Vane Or Deflector Patents (Class 415/208.1)
- Plane intersects with runner blade (Class 415/208.3)
- Plural, axially spaced vane sets acting successively or having specific spacing means (Class 415/209.1)
- Having means for mounting diaphragm or plural vane holder to casing (Class 415/209.2)
- Having specific vane mounting means (Class 415/209.3)
- Fixed between radially separate surfaces (Class 415/210.1)
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Publication number: 20140199166Abstract: An apparatus for controlling the propulsion and direction of an air cushion vehicle including a housing and a first vane pivotally coupled to the housing and pivotable about a first axis. A second vane assembly including at least one second vane is disposed within the first vane. The second vane assembly is pivotally coupled to the first vane and pivotal about a second axis. The second axis is orthogonal to the first axis. A first actuator is operably coupled to the first vane and a second actuator is operably coupled to the second vane assembly. The first actuator pivots the first vane and the second vane assembly about the first axis. The second actuator pivots the second vane assembly relative to the first vane and about the second axis to control the flow of air through the housing.Type: ApplicationFiled: January 10, 2014Publication date: July 17, 2014Inventor: CHARLES J. TROJAHN
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Publication number: 20140196464Abstract: A system includes a gas turbine engine that includes a turbine section having one or more turbine stages between an upstream end and a downstream end, an exhaust section disposed downstream from the downstream end of the turbine section, and a fluid supply system coupled to the exhaust section. The fluid supply system is configured to route an inert gas to the exhaust section.Type: ApplicationFiled: December 19, 2013Publication date: July 17, 2014Applicants: EXXONMOBIL UPSTREAM RESEARCH COMPANY, GENERAL ELECTRIC COMPANYInventors: Pramod K. Biyani, Rajarshi Saha, Anil Kumar Dasoji, Richard A. Huntington, Franklin F. Mittricker
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Patent number: 8777560Abstract: A method and apparatus for reducing a selected tonal noise generated by a fan operating in a non-uniform flow by locating at least one obstruction in the non-uniform flow such that the at least one obstruction generates a noise that is out of phase with the selected tonal noise. The noise generated by the at least one obstruction interferes with the selected tonal noise, thus reducing the selected tonal noise. It is also contemplated to use additional obstructions to reduce other tonal noises generated by the fan.Type: GrantFiled: June 23, 2010Date of Patent: July 15, 2014Assignees: Socpra—Sciences et Genie, S.E.C., Universite de Poitiers, Centre National de la Recherche ScientifiqueInventors: Anthony Gerard, Alain Berry, Patrice Masson, Yves Gervais, Michel Besombes
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Publication number: 20140190164Abstract: A duct for connection between an exhaust manifold and a high-pressure turbine inlet include a cylindrical duct body defining a longitudinal axis. A frustoconical outlet nozzle connected at one end of the duct body and extending at about eighty-five degrees from the longitudinal axis. The duct further includes an inlet bell connected at the other end of the duct body and extending at about fifty degrees from the longitudinal axis.Type: ApplicationFiled: June 24, 2013Publication date: July 10, 2014Inventors: CHARLES B. ATZ, JOHN DOWELL, VIJAYASELVAN JAYAKAR, PRATAP SUBHASH SHITOLE, CAIN PIOTROWSKI, TRENT A. LARSON, EDWARD PHANEUF, ABHIJEET WARALE, SHIRISH BHIDE
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Publication number: 20140193250Abstract: A plate closes the main part of a vane in two parts. An internal cavity is closed by the plate. Around a bearing surface of the plate, a groove receives an elastic seal, and the outer edge of the plate extends over the groove to compress the seal and to establish excellent leak proofing. The position of the plate may be guaranteed by centring pins penetrating into holes adjacent to the seal and which it fills when the pins have been removed, which completes the closing of the cavity. The plate has application in particular to stationary gas guide vanes in turbine engines.Type: ApplicationFiled: July 17, 2012Publication date: July 10, 2014Applicant: SNECMAInventors: Thierry Georges Paul Papin, Lise Lacroix, Dominique Raulin
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Publication number: 20140186173Abstract: A system, in certain embodiments, includes a plurality of detachable, three-dimensional diffuser vanes attached to a diffuser plate of a centrifugal compressor. In certain embodiments, the detachable, three-dimensional diffuser vanes may be attached to the diffuser plate using threaded fasteners. In addition, dowel pins may be used to align the detachable, three-dimensional diffuser vanes with respect to the diffuser plate. However, in other embodiments, the detachable, three-dimensional diffuser vanes may include a tab configured to fit securely within a groove in the diffuser plate. In addition, the tabs of the detachable, three-dimensional diffuser vanes may include indentions that mate with extensions extending from the diffuser plate, wherein the tabs may slide into slots between the extensions and the grooves of the diffuser plate.Type: ApplicationFiled: December 30, 2013Publication date: July 3, 2014Applicant: Cameron International CorporationInventors: Noel Blair, Charles F. Herr, David N. O'Neill
