Vanes Patents (Class 415/191)
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Patent number: 6908279Abstract: A wedge-like nozzle radial loading pin, preferably formed from steel, that contacts the bottom of a reaction nozzle along a graduated, that is inclined or stepped, surface. This contact will secure the reaction nozzle radially inward against the retaining surface of the carrier dovetail with sufficient force to maintain the designed airfoil pre-twist.Type: GrantFiled: November 25, 2003Date of Patent: June 21, 2005Assignee: General Electric CompanyInventors: Christopher Walter Sullivan, David Orus Fitts, Robert James Bracken, Gregory Lee Landry
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Patent number: 6905307Abstract: The stator vane is provided with a leading edge which is cut into a different depth in dependence on a span-wise position so that a blade inlet angle may vary along a span-wise direction according to a prescribed pattern. By thus optimizing the depth of the cut along the leading edge of the stator vane, the leading edge blade inlet angle can be optimized along the entire length of the stator vane even if the stator vane consists of a two-dimensional aerofoil, and the vane is provided with a substantially conformal cross section in parts which are not affected by the cut in the leading edge. Thereby, the efficiency of the turbine can be optimized while minimizing the cost.Type: GrantFiled: August 8, 2002Date of Patent: June 14, 2005Assignee: Honda Giken Kogyo Kabushiki KaishaInventors: Satoshi Kawarada, Tsuneharu Kushida, Kenji Kawamoto, Hakaru Takamatsu, Atsukuni Waragai
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Patent number: 6901821Abstract: An assembly for preventing rotation of a damper in a stator system includes a slot in the damper and a block for engaging the slot to prevent rotation of the damper. The block is positioned within a groove located at a mid span portion of an inner air seal.Type: GrantFiled: November 20, 2001Date of Patent: June 7, 2005Assignee: United Technologies CorporationInventors: Mark A. Torrance, David P. Dube
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Patent number: 6887041Abstract: The third stage nozzle has an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein X and Y values are in inches and define airfoil profile sections at each distance Z and Z is a non-dimensional value from 0 to 1 convertible to Z distances in inches by multiplying the Z values of Table I by a height of the airfoil in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape. The X and Y distances may be scalable to provide a scaled-up or scaled-down airfoil for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.100 inches.Type: GrantFiled: March 3, 2003Date of Patent: May 3, 2005Assignee: General Electric CompanyInventors: Robert Wayne Coke, James Bernard Fehlberg, Charles Andrew Malinowski
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Patent number: 6887040Abstract: A turbine blade/vane includes a profiled blade/vane aerofoil, which extends along a blade/vane axis to be capable of absorbing high thermal and mechanical loading, on the one hand, and to ensure a comparatively economical consumption of coolant, on the other. For this purpose, the blade/vane aerofoil includes, integrally formed on it, a hot-gas platform extending transversely to the blade/vane axis and, above it, a load platform. A mechanical connection between the load platform and the hot-gas platform occurs exclusively by way of the blade/vane aerofoil.Type: GrantFiled: January 17, 2003Date of Patent: May 3, 2005Assignee: Siemens AktiengesellschaftInventors: Iris Oltmanns, Peter Tiemann
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Patent number: 6884030Abstract: A method for securing a nozzle for a turbine is provided. The nozzle includes an airfoil having a suction side and a pressure side connected at a leading edge and a trailing edge such that a cooling cavity is defined within the airfoil, the airfoil extending between an inner band and an outer band. The method includes extending at least one member through the airfoil, and at least one of the inner band and the outer band. The method further includes securing the nozzle assembly in position with at least one fastener such that the at least one member is coupled adjacent to at least one of the inner band and the outer band.Type: GrantFiled: December 20, 2002Date of Patent: April 26, 2005Assignee: General Electric CompanyInventors: Toby George Darkins, Jr., Daniel Gene Dunn, Christopher Grace, Gregory Scot Corman, Mark Stewart Schroder
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Patent number: 6884029Abstract: A vortex-reducing fluid guide component is disclosed. The fluid guide component includes a base portion and an upstanding body portion. An internally-cooled blending element extends between the base portion and a leading edge of the body portion. The blending element includes a deflection region that advantageously disrupts horseshoe vortex formation. The fluid guide component includes a supplemental cooling channel between the blending element and the intersection of the body portion leading edge and the base portion. In one embodiment, the supplemental cooling channel captures cooling fluid used to cool the blending member and provides additional cooling to the body portion leading edge/base interface. The component includes a strategically-perforated impingement panel or member that distributes cooling fluid to selected portions of the blending member, thereby ensuring that key regions within the blending member are efficiently cooled in accordance with temperature distribution.Type: GrantFiled: September 26, 2002Date of Patent: April 26, 2005Assignee: Siemens Westinghouse Power CorporationInventor: Alexander Ralph Beeck
