Vanes Patents (Class 415/191)
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Publication number: 20140193248Abstract: 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.Type: ApplicationFiled: January 9, 2013Publication date: July 10, 2014Applicant: GM GLOBAL TECHNOLOGY OPERATIONS LLCInventor: Donnell B. Johnson
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Patent number: 8764391Abstract: A hydrokinetic turbine system, including a plurality of hydrokinetic turbines is installed on a bed of a body of water. Each turbine has a shroud with a forward entrance portion and rear exit portion. The shroud includes a propeller disposed in a middle portion thereof. An inner surface of the shroud includes a plurality of rifling vanes formed therein to induce water entering the forward entrance portion to rotate in a vortex-like fashion. A plurality of pre-spin guard blades disposed adjacent the forward entrance portion also induce rotation of water and serve to provide a barrier preventing objects from passing into the forward entrance portion. A plurality of stabilizers extending from an exterior surface of the shroud that position the forward entrance portion in the direction of current flow.Type: GrantFiled: September 10, 2010Date of Patent: July 1, 2014Assignee: Osirius InternationalInventors: Timothy Smith, Eric Otte
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Publication number: 20140178189Abstract: 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.Type: ApplicationFiled: October 9, 2013Publication date: June 26, 2014Applicant: ZEPHYR INTERNATIONAL, INC.Inventor: Joe C. Cassidy
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Patent number: 8757967Abstract: An axial flow turbine includes in axial flow series a low pressure turbine section and a turbine exhaust system. The low pressure turbine section includes a final low pressure turbine stage having a circumferential row of static aerofoil blades followed in axial succession by a circumferential row of rotating aerofoil blades. Each aerofoil blade has a radially inner hub region and a radially outer tip region. The K value, being equal to the ratio of the throat dimension (t) to the pitch dimension (p), of each static aerofoil blade of the final low pressure turbine stage varies along the height of the static aerofoil blade, between the hub region and the tip region, according to a substantially W-shaped distribution.Type: GrantFiled: January 23, 2012Date of Patent: June 24, 2014Assignee: Alstom Technology LtdInventors: Brian Robert Haller, Gursharanjit Singh
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Patent number: 8757965Abstract: A gas turbine compression system (1) comprising a gas channel (5), a low pressure compressor section (8) and a high pressure compressor section (9) for compression of the gas in the channel and a compressor structure (14) arranged between the low pressure compressor section (8) and the high pressure compressor section (9). The compressor structure (14) is designed to conduct a gas flow in the gas channel and comprises a plurality of radial struts (15,16,21,24,25) for transmission of load, wherein at least one of the struts (15,16,21,24,25) is hollow for housing service components. The compressor structure (14) is arranged directly downstream of a last rotor (10) in the low pressure compressor section (8) and designed for substantially turning a swirling gas flow from the rotor (10) by a plurality of the struts (15,16,21,24,25) having a cambered shape.Type: GrantFiled: June 2, 2005Date of Patent: June 24, 2014Assignee: Volvo Aero CorporationInventor: Stephane Baralon
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Patent number: 8757968Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of the profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.Type: GrantFiled: June 28, 2011Date of Patent: June 24, 2014Assignee: SnecmaInventors: Jean Bleuzen, Jean-Michel Guimbard, Ludovic Pintat, Pascal Routier
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Publication number: 20140169933Abstract: A windmill is disclosed having over speed protection. In a preferred embodiment, the vanes are symmetric, curved metal sheets, with each vane's shape having a circular arc corresponding to its portion of the cylindrical support structure. Each vane is mounted with a large leading portion exposed to the wind. The imbalance of surface area causes the wind to push the vane open when moving downwind and push the vane closed when moving upwind. During periods of high rotational speed, the off-axis centers of mass cause each vane to rotate towards a closed position under centrifugal force. Once the critical speed is reached, the vanes fully close as they pass through the upwind side.Type: ApplicationFiled: December 13, 2012Publication date: June 19, 2014Inventor: Kenneth B. Lane
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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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Publication number: 20140154066Abstract: 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.Type: ApplicationFiled: December 4, 2012Publication date: June 5, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Debabrata Mukhopadhyay, Steven Sebastian Burdgick, Prashant Prabhakar Sankolli, Moorthi Subramaniyan