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Publication number: 20140186171Abstract: A guide blade arrangement for an exhaust gas turbocharger may include guide blades rotatably mounted on a guide blade carrier ring via a respective blade bearing pin. A cover disc may be spaced from the guide blade carrier ring, wherein the guide blades may be arranged between the cover disc and the guide blade carrier ring. The cover disc may include a ceramic material, and the ceramic material may have a higher thermal conductivity in relation to at least one of the guide blade carrier ring, the guide blades, and the respective blade bearing pin.Type: ApplicationFiled: October 22, 2013Publication date: July 3, 2014Applicant: Bosch Mahle Turbo Systems GmbH & Co. KGInventor: Dirk Naunheim
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Patent number: 8764376Abstract: A diffuser divider shaped as disc with a central axis, a leading edge disposed at an inner radius about the central axis, a trailing edge disposed at an outer radius about the central axis, an upper surface disposed between the leading edge and the trailing edge, a lower surface disposed between the leading edge and the trailing edge and one or more mounting features configured to mount the disc in a diffuser section configured to receive air compressed by two compressor wheel faces and to direct the compressed air to a volute. Such a divider can define throats in a diffuser section of a compressor assembly. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.Type: GrantFiled: May 16, 2011Date of Patent: July 1, 2014Assignee: Honeywell International Inc.Inventors: Vai Man Lei, Glenn F. Thompson
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Publication number: 20140169956Abstract: A vane includes a platform with a fixture overmolded by a sheath.Type: ApplicationFiled: December 14, 2012Publication date: June 19, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventor: David R. Lyders
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Publication number: 20140161585Abstract: A component, a component manufacturing process, and a component operation process are disclosed. The component has a diffuser permitting compressible fluid to flow throughout a first region and a second region of the diffuser at a decreasing velocity. The diffuser includes a coating collection feature. The component manufacturing process includes positioning the component and applying the coating to at least a surface of the component outside of the diffuser and to at least a portion of the second region, not to the first region, to the coating collection feature, or a combination thereof. The component operation process includes positioning the component and transporting the compressible fluid through the diffuser.Type: ApplicationFiled: December 10, 2012Publication date: June 12, 2014Applicant: GENERAL ELECTRIC COMPANYInventor: General Electric Company
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Publication number: 20140161607Abstract: The turbomachine includes a mid turbine vane frame, with an annular compartment formed between the mid turbine vane frame and a low-pressure turbine casing being sealed by means of at least two ring seals, wherein one ring seal is in contact with the mid turbine vane frame and the other ring seal is in contact with the low-pressure turbine casing and a radial annular overlap is thereby created with the first-mentioned ring seal.Type: ApplicationFiled: December 4, 2013Publication date: June 12, 2014Applicant: MTU Aero Engines AGInventor: Klaus Pirker
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Publication number: 20140161606Abstract: A vane for an axial-flow compressor has a pressure surface generating positive pressure and a suction surface generating negative pressure, and both are located on one side of the chord line. The pressure surface includes a bulging portion, having a maximum curvature of 1.5 or more between a chordal position of 70% and 95%, in a central section of the vane's span. This configuration increases the flow velocity around the bulging portion of the pressure surface to locally decrease the static pressure. By flow continuity the flow velocity on the suction surface that faces the pressure surface is decreased, and thus locally the static pressure on the suction surface is increased. Secondary flow from the pressure surface with positive pressure to the suction surface with negative pressure from the hub region, is suppressed due to the locally increased static pressure on the suction surface.Type: ApplicationFiled: November 20, 2013Publication date: June 12, 2014Applicant: HONDA MOTOR CO., LTD.Inventors: Toyotaka Sonoda, Toshiyuki Arima, Giles Endicott, Markus Olhofer