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Patent number: 6866477Abstract: The third stage nozzle has an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein X and Y values are in inches and define airfoil profile sections at each distance Z and Z are non-dimensional values within a range from 0.1 to 0.9 convertible to Z distances in inches by multiplying the Z values of Table I within the range by a height of the airfoil in inches. The profile sections at the Z distances are joined smoothly with one another to form the nozzle airfoil shape. The X and Y distances may be scalable to provide a scaled-up or scaled-down airfoil for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.160 inches.Type: GrantFiled: July 31, 2003Date of Patent: March 15, 2005Assignee: General Electric CompanyInventors: Brian Peter Arness, Robert Romany By, Gunnar Leif Siden, Poornathresan Krishnakumar, Bruce Loren Smith, Peter Christopher Selent
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Patent number: 6866474Abstract: Acoustic vibrations generated by von Karman vortex streets are reduced by shaping members interposed in moving air flowstreams, such as fan guards and grilles used in forced flow air conditioning systems, to have either a cylindrical cross section or a non-cylindrical cross-section with non-linear or interrupted leading or trailing edges presented to the air flowstream. Relatively flat rectangular cross-section members with interrupted or non-linear leading or trailing edges formed by somewhat sawtooth or sinusoidal wave forms or connected to spaced apart support members, or cylindrical members formed in the shape of a sawtooth or sinusoidal wave form, or presented with spaced apart rings or grooves interrupting the cylindrical cross-section of the member are typical configurations which exhibit reduced or substantially eliminated acoustic vibrations caused by von Karman vortex shedding.Type: GrantFiled: January 27, 2003Date of Patent: March 15, 2005Assignee: Lennox Industries, Inc.Inventor: Robert B. Uselton
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Patent number: 6854272Abstract: An exhaust gas turbocharger for an internal combustion engine, which has an exhaust gas turbine in the exhaust system and a compressor in the induction system, comprises a variable turbine geometry, associated with the turbine, for adjustably setting a radial inlet cross section for the flow to the turbine rotor. The variable turbine geometry is configured as a guide cascade ring, which has guide vanes distributed over the periphery and encompasses the turbine rotor. The minimum distance between two adjacent guide vanes obeys a specified relationship with respect to the diameter of the turbine rotor and the number of guide vanes of the guide cascade ring. In addition, a flow edge is provided on the radially inner surface of each guide vane.Type: GrantFiled: October 30, 2002Date of Patent: February 15, 2005Assignee: DaimlerChrysler AGInventors: Helmut Finger, Lothar Lenke, Erwin Schmidt, Siegfried Sumser
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Patent number: 6848884Abstract: An object of the present invention is to reduce the adverse effect of interference between stationary blades and moving blades on the performance of an axial-flow turbine and to provide a high-performance turbine stage. Each of the stationary blades has a trailing edge convex toward a face side with respect to a radial line radially extending from the axis of the rotor shaft, and the each of the moving blades has a blade center-of-gravity line convex toward the face side with respect to a radial line radially extending from the axis of the rotor shaft, and shapes of the stationary blades and the moving blades meet conditions expressed by: 1<?nr/?nt 1<?bt/?br where, ?nt and ?nr are angles between the stationary blade tip and the stationary blade root, and radial lines, and ?bt and ?br are angles between the blade center-of-gravity line of the moving blade at the tip of the same, and the blade center-of-gravity line of the moving blade at the tip of the moving blade, and radial lines.Type: GrantFiled: February 9, 2001Date of Patent: February 1, 2005Assignee: Kabushiki Kaisha ToshibaInventor: Sakae Kawasaki
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Patent number: 6845558Abstract: This is a method for fabricating non rotating stator vanes that can be configured into a fixed stator vane or dam by forming a plurality of circumferentially spaced vanes extending from the peripheral edge(s) of an annular portion which portion is sacrificial in that after assembly it is removed. Assembling the vanes so that they are sandwiched between side plates and securing them in place. Thereafter removing the sacrificial portion. In one embodiment the vanes can be on the outer peripheral edge, in another embodiment the vanes can be on the inner peripheral edge or in a third embodiment the vanes can be on both edges. After assembly the fluid flowing between vanes are bounded by the side faces of the side plates. Hence in operation, fluid is bounded by adjacent vanes and the side plates. The vanes/side plates made by this method can also be formed in a linear configuration.Type: GrantFiled: August 27, 2003Date of Patent: January 25, 2005Assignee: Elliott Energy Systems, Inc.Inventor: William F. Beacom