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Publication number: 20140154065Abstract: 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.Type: ApplicationFiled: December 3, 2012Publication date: June 5, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Prashant Prabhakar Sankolli, Steven Sebastian Burdgick
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Patent number: 8740547Abstract: A system for controlling at least two variable geometry apparatuses of a gas turbine engine that includes at least a first body and a second body, the first apparatus including a stator blade stage with a variable setting angle of a compressor of the first body capable of switching between a closed position in an idle mode and an open position in a high-speed mode, and the second apparatus including at least one discharge valve of a compressor of the second body capable of switching between an open position in an idle mode and a closed position in a high-speed mode. The system further includes an actuator for actuating the two apparatuses.Type: GrantFiled: September 29, 2009Date of Patent: June 3, 2014Assignee: SnecmaInventors: Baptiste Benoit Colotte, Bruno Robert Gaully
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Patent number: 8740557Abstract: A strut configuration of a static vane ring used in a gas turbine engine having an enlarged end section at least at one of the opposed ends thereof to be welded or brazed to either an outer or inner duct wall of the vane ring. The enlarged end section provides a inner corner curve with a predetermined fillet radius between the strut and the duct wall.Type: GrantFiled: October 1, 2009Date of Patent: June 3, 2014Assignee: Pratt & Whitney Canada Corp.Inventor: Eric Durocher
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Publication number: 20140147261Abstract: 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.Type: ApplicationFiled: October 4, 2013Publication date: May 29, 2014Applicant: Sunonwealth Electric Machine Industry Co., Ltd.Inventor: Shih-Hang Lin
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Publication number: 20140147244Abstract: A method and at least two devices demonstrate improvements to energy extraction from a compressible rotation working fluid in a liquid ring heat engine, which has a rotor mounted in a case. A space in the case is occupied by a liquid that establishes a liquid ring piston for the rotor. The rotor defines at least a first and a second operating zone. In the first zone, the working fluid is expanded against the liquid and, in the second zone, the working fluid is re-compressed. Between the two zones, the working fluid is cooled. In one device, the cooling step occurs on the rotor in a third zone. In another device, the cooling occurs outside of the case.Type: ApplicationFiled: November 23, 2011Publication date: May 29, 2014Applicant: THE OHIO STATE UNIVERSITYInventors: Codrin-Gruie Cantemir, Fabio Chiara, Marcello Canova
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Publication number: 20140147262Abstract: 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.Type: ApplicationFiled: November 27, 2013Publication date: May 29, 2014Applicant: Techspace Aero S.A.Inventor: Herve Grelin
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Publication number: 20140147260Abstract: 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.Type: ApplicationFiled: November 28, 2012Publication date: May 29, 2014Applicant: COOLER MASTER CO., LTD.Inventors: Kai-Hsiang Hu, Shiman Xu, Jiasheng Lai, Haijun He
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Patent number: 8734089Abstract: One embodiment of the present invention is a vane assembly for a gas turbine engine. Another embodiment of the present invention is a damper seal that may be employed in conjunction with a vane assembly of a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods and combinations for vane assemblies and the sealing and damping thereof. Further embodiments, forms, features, aspects, benefits and advantages of the present application shall become apparent from the description and figures provided herewith.Type: GrantFiled: December 22, 2010Date of Patent: May 27, 2014Assignee: Rolls-Royce CorporationInventor: Justin Gilman
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Patent number: 8734116Abstract: A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: November 28, 2011Date of Patent: May 27, 2014Assignee: General Electric CompanyInventors: Paul Kendall Smith, Spencer Aaron Kareff, Srinivasa Govardhan Jayana
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Patent number: 8734096Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.Type: GrantFiled: June 29, 2011Date of Patent: May 27, 2014Assignee: SNECMAInventors: Jean-Michel Guimbard, Pierre Marche, Renaud Martet, Renaud Royan