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Publication number: 20140159373Abstract: A device for generating electrical power from fluid flow energy comprising a shaft member; at least one sleeve, wherein the shaft member passed through the at least one sleeve; a stationary stator, wherein the stationary stator coupled to the shaft member, and wherein the stationary stator comprising a first stator and a second stator, wherein the first stator is positioned adjacent to the second stator; and at least one moving stator, wherein the at least one moving stator positioned in concentric relation to the stationary stator.Type: ApplicationFiled: May 14, 2013Publication date: June 12, 2014Inventor: Mehboob Lakhani
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Publication number: 20140161605Abstract: A gas turbine structure includes a guide vane. The gas turbine structure (further includes a first housing and a second housing and the guide vane extends from the first housing to the second housing. The guide vane includes a leading edge and a trailing edge and the guide vane extends from the leading edge to the trailing edge along a mean camber line. The guide vane includes a first attachment structure, a first fastening arrangement and a second fastening arrangement. Moreover, the first attachment structure includes a stiffening member extending over at least a portion of a circumference of the first housing. Furthermore, the stiffening member includes a stiffening member center point as measured along the mean camber line.Type: ApplicationFiled: March 14, 2011Publication date: June 12, 2014Inventors: Niklas Jansson, Robert Reimers
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Patent number: 8747066Abstract: A gas turbine housing component includes a wall structure including two adjacent wall parts and a connection arrangement arranged between adjacent edges of the two wall parts. The connection arrangement includes an elongated seal strip positioned along the wall part edges and bridging the distance between the wall part edges.Type: GrantFiled: March 18, 2008Date of Patent: June 10, 2014Assignee: Volvo Aero CorporationInventors: Linda Ström, Jonas Lindskog, Per Widström
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Patent number: 8747064Abstract: A two-layer wind-guiding shroud includes a base. The interior of the base includes a first wind-guiding channel and a second wind-guiding channel longitudinally overlapped with each other. The first wind-guiding channel has a first wind entrance and a first wind exit. The second wind-guiding channel has a second wind entrance and a second wind exit. The first wind exit and the second wind exit are staggered. By this arrangement, the airflow generated by a fan can be guided into different wind-guiding channels toward different locations, thereby increasing the heat-dissipating efficiency of the fan.Type: GrantFiled: June 10, 2011Date of Patent: June 10, 2014Assignee: Super Micro Computer Inc.Inventors: Ku-Yang Chou, Richard S. Chen
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Publication number: 20140154068Abstract: An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall adjacent to the first side of at least one of said plurality of airfoils near the leading edge of the at least one of said plurality of airfoils, and a concave profiled region in the endwall and extending across said at least one of said plurality of flow passages.Type: ApplicationFiled: October 30, 2012Publication date: June 5, 2014Applicant: United Technologies CorporationInventor: United Technologies Corporation
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Publication number: 20140154069Abstract: A turbine wheel for low-pressure ratio applications is disclosed. The ratio of the outlet area of the wheel (A2) to the inlet area of the wheel (A1) is less than approximately 0.4. In an embodiment, the wheel is a radial or mixed-flow wheel.Type: ApplicationFiled: February 2, 2012Publication date: June 5, 2014Applicant: Imperial Innovations LimitedInventors: Ricardo Fernando Martinez-Botas Mateo, Alessandro Romagnoli, Aman Mohd Ihsan Bin Mamat
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Patent number: 8740546Abstract: A guide vane of a condensation turbine steam turbine is provided, wherein the guide vane includes a heating resistor. The guide vane includes fiber composite material at least in some regions. The heating resistor may be embodied as a heating wire or as a heating film. A condensation steam turbine having a guide vane as described above is also provided.Type: GrantFiled: April 29, 2009Date of Patent: June 3, 2014Assignee: Siemens AktiengesellschaftInventors: Christoph Ebert, Albert Langkamp, Markus Mantei
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Publication number: 20140147263Abstract: A turbine vane for a gas turbine engine has an inner platform, an outer platform, at least one airfoil extending between the inner and outer platforms, and a tab radially extending inward from a front side of the inner platform. The tab contains a mounting aperture and an identification aperture that identifies an engine in which the turbine vane may be installed.Type: ApplicationFiled: October 25, 2012Publication date: May 29, 2014Applicant: United Technologies CorporationInventor: United Technologies Corporation
