | 04-30-2009 |
20090123275 | Apparatus for eliminating compressor stator vibration induced by TIP leakage vortex bursting - Vibration induced compressor vane failure from tip leakage vortex bursting is eliminated or minimized. By securing the vane at opposite ends to inner and outer stationary casings, tip leakage is entirely avoided hence avoiding the mechanism for inducing vibration. By contouring the inner surface of the flow path to converge the flow in a downstream direction with a cantilevered compressor vane having a vane tip spaced from the inner casing surface, airflow lift off is precluded or minimized maintaining the flow attached to the flowpath surfaces with consequent avoidance of tip vortex induced vibration. | 05-14-2009 |
20090155061 | SECTORIZED NOZZLE FOR A TURBOMACHINE - A sectorized nozzle for a turbomachine, the nozzle being made up of cylindrical sectors and comprising two annular platforms interconnected by substantially radial vanes, together with an annular rail for supporting elements of abradable material, each inner platform having longitudinally-extending edges that are V-shaped, and each rail sector having, on at least one of its sides, means for bearing axially on corresponding means provided on an adjacent nozzle sector. | 06-18-2009 |
20090162193 | TURBINE INLET GUIDE VANE WITH SCALLOPED PLATFORM AND RELATED METHOD - A nozzle segment is disclosed that includes a first platform configured to be connected with a casing of a gas turbine engine, a second platform configured to be connected with the casing, the second platform being disposed apart from the first platform in a radial direction of the gas turbine engine, and a plurality of blades disposed between the first and second platforms and connected thereto, a portion of an inside surface of the first platform or the second platform being scalloped so as to increase a throat area of the nozzle segment in order to increase the nozzle segment's mass flow rate handling capability. | 06-25-2009 |
20090208331 | CENTRIFUGAL COMPRESSOR ASSEMBLY AND METHOD - A centrifugal compressor assembly for compressing refrigerant in a 250-ton capacity or larger chiller system comprising a motor, preferably a compact, high energy density motor or permanent magnet motor, for driving a shaft at a range of sustained operating speeds under the control of a variable speed drive. Another embodiment of the centrifugal compressor assembly comprises a mixed flow impeller and a vaneless diffuser sized such that a final stage compressor operates with an optimal specific speed range for targeted combinations of head and capacity, while a non-final stage compressor operates above the optimum specific speed of the final stage compressor. Another embodiment of the centrifugal compressor assembly comprises an integrated inlet flow conditioning assembly comprising a flow conditioning nose, a plurality of inlet guide vanes and a flow conditioning body that positions inlet guide vanes to condition flow of refrigerant into an impeller to achieve a target approximately constant angle swirl distribution with minimal guide vane turning. | 08-20-2009 |
20090274554 | Fluid flow machine including rotors with small rotor exit angles - A fluid flow machine includes at least one rotor blade row designed for high work coefficients, which—in its center section and/or averaged over the blade height—provides for an essentially swirl-free relative outflow. The respective rotor, in its trailing edge area, is essentially orientated in meridional direction, which essentially corresponds to the meridional flow direction. | 11-05-2009 |
20090280006 | TURBINE HOUSING WITH INTEGRATED RIBS - A flow direction system ( | 11-12-2009 |
20090297343 | PRECAST GROOVES FOR A STATOR BLADE ASSEMBLY - A stator, including a blade assembly with an inner circumferential surface and a plurality of pre-formed grooves in the inner circumferential surface and an outer race with an outer circumferential surface and a plurality of protrusions at least partially engaged with the plurality of pre-formed grooves. The plurality of protrusions is frictionally engaged with the plurality of pre-formed grooves. In one embodiment, the inner circumferential surface includes an area circumferentially disposed between first and second protrusions from the plurality of protrusions and a portion of the area is displaced radially inward by the engagement of the pluralities of grooves and protrusions. | 12-03-2009 |
20090317245 | Method of forming a rotating blade assembly - A method of forming a blade assembly for a gas turbine engine, the method comprising mounting turbine blades on a rotor in a number of radial stages. Sacrificial supports are placed on the blades, and nozzle guide vanes are located on the supports. The rotor is introduced into a casing, and the guide vanes are mounted to the casing. | 12-24-2009 |
20100003130 | Windmill device - A wind power engine including a stator having stator blades and a rotor having rotor blades. The rotor is positioned inside the hollow area of the stator and is rotationally movable with respect to the stator about an axis of rotation. The stator blades are positioned in such a way that an air flow coming from the outside of the stator is oriented towards the rotor and the rotor blades. The oriented airflow allows the rotor blades to drive the rotor about the axis of rotation. At least certain rotor blades have a concave-shaped profile on one of their faces. | 01-07-2010 |
20100040460 | Platforms with Curved Side Edges and Gas Turbine Engine Systems Involving Such Platforms - Platforms with curved side edges and gas turbine engine systems involving such platforms are provided. In this regard, a representative airfoil assembly for a gas turbine engine includes: a platform having a gas path side, a non-gas path side, a leading edge, a trailing edge, a first side edge extending between the leading edge and the trailing edge and exhibiting a first curve along a length thereof, and a second side edge extending between the leading edge and the trailing edge and exhibiting a second curve along a length thereof; and an airfoil extending from the gas path side of the platform; the platform and the airfoil exhibiting a unitary construction such that a continuous exterior surface blends from the airfoil to the platform. | 02-18-2010 |
20100054930 | TURBINE VANE WITH HIGH TEMPERATURE CAPABLE SKINS - A turbine vane assembly includes an airfoil extending between an inner shroud and an outer shroud. The airfoil can include a substructure having an outer peripheral surface. At least a portion of the outer peripheral surface is covered by an external skin. The external skin can be made of a high temperature capable material, such as oxide dispersion strengthened alloys, intermetallic alloys, ceramic matrix composites or refractory alloys. The external skin can be formed, and the airfoil can be subsequently bi-cast around or onto the skin. The skin and the substructure can be attached by a plurality of attachment members extending between the skin and the substructure. The skin can be spaced from the outer peripheral surface of the substructure such that a cavity is formed therebetween. Coolant can be supplied to the cavity. Skins can also be applied to the gas path faces of the inner and outer shrouds. | 03-04-2010 |
20100061845 | GUIDING DEVICE OF A FLOW MACHINE AND GUIDE VANE FOR SUCH A GUIDING DEVICE - A guide device for a turbomachine, particularly a steam turbine, with a guide vane ring and a plurality of guide vanes which are fastened to the guide vane ring so as to be distributed along the circumference of the guide vane ring. The guide vane ring has a groove, and the guide vanes also have grooves which are aligned with the groove of the guide vane ring in the assembled state. The guide vanes are fixed in their radial position at the guide vane ring by means of a retaining ring which engages in the groove of the guide vane ring and in the grooves of the guide vanes. | 03-11-2010 |
20100068045 | INLET GUIDE VANE - An inlet guide vane having a nominal profile substantially in accordance with Cartesian coordinate values of x, y, and z set forth in TABLE 1 reduces vibration of engine components at various operating conditions. A scaling factor can be applied to the values to make the airfoil larger or smaller. The TABLE 1 x and y values are distances in inches within a tolerance which, when connected by smooth curves, define airfoil profile sections at each distance z in inches, the profile sections being joined smoothly to form a complete airfoil shape. The tolerance in an embodiment is up to about 0.16 inches. | 03-18-2010 |