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Patent number: 6837679Abstract: A gas turbine engine has, in a cross section in the axial direction of an annular inner peripheral wall connected to a blade main body of a turbine blade, a concave part and a convex part on the front edge side and the rear edge side. The concave part has a negative curvature and is concave toward the axis, and the convex part has a positive curvature and is convex away from the axis. The flow rate on the upper face of the blade main body can be reduced in the concave part on the front edge side, thus suppressing generation of a shock wave, and the flow rate can be increased in the convex part on the rear edge side following the concave part, thus smoothly changing the flow rate on the upper face of the blade main body and thereby minimizing the pressure loss. In this way, the thickness of the blade main body can be reduced while ensuring the performance of the gas turbine engine, thereby contributing to a reduction in weight.Type: GrantFiled: December 22, 2000Date of Patent: January 4, 2005Assignee: Honda Giken Kogyo Kabushiki KaishaInventors: Satoshi Kawarada, Toyotaka Sonoda
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Patent number: 6834500Abstract: In a turbine for an exhaust gas turbocharger including a turbine wheel with a number of turbine wheel blades supported in a housing, which defines a first radial inlet flow channel and which includes in the radial inlet flow channel a variable guide vane structure for guiding exhaust gas radially onto the turbine wheel, and a second, semi-axial, flow channel for guiding exhaust gas semi-axially to the turbine wheel, the turbine wheel blades are arranged and sized so as to define between circumferentially adjacent blades, a flow passage with a flow cross-section which has a minimum at its inlet end.Type: GrantFiled: June 20, 2003Date of Patent: December 28, 2004Inventors: Siegfried Sumser, Erwin Schmidt, Stephan Schenkel
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Publication number: 20040253095Abstract: An assembled nozzle diaphragm according to the present invention includes a diaphragm outer ring 15 having a groove 23 opened toward an inner diameter side to be continuous in an inner peripheral direction of the diaphragm outer ring 15; a diaphragm inner ring 16 having a groove 28 opened toward an outer diameter side to be continuous in an outer peripheral direction of the diaphragm inner ring 16; and a nozzle blade 14 having a diaphragm outer ring insertion portion 12 on one end and a diaphragm inner ring insertion portion 13 on the other end, in which the groove 23 opened toward the inner diameter side of the diaphragm outer ring 15 and the diaphragm outer ring insertion portion 12 of the nozzle blade 14 are shaped to be fitted to each other only in a circumferential direction of each of the groove 23 and the diaphragm outer ring insertion portion 12, and in which the groove 28 opened toward the outer diameter side of the diaphragm inner ring 16 and the diaphragm inner ring insertion portion 13 of the nozzType: ApplicationFiled: July 1, 2004Publication date: December 16, 2004Inventors: Takashi Sasaki, Yuji Nakama, Kenichi Imai
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Publication number: 20040253096Abstract: An exhaust diffuser unit for a gas turbine engine comprises an outer ring 2, a diffuser cone 4 and vanes 8, all made from a ceramic matrix composite material. Each vane has end components 24, 26 which have apertures 36, 38 through which a metallic support strut 40 extends. The support strut 40 is rigidly secured at its radially outer end to a diffuser casing 10, and is slidably but non-rotatably received at its radially inner end in an aperture 48 in a boss 50 provided on a drum 18. Structural loads between the casing 10 and the drum 18 are transferred through the strut 40 independently of the vane 8. Gas loads on the vane 8 are transferred to the strut 40 by way of metallic end components 24, 26.Type: ApplicationFiled: June 4, 2004Publication date: December 16, 2004Applicant: ROLLS-ROYCE plcInventor: David Thomas Legg
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Patent number: 6824356Abstract: A device which can be utilized to temporarily seal substantially any opening on a turbine which is being assembled or repaired. The foreign material exclusion device includes a main body, preferably formed from a foamed polymer or rubber. The foreign material exclusion device is substantially elastic or resilient and can be compressed to fit into a desired opening and can be reexpanded to provide a snug fit about an opening. An extraction member is connected to the main body and is preferably utilized to remove the device from a portion of a cavity of a turbine.Type: GrantFiled: December 16, 2002Date of Patent: November 30, 2004Assignee: Advanced Pneumatics Inc.Inventors: Thomas Joseph Nolfi, Mario Michael Nolfi, Stephen William Orosz