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Publication number: 20140147265Abstract: The present application relates to the stator blades of an axial turbomachine intended to be fitted on a ferrule in an annular row of identical blades. Each blade includes a platform with opposed lateral edges and a means of attachment to the ferrule. The contour of the platform has, at each of the lateral edges, an angular profile designed to mate with the contiguous edge of the platform of an adjacent blade. This feature enables the angular position or pitch of the blade to be set. The present application also relates to a stator comprising the blade row. Mechanical clearances J1, J2 and J3 and the means of clamping cause an average angular orientation error. The blades are made with a compensatory angle to offset the angular orientation error.Type: ApplicationFiled: November 27, 2013Publication date: May 29, 2014Applicant: Techspace Aero S.A.Inventor: Guy Biemar
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Publication number: 20140140870Abstract: 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.Type: ApplicationFiled: November 12, 2013Publication date: May 22, 2014Applicant: Ford Global Technologies, LLCInventors: Erik Henry Hermann, Randall Alan Stec, Douglas White, Jacqueline Tomlin, William C. Ronzi, Roger Khami, Robert Bruce Bonhard, Bhaskara Rao Boddakayala
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Publication number: 20140140805Abstract: According to one embodiment, there is disclosed an inducer assembly for use with a gas turbine engine. The inducer assembly may include a cavity. The inducer assembly may also include an inducer in fluid communication with the cavity. Moreover, the inducer assembly may include at least one guide vane disposed within the cavity.Type: ApplicationFiled: November 5, 2012Publication date: May 22, 2014Applicant: General Electric CompanyInventor: General Electric Company
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Publication number: 20140140815Abstract: A surgical instrument includes a hub, a rotating member, an impeller, and an impeller enclosure. The hub has a proximal portion and a distal portion and defines a lumen therebetween. The distal portion of the hub includes a sleeve portion configured to rotatably support the rotating member. The rotating member extends through the hub and has a proximal end and a distal end. The proximal end of the rotating member is configured to couple to an external driving mechanism. The impeller is coupled to the distal end of the rotating member and is configured to accelerate fluid flowing into or out of the lumen. The impeller enclosure is coupled to the distal portion of the hub and defines an impeller volume around the impeller. One or more openings are defined around the sleeve portion of the hub such that the lumen is in fluid communication with the impeller volume.Type: ApplicationFiled: November 20, 2012Publication date: May 22, 2014Applicant: SMITH & NEPHEW, INC.Inventors: Cemal Shener-Irmakoglu, Brian J. Loreth, Rafal Z. Jezierski, Paul Robert Duhamel
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Publication number: 20140140820Abstract: A bifurcation aerofoil having a leading edge portion and flanks where the leading edge portion is mounted to an inner wall of the bypass duct using a floating seal which permits circumferential movement of the leading edge. A cowl has a wall that provides the flanks of the aerofoil. On closing of the cowl into its flight position any contact between the flanks and the leading edge portion enables realignment of the leading edge portion to the inner wall of the bypass duct.Type: ApplicationFiled: November 15, 2013Publication date: May 22, 2014Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KGInventor: Predrag TODOROVIC
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Publication number: 20140140837Abstract: A suction diffuser or arrangement is provided featuring a main suction diffuser body and a flow conditioning arrangement. The main suction diffuser body is configured with an inlet to receive an incoming fluid flow, an interior cavity to receive the incoming fluid from the inlet, and an outlet to receive the incoming fluid from the interior cavity and provide an outgoing fluid. The flow conditioning arrangement is configured in relation to the inlet and also comprises a flow conditioning portion having at least one inwardly contoured surface, configured to extend into the interior cavity, diffuse the incoming fluid passing from the inlet into the interior cavity, and provide a flow conditioning that produces a uniform flow of the outgoing fluid by directing the incoming fluid towards the outlet, based at least partly on a contoured design corresponding to the at least one inwardly contoured surface.Type: ApplicationFiled: November 4, 2013Publication date: May 22, 2014Applicant: Fluid Handling LLCInventors: Stanley P. EVANS, JR., Mikhail P. STRONGIN, Florin ROSCA, Manish SHARMA, Ravi K. LAVETI, Sameer K. ANDE
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Publication number: 20140140833Abstract: 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.Type: ApplicationFiled: November 21, 2012Publication date: May 22, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Joseph Charles Albers, Robert Proctor, Monty Lee Shelton, Richard Russo, JR.