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Patent number: 8734095Abstract: A gas turbine that can effectively cool an axial cavity between a stator blade and a rotor blade and a blade-end surface is provided. In a gas turbine in which a blade-count difference between stator-blade segments of a second-stage stator blade and a third-stage stator blade is set to zero, a relative position between the second-stage stator blade and the third-stage stator blade in the circumferential direction is set by clocking so that a wake flow produced by the stator-blade segments of the second-stage stator blade is guided to the leading edges of the stator-blade segments of the third-stage stator blade within a range of 0% to 15% of the length in a span direction from a hub side of the stator-blade segments of the third-stage stator blade.Type: GrantFiled: March 16, 2010Date of Patent: May 27, 2014Assignee: Mitsubishi Heavy Industries, Ltd.Inventor: Koichiro Iida
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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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Publication number: 20140140834Abstract: 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.Type: ApplicationFiled: November 18, 2013Publication date: May 22, 2014Applicant: ABB Turbo Systems AGInventors: Matthias RICHNER, Josef BÄTTIG
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Patent number: 8727716Abstract: A turbine nozzle includes an array of turbine vanes between inner and outer bands. Each vane includes opposed pressure and suction sides extending between opposed leading and trailing edges. The vanes define a plurality of flow passages each of which is bounded between the inner band, the outer band, and adjacent first and second vanes. A surface of the inner band in each of the passages is contoured in a non-axisymmetric shape including a peak of relatively higher radial height adjoining the pressure side of the first vane adjacent its leading edge, and a trough of relatively lower radial height is disposed parallel to and spaced-away from the suction side of the second vane aft of its leading edge. The peak and trough define cooperatively define an arcuate channel extending axially along the inner band between the first and second vanes.Type: GrantFiled: August 31, 2010Date of Patent: May 20, 2014Assignee: General Electric CompanyInventors: Jeffrey Donald Clements, Vidhu Skekhar Pandey, Ching-Pang Lee
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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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Patent number: 8721272Abstract: A ring diffuser for an axial turbomachine is provided. The ring diffuser includes an outer wall and an inner wall coaxial thereto, between which a diffuser channel extends in a ring shape along an axial extension from an inflow-side end diverging to an outflow-side end, wherein the inner wall and the outer wall each include a wall surface bounding the diffuser channel. In order to specify a diffuser channel that is tailored to an inflow that is uneven along the circumference and that facilitates a particularly efficient conversion of kinetic energy into static energy, a rotationally asymmetric wall surface bounding the diffuser channel on the inlet side is provided.Type: GrantFiled: November 19, 2009Date of Patent: May 13, 2014Assignee: Siemens AktiengesellschaftInventors: Christian Cornelius, Bernhard Küsters, Ulrich Waltke
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Patent number: 8720207Abstract: A gas turbine is disclosed which includes an annular combustion chamber defined by an inner wall and an outer wall. A stator airfoil row can be defined by an annular inner stator wall and an annular outer stator wall housing a plurality of stator airfoils, and at least a rotor airfoil row defined by an annular inner rotor wall and an annular outer rotor wall housing a plurality of rotor airfoils. A gap is arranged, for example, between at least one of the inner stator wall and the inner combustion chamber wall, and the outer stator wall and the outer combustion chamber wall, upstream of said stator airfoil row. A border of at least one of the inner and outer stator wall facing the gap can be axisymmetric.Type: GrantFiled: April 30, 2010Date of Patent: May 13, 2014Assignee: Alstom Technology LtdInventors: Frank Gersbach, Christian Sommer, Willy Heinz Hofmann, Ulrich Steiger
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Patent number: 8721273Abstract: An arrangement with a ring diffuser for an axial turbomachine, for example for a gas turbine, is provided. The ring diffuser includes an outer wall and with an inner wall coaxial thereto, between which a diffuser duct extends in ring form along an axial extent so as to diverge from an inflow-side end to an outflow-side end, the inner wall and the outer wall in each case including a wall surface delimiting the diffuser duct. In order to specify a diffuser duct which is adapted to an inflow uneven along the circumference and by means of which a specially efficient conversion of kinetic energy into static energy is possible, the wall surface which delimits the diffuser duct on the inlet side is rotationally asymmetrical.Type: GrantFiled: January 17, 2012Date of Patent: May 13, 2014Assignee: Siemens AktiengesellschaftInventors: Christian Cornelius, Bernhard Küsters, Ulrich Waltke
