Patents Represented by Attorney William S. Andes
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Patent number: 7963099Abstract: A gas turbine engine exhaust nozzle includes a fluted shell terminating in a row of chevrons. The nozzle is radially serpentine circumferentially around the shell and has a circumferentially serpentine trailing edge.Type: GrantFiled: May 21, 2007Date of Patent: June 21, 2011Assignee: General Electric CompanyInventor: Bernard James Renggli
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Patent number: 7926285Abstract: An exhaust nozzle for a gas turbine engine includes a modular chevron. The chevron includes dual skins fixedly joined together at a base flange, and at a rim extending along the trailing edge of the chevron between the base and apex thereof.Type: GrantFiled: July 18, 2007Date of Patent: April 19, 2011Assignee: General Electric CompanyInventors: Rudolph Morris Tisdale, Gregory Allen Uhler, Michael Robert Johnson, Christopher Joseph Nye
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Patent number: 7926289Abstract: A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. A first interstage bleed circuit is joined in flow communication between a first preultimate stage of the compressor and hollow blades in the turbine to provide thereto pressurized primary air. A second interstage bleed circuit is joined in flow communication between a second preultimate stage of the compressor and the turbine blades to provide thereto pressurized secondary air at a lower pressure than the primary air.Type: GrantFiled: November 10, 2006Date of Patent: April 19, 2011Assignee: General Electric CompanyInventors: Ching-Pang Lee, Thomas Ory Moniz, Robert Joseph Orlando
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Patent number: 7870742Abstract: A gas turbine engine includes a compressor, combustor, and high pressure (HP) turbine operatively joined together. An interstage cooling circuit is joined in flow communication from an intermediate stage of the compressor to a forward face of an HP disk supporting a row of turbine blades for channeling interstage bleed cooling air thereto.Type: GrantFiled: November 10, 2006Date of Patent: January 18, 2011Assignee: General Electric CompanyInventors: Ching-Pang Lee, Thomas Ory Moniz, Robert Joseph Orlando
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Patent number: 7870743Abstract: A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a nozzle followed by a row of rotor blades. A first bleed circuit is joined in flow communication between the last stage of the compressor and a forward cooling channel in vanes of the nozzle for feeding first cooling holes therein with pressurized primary air at a first pressure. A second bleed circuit is joined in flow communication between an intermediate stage of the compressor and aft cooling channels in the nozzle vanes to feed second cooling holes with pressurized secondary air at a second pressure less than the first pressure.Type: GrantFiled: November 10, 2006Date of Patent: January 18, 2011Assignee: General Electric CompanyInventors: Ching-Pang Lee, Thomas Ory Moniz, Robert Joseph Orlando
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Patent number: 7836703Abstract: A turbine nozzle includes first and second vanes joined to outer and inner bands. The vanes include outboard sides defining outboard flow passages containing axial splitlines, and opposite inboard sides defining an inboard flow passage without axial splitline. The two vanes include different cooling circuits for differently cooling the inboard and outboard vane sides.Type: GrantFiled: June 20, 2007Date of Patent: November 23, 2010Assignee: General Electric CompanyInventors: Ching-Pang Lee, Robert Joseph Orlando
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Patent number: 7823389Abstract: A gas turbine engine includes a compressor, combustor, and turbine having a row of blades mounted inside a surrounding turbine shroud. A heat exchanger is used for cooling pressurized air bled from the compressor. A distribution network joins the heat exchanger to the turbine for selectively channeling air from the heat exchanger below the blades and above the shroud for controlling blade tip clearance.Type: GrantFiled: November 15, 2006Date of Patent: November 2, 2010Assignee: General Electric CompanyInventors: Kenneth Edward Seitzer, Wojciech Sak, Zhifeng Dong, Robert Paul Ziegler, Chris Charles Glynn
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Patent number: 7824158Abstract: A turbine blade damper includes an outer part for damping vibration of the blade airfoil and a supporting inner part. The two parts are formed of different materials for the different performance required thereof in the blade.Type: GrantFiled: June 25, 2007Date of Patent: November 2, 2010Assignee: General Electric CompanyInventors: Randall Charles Bauer, D. Keith Patrick
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Patent number: 7743613Abstract: A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a row of nozzle vanes followed by a row of rotor blades. The vanes and blades have corresponding forward and aft internal cooling channels. First, second, third, and fourth bleed circuits are joined in flow communication with different stages of the compressor for bleeding pressurized air therefrom at different pressures to provide coolant to the forward and aft channels of the turbine vanes and blades.Type: GrantFiled: November 10, 2006Date of Patent: June 29, 2010Assignee: General Electric CompanyInventors: Ching-Pang Lee, Thomas Ory Moniz, Robert Joseph Orlando
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Patent number: 7740443Abstract: A row of turbine blades is surrounded by a turbine shroud. The shroud is supported by a turbine case having a pair of radially outwardly extending rails. The rails are perforate for channeling therethrough control air to control thermal radial movement of the case, and in turn radial position of the shroud supported therefrom.Type: GrantFiled: November 15, 2006Date of Patent: June 22, 2010Assignee: General Electric CompanyInventors: Kenneth Edward Seitzer, Wojciech Sak, Zhifeng Dong, Robert Paul Ziegler, William Lee Herron
