Vane Fixed Between Radially Separate Surfaces Patents (Class 415/209.4)
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Patent number: 7510372Abstract: A method for repairing or replacing a mechanically retained vane is provided. The method comprises the steps of forming an oversized cavity in a support structure, inserting a flared end of a vane in the oversized cavity, and inserting a wedge for mechanically retaining the flared end of the vane in the oversized cavity.Type: GrantFiled: April 19, 2006Date of Patent: March 31, 2009Assignee: United Technologies CorporationInventors: William Bogue, Richard B. Ringler
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Patent number: 7491030Abstract: A variable inlet guide vane assembly in a turbomachine in which the vanes can vary in angle to control the flow through into the turbomachine, each guide vane having a leading edge portion and a trailing edge portion, and where the entire vane can pivot or the trailing edge portion can pivot about the leading edge portion. The leading edge and trailing edge portions each have a magnetic field generating material located within the portion of the vane or one a surface of the vane. The vanes are offset in the shroud such that the trailing edge portion of a first vane is located closer to the leading edge portion of an adjacent vane than to the trailing edge portion of the adjacent vane. An electric current is passed through at least one of the trailing edge and leading edge portions to produce a magnetic field. The magnetic field causes the trailing edge portion to move toward the leading edge portion of the adjacent vane.Type: GrantFiled: August 25, 2006Date of Patent: February 17, 2009Assignee: Florida Turbine Technologies, Inc.Inventors: Alex Pinera, Gabriel L Johnson
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Publication number: 20090028699Abstract: A static gas turbine component includes an inner and an outer annular support member and a plurality of circumferentially spaced radial struts arranged between the support members for transmitting structural loads. Each of a plurality of the struts includes a load carrying core rigidly fixed to both the inner and the outer support member forming a unitary carcass with the support members, an impact resistant shell surrounding the core, and an energy absorbing material arranged between the core and the shell.Type: ApplicationFiled: December 19, 2005Publication date: January 29, 2009Applicant: VOLVO AERO CORPORATIONInventor: Anders Sjunnesson
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Patent number: 7470109Abstract: Partitions have an airfoil coupled at opposite ends to inner and outer side walls. The side walls each mount radially extending male dovetails. The inner web and outer ring of a diaphragm include complementary shaped dovetail grooves. The male dovetails have reduced diameter portions while the female grooves similarly have corresponding reduced diameter groove portions. The male dovetails are inserted into the female dovetail grooves in an aft direction with stops of the reduced male and female dovetails preventing further movement aft. Seal welds are applied to prevent forward movement of the partitions relative to the web and outer ring.Type: GrantFiled: November 2, 2007Date of Patent: December 30, 2008Assignee: General Electric Co.Inventors: Andrew John Tomko, John Francis Nolan
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Patent number: 7452182Abstract: Aspects of the invention relate to a modular turbine vane assembly. The vane assembly includes an airfoil portion, an outer shroud and an inner shroud. The airfoil portion can be made of at least two segments. Preferably, the components are connected together so as to permit assembly and disassembly of the vane. Thus, in the event of damage to the vane, repair involves the replacement of only the damaged subcomponents as opposed to the entire vane. The modular design facilitates the use of various materials in the vane, including materials that are dissimilar. Thus, suitable materials can be selected to optimize component life, cooling air usage, aerodynamic performance, and cost. Because the vane is an assemblage of smaller sub-components as opposed to one unitary structure, the individual components of the vane can be more easily manufactured and more intricate features can be included.Type: GrantFiled: April 7, 2005Date of Patent: November 18, 2008Assignee: Siemens Energy, Inc.Inventors: Steven J. Vance, Allister W. James