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Patent number: 6821087Abstract: A flow-rectifying member comprising a plurality of vanes, an outer platform and an inner platform for having a flow-rectifying function to a fluid flowing thereinto, which is integrally constituted by annularly connecting a plurality of flow-rectifying member units each having an integral structure comprising a vane, an outer platform piece and an inner platform piece, with the adjacent outer platform pieces connected to each other, and with the adjacent inner platform pieces connected to each other; each flow-rectifying member unit comprising (a) a core comprising a web constituting the vane, and flanges integrally connected to both ends of the web for constituting the outer platform piece and the inner platform piece, and (b) a skin layer covering a surface of the core; and the skin layer being made of a rubber or a thermosetting resin having rubber elasticity.Type: GrantFiled: January 21, 2003Date of Patent: November 23, 2004Assignee: Honda Giken Kogyo Kabushiki KaishaInventors: Keizo Matsumoto, Hiroichi Fukuda, Yasuhisa Tateoka
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Patent number: 6811373Abstract: The present invention provides a turbine moving blade, a turbine stationary blade, and a turbine split ring which are capable of restraining the deterioration and peeling-off of a thermal barrier coating easily and surely, and a gas turbine capable of enhancing the energy efficiency by increasing the temperature of combustion gas. The turbine moving blade provided in a turbine constituting the gas turbine includes a platform having a gas path surface extending in the combustion gas flow direction, and a blade portion erecting on the platform. The thermal barrier coating covering the gas path surface is formed so as to go around from the gas path surface to an upstream-side end face and a downstream-side end face of the outer peripheral faces of the platform.Type: GrantFiled: February 8, 2002Date of Patent: November 2, 2004Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Yasuoki Tomita, Shigehiro Shiozaki, Kengo Yamaguchi, Hideaki Kaneko, Kotaro Ohshima
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Patent number: 6808364Abstract: A method enables a variable vane assembly for a gas turbine engine including a casing to be assembled. The variable vane assembly includes a seal assembly and at least one variable vane that includes a platform and a trunnion, wherein the platform extends outwardly from the trunnion. The method comprises coupling a seal assembly journal bushing to the variable vane such that the journal bushing is against the trunnion and between the trunnion and the engine casing, and wherein the journal bushing has a substantially constant diameter extending between a first and a second end of the journal bushing, and positioning a substantially flat first washer on the variable vane ledge to prevent contact between the variable vane assembly and the engine casing.Type: GrantFiled: December 17, 2002Date of Patent: October 26, 2004Assignee: General Electric CompanyInventors: Daniel Padraic O'Reilly, Thomas Carl Mesing, William Terence Dingwell
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Patent number: 6796765Abstract: A method for installing an expandable stiffener includes providing an assembly including a first sidewall and a second sidewall connected at a leading and trailing edge such that a cavity is defined therebetween, forming an opening extending through the first sidewall and the second sidewall, inserting a first expandable sleeve through the assembly opening such that the sleeve extends between the first and second strut sidewalls, and coupling the sleeve to the first and second sidewalls.Type: GrantFiled: December 27, 2001Date of Patent: September 28, 2004Assignee: General Electric CompanyInventors: Russell Dean Kosel, Paul Bernard Stumbo, Arshad Rehman
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Publication number: 20040184912Abstract: A housing (21) comprises an outer casing (22) provided with bearer hooks (24) for stator rings (26) and sealing rings(27); hooks (24) are discontinuous angularly and joined to casing (22) by tenon and mortise assemblies (28,29). The hooks and the casing may therefore be made in different materials, the hook material having good resistance to heating and the other material lending itself better to machining and forming. Ventilation, clearance piloting and heat protection are facilitated.Type: ApplicationFiled: February 20, 2004Publication date: September 23, 2004Inventors: Francois Crozet, Daniel Didier, Christian Ducrocq, Sebastien Imbourg, Laurent Palmisano, Jean-Marc Rongvaux, Andre Verbrugge
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Patent number: 6779973Abstract: The pressure ratio &Dgr;P4S of a final stage moving blade is reduced. As a result, the Mach number in the final stage moving blade can be suppressed, and in the gas turbine operating at a pressure ratio of 20 or more, therefore, decline of turbine efficiency due to shock wave loss can be prevented securely.Type: GrantFiled: December 6, 2001Date of Patent: August 24, 2004Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Eisaku Ito, Kazuo Uematsu
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Patent number: 6773229Abstract: A turbine nozzle is disclosed having a nozzle blade with an inner band, wherein the inner band has a region to receive a nozzle cover plate and at least one raised angel wing seal land section proximate a side of the recess; the nozzle cover plate is seated on the region of the inner band and the plate has a raised angel wing seal land section aligned with the at least one raised angel wing seal land section on the inner band, wherein the perimeter of the nozzle cover is welded to the inner band; a slot in the angel wing seal land is adjacent the perimeter of the cover plate, and the slot is filled with an insert after the cover plate is welded to the nozzle inner band.Type: GrantFiled: March 14, 2003Date of Patent: August 10, 2004Assignee: General Electric CompanyInventors: Gary Michael Itzel, Robert Henry Devine, II, John Alan Eastman, Charles Lewis Davis, III