20100080695 | TURBINE NOZZLE FOR A GAS TURBINE ENGINE - A turbine nozzle includes: a hollow, airfoil-shaped turbine vane; and an arcuate first band disposed at a first end of the turbine vane, the first band having a flowpath face adjacent the turbine vane, and an opposed back face. The back face includes at least one open pocket, the at least one pocket defined in part by a bottom wall recessed from the back face, opposed ends of the bottom wall merging with the back face. The bottom wall is substantially free of interior corners. | 04-01-2010 |
20100104432 | ARRANGEMENT FOR A GAS TURBINE ENGINE - An inlet guide vane arrangement for a gas turbine is provided. The arrangement includes a plurality of guide vane duct elements, the guide vane duct elements include a suction side wall and a pressure side wall, both walls facing each other, and are designed to be adjoinable to another of the guide vane duct elements, such that the pressure side wall of one guide vane duct element cooperates with the suction side wall of the adjacent guide vane duct element thereby forming a guide vane. The guide vane duct element includes features to accept a key element adapted to be arranged between the pressure side wall and the adjacent suction side wall, when two guide vane duct elements are adjoining to one another, and to attach together both adjoining guide vane duct elements. | 04-29-2010 |
20100111682 | CRENELATED TURBINE NOZZLE - A turbine nozzle includes a row of vanes extending radially between annular outer and inner bands. The outer band includes a pair of radial flanges defining an annular seal groove therebetween. One of the flanges is crenelated to improve nozzle life. | 05-06-2010 |
20100111683 | FLUID FLOW MACHINE - A fluid flow engine ( | 05-06-2010 |
20100119361 | TURBINE WITH MIXERS AND EJECTORS - A Mixer/Ejector Wind/Water Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. Unique ejector concepts are used to fluid-dynamically improve many operational characteristics of conventional wind/water turbines for potential power generation improvements of 50% and above. Applicants' preferred MEWT embodiment comprises: an aerodynamically contoured turbine shroud with an inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer/ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass fluid flow. The MEWT can produce three or more time the power of its un-shrouded counterparts for the same frontal area, and can increase the productivity of wind farms by a factor of two or more. The same MEWT is safer and quieter providing improved wind turbine options for populated areas. | 05-13-2010 |
20100119362 | Shrouded Turbine Assembly - A turbine that allows for the conversion of the kinetic energy of waterway to mechanical power for use in an energy accepting apparatus is described. The turbine has complimentary components that improve the power efficiency of the turbine. The turbine may include a blade shroud and a plurality of blades that are connected to the blade shroud. On the external surface of the blade shroud, a drive mechanism and/or a brake mechanism may be disposed. An inlet nozzle and outlet diffuser may be used in combination with the turbine. The turbine may be useful in a number of settings, including, but not limited to, streams, rivers, dams, ocean currents, or tidal areas that have continuous or semi-continuous water flow rates and windy environments. | 05-13-2010 |
20100172748 | METHODS AND APPARATUS FOR REDUCING NOZZLE STRESS - A gas turbine engine nozzle is described. The gas turbine engine nozzle includes at least one nozzle vane having a first end and a second end. The first end is coupled to an inner sidewall and the second end is coupled to an outer sidewall. The gas turbine engine nozzle also includes at least one stress relief pocket defined within at least one of the inner sidewall and the outer sidewall proximate to the at least one nozzle vane. The at least one stress relief pocket is configured to reduce stress on the proximate nozzle vane. | 07-08-2010 |
20100196150 | BOUNDARY LAYER WIND TURBINE WITH TANGENTIAL ROTOR BLADES - A wind turbine having rotor assembly with a plurality of stacked disks ( | 08-05-2010 |
20100266395 | Inlet Swirl Control for Turbochargers - An inlet duct, an induction system, and a system are disclosed for directing an inlet flow into an inlet compressor for use in an internal combustion engine. An example inlet duct may include one or more relief features disposed on an inner surface of the inlet duct. The one or more relief features may be made integral with the inlet duct. The one or more relief features may be disposed to protrude into the inlet flow to cause the inlet flow to swirl before reaching the inlet compressor. | 10-21-2010 |
20100310360 | GUIDE VANE ASSEMBLY - A guide vane assembly for a turbomachine, comprising a guide vane and a liner: the guide vane comprising an aerofoil portion having a radially outer platform, wherein one of the outer platform and the liner has a hook element, the hook element comprising an opening and a circumferentially extending channel, and the other one of the outer platform and the liner comprises a retaining element having a head portion, wherein in an operational orientation the head portion located within the channel and is too wide to be withdrawn through the opening of the hook element. | 12-09-2010 |
20100316493 | TURBINE WITH MIXERS AND EJECTORS - A Mixer/Ejector Wind Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. Unique ejector concepts are used to fluid-dynamically improve many operational characteristics of conventional wind turbines for potential power generation improvements of 50% and above. Applicants' preferred MEWT embodiment comprises: an aerodynamically contoured turbine shroud with an inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer/ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass fluid flow. The MEWT can produce three or more time the power of its un-shrouded counterparts for the same frontal area, and can increase the productivity of wind farms by a factor of two or more. The same MEWT is safer and quieter providing improved wind turbine options for populated areas. | 12-16-2010 |
20110020118 | TURBINE NOZZLE ASSEMBLY INCLUDING RADIALLY-COMPLIANT SPRING MEMBER FOR GAS TURBINE ENGINE - Embodiments of a turbine nozzle assembly are provided for deployment within a gas turbine engine (GTE) including a first GTE-nozzle mounting interface. In one embodiment, the turbine nozzle assembly includes a turbine nozzle flowbody, a first mounting flange configured to be mounted to the first GTE-nozzle mounting interface, and a first radially-compliant spring member coupled between the turbine nozzle flowbody and the first mounting flange. The turbine nozzle flowbody has an inner nozzle endwall and an outer nozzle endwall, which is fixedly coupled to the inner nozzle endwall and which cooperates therewith to define a flow passage through the turbine nozzle flowbody. The first radially-compliant spring member accommodates relative thermal movement between the turbine nozzle flowbody and the first mounting flange to alleviate thermomechanical stress during operation of the GTE. | 01-27-2011 |
20110052381 | COMBUSTOR TURBINE INTERFACE FOR A GAS TURBINE ENGINE - A turbine vane downstream of a combustor section includes an arcuate outer vane platform defined about an axis, the arcuate outer vane platform includes a segment of the arcuate outer vane platform along the axis which follows an outer combustor liner panel structure and an arcuate inner vane platform defined about the axis, the arcuate inner vane platform includes a segment of the arcuate inner vane platform along the axis which follows an inner combustor liner panel structure. | 03-03-2011 |