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Patent number: 7434313Abstract: A repaired turbine engine stationary vane assembly, including at least one airfoil bonded between inner and outer bands, is provided by a method of providing first and second vane assembly members bonded at respective circumferential edges, for example by brazing or welding. The first vane assembly member includes the outer band, the airfoil, an inner flange, and a first segment of the inner band with a first edge, spaced from the flange and extending between and through inner band circumferential edge portions. The second vane assembly member includes a second segment of the inner band including a second edge of shape and size matched with the first edge and extending through the inner band circumferential edge portions.Type: GrantFiled: December 22, 2005Date of Patent: October 14, 2008Assignee: General Electric CompanyInventors: Paul D. Dasilva, Timothy Lee Siebert, Gregory Matthew Ford
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Patent number: 7427187Abstract: A steam turbine nozzle singlet having a blade or airfoil between inner and outer sidewalls is provided. The sidewalls include steps or flanges which are received in complementary recesses in the rings enabling axially short low heat input welds e.g., e-beam welds. These complementary steps and recesses mechanically interlock the singlet between the rings preventing displacement of the singlet in the event of weld failure. The low heat input welds minimize or eliminate distortion of the nozzle flow path. Additional features on the singlets, provide a datum for milling machines to form singlets of different sizes.Type: GrantFiled: January 13, 2006Date of Patent: September 23, 2008Assignee: General Electric CompanyInventors: Steven Sebastian Burdgick, Thomas William Crall, Thomas Patrick Russo
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Patent number: 7410342Abstract: A blade or a vane preferably used in a gas turbine engine, the blade or vane being formed of a metallic core or insert with a ceramic airfoil surface bonded to the metallic insert. The insert includes a series of concave and convex portions arranged along the outer surface, in which a plurality of hoop fibers are secured within a resin matrix to firmly secure the metallic insert to the ceramic airfoil body. Axial loads between the insert and the ceramic body are transferred to the hoop fibers. The hoop fibers are strong enough to resist extending in length that would permit the hoop fibers from sliding over the widest portion of the insert.Type: GrantFiled: August 18, 2005Date of Patent: August 12, 2008Assignee: Florida Turbine Technologies, Inc.Inventor: Alfred P. Matheny
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Publication number: 20080152488Abstract: A flange for supporting arcuate components comprising at least one arcuate rail, each arcuate rail having an inner radius, a first taper location, a first taper region, a second taper location, a second taper region, wherein the thickness of at least a portion of the first taper region is tapered and wherein the thickness of at least a portion of the second taper region is tapered.Type: ApplicationFiled: December 21, 2006Publication date: June 26, 2008Inventors: Raafat A. Kammel, Humphrey W. Chow, Michael Peter Kulyk
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Publication number: 20080138201Abstract: A flow-guiding device, connected between two fans disposed in series and rotating in the same rotation direction, includes a main frame and a plurality of flow-guiding pieces. The flow-guiding pieces are connected with the main frame. Each of the flow-guiding pieces is disposed corresponding to the stationary flow guiding device of the above fan so as to form a completed flow guiding device. A fan assembly including the flow-guiding device is also disclosed.Type: ApplicationFiled: December 3, 2007Publication date: June 12, 2008Inventors: Wei-Yi LIN, Jiun-Ying Lin, Cheng-Wei Yan, Ching-Shyang Huang
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Publication number: 20080131276Abstract: The present invention provides a mixer assembly including a mixer and a plurality of scoops attached around a circumference of the mixer element via a combination of sliding brackets and fixed brackets. The sliding brackets provide attachment and allow relative movement between the plurality of scoops and the mixer element while the fixed brackets provide only attachment between the mixer element and the plurality of scoops. The first sliding bracket includes a first flange that is fixedly mounted to the mixer element and a second flange that is biased against a surface of the scoop. A second sliding bracket is fixedly mounted to the mixer element and adjustably mounted to the scoop. The second sliding bracket includes an attachment hole and the scoop includes an adjustment slot. A fastener assembly including a spacer is received within the adjustment hole and the adjustment slot to allow relative movement between the mixer element and the scoop.Type: ApplicationFiled: November 30, 2006Publication date: June 5, 2008Inventors: Adeyemi E. Alade, Paul W. Palmer