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Patent number: 8726940Abstract: A fuel equalization system includes a filter box for accepting an air stream and a fuel stream, the air stream and the fuel stream mixing to form a mixed air/fuel stream. A blower is provided that has an inlet for accepting the mixed air/fuel stream from the filter box. An air deflection member is positioned in the path of the mixed air/fuel stream, between the filter box and the inlet, so as to reduce the turbulence of the mixed air/fuel stream.Type: GrantFiled: February 16, 2010Date of Patent: May 20, 2014Assignee: Westcast, Inc.Inventor: Kenneth W. Cohen
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Publication number: 20140134399Abstract: Components having an environmental barrier coating and a sintered layer overlying the environmental barrier coating, the sintered layer defining an outer surface having a lower surface roughness than the environmental barrier coating. The sintered layer is formed from a slurry applied to and then sintered on the environmental barrier coating. The sintered layer comprises a primary material, at least one sintering aid dissolved in the primary material, and optionally a secondary material. The sintering aid contains at least one doping composition. The primary material is a rare earth disilicate or a rare earth monosilicate and is doped with the doping composition so as to be either a doped rare earth disilicate or a doped rare earth monosilicate. The optional secondary material is a reaction product of the primary material and any of the sintering aid not dissolved in the primary material.Type: ApplicationFiled: January 21, 2014Publication date: May 15, 2014Applicant: General Electric CompanyInventors: Glen Harold Kirby, Brett Allen Boutwell, Jessica Licardi Subit
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Patent number: 8721262Abstract: A vertical centrifugal pump comprises a housing, impeller, annular guiding vanes, annular outlet with outer and inner casings, forming a collector with a pressure pipe, and flow channels to lower and upper rims. Channels to the lower rim pass through the center of the pump axis. Blades direct flow between pipes into the pressure pipe. Pipes are connected with the lower rim through the lower confuser with flat radial ribs, positioned with the inner part of the confuser from the pipes and the outer part from the inner casing to the lower rim. An annular baffle is implemented between the housing and outer casing, dividing the inlet to the rims. Channels to the upper rim are created between the two annular elements, connected by radial outer ribs with a thickened, streamlined form and mated with flat inner ribs, merged in the upper confuser similarly to the lower confuser.Type: GrantFiled: November 11, 2013Date of Patent: May 13, 2014Inventor: Alexander Ivanovich Kuropatov
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Publication number: 20140127010Abstract: The present invention relates to a nozzle with a nozzle surface area and a nozzle rim, on which first and second guiding devices are alternatingly provided in the circumferential direction, where the first guiding devices are of the nozzle-type design and the second guiding devices are of the diffuser-type design. The first guiding devices each have a first azimuthal guide wall and two wall elements, with the first azimuthal guide wall forming a first trailing edge and two first edges to the wall elements. The second guiding devices each have a second azimuthal guide wall and two wall elements, with the second azimuthal guide wail forming a second trailing edge and two second edges to the wall elements. A wall element connects a first guiding device and a second guiding device. The wall elements have a curved course in the axial direction.Type: ApplicationFiled: November 5, 2013Publication date: May 8, 2014Applicant: Rolls-Royce Deutschland Ltd & Co KGInventors: Marco ROSE, Rene SPIEWEG
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Publication number: 20140127008Abstract: Transition ducts, hot gas path assemblies, and turbomachines are provided. A hot gas path assembly includes an outer support ring, an inner support ring, and a transition duct coupled to the outer support ring and the inner support ring. The transition duct includes a conduit defining a passage extending between an inlet and an outlet. The inlet and the outlet are generally aligned along a longitudinal axis. The transition duct further includes an airfoil disposed within the conduit and configured to alter a hot gas flow direction.Type: ApplicationFiled: November 8, 2012Publication date: May 8, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Michael Alan Davi, Khan Mohamed Khirullah Genghis Khan, Thomas Raymond Farrell
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Patent number: 8714921Abstract: A fan shroud with modular vane members for a cooling system. A plurality of modular vane set members are positioned around the inner surface of the fan shroud ring, each of the modular vane set members having a plurality of vane members. The modularity provides flexibility and versatility for the fan shroud and corresponding efficiencies in costs and manufacturing.Type: GrantFiled: February 18, 2009Date of Patent: May 6, 2014Assignee: BorgWarner Inc.Inventors: Thomas M. Tembreull, Kevin M. Taylor