20110058937 | NACELLE CONFIGURATIONS FOR A SHROUDED WIND TURBINE - A shrouded wind turbine comprises a shroud disposed about an impeller. The impeller surrounds a nacelle body which is shaped to enhance smooth flow of wind through the impeller. Some embodiments include an inlet and an outlet in the nacelle body, allowing airflow through an interior cavity. Other nacelle bodies may be tapered, flared, include mixing lobes around a trailing edge, or may have other shapes that enhance fluid flow. Some nacelle bodies include an annular groove that promotes flow attachment. Maintaining airflow attachment to the nacelle body within the turbine increases the energy generation capacity of the wind turbine. | 03-10-2011 |
20110103943 | Device for a Horizontally Split Turbomachine Housing, Guide Disc Segment and Guide Blade Carrier for a Horizontally Split Turbomachine Housing - A guide disc segment for a horizontally split turbomachine housing is provided. The guide disc segment includes a plurality of guide blades and an outer ring segment. The guide blades are fixed to the outer ring segment along an inner circumference. The outer ring segment can be rolled into or out of a guide blade carrier of the turbomachine housing. The outer ring segment has, along an outer circumference, a toothing into which a drive device engages. A tangential force can be applied to the outer ring segment by the toothing such that the guide disc segment can be driven during the rolling into or rolling out of the outer ring segment. | 05-05-2011 |
20110110773 | TURBOMACHINE COMPRESSOR - Turbomachine compressor comprising variable-pitch vanes comprising an aerofoil section connected by a mounting plate ( | 05-12-2011 |
20110123322 | FLOW PASSAGE FOR GAS TURBINE ENGINE - Inefficiencies associated with the formation of horseshoe vortices in a gas turbine engine having a row of radially extending airfoils, are mitigated with an improved flow passage defined by the suction and pressure surface of two adjacent airfoils and endwalls (disposed proximal to the radially inner and outer ends of the airfoils). The flow passage includes a ridge disposed in one of the endwalls adjacent a suction surface of one of the airfoils, the ridge extending longitudinally from a location at or near the maximum circumferential extent of the airfoil suction side to a downstream location proximal to the trailing edge of the suction surface. | 05-26-2011 |
20110150640 | Labyrinth Seal in a Stationary Gas Turbine - A segmented inner ring for holding guide blades is provided. A lateral wall opposing the front side of the inner ring and pertaining to a shaft shoulder formed on the rotor shaft extends radially. Also a stationary gas turbine comprising a segmented inner ring is provided. | 06-23-2011 |
20110150641 | STEAM TURBINE AND STEAM TURBINE BLADE - A steam turbine | 06-23-2011 |
20110158795 | CENTRIFUGAL PUMP IMPELLERS - A centrifugal pump impeller includes front and back shrouds and a plurality of pumping vanes therebetween, each pumping vane having a leading edge in the region of an impeller inlet and a trailing edge, the front shroud has an arcuate inner face in the region of the impeller inlet, the arcuate inner face having a radius of curvature (R | 06-30-2011 |
20110189002 | TURBINE GUIDE VANE - A turbine guide vane ( | 08-04-2011 |
20110200429 | IMPELLER AND BLOWER FAN INCLUDING THE SAME - An impeller includes a substantially cylindrical cup portion arranged to rotate about a center axis, a plurality of blades fixed to an outer circumferential surface of the cup portion for unitary rotation with the cup portion to draw air from one axial side and discharge the air to the other axial side, and an annular connector portion arranged to interconnect the blades. The connector portion has a substantially cylindrical shape in a position spaced apart about 70% to about 90% of the radial length of the blades from the base of each of the blades on the outer circumferential surface of the cup portion, and the ratio of a total axial height of the connector portion to a total radial gap between the outer circumferential surface of the cup portion and the inner circumferential surface of the connector portion is equal to or smaller than about 0.9. | 08-18-2011 |
20110229314 | HIGH-PRESSURE TURBINE FOR TURBOMACHINE, ASSOCIATED GUIDE VANE SECTOR AND AIRCRAFT ENGINE - An assembling of a guide vane assembly of a turbomachine turbine, formed by an annular row of stationary flow-stabilizing vanes. An outer edge of the guide vane assembly is axially bearing on a line of an external casing of the turbine and an inner edge of the guide vane assembly is in axial sliding connection with the line of the internal casing of the turbine, the axial sliding connection allowing the inner edge to be free along the motor axis with the axial stop being achieved by the axial bearing of the outer edge of the vane. | 09-22-2011 |
20110229315 | HIGH EFFICIENCY ROTOR BLADES FOR A FLUID TURBINE - A shrouded fluid turbine includes an impeller surrounded by a turbine shroud. The turbine shroud has a plurality of mixing lobes on a trailing edge, resulting in the trailing edge having a circular crenellated shape. An ejector shroud is located downstream of the turbine shroud, an inlet end of the ejector shroud surrounding the mixing lobes of the turbine shroud. The impeller is a rotor/stator assembly. In particular, the rotor comprises a rotor hub formed from a cylindrical sidewall and has seven rotor blades extending radially from the hub. It has been found that seven rotor blades optimizes the total-to-total efficiency of the shrouded fluid turbine. | 09-22-2011 |
20110299980 | GAS TURBINE ENGINE AND A GAS TURBINE ENGINE COMPONENT - A gas turbine engine component providing a gas flow passage is provided, which gas flow passage surrounds an inner passage surface, an outer passage surface forming an outer delimitation of said gas flow passage. In an aspect, the trace of the inner passage surface in a cross-section perpendicular to a central axis of the component presents at least one substantially straight portion. In another aspect, where a plurality of circumferentially spaced blades extends between the inner and outer passage surfaces, two portions of the trace, in a cross-section perpendicular to a central axis of the component, of the outer passage surface between two adjacent blades are substantially straight and oriented in an angle in relation to each other so as to form a concavity in the gas flow passage. | 12-08-2011 |
20120063892 | BIDIRECTIONAL FAN HAVING SELF-ADJUSTING VANE - A bidirectional centrifugal fan having a self-adjusting vane is disclosed. In one embodiment, the fan includes a driving disc having a pivot pin extending therefrom; a vane pivotably attached to the pivot pin, the vane including an aperture extending at least partially therethrough; and a trailing disc including a guide arm for receiving the aperture of the vane. | 03-15-2012 |
20120093635 | AXIAL FLOW FAN - An axial flow fan includes an impeller rotatable about a central axis with a plurality of rotor vanes, a motor that drives the impeller, a base portion that supports the motor, a housing that includes an intake vent, an exhaust vent, and an inner peripheral surface surrounding the impeller and the motor, and a plurality of stator vanes that respectively connects the base portion and the housing, wherein the inner peripheral surface includes a first inner peripheral surface arranged to increase a distance from the central axis toward the intake vent or the exhaust vent in an axial direction, and a recess provided between the first inner peripheral surface and a stator vane included in the plurality of stator vanes and facing the first inner peripheral surface. Thus, airflow is allowed to smoothly pass through the housing, resulting in a decrease in noise generated in the fan. | 04-19-2012 |
20120141260 | STEAM TURBINE SINGLET INTERFACE FOR MARGIN STAGE NOZZLES WITH PINNED OR BOLTED INNER RING - A steam turbine singlet nozzle airfoil with integral outer sidewall is engaged with an inner ring and an outer ring in a nozzle assembly. The interface of the outer sidewall with the outer ring may include a plurality of mechanical hooks on one or both of the upstream face and the outer radial face of the outer sidewall that engage with complimentary structures on the outer ring. The outer interface may further include low energy welds along limited distances of one or both of the upstream or downstream interface of the outer sidewall and the outer ring. An inner radial end of the singlet nozzle airfoil is pinned into position and fastened to the inner ring. Without a need for high heat welds, distortion of the airfoil and the steam flow path and the associated rework is eliminated and stage performance is improved. | 06-07-2012 |