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Patent number: 7360990Abstract: A method enables a variable vane assembly for a gas turbine engine including a casing and an inner shroud to be assembled. The method comprises providing at least one variable vane including a radially inner spindle that has a substantially circular cross-sectional shape, and coupling the variable vane radially between the casing and the inner shroud such that the radially inner spindle is rotatably coupled within an opening extending through the inner shroud, wherein the opening has a non-circular cross-sectional profile.Type: GrantFiled: October 13, 2004Date of Patent: April 22, 2008Assignee: General Electric CompanyInventors: Roger Owen Barbe, Mitchell Jay Headley, Scott Howard Pelletier, David N. Rosenow
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Patent number: 7329087Abstract: A stator vane assembly for a gas turbine includes a ceramic matrix composite airfoil held between radially inner and outer metal platforms wherein an interface between the airfoil and at least one of the radially inner and outer platforms is shaped to create a circuitous leakage path for gas from the gas turbine hot gas path.Type: GrantFiled: September 19, 2005Date of Patent: February 12, 2008Assignee: General Electric CompanyInventors: Ronald Ralph Cairo, Nitin Bhate
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Patent number: 7329096Abstract: Partitions have an airfoil coupled at opposite ends to inner and outer side walls. The side walls each mount radially extending male dovetails. The inner web and outer ring of a diaphragm include complementary shaped dovetail grooves. The male dovetails have reduced diameter portions while the female grooves similarly have corresponding reduced diameter groove portions. The male dovetails are inserted into the female dovetail grooves in an aft direction with stops of the reduced male and female dovetails preventing further movement aft. Seal welds are applied to prevent forward movement of the partitions relative to the web and outer ring.Type: GrantFiled: October 18, 2005Date of Patent: February 12, 2008Assignee: General Electric CompanyInventors: Andrew John Tomko, John Francis Nolan
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Patent number: 7311495Abstract: A fluid flow machine comprises an array of vanes (2) which are supported at their ends by inner and outer support structures 4, 6. The ends of the vanes are received in slots 8, 10, with resilient material 12 disposed between the vane 2 and the wall of the slot 8, 10. A restraint element 14, 34 is mounted in a recess 26, 28; 48 of the support structure 4, 6 and is engaged by a notch 30, 32 in the vane 2 to restrict axial displacement of the vane 2. Consequently, vibration of the vane in directions perpendicular to the lengthwise direction of the vane are damped by the elastomeric material 12 but bodily axial displacement of the vane 2 is prevented by the restraint elements 14, 34.Type: GrantFiled: June 30, 2006Date of Patent: December 25, 2007Assignee: Rolls-Royce PLCInventors: Duncan E Ashley, Peter Allford, Martin Lawrence
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Patent number: 7195454Abstract: A turbine airfoil includes opposite pressure and suction sides extending in span from a flowpath surface. The flowpath surface has chordally opposite forward and aft edges and laterally opposite first and second endfaces corresponding with the airfoil pressure and suction sides. The flowpath surface joins the first endface at the forward edge in a forward bullnose and joins the second endface at the aft edge in an aft bullnose, with the bullnoses varying in radius from the opposite edges.Type: GrantFiled: December 2, 2004Date of Patent: March 27, 2007Assignee: General Electric CompanyInventors: Wenfeng Lu, Ching-Pang Lee, Nicholas Charles Palmer
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Patent number: 7185433Abstract: A method for repairing a stationary turbine nozzle segment having at least one vane disposed between outer and inner structural bands includes providing an engine-run turbine nozzle segment having at least one vane disposed between outer and inner bands, wherein the outer band and the vanes are previously replaced components of the segment and the inner band is an original component of the segment; separating the inner band from the nozzle segment; repairing damage in the outer band and/or the vane; and joining the outer band and the vane to a newly manufactured replacement inner band segment. The replacement inner band segment includes: a structural inner band; and an integral structural collar adapted to receive an inner end of the at least one vane.Type: GrantFiled: December 17, 2004Date of Patent: March 6, 2007Assignee: General Electric CompanyInventors: Matthew N. Miller, James W. Caddell, Jr., James M. Caldwell, Brian A. Norton