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Patent number: 7736124Abstract: A turbine rotor blade includes a hollow airfoil joined to a platform and dovetail. A main flow channel extends longitudinally in span through the blade and is bound chordally by opposite partitions transversely bridging opposite sidewalls of the airfoil. A damper rib and transversely opposite damper pad are arranged together in a plurality of pairs spaced longitudinally apart in the airfoil and chordally positioned intermediate to the partitions to provide unobstructed forward and aft portions of the flow channel for channeling a coolant therethrough. The damper ribs and pads are configured to receive a wire damper through the channel to locally dampen vibration while minimizing obstruction of the coolant flow therethrough.Type: GrantFiled: April 10, 2007Date of Patent: June 15, 2010Assignee: General Electric CompanyInventors: Randall Charles Bauer, Gregory Terrence Garay, Matthew Mark Weaver, James Robert Bailey, Bruce Clark Busbey
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Patent number: 7695243Abstract: A hollow turbine airfoil includes a tip cap bounding an internal cooling circuit between opposite pressure and suction sidewalls. The tip cap includes an internal dome surrounding a dust hole, and the dome is inclined inwardly toward the airfoil root both transversely between the opposite sidewalls and chordally between opposite leading and trailing edges of the airfoil.Type: GrantFiled: July 27, 2006Date of Patent: April 13, 2010Assignee: General Electric CompanyInventors: Ching-Pang Lee, Tingfan Pang, Brian Alan Norton, Jan Christopher Schilling, Aspi Rustom Wadia
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Patent number: 7686578Abstract: A turbine blade includes an airfoil tip with first and second tip ribs extending from a tip floor. The ribs extend along the opposite pressure and suction sides of the blade and are joined together at opposite leading and trailing edges. A tip baffle is nested transversely between the ribs, and conforms with the second rib to bifurcate the airfoil tip into first and second tip pockets extending along the corresponding pressure and suction sides.Type: GrantFiled: August 21, 2006Date of Patent: March 30, 2010Assignee: General Electric CompanyInventors: Kevin Samuel Klasing, Ching-Pang Lee, Paul Hadley Vitt, Brian David Keith
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Patent number: 7674093Abstract: A casting core for a turbine blade includes a plurality of rods extending above a shank. The rods define internal cooling channels in the airfoil of the blade, and the shank defines an inlet channel in the dovetail of the blade. A plurality of stubs are clustered together at a bulb joined to the shank and radiate outwardly to integrally join different ones of the rods for increasing strength of the core.Type: GrantFiled: December 19, 2006Date of Patent: March 9, 2010Assignee: General Electric CompanyInventors: Ching-Pang Lee, Steven Robert Brassfield
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Patent number: 7624581Abstract: A Turbofan engine includes a fan mounted to a fan frame inside a fan nacelle. A booster compressor is joined to the fan inboard a flow splitter. A booster bleed system is disposed inside the splitter, and includes an inlet at the compressor outlet, and an outlet joined to the bypass duct following the fan.Type: GrantFiled: December 21, 2005Date of Patent: December 1, 2009Assignee: General Electric CompanyInventor: Thomas Ory Moniz
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Patent number: 7614210Abstract: A variable cycle turbofan engine includes first and second fans independently joined to respective turbines. A first bypass duct surrounds a core engine disposed in flow communication with the second fan. A second bypass duct surrounds the first bypass duct in flow communication with the first fan. A first exhaust nozzle is joined to both the core engine and first bypass duct. And, a second exhaust nozzle is joined to the second bypass duct.Type: GrantFiled: February 13, 2006Date of Patent: November 10, 2009Assignee: General Electric CompanyInventors: Brandon Flowers Powell, John Jared Decker
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Patent number: 7607893Abstract: A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. The tip ribs are spaced apart between the leading and trailing edges of the airfoil to include a tip baffle. The baffle extends chordally in counter profile with the first rib to define a first pocket, and in counter profile with the second rib to define a second pocket.Type: GrantFiled: August 21, 2006Date of Patent: October 27, 2009Assignee: General Electric CompanyInventors: Ching-Pang Lee, Kevin Samuel Klasing, Paul Hadley Vitt, Brian David Keith
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Patent number: 7607308Abstract: A bleed duct is configured for bleeding fan air from the fan bypass duct in a turbofan aircraft engine. The bleed duct includes a tubular conduit having an inlet and outlet at opposite ends. The conduit is configured in flow area for recovering pressure from speeding fan air bled therethrough. A shroud extends forwardly from the duct inlet for suppressing dynamic pressure oscillations inside the conduit without degrading the pressure recovery.Type: GrantFiled: December 8, 2005Date of Patent: October 27, 2009Assignee: General Electric CompanyInventors: Robert Eugene Kraft, Nelson Dirk Gibbens, Rolf Robert Hetico, William Charles Groll, William Andrew Bailey, James Edward Stoker
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Patent number: 7594388Abstract: A turbofan engine includes a fan, compressor, combustor, high pressure turbine, and low pressure turbine joined in serial flow communication. The high pressure turbine includes two stages of rotor blades to effect corresponding exit swirl in the combustion gases discharged therefrom. A transition duct includes fairings extending between platforms for channeling the combustion gases to the low pressure turbine with corresponding swirl. First stage rotor blades in the low pressure turbine are oriented oppositely to the rotor blades in the high pressure turbine for counterrotation.Type: GrantFiled: June 6, 2005Date of Patent: September 29, 2009Assignee: General Electric CompanyInventors: David Glenn Cherry, Robert John Beacock, William Larson Clifford, Robert Joseph Orlando, Thomas Ory Moniz, Ching-Pang Lee
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Patent number: 7581398Abstract: A fuel shield is configured for use in the afterburner of a turbofan aircraft engine. The shield includes wings obliquely joined together at a nose to conform with the leading edge region of a flameholder vane. A hood is joined to the wings and extends obliquely therefrom to conform with a supporting outer shell of the flameholder.Type: GrantFiled: June 29, 2006Date of Patent: September 1, 2009Assignee: General Electric CompanyInventors: Jeffrey Carl Mayer, Brian Benscoter Roberts