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Publication number: 20040120810Abstract: A method facilitates assembling a turbine nozzle for a gas turbine engine. The method includes providing a turbine nozzle including a plurality of airfoil vanes that extend between an inner band and an outer band, and forming a compound radii fillet that extends between a first of the airfoil vanes and the outer band, such that at least a second of the airfoil vanes is coupled to the outer band only by a single radii fillet.Type: ApplicationFiled: December 20, 2002Publication date: June 24, 2004Inventors: Gulcharan S. Brainch, William Miller, Richard W. Albrecht, David B. Stewart, Todd Stephen Heffron
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Publication number: 20040120811Abstract: A method for securing a nozzle for a turbine is provided. The nozzle includes an airfoil having a suction side and a pressure side connected at a leading edge and a trailing edge such that a cooling cavity is defined within the airfoil, the airfoil extending between an inner band and an outer band. The method includes extending at least one member through the airfoil, and at least one of the inner band and the outer band. The method further includes securing the nozzle assembly in position with at least one fastener such that the at least one member is coupled adjacent to at least one of the inner band and the outer band.Type: ApplicationFiled: December 20, 2002Publication date: June 24, 2004Inventors: Toby George Darkins, Daniel Gene Dunn, Christopher Grace, Gregory Scot Corman, Mark Stewart Schroder
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Patent number: 6752592Abstract: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner bands of the nozzle segments on a lower pressure side of the chordal hinge seals. To minimize or prevent leakage flow across the chordal hinge seals, a generally U-shaped supplemental seal having reversely folded U-shaped marginal portions is received in a cavity formed in the axially extending sealing surface of the inner rail of the nozzle segment. At operating conditions, the marginal portions seal against the base of the cavity and the annular sealing surface of the nozzle support ring to prevent leakage flow past the chordal hinge seal from entering the hot gas path.Type: GrantFiled: December 28, 2001Date of Patent: June 22, 2004Assignee: General Electric CompanyInventors: Abdul-Azeez Mohammed-Fakir, Mahmut Faruk Aksit, Ahmad Safi, Srikanth Vedantam, Ning Fang
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Patent number: 6742988Abstract: Upper and lower diaphragms of a steam turbine have mating flanges forming a horizontal midline joint interface. Each flange has a groove which registers with a corresponding groove in the opposite flange. A composite woven tubular seal is provided in the mating grooves. The seal comprises an inner woven metal core surrounded by an annular silica fiber layer, in turn surrounded by a metal foil with an outer protective covering of a braided stainless steel. Upon joining the diaphragms to one another, the compliant seal generally conforms to a maximum to the shape of the grooves, maintaining a seal between the diaphragms along the horizontal midline joint.Type: GrantFiled: October 30, 2002Date of Patent: June 1, 2004Assignee: General Electric CompanyInventors: Kamlesh Mundra, John Cao, Daniel R. Predmore, Abdul-Azeez Mohammed-Fakir, Gene Palmer, Jonathan Munshi
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Patent number: 6742987Abstract: A turbine nozzle includes a row of vanes in corresponding segmented outer and inner bands. The inner band of each segment includes a retention flange. A nozzle support includes forward and aft flanges defining a retention slot receiving the retention flange. The retention flange includes a radial lug trapped axially in the retention slot, and a tangential lug at an opposite circumferential end disposed on the forward flange. The aft flange includes an outer hinge, and the retention flange further includes an inner hinge for cradle mounting the retention flange in the nozzle support.Type: GrantFiled: July 16, 2002Date of Patent: June 1, 2004Assignee: General Electric CompanyInventors: Victor Hugo Silva Correia, Robert Alan Jacobson
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Patent number: 6739832Abstract: The exhaust turbocharger includes an exhaust gas turbine and a turbine casing, in which is formed the volute inlet flow duct which starts with an inlet connection. An exhaust gas flow is carried to the exhaust gas turbine in this duct. The turbocharger also includes a flow straightener, which is arranged in the inlet connection and guides the exhaust gas flow in the volute direction of the inlet flow duct.Type: GrantFiled: March 26, 2002Date of Patent: May 25, 2004Assignee: ABB Turbo Systems AGInventors: Andreas Hansen, Reto Meier, Pierre Chappuis