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Patent number: 7172388Abstract: A spring seal for sealing a gap defined between first and second gas turbine engine components. The spring seal has a grasping portion for graspingly receiving a portion of the first component, and a spring loading portion adapted to extend between the first and second gas turbine engine components for spring loading the first and second gas turbine engine components relative to one another.Type: GrantFiled: August 24, 2004Date of Patent: February 6, 2007Assignee: Pratt & Whitney Canada Corp.Inventor: Remy Synnott
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Patent number: 7172389Abstract: A method is provided for making a repaired turbine engine stationary vane assembly including at least one airfoil bonded between spaced apart first and second platforms. The method comprises providing a first vane assembly member including at least a portion of the first platform, the airfoil, and a first segment of the second platform bonded with the airfoil. Also provided is a second vane assembly member including a second segment of the second platform with a recess of a shape and size sufficient to receive the first segment of the second platform. The first segment is placed in the recess after which the first and second segments are bonded, for example by brazing or welding. Provided is a more structurally sound repaired turbine engine stationary vane assembly including the first and second vane assembly members bonded together.Type: GrantFiled: November 16, 2004Date of Patent: February 6, 2007Assignee: General Electric CompanyInventors: Michael Philip Hagle, Timothy Lee Siebert, Jeffrey John Reverman, Dana Leigh Ferguson, Gregory Matthew Ford
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Patent number: 7160078Abstract: A mechanical arrangement for protection against catastrophic nozzle failures includes a turbine nozzle segment including an inner platform rail, a turbine nozzle inner support ring in part in axial registration with the rail on one side, an inner retainer segment secured to the inner support ring and in part in axially spaced registration relative to the rail on an axial side of the rail opposite from the support ring, a first inclined conical surface on the inner retainer segment, and a second inclined conical surface on the inner platform rail of the turbine nozzle, the second inclined conical surface opposing the first inclined conical surface, so as to bind the inner platform rail to the turbine nozzle between the inner retainer segment and the inner support ring, resulting in a wedge lock that prevents the inner platform from being lost downstream into rotating hardware of the turbine.Type: GrantFiled: September 23, 2004Date of Patent: January 9, 2007Assignee: General Electric CompanyInventors: Robert Walter Coign, David John Humanchuk, Leslie Tucker
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Patent number: 7147434Abstract: Blades (3) extending radially from the inner shroud (1) to the outer shroud (2) are attached to the inner shroud by means of a sealing cement containing an organic polyimide-based polymer adhesive.Type: GrantFiled: June 28, 2004Date of Patent: December 12, 2006Assignee: Snecma MoteursInventors: Claude Marcel Mons, Sandra Andrieu, Manuel Girard, Francois Pierre Georges Maurice Ribassin
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Patent number: 7121793Abstract: A turbine nozzle includes a vane joined to opposite inner and outer bands. The inner band includes a pocket adjoining a flange which recesses in part the inner surface of the band. The pocket undercuts the flange to form a notch at the base thereof.Type: GrantFiled: September 9, 2004Date of Patent: October 17, 2006Assignee: General Electric CompanyInventor: Victor Hugo Silva Correia
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Patent number: 7063505Abstract: A gas turbine engine strut segment includes a strut, which may be hollow, extending radially between co-annular radially inner and outer platforms, axially spaced apart inner platform flanges extending radially inwardly from the inner platform, and axially spaced apart outer platform flanges extending radially outwardly from the inner platform. At least one inner set of coaxial tapered inner holes extend axially through the inner platform flanges and at least one outer set of coaxial tapered outer holes extend axially through the outer platform flanges. The inner set of coaxial inner holes define an inner conical surface and the outer set of coaxial outer holes define an outer conical surface. Each of the axial spaced apart platform flanges may be circumferentially continuous or scalloped having spaced circumferentially apart lugs. The strut may have two inner sets of coaxial tapered inner and outer holes extending axially through the inner and outer platform flanges, respectively.Type: GrantFiled: February 7, 2003Date of Patent: June 20, 2006Assignee: General Electric CompanyInventor: Robert Paul Czachor