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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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Patent number: 8714920Abstract: A turbine airfoil (31) with an end portion (42) that tapers (44) toward the end (43) of the airfoil. A ridge (46) extends around the end portion. It has proximal (66) and distal (67) sides. A shroud platform (50) is bi-cast onto the end portion around the ridge without bonding. Cooling shrinks the platform into compression (62) on the end portion (42) of the airfoil. Gaps between the airfoil and platform are formed using a fugitive material (56) in the bi-casting stage. These gaps are designed in combination with the taper angle (44) to accommodate differential thermal expansion while maintaining a gas seal along the contact surfaces. The taper angle (44) may vary from lesser on the pressure side (36) to greater on the suction side (38) of the airfoil. A collar portion (52) of the platform provides sufficient contact area for connection stability.Type: GrantFiled: April 1, 2010Date of Patent: May 6, 2014Assignee: Siemens Energy, Inc.Inventors: Christian X. Campbell, Jay A. Morrison, Allister W. James, Raymond G. Snider, Daniel M. Eshak, John J. Marra, Brian J. Wessell
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Patent number: 8718975Abstract: A method and system for accepting or rejecting a curved surface of a body under evaluation involves conducting a comparison between the curvature of a surface profile for the surface under evaluation and higher and lower curvature tolerance boundaries. The higher and lower curvature tolerance boundaries are determined from a desired surface profile. The curvature at a plurality of locations on the curve profile under evaluation may be defined with reference to a geometric variable for said curved surface and may be plotted on a graph. The higher and lower curvature tolerance boundaries may also be plotted on the graph so as to determine whether the plot of curvature for the surface under evaluation falls within the bounds of the higher and lower tolerance boundaries.Type: GrantFiled: February 24, 2010Date of Patent: May 6, 2014Assignee: Rolls-Royce, PLCInventors: Hugo M P Lobato, Ian R Gower, Christopher A Powell, Nicholas B Orchard
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Patent number: 8702384Abstract: A turbomachine component includes a compressor stator vane having an airfoil core shape. The airfoil core shape includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil core shape.Type: GrantFiled: March 1, 2011Date of Patent: April 22, 2014Assignee: General Electric CompanyInventors: Julianne Edna Baer, Umesh Garg
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Patent number: 8702385Abstract: A nozzle blade and nozzle ring assembly includes a nozzle blade having radially inner and outer sidewalls with an airfoil portion extending therebetween; the inner and outer sidewalls walls formed with axially-extending first surface features along forward and aft marginal edges of the inner and outer sidewalls, respectively; and radially inner and outer nozzle rings formed with corresponding axially-extending second surface features mated with the first surface features, wherein the radially inner and outer sidewalls are welded to the radially inner and outer nozzle rings only along the mated first and second surface features.Type: GrantFiled: May 12, 2011Date of Patent: April 22, 2014Assignee: General Electric CompanyInventors: Steven Sebastion Burdgick, Thomas Patrick Russo
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Publication number: 20140105720Abstract: The various embodiments herein provide a method and a system for controlling a nozzle area in a steam turbine. The system comprises a nozzle ring provided with a plurality of nozzle blades at an outer edge. The steam enters into the nozzle ring and jets out on the blades of the rotor disk. When there is an off design condition, the nozzle blades are plugged or opened by adding or removing the inserts. The nozzle area is increased or decreased by opening or plugging the nozzle passages manually or automatically with the help of the inserts. The embodiments herein provide a cost effective and simple solution to deal with the off design conditions.Type: ApplicationFiled: October 9, 2013Publication date: April 17, 2014Inventor: KRISHNA KUMAR BINDINGNAVALE RANGA
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Patent number: 8696309Abstract: A gas leakage seal for a turbine, including first and second cloth layers having woven warp and weft wires, wherein the first and second cloth layers are brazed together by a flux paste whereby the cloth layers have their edges aligned and the brazing substantially seals gaps between the wires along substantially the entire length and width of the brazed together cloth layers. Weld beads having a thickness greater than the combined thickness of the brazed together cloth layers connect the edges of the cloth layers along their length. The turbine includes two members with aligned recesses in which opposite of the weld beads are received. The seal is made by brushing a nickel and/or cobalt based flux paste on one side of one of the cloth layers, brazing that cloth layer to a side of the second cloth layer to substantially seal the gaps between the wires, and creating weld beads with an electron beam to connect the edges of the cloth layers along their length.Type: GrantFiled: June 27, 2011Date of Patent: April 15, 2014Assignee: Turbine Services Ltd.Inventors: Vincent T. Riggi, Jr., Barry Monshower, Justin D. Hyslop