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Publication number: 20140119908Abstract: A fan housing has a radially outer surface. A pair of radially intermediate surfaces includes a first surface spaced towards a first axial end, which has an inner bore positioned radially outward of an inner bore of a second surface. Vanes extend between the radially outer surface and an outer periphery of the pair of radially intermediate surfaces. A bearing bore extends radially inwardly of the first surface. A mounting lug nub is formed on an outer periphery of the radially outer surface. A first distance is defined between the first axial one end of the fan housing and an opposed axial end. A second distance is defined between the first axial end and a center of the mounting lug. A ratio of the first distance to the second distance is between 2.13 and 2.11. An intermediate part, a ram air fan and a method are also disclosed.Type: ApplicationFiled: October 31, 2012Publication date: May 1, 2014Applicant: HAMILTON SUNDSTRAND CORPORATIONInventors: Eric Chrabascz, Victoria S. Richardson, Brent J. Merritt
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Publication number: 20140119909Abstract: A fan module, disposed inside a case of an electronic device, includes a case body, a blade assembly, a stopping plate and an adjusting element. The case body, including a first case unit, a sidewall and a second case unit, forms an accommodating space. The first case unit or/and the second case unit has an air inlet. The sidewall has an air outlet and an adjusting opening. The blade assembly is disposed inside the accommodating space. The stopping plate, disposed on the sidewall, is for opening or closing the adjusting opening. The adjusting element is movably disposed on the stopping plate and for pressing against the stopping plate. When the adjusting element moves from a first position toward a second position, the adjusting element pushes against and makes the stopping plate to be offset toward the blade assembly, and produces a gap between the stopping plate and the sidewall.Type: ApplicationFiled: March 4, 2013Publication date: May 1, 2014Applicants: INVENTEC CORPORATION, INVENTEC (PUDONG) TECHNOLOGY CORPORATIONInventor: Meng-Lung Chiang
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Publication number: 20140119895Abstract: An inner bushing assembly (280) to provide a biasing force between a guide vane (260) and an inner ring half (261) of a gas turbine engine compressor (200) is disclosed. The inner bushing assembly (280) includes a first bushing (281), a second bushing (282), and a biasing element (283). The first bushing (281) is configured to be installed about an inner vane shaft (267) of the guide vane (260) adjacent to an airfoil (265) of the guide vane (260). The second bushing (282) is configured to be installed about the inner vane shaft (267) distal to the airfoil (265). The biasing element (283) is configured to be installed about the inner vane shaft (267) between the first bushing (281) and the second bushing (282).Type: ApplicationFiled: November 1, 2012Publication date: May 1, 2014Applicant: SOLAR TURBINES INCORPORATEDInventor: John Frederick Lockyer
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Publication number: 20140099516Abstract: An article comprising a substrate, the substrate having a surface; a diffusion barrier layer disposed on a portion of the surface of the substrate, a brazing layer disposed on the diffusion barrier layer, the brazing layer comprising at least one diffusible element, wherein the diffusion barrier layer inhibits the at least one diffusible element from diffusing into the diffusion barrier layer and the substrate. Also provided herein is a method of making an article comprising providing a substrate, the substrate having a surface; forming a diffusion barrier layer on a portion of the surface of the substrate, the diffusion barrier layer being formed by electro-spark deposition; forming a brazing layer on the diffusion barrier layer, the brazing layer comprising at least one diffusible element, wherein the diffusion barrier layer inhibits the at least one diffusible element from diffusing into the substrate.Type: ApplicationFiled: October 5, 2012Publication date: April 10, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Mark Lawrence Hunt, Gary Charles Shubert, Jerry Ellison Gould
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Publication number: 20140096500Abstract: An exhaust diffuser includes an outer shroud and an inner shroud radially separated from the outer shroud so as to define a fluid passage between the outer shroud and the inner shroud. A strut extends between the outer shroud and the inner shroud. The strut generally includes an outer surface, a leading edge, a trailing edge, a first side and a second side. At least one turbulator may be positioned along a radial span of the strut. The at least one turbulator extends generally outwardly from the strut outer surface. The turbulator extends across the leading edge of the strut from the first side to the second side of the strut.Type: ApplicationFiled: October 5, 2012Publication date: April 10, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Manjunath Bangalore Chengappa, Moorthi Subramaniyan, Vignesh Radhakrishnan