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Patent number: 7052234Abstract: A collar seal is configured for a turbine nozzle vane. The seal includes a retainer having a circumferential airfoil contour conforming with the airfoil contour of the vane. A flexible leaf is surrounded by the retainer and fixedly joined thereto. A woven sheath encases the leaf and is fixedly joined to the retainer. In an exemplary embodiment, the collar seal surrounds one end of a ceramic turbine vane mounted in a metal supporting band.Type: GrantFiled: June 23, 2004Date of Patent: May 30, 2006Assignee: General Electric CompanyInventors: Thomas Allen Wells, Mark Eugene Noe, David Edward Bulman, Nitin Bhate
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Patent number: 7048499Abstract: An inline centrifugal mixed flow fan (20) includes an axially extending intake conduit (22). An inlet cone (28) is disposed at an intake end (24). An impeller (30) is disposed downstream of the inlet cone and includes a centrally disposed wheel-back (32) rotated by an electric motor (44), plural fan blades (34) extending radially outwardly from the wheel-back and a wheel cone fixedly (36) attached to and circumscribing the wheel blades. A driver chamber (48) downstream of the impeller includes plural radially extending straight vanes (50) to direct air to an outlet end (26). The fan is configured to achieve reduced sound level and increased efficiency.Type: GrantFiled: June 14, 2001Date of Patent: May 23, 2006Assignee: Greenheck Fan CorporationInventors: Timothy R. Mathson, Timothy D. Kuski
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Patent number: 6942453Abstract: A turbine nozzle segment 1 of a turbine nozzle assembly comprises a plurality of stator vanes 7, an arc-like inner band 9 integrally molded at the inner end of a plurality of the stator vanes 7, an arc-like outer band 11 integrally molded at the outer end of a plurality of the stator vanes 7. An outer band 11 includes an outer platform 19, a forward outer leg 21, a aft outer leg 23 and a hook member 29 formed at the back end and also in the central portion in the circumferential direction of the outer platform 19.Type: GrantFiled: January 27, 2004Date of Patent: September 13, 2005Assignee: Ishikawajima-Harima Heavy Industries Co., Ltd.Inventors: Atsushi Tsuru, Keiji Nishimura
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Patent number: 6935837Abstract: A method enables a gas turbine engine including a first rotor assembly and a second rotor assembly coupled in axial flow communication downstream from the first rotor assembly to be assembled. The method comprises coupling an upstream end of an extension duct to an outlet of the first rotor assembly, wherein the extension duct includes a plurality of panels coupled circumferentially, and coupling a downstream end of the extension duct to an inlet of the second rotor assembly using at least one fish mouth seal.Type: GrantFiled: February 27, 2003Date of Patent: August 30, 2005Assignee: General Electric CompanyInventors: Thomas Ory Moniz, Robert Joseph Orlando, John Christopher Brauer
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Patent number: 6921246Abstract: 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: GrantFiled: December 20, 2002Date of Patent: July 26, 2005Assignee: General Electric CompanyInventors: Gulcharan S. Brainch, William Miller, Richard W. Albrecht, David B. Stewart, Todd Stephen Heffron
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Patent number: 6905308Abstract: A method is provided for repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes separating the inner band from the nozzle segment, and joining the inner band to a newly manufactured replacement casting having an outer band and a vane. The replacement casting includes an airfoil stub. The airfoil stub is received in a recess formed in the inner band. Joining is completed by joining the airfoil stub to the inner band. The replacement casting may be modified from a newly manufactured singlet casting.Type: GrantFiled: November 20, 2002Date of Patent: June 14, 2005Assignee: General Electric CompanyInventors: Michael Philip Hagle, Brian Alan Norton, James Walter Caddell, Jr.