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Patent number: 8690521Abstract: A system for controlling at least two sets of variable geometry equipment of a turbine engine. The turbine engine includes at least one first body and a second body, the first set of equipment being a stage of variable stator vanes of a compressor of the first body moving between a closed position during idling and an open position at high speed, and the second set of equipment being at least one bleed valve of a compressor of the second body moving between an open position during idling and a closed position at high speed. The actuator drives the second set of equipment by an actuating part that is actuated over part of the course of the actuator and idle on an abutment over the rest of the course, and by a sliding joining element providing a backlash in the actuation of the second set of equipment.Type: GrantFiled: September 29, 2009Date of Patent: April 8, 2014Assignee: SNECMAInventors: Baptiste Benoit Colotte, Bruno Robert Gaully
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Patent number: 8690520Abstract: A system for controlling at least two sets of variable geometry equipment of a gas turbine engine including at least one first body and a second body, the first set of equipment being a stage of variable stator vanes of a compressor of the first body moving between a closed position during idling and an open position at high speed, and the second set of equipment being at least one bleed valve of a compressor of the second body moving between an open position during idling and a closed position at high speed. An actuator actuates the two sets of equipment.Type: GrantFiled: September 29, 2009Date of Patent: April 8, 2014Assignee: SnecmaInventors: Baptiste Benoit Colotte, Bruno Robert Gaully
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Publication number: 20140093364Abstract: 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.Type: ApplicationFiled: June 8, 2012Publication date: April 3, 2014Applicant: BORGWARNER INC.Inventors: Abraham C. Narehood, Vahidin Alajbegovic, John P. Watson
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Patent number: 8678757Abstract: A compressor vane or compressor blade is provided. The axial flow compressor includes an axial direction, a radial direction, a compressor hub and a compressor casing. The vane or blade includes an airfoil with airfoil sections having a span, a chamber line and a leading edge at which the chamber line includes a leading edge blade angle with the axial direction of the compressor and a trailing edge at which the chamber line includes a trailing edge blade angle with the axial direction of the compressor. The airfoil sections are stacked at the leading edge on a straight line extending along a radial direction of the compressor from the compressor hub towards a compressor casing and in that the leading edge angles of the airfoil sections vary along the span and are larger for airfoil sections close to the hub and close to the wall than for mid-span airfoil sections.Type: GrantFiled: April 3, 2009Date of Patent: March 25, 2014Assignee: Siemens AktiengesellschaftInventor: Yan Sheng Li
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Patent number: 8672619Abstract: A vane (234) is provided which reduces leakage of gas in a variable geometry turbocharger (210) from the high pressure side of the vane (234) to the low pressure side of the vane (234). The vane (234) can have a channel (330, 430) along a gas bearing surface (325, 425) for reducing the leakage. The channel (330, 430) can be defined at least in part by sideplates (300, 350). The sideplates (300, 350) can be integrally cast with the rest of the vane (234). At least one of the sideplates (300, 350) can have a hole therein for a vane shaft (228) which allows movement of the vane (234) for gas flow control. The sideplates (300, 350) can have edges (301, 351) that conform to the shape of the gas bearing surface (325, 425).Type: GrantFiled: September 20, 2012Date of Patent: March 18, 2014Assignee: BorgWarnerInventors: Steve Roby, David M. Decker, Dietmar Metz
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Patent number: 8672620Abstract: 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 Y-coordinates.Type: GrantFiled: August 17, 2010Date of Patent: March 18, 2014Assignee: Hamilton Sundstrand CorporationInventors: David J. Zawilinski, Jeffrey M. Makulec, Matthew Slayter
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Publication number: 20140060081Abstract: A vane cluster for a gas turbine engine includes multiple singlet vanes and a forward wear liner connecting a forward edge of each singlet vane, thereby allowing the vane cluster to be manipulated as a single component.Type: ApplicationFiled: August 28, 2012Publication date: March 6, 2014Inventors: Jonathan J. Earl, Eric A. Kuehne