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Publication number: 20140093407Abstract: A hydraulic turbocharger having replaceable, insertable components, including volute inserts, vaned diffuser inserts, nozzle inserts, diffuser inserts, nozzle liners and diffuser liners, that define the internal passageways of a hydraulic turbocharger. By making various components of the turbocharger removably insertable and replaceable, turbochargers can be manufactured in a cost-effective way to maximize efficiency, obtain improved performance and make it easier to operate these types of devices over a wide range of operating conditions. Moreover, the devices can be readily modified while in the field when operating conditions change.Type: ApplicationFiled: September 20, 2013Publication date: April 3, 2014Inventors: Jeff Calkins, Bart Biche, Eric Kadaj, Prem Krish
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Publication number: 20140093367Abstract: An airfoil includes an airfoil body made of a first metal with a leading edge, a trailing edge, pressure side and suction side; a sheath with first and second flanks made of a second metal; a first layer of non-conductive material adhesively bonded between a portion of the end of the first flank and the airfoil body and extending beyond the end of the first flank on the pressure side; and a second layer of non-conductive material adhesively between a portion of the end of the second flank and the airfoil body and extending beyond the end of the second flank on the suction side.Type: ApplicationFiled: September 28, 2012Publication date: April 3, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Michael Parkin, Mark Quinn, Leland Wiegman, Brandon A. Gates
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Patent number: 8684687Abstract: A fan assembly includes a device for creating an air flow and an air outlet for emitting the air flow. The air outlet is mounted on a stand for conveying the air flow to the air outlet. The fan assembly also includes a tilt mechanism for tilting the air outlet relative to at least part of the stand. The tilt mechanism comprises a flexible hose defining, at least in part, an air passage through the tilt mechanism.Type: GrantFiled: April 30, 2013Date of Patent: April 1, 2014Assignee: Dyson Technology LimitedInventors: James Dyson, Ian John Brough
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Publication number: 20140086728Abstract: A diffuser (3) for a fan (2) of axial, radial or diagonal type of construction, has an inlet opening (10) and having an outlet opening (20) for a gaseous medium which flows through a diffuser interior (I), which is enclosed by an outer housing (30), in an axially oriented main flow direction (S) from the inlet opening (10) to the outlet opening (20). The cross section of the diffuser interior (I) increases from the cross section (11) of the inlet opening to the cross section (21) of the outlet opening (20), wherein the outer housing (30) forms an outer diffuser part (AD) which delimits the diffuser interior (I) to the outside. Along the main flow direction (S), the cross section of the outer diffuser part (AD) changes from a circular cross section (31) at the inlet opening (10) to a non-circular cross section (32) at the outlet opening (20).Type: ApplicationFiled: December 16, 2011Publication date: March 27, 2014Applicant: emb-papst Mulfingen GmbH & Co. KGInventors: Markus Engert, Erik Reichert, Oliver Haaf, Christian Pfaff, Marc Schneider, Jürgen Schöne, Katrin Bohl, Sven Beck, Dieter Best, Tobias Ehmann, Alexander Frank, Erhard Gruber, Matthias Maschke, Thomas Sauer
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Publication number: 20140086738Abstract: A nacelle for an aircraft bypass turbojet engine includes downstream, an internal stationary structure surrounding part of the bypass turbojet engine, and an external structure surrounding the internal stationary structure, defining an annular flow path along which an air flow circulates. The external structure includes a mobile flap disposed at the downstream end of the external structure and positioned facing the annular flow path. Each mobile flap can rotate such as to move into a position that increases or reduces the height of the cross-section of the annular flow path in relation to an idle position, in response to the pressure exerted on the mobile flap by the air flow circulating through the facing annular flow path. The mobile flap can return from the cross-section-increasing or -reducing position to another position under the effect of an elastic return means.Type: ApplicationFiled: December 2, 2013Publication date: March 27, 2014Applicant: AIRCELLEInventors: Nicolas DEZEUSTRE, Patrick STELLA
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Publication number: 20140086737Abstract: A disclosed structural guide vane for a gas turbine engine includes a strut defining a plurality of channels and a cover attached over the plurality of channels. The strut includes a first side defining a first surface of an airfoil and a second side including a plurality of channels. At least one of the plurality of channels defines a wall thickness of a portion of the first side that varies in a chord wise direction.Type: ApplicationFiled: December 12, 2012Publication date: March 27, 2014Applicant: United Technologies CorporationInventors: Thomas B. Hyatt, Carl Brian Klinetob, Jason Leroux