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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: 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: 6793457Abstract: A method for repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands includes separating the inner band from the nozzle segment, and joining the inner band to a newly manufactured replacement casting having an outer band and at least one vane. The replacement casting includes a mounting platform formed on one end of the vane and a boss formed on the mounting platform. A collar is joined to the inner band and has a slot formed therein. The boss is then inserted into the slot, and the mounting platform is received in a recess formed in the inner band. Joining is completed by joining the boss to the collar and the mounting platform to the inner band. The thickness of the collar is tapered in an axial direction, and a relief is formed in the collar to provide assembly clearance with adjacent components.Type: GrantFiled: November 15, 2002Date of Patent: September 21, 2004Assignee: General Electric CompanyInventors: James Walter Caddell, Matthew Nicklus Miller, Brian Alan Norton
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Publication number: 20040179939Abstract: An embodiment of a disclosed apparatus for sizing an engine stator has a plurality of radially moveable shoes for engaging the inner and outer rings of the stator. The shoes apply a radially directed force to the inner and outer rings to cause the rings to expand. In particular embodiments, one or more heating mechanisms, such as a ceramic heating blanket, may be used to heat the stator prior to sizing. A method for sizing an engine stator also is disclosed. The method comprises simultaneously displacing the inner and outer rings of the stator generally radially outwardly so as to increase the respective diameters of the inner and outer rings.Type: ApplicationFiled: March 12, 2003Publication date: September 16, 2004Applicant: PCC Structurals, Inc.Inventors: Gerald Bluhm, James R. Barrett
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Publication number: 20040156719Abstract: A gas turbine engine strut segment includes a strut, which may be hollow, extending radially between co-annular radially inner and outer platforms, axially spaced apart inner platform flanges extending radially inwardly from the inner platform, and axially spaced apart outer platform flanges extending radially outwardly from the inner platform. At least one inner set of coaxial tapered inner holes extend axially through the inner platform flanges and at least one outer set of coaxial tapered outer holes extend axially through the outer platform flanges. The inner set of coaxial inner holes define an inner conical surface and the outer set of coaxial outer holes define an outer conical surface. Each of the axial spaced apart platform flanges may be circumferentially continuous or scalloped having spaced circumferentially apart lugs. The strut may have two inner sets of coaxial tapered inner and outer holes extending axially through the inner and outer platform flanges, respectively.Type: ApplicationFiled: February 7, 2003Publication date: August 12, 2004Inventor: Robert Paul Czachor
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Publication number: 20040120813Abstract: A method for assembling a turbine, wherein the method includes coupling at least one nozzle assembly including an outer band, an inner band, a nozzle, and a dovetail, to a stator that includes a plurality of dovetail slots and channels defined therein, slidably coupling the at least one nozzle assembly into a respective dovetail slot, and fixedly securing the at least one nozzle assembly to the stator with a load pin that extends between the nozzle assembly and the dovetail slot.Type: ApplicationFiled: December 23, 2002Publication date: June 24, 2004Applicant: GENERAL ELECTRIC COMPANYInventors: Bernard Arthur Couture, Ronald Wayne Korzun
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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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Publication number: 20040086383Abstract: Nozzles for a turbine have dovetail-shaped bases for reception in corresponding dovetail-shaped grooves in the carrier halves of a turbine. The nozzles at each of the horizontal joint faces of each carrier half have notches formed along their bases including an abutment face. Key slots are formed in the horizontal joint faces and receive keys bearing against the abutment faces. The keys are peened or screwed into the carrier half at the horizontal joint faces. Radial loading pins engage the end nozzle bases to bias the end nozzles radially inwardly without interfering with the keys retaining the nozzles in the grooves.Type: ApplicationFiled: October 31, 2002Publication date: May 6, 2004Inventors: Bernard Arthur Couture, David Orus Fitts, Ronald Wayne Korzun, James David Schuhl
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Patent number: 6685431Abstract: The present invention relates to a method for repairing a vane used in a gas turbine engine. The method broadly comprises the steps of providing a vane to be repaired, which vane has a first platform, a first buttress, a second platform, a second buttress, and an airfoil extending between the first and second platforms, removing the first platform, the first buttress, and the airfoil from the vane in their entirety and removing part of the second platform and the second buttress leaving a machined vane portion, providing a replacement detail having at least a replacement first platform, a replacement first buttress and a replacement airfoil, positioning the replacement detail relative to the machined vane portion, and forming a joint between the machined vane portion and the replacement detail.Type: GrantFiled: October 24, 2001Date of Patent: February 3, 2004Assignee: United Technologies CorporationInventor: David J. Hiskes