20120163964 | AXIAL RETENTION FEATURE FOR GAS TURBINE ENGINE VANES - A case assembly for a gas turbine engine is provided that includes an outer case with circumferentially spaced individual bosses that include a recess. A vane assembly is received in the outer case. An axial retention ring has uninstalled and installed conditions. The axial retention ring outside of the recess is in the uninstalled condition and received in the recess in the installed condition. An anti-rotation feature, such as a ring, is arranged between the bosses in a locking condition to prevent rotation of the axial retention ring between the installed and uninstalled conditions. | 06-28-2012 |
20120171025 | VANE WITH SPAR MOUNTED COMPOSITE AIRFOIL - A vane includes a composite airfoil having one or more outer pockets and one or more outer spars received therein respectively. The outer spars extending radially inwardly from an outer bridge of the outer vane mount outwardly supporting airfoil. The spars may be integrally formed with the bridge and adhesively bonded to the composite airfoil within the pockets with a passage extending between an airfoil base and an airfoil tip. A metallic leading edge tip may be disposed along the leading edge of the composite airfoil. A gas turbine engine annular fan frame incorporates the vanes in an annular row of composite outlet guide vanes extending radially between and connecting radially inner and outer rings of the fan frame. | 07-05-2012 |
20120207591 | COOLING SYSTEM HAVING REDUCED MASS PIN FINS FOR COMPONENTS IN A GAS TURBINE ENGINE - A cooling system having one or more pin fins with reduced mass for a gas turbine engine is disclosed. The cooling system may include one or more first surfaces defining at least a portion of the cooling system. The pin fin may extend from the surface defining the cooling system and may have a noncircular cross-section taken generally parallel to the surface and at least part of an outer surface of the cross-section forms at least a quartercircle. A downstream side of the pin fin may have a cavity to reduce mass, thereby creating a more efficient turbine airfoil. | 08-16-2012 |
20120237344 | ADVANCED BOOSTER SYSTEM - A compression stage having a plurality of stator vanes and rotor blades coaxial with a longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location and each rotor blade having a blade leading edge adapted to receive the flow from the stator vanes with the exit swirl angle distribution profile. | 09-20-2012 |
20120275911 | Gas Turbine Stator Vane - A gas turbine stator vane is effective for suppressing a secondary flow in a region sandwiched between a suction surface side and a pressure surface side, as well as for suppressing augmentation of a horseshoe-shaped vortex occurring near a leading edge of the vane. The stator vane includes a vane profile portion having a pressure surface concaved to a chord line of the vane, and a suction surface convexed to the chord line; an outer-circumferential end wall positioned at an outer circumferential side of the vane profile portion; and an inner-circumferential end wall positioned at an inner circumferential side of the vane profile portion. An outer-circumferential end wall inner surface that is an inner-circumferential surface of the outer-circumferential end wall has an inward convexed shape and an outward convexed shape, at the suction surface side of the vane profile portion. | 11-01-2012 |
20120301285 | CERAMIC MATRIX COMPOSITE VANE STRUCTURES FOR A GAS TURBINE ENGINE TURBINE - A vane structure for a gas turbine engine according includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a CMC inner ring. | 11-29-2012 |
20120321454 | WIND POWER GENERATION APPARATUS - A wind power generation apparatus includes a wind collecting hood, a rotary shaft, a rotary structure and a wind guiding structure. The wind collecting hood is a hollow circular barrel to form an airflow passage. The rotary shaft is located in the airflow passage of the wind collecting hood. The rotary structure is mounted onto the rotary shaft. The wind guiding structure is fastened to the wind collecting hood and located at the front end of the rotary structure. The wind guiding structure directs direction of airflow and accelerates the airflow to become swirling airflow to directly blow the rotary structure at optimal angles, thus capability of driving the rotary structure to rotate by wind is increased and starting wind power of the rotary structure is reduced. The rotary structure is still rotated at where the wind is smaller to provide electric power. | 12-20-2012 |
20120328426 | AIR TURBINE STARTER TURBINE NOZZLE AIRFOIL - A vane profile section for an air turbine starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge, the airfoil profile section defined by a set of X-coordinates and Z-coordinates. | 12-27-2012 |
20130022454 | AIR TURBINE STARTER - A blade profile section for an air turbine starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge. The airfoil profile section is defined by a set of X-coordinates and Z-coordinates defined in any of Table I, Table II, Table III or Table IV scaled by a desired factor. The X-coordinate is the tangential direction, and the Z-coordinate is a radial direction between an airfoil root and an airfoil tip. | 01-24-2013 |
20130034433 | INTER-TURBINE DUCTS WITH GUIDE VANES - A turbine section of a gas turbine engine is provided. The turbine section is annular about a longitudinal axis and includes first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine; and a first guide vane disposed within the inter-turbine duct. | 02-07-2013 |
20130058771 | SPRING-TENSIONED STATOR RESTRAINING STRAP - A vane assembly of a gas turbine engine includes a plurality of circumferentially spaced vanes extending radially between an outer case and an inner case. A spring-tensioned stator restraining strap is provided around the outer case and surrounding outer ends of the respective vanes. The outer ends of the vanes are received in corresponding openings defined in the outer case and project radially outwardly from the outer case. The spring-tensioned strap compresses the respective vanes radially and inwardly in position. | 03-07-2013 |
20130094950 | COMPRESSOR UNIT - A compressor unit includes a motor and a compressor in a casing of a gastight form. The casing houses the motor and the compressor. The motor includes a rotor surrounded by a stator which has an encapsulation formed on the inner diameter as a separating can, so that a medium being handled does not damage the stator. The separating can includes a polymer matrix which is reinforced using a plurality of fibers. The polymer matrix is at least partly a ceramic fiber reinforced polymer matrix. The plurality of fibers are formed as continuous filaments. The continuous filaments include the length of at least 30 mm. | 04-18-2013 |
20130101405 | FAN, MOLDING DIE, AND FLUID FEEDER - A cross-flow fan includes a plurality of fan blades. The fan blade has an inner edge portion arranged on an inner circumferential side and an outer edge portion arranged on an outer circumferential side. In the fan blade, a blade surface extending between the inner edge portion and the outer edge portion and constituted of a positive pressure surface and a negative pressure surface is formed. The fan blade has such a blade cross-sectional shape that a large-thickness portion at which a thickness between the positive pressure surface and the negative pressure surface is greatest is arranged closer to the inner edge portion. A recess recessed in the blade surface is formed at a position closer to the inner edge portion where the large-thickness portion is arranged, than to the outer edge portion. | 04-25-2013 |
20130108425 | ROTATING VANE SEAL WITH COOLING AIR PASSAGES | 05-02-2013 |
20130115068 | WIND TURBINE ROTOR AND WIND TURBINE - A wind turbine comprising: a shaft ( | 05-09-2013 |