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Publication number: 20140083113Abstract: Flow control tabs for turbine sections are provided. The turbine section includes a stator assembly and a rotor assembly. The rotor assembly includes a bucket, the bucket having a shank. The rotor assembly and the stator assembly are spaced apart along a longitudinal axis and defining a flow cavity therebetween such that a cooling fluid flows therein. The flow control tab includes a mount surface configured for mounting to the stator assembly, a radially outer surface, a radially inner surface, and a leading edge. The leading edge connects the outer surface and the inner surface such that cooling fluid interacting with the leading edge is divided into an outer purge flow and an inner recirculation flow.Type: ApplicationFiled: September 27, 2012Publication date: March 27, 2014Applicant: GENERAL ELECTRIC COMPANYInventor: John Ellington Greene
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Publication number: 20140079534Abstract: A wind turbine, of the savonius wind turbine type, comprises a rotatable member extending along a longitudinal axis and a plurality of blades extending radially outwards from the rotatable member and spaced apart around the circumference thereof. The rotatable member is arranged such that, in normal use, the longitudinal axis extends in a substantially vertical direction and the blades travel around the longitudinal axis. The wind turbine further comprising a wind deflector operable to deflect wind to provide a sheltered region for the blades as they travel towards the wind and thereby substantially reducing the drag induced on the turbine.Type: ApplicationFiled: March 26, 2012Publication date: March 20, 2014Applicant: THE LIVERPOOL RENEWABLE ENERGY RESEARCH CENTREInventor: Gary Murphy
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Publication number: 20140079542Abstract: A casting mold assembly comprises an airfoil defining section and a casting core. The airfoil defining section includes an outer mold wall and a direct-shelled inner mold wall. The direct-shelled inner mold wall is disposed within a forward chordwise portion of the airfoil defining section. The direct-shelled inner mold wall includes an aft end having an external radius measuring more than about 0.075 in. (1.9 mm). The casting core is secured within an aft chordwise portion of the airfoil defining section, and includes an aft end with an external radius measuring less than about 0.075 in. (1.9 mm). A cast component and a method for making the casting mold assembly are also disclosed.Type: ApplicationFiled: September 14, 2012Publication date: March 20, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Steven J. Bullied, Carl R. Verner, Steven D. Porter, James B. Park
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Patent number: 8672622Abstract: A fluid machine includes a non-streamline casing capable of forming a stable vortex street on a downstream side by internal and external flows, and an impeller disposed inside the casing. The casing has a vortex generator configured to form the vortex street on the downstream side. The vortex generator is provided with a phase control structure which regulates a phase of a vortex formation that fluctuates along a circumferential direction in a plane including a rear face of the casing and which clarifies a cell structure to be formed along the circumferential direction of the casing to fix, on a surface of the casing, respective positions of cells into a plurality of segmented regions arranged in the circumferential direction. The velocity of the internal flow is increased by the phase control structure.Type: GrantFiled: November 5, 2008Date of Patent: March 18, 2014Assignee: Kyushu University, National University CorporationInventors: Yuji Ohya, Takashi Karasudani, Kimihiko Watanabe
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Publication number: 20140072425Abstract: A fluid pump includes an outlet for discharging fluid from the fluid pump, a housing, and a motor with a shaft that rotates about an axis. The fluid pump also includes an impeller having a first array of blades radially surrounding the axis and a second array of blades radially surrounding the first array of blades. The fluid pump also includes an inlet plate adjacent to the impeller and has an inlet for introducing fluid into the fluid pump, a first inlet plate flow channel aligned with the first array of blades and having a first inlet plate flow channel cross-sectional area, and a second inlet plate flow channel aligned with the second array of blades and having a second inlet plate flow channel cross-sectional area. The second inlet plate flow channel cross-sectional area is synchronized with the first inlet plate flow channel cross-sectional area.Type: ApplicationFiled: September 10, 2012Publication date: March 13, 2014Applicant: DELPHI TECHNOLOGIES, INC.Inventors: PARTAB JESWANI, MOHAMMED ASLAM, PHILIP M. ANDERSON
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Publication number: 20140064934Abstract: Embodiments of a diffuser vane comprise a vane body with a leading edge and a trialing edge that can rotate about the leading edge to improve performance of a compressor device. This configuration maintains the position of the leading edge on the diffuser vane relative to the orientation of the working fluid. In one embodiment, the diffuser vane incorporates a support element that couples with the vane body. The support element counteracts stimulating frequencies to reduce vibration of the vane body. The diffuser vane can also comprise an armature, which couples with a force coupler to facilitate rotation of the trailing edge when in position in a compressor device.Type: ApplicationFiled: August 31, 2012Publication date: March 6, 2014Applicant: General Electric CompanyInventor: Dale Eugene Husted