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Patent number: 6655912Abstract: The present invention relates to a guide vane stage of a compressor comprising an outer ring and an inner ring, which are both concentric and preferably circular. The rings are connected to each other via a series of fixed vanes, and are characterized in that at least the inner ring is provided with holes or apertures which allows one of the ends of the vanes to pass through these holes or apertures. The vanes also have at their end a second aperture intended to allow the passage of a retaining and rigidifying component having an elastic function, in order to hold them in pairs.Type: GrantFiled: November 30, 2001Date of Patent: December 2, 2003Assignee: Techspace Aero S.A.Inventor: Mathieu Bos
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Patent number: 6644916Abstract: Vanes of the type for directing a fluid radially are fabricated by forming the vanes integrally to a support structure made from a sacrificial material which is removed in assembly so that the vanes are supported for operative use. In one embodiment, the vanes are formed in the dams of an annular burner by preforming the vanes supported to a disk; the vanes and disk apparatus is fitted to side plates which are then brazed together and the disk portion and complementary side plate portions are removed, for defining the dam that is affixed to the liner of the annular combustor. Other configurations are contemplated that are tailored to fit the intended embodiment. The vane and support portion made from a sacrificial material constitute an apparatus of this invention.Type: GrantFiled: June 10, 2002Date of Patent: November 11, 2003Assignee: Elliott Energy Systems, IncInventor: William F. Beacom
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Patent number: 6626641Abstract: A steam turbine of the type which incorporates a turbine case defining a plurality of passages having outlets opening through an inside end wall of the turbine case in a direction generally parallel to the turbine shaft, with nozzles positioned over the outlets to direct steam against the periphery of the turbine wheel, can be modified to a higher efficiency design. To perform the modification, the nozzles are removed, an arcuately shaped housing is positioned in covering relationship with the outlets, and an arcuately shaped louver is positioned so as to form an end wall of the housing. The louver has a plurality of vanes to direct the steam against the periphery of the turbine wheel to cause rotation of the turbine shaft and the housing forms a confined steam flow path from the outlets to the louver. The downstream turbine blading can be modified if desired.Type: GrantFiled: October 24, 2000Date of Patent: September 30, 2003Assignee: Alfred Conhagen, Inc.Inventors: Alton Burns, Michael L. Macek
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Patent number: 6619917Abstract: The present invention relates to an improved system for installing a vane in a gas turbine. The system includes a receptor pocket positioned within a first support structure and a boot attached to a first or inner end of a vane for insertion into the receptor pocket. In a first embodiment of the present invention, the receptor pocket is formed by machining it into the support structure. In a second embodiment of the present invention, the receptor pocket is formed by an insert which is installed into the support structure. In accordance with the present invention, the inner end of the vane having the boot is first inserted into the receptor pocket. After insertion has been completed, the vane is rotated until an outer base is brought into position against an outer support structure. The outer end of the vane is then secured to the outer support structure using studs and nuts.Type: GrantFiled: December 19, 2000Date of Patent: September 16, 2003Assignee: United Technologies CorporationInventors: Samuel L. Glover, Thomas E. Manning
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Patent number: 6595747Abstract: A guide vane stage of a compressor comprising an outer ring and an inner ring, both of which are concentric and preferably circular is provided. The rings are connected to each other via a series of fixed vanes, characterized in that at least one of the rings is provided with a series of holes or apertures which allow the vanes to pass through these holes or apertures. The fixed vanes also have, at at least one of their ends, an aperture to allow at least one locking element to pass through, making it possible to simultaneously securely fasten all the present in the guide vane stage, on the non-functional side of the ring. The end of the fixed vanes through which the locking element passes is buried in an elastomeric element.Type: GrantFiled: November 30, 2001Date of Patent: July 22, 2003Assignee: Techspace Aero S.A.Inventor: Mathieu Bos
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Patent number: 6579061Abstract: A turbine nozzle includes segments of outer and inner bands supporting corresponding vane pairs. The bands adjoin each other at corresponding ends along splitlines, with each band having a forward land, an opposite aft land, and a middle land extending therebetween. The forward lands have a nominal aft-facing step, the aft lands have a nominal forward-facing step and the middle lands are nominally flush.Type: GrantFiled: July 27, 2001Date of Patent: June 17, 2003Assignee: General Electric CompanyInventors: John Peter Heyward, Robert Ingram Ackerman, Gregory Alan White
