Patents Represented by Attorney William S. Andes
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Patent number: 7578653Abstract: A turbine stage includes a stator nozzle having a row of vanes mounted between inner and outer bands. The inner band terminates in an ovate ledge converging aft from the vanes with radially outer and inner convex surfaces joined at a convex apex. The ovate ledge reduces aerodynamic losses at the rotary seal with a row of following turbine rotor blades.Type: GrantFiled: December 19, 2006Date of Patent: August 25, 2009Assignee: General Electric CompanyInventors: Kevin Samuel Klasing, Ching-Pang Lee, Scott David Hunter
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Patent number: 7565804Abstract: 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, with each of the wings including an offset mounting tab at a proximal end thereof. The wings and tabs are configured to complement a flameholder vane around its leading edge, with the tabs contacting the vane sidewalls to offset the wings outwardly therefrom and form a thermally insulating gap therebetween.Type: GrantFiled: June 29, 2006Date of Patent: July 28, 2009Assignee: General Electric CompanyInventors: Martin Wayne Frash, Brian Benscoter Roberts
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Patent number: 7513102Abstract: A turbofan engine includes a fan, compressor, combustor, single-stage high pressure turbine, and low pressure turbine joined in serial flow communication. First stage rotor blades in the low pressure turbine are oriented oppositely to the rotor blades in the high pressure turbine for counterrotation. First stage stator vanes in the low pressure turbine have camber and twist for carrying swirl directly between the rotor blades of the high and low pressure turbines.Type: GrantFiled: June 6, 2005Date of Patent: April 7, 2009Assignee: General Electric CompanyInventors: Thomas Ory Moniz, Scott Michael Carson, Robert Joseph Orlando, Ching-Pang Lee, David Glenn Cherry
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Patent number: 7510376Abstract: A turbine blade includes a hollow airfoil having a plurality of bowed tip holes extending through a tip floor thereof and skewed toward a squealer rib extending outwardly from the floor.Type: GrantFiled: August 25, 2005Date of Patent: March 31, 2009Assignee: General Electric CompanyInventors: Ching-Pang Lee, Nicholas Charles Palmer, Kevin Lee Kirkeng
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Patent number: 7509797Abstract: A turbojet engine includes a core engine, an afterburner, and a converging-diverging exhaust nozzle in serial flow communication. A thrust vectoring system is joined between a compressor and the nozzle. A controller is operatively joined to the thrust vectoring system for selectively varying distribution of air bled from the compressor into the exhaust nozzle for vectoring propulsion thrust.Type: GrantFiled: April 29, 2005Date of Patent: March 31, 2009Assignee: General Electric CompanyInventor: James Edward Johnson
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Patent number: 7510371Abstract: A turbine nozzle includes a row of vanes joined to radially outwardly inclined outer and inner bands. Each vane has camber and an acute twist angle for importing swirl in combustion gases discharged at trailing edges thereof. The trailing edges are tilted forwardly from the inner band to the outer band for increasing aerodynamic efficiency.Type: GrantFiled: June 6, 2005Date of Patent: March 31, 2009Assignee: General Electric CompanyInventors: Robert Joseph Orlando, Thomas Ory Moniz, Ching-Pang Lee, David Glenn Cherry, Robert John Beacock, William Larson Clifford, Scott Michael Carson
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Patent number: 7476086Abstract: A fan blade includes an airfoil having opposite pressure and suction sides extending in span between a root and tip, and extending in chord between opposite leading and trailing edges. From root toward tip, the airfoil includes increasing stagger and decreasing camber, and increasing chord length to barrel the airfoil along both the leading and trailing edges. The airfoil further includes forward aerodynamic sweep at the tip, and non-forward aerodynamic sweep between the maximum barrel and the root.Type: GrantFiled: August 22, 2005Date of Patent: January 13, 2009Assignee: General Electric CompanyInventors: Aspi Rustom Wadia, Peter Nicholas Szucs, Max Robert Farson, Virginia Louise Wilson, William Joseph Solomon
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Patent number: 7475545Abstract: A turbojet engine includes a core engine, afterburner, and converging-diverging exhaust nozzle disposed in serial flow communication. A bypass duct surrounds the core engine and afterburner and terminates in flow communication with the exhaust nozzle. The compressor includes first stage fan blades having integral flades at the tips thereof disposed inside the bypass duct. The bypass duct includes a row of variable inlet guide vanes disposed forward of the flades for controlling airflow thereto.Type: GrantFiled: April 29, 2005Date of Patent: January 13, 2009Assignee: General Electric CompanyInventor: James Edward Johnson
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Patent number: 7448199Abstract: A turbojet engine includes a core engine, an afterburner, and a converging-diverging exhaust nozzle in serial flow communication. An integral starter-generator is disposed inside the core engine and is joined to the rotor for equal speed rotation therewith. An electrical controller coordinates operation of the engine for subsonic, transonic, and supersonic operation of the engine in a missile self-powered by the starter-generator.Type: GrantFiled: April 29, 2005Date of Patent: November 11, 2008Assignee: General Electric CompanyInventor: James Edward Johnson
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Patent number: 7424805Abstract: A turbojet engine includes a core engine, an afterburner, and a converging-diverging exhaust nozzle in serial flow communication. A controller is operatively joined to the core engine and afterburner and configured for scheduling fuel thereto for operating the afterburner dry during subsonic flight operation of the engine, wet during transonic flight, and dry during supersonic flight.Type: GrantFiled: April 29, 2005Date of Patent: September 16, 2008Assignee: General Electric CompanyInventor: James Edward Johnson