20130115069 | Vertical Axis Wind Turbine - A vertical axis wind turbine formed from a concentric arrangement of fixed stator blades to provide fluid flow acceleration into an arrangement of rotatable blades secured to a generator for invoking electrical power generation. The stator blades are maintained in a fixed position by use of an upper and lower stator plate. The rotor blades include an upper and lower plate, the upper plate coupled to the upper stator plate, and the lower rotor plate coupled to the generator. The amount of stator and rotor blades may be scaled in number and size depending upon the type of generator to be driven and associated mechanical energy to be obtained. The stator blades are designed for air deflection in a direction for optimal rotor blade rotation by accelerating air flow into a pre-swirl before the flow contacts the rotor blades. Each stator blade is oriented at a sufficient stagger angle so that an angle of the relative velocity does not exceed the stall angle of said rotor blade. | 05-09-2013 |
20130121815 | HERMETICALLY SEALED COMPRESSOR - A hermetically sealed compressor in which heat generation and insulation breakdown are hardly to occur at the connection portion between a lead wire of a motor and an external terminal is configured as follows. The compressor main body and the motor are integrally structured. The flow path of a fluid to be compressed is communicated with the internal space of the motor. The stator ( | 05-16-2013 |
20130129493 | TURBINE - A turbine is provided including an annular turbine blade body ( | 05-23-2013 |
20130129494 | AXIAL TURBOMACHINE COMPRESSOR OUTER CASING - The invention relates to a casing, particularly of an axial turbomachine compressor. This casing comprises a support of cylindrical overall shape made of composite material, a metal ring fitted by bonding to the internal surface of the support, and a layer of abradable material fitted by plasma spray onto the internal surface of the metal ring. The metal ring is preferably made of stainless steel and is preferably perforated. The perforation allows better keying of the adhesive and allows the degassing thereof. The external surface of the metal ring is preferably sandblasted prior to bonding. Its internal surface is also preferably sandblasted prior to the plasma spraying of the abradable material. | 05-23-2013 |
20130136586 | ELECTRIC PUMP - An electric pump includes a pump portion, a motor portion including a rotor formed in a cylinder form sharing an axis with a rotation shaft provided at the pump portion and a stator formed in an annular form arranged at an outer periphery of the rotor with a clearance between the stator and the rotor, and a driver portion arranged at a position between the pump portion and the motor portion when viewed in a direction orthogonal to an axial direction of the rotation shaft, the driver portion controlling the motor portion, the driver portion arranged in a state where a portion of the driver portion overlaps with at least a portion of the pump portion or with at least a portion of the motor portion when viewed in the axial direction. | 05-30-2013 |
20130136587 | CENTRIFUGAL COMPRESSOR - A centrifugal compressor, including: a housing, the housing including: an inlet, a flow channel, an impeller outlet, and an air diffusing channel; a centrifugal impeller disposed inside the housing; a rotating wall, the rotating wall including a front cascade; and a rotating disc, the rotating disc including a rear cascade. The impeller outlet is disposed adjacent to a rear part of the centrifugal impeller and is connected to the flow channel via the air diffusing channel. The rotating wall is disposed between the centrifugal impeller and the housing. The front cascade is disposed inside the front part of the rotating wall and is connected to a dynamic driving device. The rotating disc is disposed inside the housing adjacent to the air diffusing channel and is in a rigid connection with the rotating wall. | 05-30-2013 |
20130149123 | RADIAL ACTIVE CLEARANCE CONTROL FOR A GAS TURBINE ENGINE - The present invention comprises a gas turbine engine with a compressor for generating compressed air, a turbine comprising upstream and downstream rows of vanes, vane carrier structure surrounding at least one row of vanes and plenum structure at least partially surrounding the vane carrier structure capable of impinging compressed air onto the vane carrier structure. The gas turbine engine further comprises fluid supply structure including first fluid path structure defining a first path for compressed air to travel to the plenum structure, second fluid path structure defining a second path for compressed air to travel toward the downstream row of vanes, and fluid control structure selectively controlling fluid flow to the first and second fluid path structures. | 06-13-2013 |
20130149124 | TURBINE - The turbine ( | 06-13-2013 |
20130149125 | TURBINE AND METHOD FOR MANUFACTURING TURBINE - The turbine includes: a shaft body supported rotatably; a plurality of turbine blade members; a casing covering the shaft body and the turbine blade row; an outer ring member that is provided on an inner periphery of the casing and includes an inner peripheral portion in which a cross-section having a uneven shape is continuous in a circumferential direction; a plurality of turbine vane members that each has a shroud fitted into the inner peripheral portion of the outer ring member and a turbine vane main body extending from the shroud to a radially inward side; and a plate member that connects at least some of the plurality of turbine vane members and covers one side of the shrouds in the axial direction, thereby sealing a shroud gap formed between the shrouds adjacent to each other in the circumferential direction. | 06-13-2013 |
20130156562 | TURBOMACHINE AND TURBOMACHINE STAGE - A turbomachine stage including guide vanes, radially inner and/or radially outer airfoil platforms, which together form a guide vane cascade, and further including rotor blades, radially inner and/or radially outer airfoil platforms, which together form a rotor blade cascade adjacent to the guide vane cascade. Radially outer airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies, in particular periodically, in the radial and/or axial direction around the circumference. | 06-20-2013 |
20130156563 | TURBOMACHINE AND TURBOMACHINE STAGE - A turbomachine stage includes guide vanes and an airfoil platform forming a guide vane cascade, and rotor blades and an airfoil platform forming a rotor blade cascade. Airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies in the radial and/or axial direction around the circumference. A maximum extent of this contour in the radial direction toward the spoke-like pattern is circumferentially spaced from an airfoil edge of this cascade by no more than 50% of the cascade pitch, a maximum variation in the radial direction being no more than 50% of the cascade pitch and/or a maximum extent in the axial direction away from the spoke-like pattern is circumferentially spaced from an airfoil edge of this cascade by no more than 50% of the cascade pitch, a maximum variation in the axial direction being no more than 50% of the cascade pitch. | 06-20-2013 |
20130170969 | Turbine Diffuser - The present application provides a diffuser for use with a gas turbine. The diffuser may include hub, a number of struts extending from the hub, and a number of airfoils extending from the hub. | 07-04-2013 |
20130189091 | MOTOR-DRIVEN COMPRESSOR AND METHOD FOR MANUFACTURING THE SAME - A motor-driven compressor includes an electric motor having a stator core, a compression mechanism driven by the electric motor, a motor housing accommodating the electric motor, and a cluster block engaged with the stator core in the motor housing. The stator core of the electric motor and the motor housing are assembled by shrink fit. The cluster block accommodates a connecting terminal for electrical connection between a conductor connected to a motor drive circuit and a lead wire drawn from the electric motor. The cluster block has a terminal hole for receiving the connecting terminal and has an opening that is provided separately from the terminal hole. | 07-25-2013 |
20130195634 | FAN DEVICE - A fan device includes a rotor | 08-01-2013 |
20130202422 | COMPRESSOR OF USE IN GAS TURBINE ENGINE - Provided is a compressor for use in a gas turbine engine, capable of preventing a creation of rust on an inner surface of the compressor casing, without complicating assembling process. The casing | 08-08-2013 |