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Patent number: 6736599Abstract: The first stage nozzles have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table 1. The X and Y values are in inches and the Z value is non-dimensional along the nozzle-stacking axis coincident with a turbine radius and convertible to a Z distance in inches from the turbine axis by multiplying the Z value by the height of the airfoil and adding the root radius to the result. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.160 inches.Type: GrantFiled: May 14, 2003Date of Patent: May 18, 2004Assignee: General Electric CompanyInventors: Curtis John Jacks, Craig Allen Bielek, Robert Walter Coign, Randall Gill
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Patent number: 6733234Abstract: A biased, wear resistant seal assembly for sealing gas flow paths in a turbine system includes a planar shim having transverse legs at each end, a flattened leaf spring to urge the shim into sealing contact with the sealing surfaces of the turbine parts, and a shim protection material to avoid wear to the shim on the contact side. The shim protection material can include one or more metal fiber cloth layers secured to the shim, for example, by seam welding to a pair of rails or to the legs of the shim.Type: GrantFiled: September 13, 2002Date of Patent: May 11, 2004Assignee: Siemens Westinghouse Power CorporationInventors: Hubertus E. Paprotna, Michael J. Morrision
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Publication number: 20040086382Abstract: The invention relates to an axial compressor stator for a gas turbine, said stator comprising a rigid, external, annular frame (2), furthermore axially juxtaposed rings (4a, 4b, 4c) configured within the frame (2) and bearing annuli of stationary vanes (5), said rings being constituted by arcuate segments (7) affixed to the frame, the inside walls of said arcuate segments externally defining the aerodynamic conduit for the compressed gaseous fluid, and this invention is characterized in that the arcuate segments (2) are brazed segments consisting of a honeycomb component (8) sandwiched between an inner sheetmetal (10) bounding the aerodynamic conduit and an outer sheetmetal (9), and in that the connection to the frame (2) is solely implemented by the outer sheetmetal (9).Type: ApplicationFiled: December 9, 2003Publication date: May 6, 2004Inventors: Stephane Caron, Pierre Debeneix, Philippe Guerout
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Patent number: 6726445Abstract: A low noise fan stationary blade, wherein a negative lean angle &thgr;L in the reverse direction of a rotating direction is provided near a hub and a positive lean angle &thgr;L in the rotating direction is provided on the other tip side, the negative lean angle &thgr;L is −10°±3° in a high loss area near the hub and the positive lean angle &thgr;L is 30°±3° on the tip side, a positive sweep angle &thgr;s is provided, and the positive sweep angle &thgr;s is 20°±3° on the hub side and 20°±3° also on the tip side, whereby a total pressure loss on both hub and tip sides can be reduced, noise can be reduced on both hub and tip sides, and thus noise can be reduced without lowering an aerodynamic performance.Type: GrantFiled: August 28, 2002Date of Patent: April 27, 2004Assignee: Ishikawajima-Harima Heavy Industries Co., Ltd.Inventors: Naoki Tsuchiya, Ryou Umeyama, Dai Kato
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Patent number: 6719528Abstract: In a stator vane arrangement including a plurality of stator vanes axially opposing a plurality of rotor vanes in rotating machinery, each stator vane is tilted with respect to a radial line so that the load acting on the hub end of each stator vane is reduced and a secondary flow is minimized. This allows the aspect ratio of each stator vane to be reduced, and the number of stator vanes to be reduced without impairing the efficiency of the rotating machinery. This in turn allows the frequency of the oscillator force produced by the stator vane in relation with the motion of the rotor vanes to be lowered so that a resonant condition of the stator vanes can be avoided relatively easily.Type: GrantFiled: October 1, 2002Date of Patent: April 13, 2004Assignee: Honda Giken Kogyo Kabushiki KaishaInventors: Naoki Kuno, Gensuke Hoshino, Shuichi Honda, Toyotaka Sonoda
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Publication number: 20040067131Abstract: A vane cluster for a turbine engine compressor or turbine includes a shroud 12 with a nonlinear slot 26 extending therethrough to divide the shroud into thermally independent shroud segments 24. The slot is bordered by matching nonlinear surfaces 28 that are easy and inexpensive to produce with conventional wire EDM equipment. The nonlinear profile of the slots effectively resists fluid leakage.Type: ApplicationFiled: October 8, 2002Publication date: April 8, 2004Inventor: Frederick R. Joslin
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Patent number: 6715987Abstract: Stator blading (10) of return channels for two-dimensional centrifugal stages of a multi-stage centrifugal compressor with improved efficiency, of the type comprising a plurality of blades (20) disposed circumferentially equally spaced on a ring (12) which surrounds a rotor of the compressor, these blades (20) each having a cross-section in the shape of a half-moon formed by a concave area (21) and a convex area (22), these concave (21) and convex (22) areas being connected to one another such as to determine a trailing edge (24) and a leading edge (23) on an inner radius (R); the profile of the concave area (21) of each blade (20) is produced by connecting to one another points which have particular Cartesian co-ordinates relative to a system of axes which are at right-angles to one another, of x-co-ordinates (X) and y-co-ordinates (Y) with an origin (O) located on the axis of rotation.Type: GrantFiled: October 15, 2002Date of Patent: April 6, 2004Assignee: Nuovo Pignone Holding S.p.A.Inventors: Eugenio Rossi, Antonio Pelagotti