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Publication number: 20140064945Abstract: 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.Type: ApplicationFiled: September 4, 2012Publication date: March 6, 2014Applicant: GENERAL ELECTRIC COMPANYInventor: Michael T. Hudson
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Patent number: 8662837Abstract: A two-stage high pressure turbine includes a second stage vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.Type: GrantFiled: January 21, 2011Date of Patent: March 4, 2014Assignee: Pratt & Whitney Canada Corp.Inventor: Remo Marini
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Patent number: 8662836Abstract: An exhaust gas turbocharger, including either a variable turbine with rotatably mounted guide vanes or a compressor geometry with rotatably mounted guide vanes. At least one of the guide vanes has a profile center line with at least one of a jump and a kink.Type: GrantFiled: December 10, 2010Date of Patent: March 4, 2014Assignee: Bosch Mahle Turbo Systems GmbH & Co. KGInventors: Gunter Winkler, Florian Rentz, Tobias Dettmann
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Patent number: 8651806Abstract: An inlet housing assembly for an Air Turbine Starter includes an outer flowpath curve of an inlet flowpath defined by a multiple of arcuate surfaces in cross-section.Type: GrantFiled: August 17, 2010Date of Patent: February 18, 2014Assignee: Hamilton Sundstrand CorporationInventors: David J. Zawilinski, Jeffrey M. Makulec, Matthew Slayter
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Patent number: 8641361Abstract: Methods, apparatus, and products are disclosed for improving the airflow exiting a blower that has one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower that include: determining a rotational speed of an impeller in the blower and adjusting a position of at least one of the adjustable guide vanes in dependence upon the rotational speed of the impeller.Type: GrantFiled: April 8, 2010Date of Patent: February 4, 2014Assignee: International Business Machines CorporationInventors: Michael S. June, Jason A. Matteson, Mark E. Steinke
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Patent number: 8636466Abstract: A ferrule of a stator with blades of an axial turbomachine consists of at least two segments having the general form of an arc of a circle and intended to be arranged end to end, so as to form the ferrule, where each segment contains on its outside a plurality of openings arranged at regular distances along the general arc of the circle of the segment, into each of which fits the end of a blade of the stator. Each end of a segment possesses a section of which the profile essentially corresponds with that of the end of the corresponding blade when the segment is placed on the blades of the stator, such that the joint between two adjacent segments corresponds with the profile of the corresponding blade.Type: GrantFiled: December 10, 2009Date of Patent: January 28, 2014Assignee: Techspace Aero S.A.Inventor: Jean-François Cortequisse
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Patent number: 8621874Abstract: A coupling assembly for an engine core of a turbomachine is provided. The coupling assembly comprises a duct having a substantially circular shape and surrounding the engine core, and a plurality of coupling struts, each coupling strut extending only in a substantially vertical direction relative to the direction of gravity when the engine core is at a rest position with zero pitch and zero roll, each of the plurality of coupling struts coupling the engine core to the duct.Type: GrantFiled: August 25, 2009Date of Patent: January 7, 2014Assignee: Honeywell International Inc.Inventors: Bill Russell Watson, Max Warden
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Publication number: 20140003928Abstract: A spool for turbo machinery comprises a fluid flow path defined by an axial compressor stage adjacent to a mixed flow compressor stage to thereby provide a compression system which has a relatively high ratio of efficiency to compressor diameter.Type: ApplicationFiled: June 18, 2013Publication date: January 2, 2014Inventors: Stephen John BRADBROOK, Brian DAVIS
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Publication number: 20140003927Abstract: A blower assembly includes a housing having a blower wheel disposed therein and a pre-swirler disposed in a fluid inlet of the housing. The pre-swirler includes an array of spaced apart vanes extending radially outwardly from a central hub. The vanes extend from the hub to an outer ring that is attached to the housing of the blower assembly. The vanes are configured to cooperate with the blower wheel to minimize a noise, a vibration, and a harshness (NVH) of the blower assembly, while maximizing an efficiency thereof.Type: ApplicationFiled: March 14, 2013Publication date: January 2, 2014Applicant: VISTEON GLOBAL TECHNOLOGIES, INC.Inventor: Jayanthi Iyer