20130202423 | ANGULAR SECTOR OF A STATOR FOR A TURBINE ENGINE COMPRESSOR, A TURBINE ENGINE STATOR, AND A TURBINE ENGINE INCLUDING SUCH A SECTOR - A stator angular sector for a turbine engine compressor and including: an outer shroud and an inner shroud; and at least one vane extending radially between the shrouds and connected thereto at its radial ends. At one of its axial ends the outer shroud includes a cavity opening out to the axial end and extending between a radially-inner tongue of the outer shroud to which the radially-outer end of the vane is connected, and a radially-outer tongue of the outer shroud carrying a mounting mechanism for mounting the stator angular sector to a casing of the engine. An abutment-forming insert is housed at least in part in the cavity, the abutment-forming insert configured to limit radial movements of the radially-inner tongue by contact and thus to modify vibratory behavior of the radially-inner tongue. | 08-08-2013 |
20130209243 | ROTARY DISPLACEMENT PUMP FOR PUMPING SOLIDS EMULSIONS, ESPECIALLY LIQUID EXPLOSIVES - A rotary displacement pump of an undulatory disk type; with a pump housing ( | 08-15-2013 |
20130224004 | Radial Diffuser Vane for Centrifugal Compressors - A turbo machine comprising a rotor assembly comprising at least one impeller, a bearing connected to the rotor assembly, wherein the bearing is configured to rotatably support the rotor assembly, and a stator comprising at least one diffuser connected to an exit portion of the at least one impeller, wherein the at least one diffuser comprises a plurality of diffuser vanes, wherein at least one of the plurality of diffuser vanes comprising a camber line defined by a function comprising an inflection point. | 08-29-2013 |
20130243583 | Vacuum Pump - In a rotor blade cylindrical portion or a stator portion in which thread grooves are formed, convex surfaces (thread groove peak surfaces) configuring the peak sections of the thread grooves are cut by a desired amount over the entire circumference (a circumferential direction of the thread grooves) of a certain range in an axial direction. As a result, the gap on the lower side of the thread groove portion can partially be expanded by cutting the thread groove peak surfaces by a desired amount. | 09-19-2013 |
20130280054 | TURBINE ENGINE STATOR AND METHOD OF ASSEMBLY OF THE SAME - A turbine engine stator stage includes a plurality of vanes with each of the plurality of vanes having a camber angle. The plurality of vanes is arranged in a plurality of groups with each group including a pre-determined sequence of vanes. The ordering of vanes within each group is determined by the camber of the individual vanes. This results in an arrangement of vanes within the stator stage which can modify the flow characteristics of the air entering the stator stage to reduce the circumferential pressure variation in the flow region immediately downstream of the stator stage. | 10-24-2013 |
20130302151 | Stator Assembly - A stator assembly or a stator stage is disclosed. The stator assembly includes an endless case that is coupled to or includes at least one lug for engaging an anti-rotation stator segment. The anti-rotator segment includes one curved side edge and one straight or linear side edge. The case also accommodates a plurality of middle stator segments, each having curved side edges on both sides. Finally, a third type of stator segment is a “neighbor” stator segment with one curved side edge and one linear side edge that abuttingly engages the linear side edge of the anti-rotation stator segment. The straight or linear side edges of the anti-rotation stator segments and the neighbor stator segments enable an endless case to be loaded with stator segments from an axial direction. None of the stator segments need to be installed from a radial direction. | 11-14-2013 |
20130302152 | STATOR - A stator includes: a plurality of stator pieces around which coils are wound; a stator holder which supports the plurality of stator pieces by arranging the plurality of stator pieces in a peripheral wall portion in an annular shape; and a housing which is disposed on an outer side of the stator holder to support the stator holder, wherein the stator holder includes a flange portion which continuously protrudes outward in a radial direction thereof from an edge of one end side in an axial line direction thereof and is fixed to the housing, and a reinforcing portion which suppresses vibration in the radial direction of the stator holder on an outer peripheral surface of the peripheral wall portion. | 11-14-2013 |
20130309075 | TURBINE DIAPHRAGM CONSTRUCTION - An axial flow turbine diaphragm is constructed without welding or other metal joining techniques as an annular array of static blade units. Each blade unit comprises an aerofoil and radially inner and outer platforms integral with the aerofoil. The radially inner platform consists of a segment of the inner diaphragm ring and the radially outer platform consists of a segment of the outer diaphragm ring. At least the outer ring segment has engagement features that mechanically engage with complementary engagement features on neighbouring outer ring segments in the annular array of blade units, the engagement features acting to mechanically interlock neighbouring outer ring segments and produce a self-supporting turbine diaphragm. | 11-21-2013 |
20130323038 | STATOR VANE BUMPER RING - An assembly for use in a gas turbine engine includes an inner diameter (ID) shroud having a plurality of ID slots and an outer diameter (OD) shroud having a plurality of OD slots and positioned radially outward from the ID shroud. A plurality of stator airfoils extend from the ID shroud to the OD shroud. Each of the stator airfoils is positioned at least partially in one of the ID slots and is positioned at least partially in one of the OD slots. A bumper is positioned proximate a first end of each of the stator airfoils so as to limit movement of the stator airfoils in a radial direction. | 12-05-2013 |
20130323039 | Compressor - A compressor is provided that can avoid fretting damage to improve fatigue strength reliability. | 12-05-2013 |
20140003927 | BLOWER ASSEMBLY | 01-02-2014 |
20140003928 | SPOOL FOR TURBO MACHINERY | 01-02-2014 |
20140064945 | Stator Vane Assembly - The present application thus provides a stator vane assembly for a turbine engine. The stator vane assembly may include a casing slot and a number of ring segments positioned within the casing slot. Each of the ring segments may include a first end and a second end. The first end and the second end may have a stepped configuration. | 03-06-2014 |
20140093364 | DOUBLE FLOW TURBINE HOUSING TURBOCHARGER - Implementations of the present disclosure are directed to turbine assemblies for turbocharger systems. In some implementations, turbine housings include a body that defines an inlet for fluid communication with a fluid source, and a wall, the wall dividing the inlet into an inner inlet and an outer inlet, and a fluid guide assembly disposed within the housing, the fluid guide assembly including a plurality of vanes that demarcate an inner volute and an outer volute within the housing, the inner volute being in fluid communication with the inner inlet and the outer volute being in fluid communication with the outer inlet, each vane of the plurality of vanes being fixed at a respective angle relative to a radial direction, the plurality of vanes guiding fluid flow from the outer volute to the inner volute. | 04-03-2014 |
20140140833 | TURBINE SHROUD MOUNTING AND SEALING ARRANGEMENT - A turbine shroud apparatus for a gas turbine engine having a centerline axis includes: a shroud segment having: an arcuate body extending axially between forward and aft ends and laterally between opposed end faces, wherein each of the end faces includes seal slots formed therein; and an arcuate stationary seal member mounted to the body; a turbine vane disposed axially aft of the shroud segment; and a casing surrounding the shroud segment and the turbine vane; wherein the turbine vane is mounted to the case so as to bear against the stationary seal member, compressing it and forcing the shroud segment radially outward against the casing. | 05-22-2014 |