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Publication number: 20040062636Abstract: A crack-resistant vane segment assembly member for an industrial turbine engine is disclosed. The vane segment includes at least one internally-cooled body portion and inner and outer shroud portions. The body portions include end regions characterized by blending and transition zones that ensure heat is transferred at a non-crack-inducing rate from the shroud portions to the body portions. The vane segment assembly also includes a cooling arrangement that reduces the impact of thermal gradient-induced stresses acting at the interface between the body portions and shroud portions. The cooling arrangement cooperates with the transition and blending zones to produce synergistically-enhanced crack resistance properties.Type: ApplicationFiled: September 27, 2002Publication date: April 1, 2004Inventors: Stefan Mazzola, Keith L. Nickols, Friedrich Rogers, W. David Day, Kelly M. Flannery
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Patent number: 6709228Abstract: A compound vacuum pump comprising at least one turbo-molecular stage and downstream therefrom a multi-channel molecular drag stage, a first inlet through which fluid can pass through the turbo-molecular stage and the molecular drag stage towards a pump outlet, a second inlet through which fluid can enter the pump at a location between the turbo-molecular and the molecular drag stages to pass only through the molecular drag stage towards the pump outlet, in which one or more channels of the molecular drag stage are adapted to communicate directly with the second inlet whilst the remaining channel or channels communicate with the turbo-molecular stage.Type: GrantFiled: October 15, 2002Date of Patent: March 23, 2004Assignee: The BOC Group plcInventor: Martin Nicholas Stuart
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Patent number: 6705832Abstract: A turbine includes a sealing element with a receiving area for sealing the guide blade vanes which are adjacent to each other in the peripheral direction of the turbine. The foot plates of the guide blade vanes extend into the receiving area. The edge area of the foot plates does not have to be reinforced compared to a conventional seal, which enables the entire foot plate to be cooled homogeneously. A closed cooling system can therefore be used for cooling, especially with steam.Type: GrantFiled: August 30, 2002Date of Patent: March 16, 2004Assignee: Siemens AktiengesellschaftInventor: Peter Tiemann
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Patent number: 6702549Abstract: A turbine installation, especially a gas turbine installation, includes foot plates of the guide blades of adjacent turbine stages being interconnected with a clip-type sealing element on their rear sides facing away from the gas area. This provides a simple seal between adjacent foot plates which is effective regardless of the thermal expansion of the foot plates. The clip-type sealing element is also suitable for sealing the tiles of a combustor of the turbine installation together.Type: GrantFiled: August 29, 2002Date of Patent: March 9, 2004Assignee: Siemens AktiengesellschaftInventor: Peter Tiemann
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Patent number: 6692318Abstract: The present invention relates to propulsion and hydraulic systems having a co-axial design wherein the inlet section, impeller section, and outlet section of a mixed flow pump system all have a common centerline axis or axis of rotation. The mixed flow pump system includes an outer casing and a central body disposed co-axially within the outer casing. A pump impeller is rotatably connected to the central body for imparting hydraulic energy to the fluid flowing through the mixed flow pump system. The mixed flow pump system may also include inlet flow conditioning vanes for conditioning an inlet flow of fluid to the mixed flow impeller for improving the cavitation performance and/or acoustic performance of the pump module. Stator vanes are provided for connecting the central body to the outer casing and to remove any swirl velocity from the fluid flow exiting the mixed flow pump impeller.Type: GrantFiled: June 7, 2002Date of Patent: February 17, 2004Assignee: The Penn State Research FoundationInventor: Mark W. McBride
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Patent number: 6685429Abstract: A method of prestressing a component (30) includes the use of an electrical discharge or current to produce a plasma (39) within a medium (32) located adjacent the component (30). The plasma generates a shock wave which impacts a surface of the component to produce a region of compressive residual stress within the component.Type: GrantFiled: September 12, 2001Date of Patent: February 3, 2004Assignee: Rolls-Royce plcInventor: John R Webster