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Patent number: 7413001Abstract: A synthetic model of a component is created from a 3-D numerical model thereof. A core is then cast inside the synthetic model. The synthetic model may then be removed from the cast core, and then the cast core is used for casting an authentic component therearound. The core is removed from inside the authentic component, which authentic component precisely matches the original synthetic model therefor.Type: GrantFiled: May 16, 2005Date of Patent: August 19, 2008Assignee: General Electric CompanyInventors: Hsin-Pang Wang, Ching-Pang Lee
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Patent number: 7413405Abstract: A turbine blade includes an airfoil, platform, and dovetail. The airfoil includes a plurality of flow channels being separated by partitions. A primary partition includes an inner saddle. And, a bipedal damper includes a pair of legs extending into the flow channels, and integrally joined together at a seat bridging the saddle.Type: GrantFiled: June 14, 2005Date of Patent: August 19, 2008Assignee: General Electric CompanyInventors: Bruce Clark Busbey, Matthew Mark Weaver, Gregory Terrence Garay
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Patent number: 7377743Abstract: A turbine nozzle includes a mid vane mounted between a pair of end vanes in outer and inner bands. The mid vane includes a first pattern of film cooling holes configured to discharge more cooling air than each of the two end vanes having respective second patterns of film cooling holes.Type: GrantFiled: December 19, 2005Date of Patent: May 27, 2008Assignee: General Electric CompanyInventors: David Allen Flodman, Jason David Shapiro, Michael Peter Kulyk
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Patent number: 7374403Abstract: A turbofan includes a row of fan blades extending from a supporting disk inside an annular casing. Each blade includes an airfoil having opposite pressure and suction sides extending radially in span between a root and tip and axially in chord between leading and trailing edges. Adjacent airfoils define corresponding flow passages therebetween for pressurizing air. Each airfoil includes stagger increasing between the root and tip, and the flow passage has a mouth between the airfoil leading edge and the suction side of an adjacent airfoil and converges to a throat aft from the mouth. The row includes no more than twenty fan blades having low tip solidity for increasing the width of the passage throat.Type: GrantFiled: April 7, 2005Date of Patent: May 20, 2008Assignee: General Electric CompanyInventors: John Jared Decker, Peter Nicholas Szucs, William Joseph Solomon, Virginia Louise Wilson
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Patent number: 7328580Abstract: A wall in a gas turbine engine includes inner and outer surfaces having a row of compound chevron film cooling holes extending therethrough. The chevron holes diverge both longitudinally and laterally between an inlet at the wall inner surface and a chevron outlet at the wall outer surface.Type: GrantFiled: June 23, 2004Date of Patent: February 12, 2008Assignee: General Electric CompanyInventors: Ching-Pang Lee, Steven Robert Brassfield, Ronald Scott Bunker
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Patent number: 7322797Abstract: A turbine blade includes an airfoil, platform, shank, and dovetail integrally joined together. A cooling chamber is located under the platform and has a portal exposed outwardly from the shank. A damper seat surrounds the portal and is recessed under the platform for receiving a vibration damper to sealingly close the chamber across the portal.Type: GrantFiled: December 8, 2005Date of Patent: January 29, 2008Assignee: General Electric CompanyInventors: Ching-Pang Lee, Steven Robert Brassfield, Jan Christopher Schilling
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Patent number: 7305817Abstract: A gas turbine engine exhaust nozzle includes a row of laterally sinuous chevrons extending from an aft end of an exhaust duct. The chevrons have radially outer and inner surfaces bound by a laterally sinuous trailing edge extending between a base of the chevrons adjoining the duct and an axially opposite apex of the chevrons. Each chevron has a compound arcuate contour both axially and laterally, and the sinuous trailing edge of the chevrons further compounds the arcuate configuration of each chevron.Type: GrantFiled: February 9, 2004Date of Patent: December 11, 2007Assignee: General Electric CompanyInventors: Keith Edward James Blodgett, Kevin Sean Early, Steven Martens, William Andrew Bailey, Kenneth Daniel Price
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Patent number: 7296973Abstract: A turbine blade includes an airfoil having opposite pressure and suction sidewalls joined together at opposite leading and trailing edges and extending longitudinally from root to tip. A plurality of independent cooling circuits are disposed inside the airfoil correspondingly along the pressure and suction sidewalls thereof. A first serpentine circuit is disposed along the pressure sidewall. A second serpentine circuit is disposed along the suction sidewall in parallel with the first circuit. And a third impingement circuit is disposed at the leading edge forward of the first and second circuits.Type: GrantFiled: December 5, 2005Date of Patent: November 20, 2007Assignee: General Electric CompanyInventors: Ching-Pang Lee, Aspi Rustom Wadia, Steven Robert Brassfield
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Patent number: 7293961Abstract: A turbine airfoil includes pressure and suction sidewalls spaced apart to define flow channels extending in span and separated by ribs. Side channels are disposed along one sidewall and spaced from the opposite sidewall by the ribs, and a mid channel bridges the sidewalls. The side and mid channels are arranged in a zigzag serpentine cooling circuit alternating therebetween for transferring heat from the sidewall into the mid channel.Type: GrantFiled: December 5, 2005Date of Patent: November 13, 2007Assignee: General Electric CompanyInventors: Ching-Pang Lee, Aspi Rustom Wadia, Steven Robert Brassfield
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Patent number: 7287959Abstract: A turbine airfoil includes opposite pressure and suction sidewalls, and extends in chord between opposite leading and trailing edges and in span from a root to an outer tip cap. The tip cap bridges the sidewalls, and a flute extends chordally along the pressure sidewall and below the tip cap.Type: GrantFiled: December 5, 2005Date of Patent: October 30, 2007Assignee: General Electric CompanyInventors: Ching-Pang Lee, Aspi Rustom Wadia, John Christopher Brauer