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Patent number: 6558115Abstract: A turbine guide blade includes a platform which absorbs thermal loads and a fastening region adjoining the platform for absorbing mechanical loads. The fastening region has such a slim construction that it leaves a cold side of the platform readily accessible.Type: GrantFiled: February 28, 2001Date of Patent: May 6, 2003Assignee: Siemens AktiengesellschaftInventor: Peter Tiemann
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Patent number: 6553665Abstract: Turbine vane segments having outer and inner bands and a vane extending therebetween are welded one to the other by E-beam welding along their adjoining margins and from the outside of the bands. The adjoining margins on the hot gas path sides of the outer and inner bands are chamfered, TIG-welded and machined to provide a smooth, continuous gas path surface. The aft hook of each segment is cut back to provide inset faces in a radially projecting flange and a flange extending axially from the radial flange. A filler piece having a body shaped to correspond to the shape of the space between the inset faces of the radial flange is E-beam welded to the radial flange. Gaps between a tongue on the filler piece and the inset faces of the axially extending flange are provided with weld filler material and TIG-welded to complete the welding of the aft hook.Type: GrantFiled: March 8, 2000Date of Patent: April 29, 2003Assignee: General Electric CompanyInventors: George Gerald Gunn, John Robert Fulton, Francis Lawrence Kirkpatrick, Raymond Joseph Jones
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Publication number: 20030077171Abstract: The present invention relates to a method for repairing a vane used in a gas turbine engine. The method broadly comprises the steps of providing a vane to be repaired, which vane has a first platform, a first buttress, a second platform, a second buttress, and an airfoil extending between the first and second platforms, removing the first platform, the first buttress, and the airfoil from the vane in their entirety and removing part of the second platform and the second buttress leaving a machined vane portion, providing a replacement detail having at least a replacement first platform, a replacement first buttress and a replacement airfoil, positioning the replacement detail relative to the machined vane portion, and forming a joint between the machined vane portion and the replacement detail.Type: ApplicationFiled: October 24, 2001Publication date: April 24, 2003Inventor: David J. Hiskes
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Patent number: 6547518Abstract: A gas turbine frame has inner and outer annular bands, respectively, joined together by generally radially extending struts therebetween. A radially outer conical support arm extends radially outwardly from the outer band and a radially inner conical support arm extends radially inwardly from the inner band. Circumferentially spaced apart inner and outer openings are disposed in the inner and outer conical support arms, respectively. Each of the struts has at least one radially extending hollow passage which extends through the inner and outer bands. The frame is a single piece integral casting. The inner and outer conical support arms have an equal number of the inner and outer circumferentially spaced apart openings. The inner circumferentially spaced apart openings are equi-angularly spaced apart and the outer circumferentially spaced apart openings are equi-angularly spaced apart.Type: GrantFiled: April 6, 2001Date of Patent: April 15, 2003Assignee: General Electric CompanyInventors: Robert Paul Czachor, Steven Andrew Strang
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Patent number: 6517313Abstract: A segmented vane support structure for use in a gas turbine engine having an engine casing, includes a single piece inner ring and separated front outer and rear outer rings. The vane segments circumferentially abut to form a stator ring which is clamped at the respective opposed outer ends by the front outer and rear outer rings therebetween onto the inner ring. The front outer and rear outer rings are axially restrained to the engine casing by a retaining ring which is fitted in an inner annular groove of the engine casing. Each vane segment has a lug member at its outer diameter which radially and slidably engages in a slot of the engine casing to provide angular positioning of the vane segments within the engine casing and to transmit circumferential vane load into the engine casing. This support structure arrangement transmits circumferential loading to the engine casing and isolates radial loading from the engine casing caused by thermal growth changes of the vane segments.Type: GrantFiled: June 25, 2001Date of Patent: February 11, 2003Assignee: Pratt & Whitney Canada Corp.Inventor: Mark John Rogers
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Publication number: 20030002979Abstract: A turbine nozzle includes ceramic outer and inner bands and an integral ceramic vane aft segment. A metal vane forward segment adjoins the aft segment in a hybrid assembly.Type: ApplicationFiled: June 28, 2001Publication date: January 2, 2003Inventor: Angelo Von Koschier