20140140834 | NOZZLE RING - An exemplary nozzle ring has two fastening rings and a plurality of guide vanes, wherein holes are provided in one of the fastening rings for accommodating pins of the guide vanes, and openings are provided in the other fastening ring for accommodating positioning aids on the guide vanes. | 05-22-2014 |
20140147260 | HEAT DISSIPATING FAN - A heat dissipating fan includes a stator and a rotor. The stator includes a bearing and a winding structure, wherein the bearing is disposed in the winding structure. The rotor includes a fan wheel, a ring-shaped casing and a magnetic member, wherein the ring-shaped casing is disposed in the fan wheel and the magnetic member is disposed in the ring-shaped casing. The fan wheel has an axle inserted into the bearing such that the winding structure is located within the magnetic member. At least one protruding portion protrudes from one side of the ring-shaped casing inwardly and is extended below the winding structure so as to hold the magnetic member and interfere with the winding structure. | 05-29-2014 |
20140147261 | Centrifugal Fan - A centrifugal fan includes a fan frame, a stator assembly and an impeller. The fan frame has a base plate portion, a cover plate portion and a lateral wall portion. The cover plate portion includes first and second faces. The cover plate portion includes an air inlet, and the lateral wall portion includes an air outlet. The impeller has a radial rotational range. The cover plate portion includes an air-guiding section and an enlarged guiding section. The air-guiding section is aligned with the radial rotational range, and the enlarged guiding section is aligned with an area outside the radial rotational range. A part of the second face is spaced from a bottom of the base plate portion by a first minimal axial distance, and another part of the second face is spaced from the bottom by a second minimal axial distance smaller than the first minimal axial distance. | 05-29-2014 |
20140147262 | Axial Turbomachine Stator with Segmented Inner Shell - The present application relates to a compressor stator of an axial turbomachine having an inner shell formed of a plurality of annular segments arranged end to end, a layer of abradable material applied on the inner face of the shell, and an annular array of blades connected to the shell. The stator has at least one strip located in the layer of abradable material and extending from either side of the junctions between two adjacent annular segments. The inner tips of the blades have hooks mating mechanically with the strip. | 05-29-2014 |
20140154065 | TURBOMACHINE FLOW DIVIDER AND RELATED TURBOMACHINE - Various embodiments include a turbomachine flow divider. In various particular embodiments, a flow divider for connecting with a first inner diaphragm ring and a second inner diaphragm ring of a turbomachine includes: a body section; and a pair of axially extending flanges extending from the body section, each of the axially extending flanges for engaging with the first inner diaphragm ring and the second inner diaphragm ring, respectively, wherein the flow divider is formed substantially of a rolled plate metal or a sheet metal. | 06-05-2014 |
20140154066 | TURBOMACHINE NOZZLE HAVING FLUID CONDUIT AND RELATED TURBOMACHINE - Various embodiments include a steam turbine nozzle and turbomachinery including such a nozzle. In various particular embodiments, a steam turbine nozzle includes: a body having: a first sidewall and a second sidewall opposite the first sidewall; a pressure side and a suction side each extending between the first sidewall and the second sidewall; and a leading edge section at a first junction of the pressure side and the suction side, and a trailing edge section at a second junction of the pressure side and the suction side; and a bypass fluid conduit including: a channel having an opening to at least one of the first sidewall or the second sidewall; and an outlet passageway fluidly connected with the channel between the first sidewall and the second sidewall, the outlet passageway including a first opening on at least one of the pressure side of the body, the suction side of the body or the trailing edge section. | 06-05-2014 |
20140178189 | VERTICAL AXIS DUAL VORTEX DOWNWIND INWARD FLOW IMPULSE WIND TURBINE - A wind-powered turbine has a housing with an inlet and an outlet. Located in the housing is a cylindrical stator array having a plurality of spaced-apart stators located in it. An annular cylindrical rotor array having a plurality of cups rotates about a central axis, fits inside of the stator array. The stators are positioned to cause air which flows around the outer periphery of the stator array to impinge on the rotors and an air handling system causes air entering the housing to be distributed substantially around the periphery of the stator array. | 06-26-2014 |
20140193248 | LOCKING DEVICE FOR COOLING FAN ASSEMBLY - A locking device is provided for a cooling fan assembly. The assembly includes a central hub. A plurality of blades are operatively connected to and configured to selectively rotate around the central hub. A blade ring is fixedly connected to respective outermost radial portions of the plurality of blades. The blade ring may be annularly-shaped and defines at least one blade ring slot. The locking device is configured to selectively prevent the plurality of blades from rotating. The locking device includes a movable member and an actuation device for moving the movable member. The movable member is slidable relative to the blade ring between two positions, an unlocked position that substantially permits the plurality of blades to rotate and a locked position that substantially prevents the plurality of blades from rotating. | 07-10-2014 |
20140212280 | FAN DEVICE FOR HIGH TORQUE OUTPUT - A fan device for high torque output has two base plates, multiple fans, and a spindle. The base plates are mounted parallel to each other. The fans are mounted between the base plates, and each fan has an inner side, an outer side, and an inflection point. The spindle is connected with one of the base plates and is located at a middle position of the base plate. A connecting line that connects the inflection point and the spindle is out of an area defined between a connecting line that connects the spindle and the inner side and a connecting line that connects the spindle and the outer side when the inflection point, the inner side, and the outer side are located at the same horizontal plane. Therefore, each fan has a large frontal area to be pushed by fluid. | 07-31-2014 |
20140241867 | DRUM ROTOR DOVETAIL COMPONENT AND RELATED DRUM ROTOR SYSTEM - Systems and devices adapted to retain dovetail components (e.g., buckets) in a turbine drum rotor and reduce rotor component displacement are disclosed. In one embodiment, a turbine bucket includes: a bucket base portion shaped to complement a bucket shank slot in a rotor of a turbine, the bucket base portion including: a forward portion shaped to extend upstream of a first stage circumferential slot of the rotor in to a first rotor post of the rotor; a circumferential protrusion formed in an aft end of the bucket base portion and shaped to connect to the rotor, and a set of axial protrusions formed on tangential sides of the bucket base portion and shaped to connect to the rotor; and a bucket platform extending radially outboard from the bucket base portion, the bucket platform configured to complement a vane. | 08-28-2014 |
20140241868 | FAN ASSEMBLIES AND STATOR ASSEMBLIES - Fan assemblies, and in particular fan wheels and stator assemblies for fan assemblies, are disclosed. In one embodiment, the fan wheel includes a wheel back having an outer surface forming one of a curved dome-shape and a truncated cone-shape. The fan wheel may also include a plurality of fan blades radially spaced about and mounted to the outer surface of the wheel back. In one embodiment, each of the fan blades is formed from a segment of an airfoil-shaped aluminum extrusion defining at least one internal cavity. The fan blade first ends can be provided with a compound cut profile with at least one curved cut such that the first end of the blade is mounted flush to the wheel back outer surface. The stator assembly can also be provided with a plurality of stator blades formed from airfoil-shaped aluminum extrusion segments and provided with compound cut profiles. | 08-28-2014 |