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Patent number: 6682301Abstract: A transonic turbine blade. Expansion waves are generated by a lifting surface on the blade. The expansion waves extend downstream, through a shock generated at the trailing edge of an adjacent blade. The invention increases the strength of the shock, thereby attenuating the expansion waves passing through the shock. One stratagem for increasing the shock is to reduce the aerodynamic load of the trailing edge generating the shock.Type: GrantFiled: October 5, 2001Date of Patent: January 27, 2004Assignee: General Electric CompanyInventor: Craig Miller Kuhne
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Patent number: 6682300Abstract: The invention pertains to a seal element (1) for sealing a gas-path leakage-gap (5) between spaced apart first and second components (2,3) of a turbo machinery (22), which first and second components (2,3) having opposing inner and outer surfaces (9, 10) situated outside the leakage-gap (5). The seal element (1) comprises a generally gas impervious sealing member (4) and a layer (6) comprising ceramic fibers. The layer (6) covers at least partially said sealing element (1) and defines a sealing surface (21) for contacting outside the gap (5) the outer surfaces (10) of the first and second components (2,3) of the turbo machinery (22).Type: GrantFiled: April 4, 2002Date of Patent: January 27, 2004Assignee: Siemens AktiengesellschaftInventor: Hans-Thomas Bolms
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Patent number: 6676373Abstract: A part is used that constitutes a platform web and that has a shape close to the shape of the platform with an inside face and an outside face that are opposite each other. Fiber reinforcement plies are draped on a blade core and at least some of these plies extend beyond an end of the blade that is to be connected to the platform so as to form ply extensions. The ply extensions are folded down against the inside and outside faces of the platform to form flaps securing the blade to the platform, and fiber reinforcement plies are draped around the platform web and over the flaps so as to form a platform box retaining the flaps.Type: GrantFiled: November 27, 2001Date of Patent: January 13, 2004Assignee: SNECMA MoteursInventors: François Marlin, Cyrille Mathias, François Ribassin
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Patent number: 6676378Abstract: A turbomachine stator flap including a structural beam which is formed integrally with a structural core for a vane, and fastening portions, and a composite envelope surrounding the structural core and forming at least the aerodynamic profile of the vane.Type: GrantFiled: December 10, 2001Date of Patent: January 13, 2004Assignee: SNECMA MoteursInventors: Claude-Gaston Corbin, Jean-Marie Le Francois, Cyrille Mathias
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Patent number: 6672832Abstract: A turbine includes a row of blades each having an integral airfoil, platform, and dovetail. Each platform has opposite first and second side edges corresponding with the opposite pressure and suction sides of the airfoil. The platform first side edge is radially higher than the platform second side edge continuously between opposite forward and aft edges of the platform. In this way, adjacent platforms define a down step therebetween for preventing obstruction of combustion gases flowable downstream thereover.Type: GrantFiled: January 7, 2002Date of Patent: January 6, 2004Assignee: General Electric CompanyInventors: Leslie Eugene Leeke, Sean Robert Keith, Lawrence Paul Timko
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Patent number: 6663342Abstract: Disclosed is a composite heat-dissipating system and its used fan guard which can impart a supercharging function to the heat-dissipating fans of the composite heat-dissipating system for efficient heat dissipation and reduces the noise generated when the heat-dissipating fans are operated. The fan guard includes a frame and a set of guard blades arranged inside and fixed onto an inner surface of the frame. The fan guard can be arranged upstream or downstream of the rotor blades of the heat-dissipating fans and assembled with the heat-dissipating fans in series or in parallel to supercharge the airflow out of the heat-dissipating fans.Type: GrantFiled: February 1, 2002Date of Patent: December 16, 2003Assignee: Delta Electronics Inc.Inventors: Wen-Shi Huang, Kuo-Cheng Lin, Shun-Chen Chang
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Publication number: 20030228214Abstract: The present invention relates to propulsion and hydraulic systems having a co-axial design wherein the inlet section, impeller section, and outlet section of a mixed flow pump system all have a common centerline axis or axis of rotation. The mixed flow pump system includes an outer casing and a central body disposed co-axially within the outer casing. A pump impeller is rotatably connected to the central body for imparting hydraulic energy to the fluid flowing through the mixed flow pump system. The mixed flow pump system may also include inlet flow conditioning vanes for conditioning an inlet flow of fluid to the mixed flow impeller for improving the cavitation performance and/or acoustic performance of the pump module. Stator vanes are provided for connecting the central body to the outer casing and to remove any swirl velocity from the fluid flow exiting the mixed flow pump impeller.Type: ApplicationFiled: June 7, 2002Publication date: December 11, 2003Inventor: Mark W. McBride