20140241869 | STEAM TURBINE INNER SHELL ASSEMBLY WITH COMMON GROOVES - An inner shell assembly for a steam turbine includes an inner shell with a plurality of grooves of preset dimensions, and a plurality of nozzle carriers respectively securable in the plurality of grooves. Each of the nozzle carriers supports at least one nozzle and bucket for a turbine stage via a dovetail, where the inner shell, the plurality of nozzle carriers and the nozzles and buckets define a steam path. A radial position of the dovetails in the nozzle carriers within its corresponding grooves is selectable according to the steam path, and an axial width of each of the nozzle carriers is selectable according to the steam path. | 08-28-2014 |
20140294574 | Stator Blades of an Axial Turbocompressor and Manufacturing Process - The present application relates to a stator of an axial turbomachine compressor having an external shell with a row of openings and an internal annular groove designed to hold an annular layer of abradable material forming a strip. The stator further includes a row of stator blades adjacent to the row of openings. The stator blades include platforms with surfaces matching the openings, the said platforms being fitted in the openings so as to mask them. Weld beads fix the platforms at their junctions with the openings. On one side of the row of stator blades a portion of the weld bead is situated axially in the internal annular groove. The present application also relates to methods of manufacturing the stator. | 10-02-2014 |
20140322000 | Turbine Nozzle for Air Cycle Machine - A nozzle for use in an air cycle machine has a plate. A plurality of vanes extends in a second axial direction away from the plate. The plurality of vanes extends for a height away from the plate and a width defined as the closest distance between two adjacent vanes, with a ratio of the nozzle height to the nozzle width being between 0.3563 and 0.4051. An air cycle machine and a method are also disclosed. | 10-30-2014 |
20140363280 | METHOD OF REFURBISHING AN ENERGY CONVERSION FACILITY AND REFURBISHED ENERGY COVERSION FACILITY - This method can be used for refurbishing a facility for converting hydraulic energy into electrical or mechanical energy, and vice versa. The facility includes a Francis type pump-turbine. The pump-turbine includes a runner movable about an axis, a pre-distributor, including stay vanes defining between each pair of two adjacent stay vanes a first water passage channel and a distributor, including guide vanes arranged downstream of the stay vanes in the direction of water flow feeding the pump-turbine operating in turbine mode. The guide vanes define between each pair of two adjacent guide vanes a second water passage channel. This method includes steps of reducing the height, taken parallel to the axis of rotation of the runner, of the first water passage channels and reducing the height, taken parallel to the axis of rotation of the runner, of the second water passage channels. | 12-11-2014 |
20150030439 | VORTEX GENERATORS PLACED IN THE INTERBLADE CHANNEL OF A COMPRESSOR RECTIFIER - A compressor rectifier of a turbomachine including a plurality of stationary blades extending in a circular fashion between an inner shroud and an outer shroud that are concentric and define interblade channels forming an air duct in which air to be compressed flows, the inner shroud including at least one vortex generator extending into the air duct to reduce corner vortices. The vortex generator is positioned axially in the interblade channel, between the axial position of a leading edge of the blades and those of a trailing edge thereof. | 01-29-2015 |
20150050134 | FULL ARC ADMISSION STEAM TURBINE - The invention relates to a full arc admission steam turbine, which includes a plurality of nozzle boxes for inducing steam, and a plurality of nozzle plates for bearing nozzles, one nozzle plate corresponding to each nozzle box. The steam turbine | 02-19-2015 |
20150078890 | COMPRESSOR CASING COMPRISING CAVITIES WITH OPTIMISED SETTING - A compressor for a turbine engine, including: a casing, at least one compressor stage including an impeller having stationary blades and an impeller having moving blades positioned downstream of the stationary blade impeller, and cavities in a thickness of the casing that are disposed along a circumference of the casing opposite the moving blades. The cavities, which are elongate and extend along a main direction of orientation, are closed upstream and downstream by upstream and downstream faces respectively, and an upstream border and a downstream border are formed at the intersections between same and the casing. The cavities are offset in relation to the moving blades to overlap the moving blade impeller in the upstream portion, thereby covering the upstream end thereof. The downstream border of the cavities is oriented parallel to the chord at the head of the moving blade. | 03-19-2015 |
20150118035 | TURBINE STAGE FOR A TURBINE ENGINE - A turbine stage for a turbine engine, the stage including a nozzle and a wheel mounted inside a sectorized ring carried by a casing. The nozzle is attached to the casing and is retained axially downstream by bearing against an annular split ring. Each ring sector includes at its upstream end a member of C-shaped section that is engaged on the casing rail and that holds the split ring radially. A radially inner wall of the C-shaped member of each ring sector extends inside the split ring over an entire axial dimension thereof and its upstream end portion is engaged in at least one recess of the nozzle. | 04-30-2015 |
20150300185 | METHOD OF DESIGNING GUIDE VANE FORMATIONS - A computer-based method of designing a guide vane formation is provided. The vane formation is for use in a gas turbine engine which has a cascade of circumferentially arranged identical guide vane formations. The vane formation has radially inner and radially outer chordal seals. The method allows the elimination of “saw-tooth” leakage gaps between inner chordal seals of neighbouring vane formations and between outer chordal seals of neighbouring vane formations even when the inner and outer chordal seals are axially offset from each other. | 10-22-2015 |
20150377245 | BUSHING STRUCTURE AND FAN - A bushing structure cooperating with a shaft is disclosed. The bushing structure includes a cylindrical body and an extension portion. The cylindrical body has a shaft hole and the shaft is disposed in the shaft hole. The extension portion is disposed at one end of the cylindrical body and surrounds the cylindrical body. The cylindrical body and the extension portion are made of an iron-contained material. | 12-31-2015 |
20160003075 | GAS TURBINE ENGINE STATOR VANE ASSEMBLY WITH SPLIT SHROUD - A method of assembling gas turbine engine front architecture includes positioning a first shroud and a first shroud portion radially relative to one another. Multiple vanes are arranged circumferentially between the first shroud and the first shroud portion. A second shroud portion is secured to the first shroud portion about the vanes. The first and second shroud portions provide a second shroud. The vanes are mechanically isolated from the first and second shrouds. | 01-07-2016 |
20160010474 | TURBINE NOZZLE COMPONENTS HAVING REDUCED FLOW AREAS | 01-14-2016 |
20160108885 | AIR TURBINE FOR APPLICATIONS IN WAVE ENERGY CONVERSION - The present invention relates to an air turbine capable of without change in its rotational velocity direction, efficiently absorbing the energy associated with a pressure difference between two spaces (A) and (B) of successively changing sign, as in the case of sea wave energy systems. The turbine comprises two sets of blades (I) and (II), each of which is similar to the blade system of a conventional turbine of radial-, mixed- or axial-flow type. The turbine also comprises a system of ducts that connect spaces (A) and (B) through any of the two blade sets (I) and (II). The turbine may be equipped with a fast-acting valve that stops the flow through one or both blade sets (I) and (II). | 04-21-2016 |
20160153293 | AXIAL FLOW EXPANDER | 06-02-2016 |
20170234149 | NOZZLE BOX ASSEMBLY | 08-17-2017 |