Patents by Inventor Lawrence W. Dunbar
Lawrence W. Dunbar has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 6732502Abstract: An aircraft gas turbine engine includes high and low pressure turbines having respective counter rotatable low pressure inner and outer rotors with low pressure inner and outer shafts in part rotatably disposed co-axially within a high pressure rotor and drivingly connected to first and second fan blade rows and first and second boosters respectively. A bypass duct radially bounded by a fan casing and an annular radially inner bypass duct wall surrounds the boosters axially located between the first and second fan blade rows. The engine has a high pressure compressor operable to produce an overall pressure ratio in a range of about 40-65 and a fan inlet hub to tip radius ratio in a range between 0.20 and 0.35, a bypass ratio in a range of 5-15, an operational fan pressure ratio in a range of 1.4-2.5, and a sum of operational fan tip speeds in a range of 1000 to 2500 feet per second.Type: GrantFiled: March 1, 2002Date of Patent: May 11, 2004Assignee: General Electric CompanyInventors: Jorge F. Seda, Lawrence W. Dunbar, Peter N. Szucs, John C. Brauer, James E. Johnson
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Patent number: 6619030Abstract: An aircraft gas turbine engine assembly includes an inter-turbine frame axially located between high and low pressure turbines. Low pressure turbine has counter rotating low pressure inner and outer rotors with low pressure inner and outer shafts which are at least in part rotatably disposed co-axially within a high pressure rotor. Inter-turbine frame includes radially spaced apart radially outer first and inner second structural rings disposed co-axially about a centerline and connected by a plurality of circumferentially spaced apart struts. Forward and aft sump members having forward and aft central bores are fixedly joined to axially spaced apart forward and aft portions of the inter-turbine frame. Low pressure inner and outer rotors are rotatably supported by a second turbine frame bearing mounted in aft central bore of aft sump member. A mount for connecting the engine to an aircraft is located on first structural ring.Type: GrantFiled: March 1, 2002Date of Patent: September 16, 2003Assignee: General Electric CompanyInventors: Jorge F. Seda, Lawrence W. Dunbar, Philip R. Gliebe, Peter N. Szucs, John C. Brauer, James E. Johnson, Thomas Moniz, Gregory T. Steinmetz
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Publication number: 20030163984Abstract: An aircraft gas turbine engine assembly includes an inter-turbine frame axially located between high and low pressure turbines. Low pressure turbine has counter rotating low pressure inner and outer rotors with low pressure inner and outer shafts which are at least in part rotatably disposed co-axially within a high pressure rotor. Inter-turbine frame includes radially spaced apart radially outer first and inner second structural rings disposed co-axially about a centerline and connected by a plurality of circumferentially spaced apart struts. Forward and aft sump members having forward and aft central bores are fixedly joined to axially spaced apart forward and aft portions of the inter-turbine frame. Low pressure inner and outer rotors are rotatably supported by a second turbine frame bearing mounted in aft central bore of aft sump member. A mount for connecting the engine to an aircraft is located on first structural ring.Type: ApplicationFiled: March 1, 2002Publication date: September 4, 2003Inventors: Jorge F. Seda, Lawrence W. Dunbar, Philip R. Gliebe, Peter N. Szucs, John C. Brauer, James E. Johnson, Thomas Moniz, Gregory T. Steinmetz
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Publication number: 20030163983Abstract: An aircraft gas turbine engine includes high and low pressure turbines having respective counter rotatable low pressure inner and outer rotors with low pressure inner and outer shafts in part rotatably disposed co-axially within a high pressure rotor and drivingly connected to first and second fan blade rows and first and second boosters respectively. A bypass duct radially bounded by a fan casing and an annular radially inner bypass duct wall surrounds the boosters axially located between the first and second fan blade rows. The engine has a high pressure compressor operable to produce an overall pressure ratio in a range of about 40-65 and a fan inlet hub to tip radius ratio in a range between 0.20 and 0.35, a bypass ratio in a range of 5-15, an operational fan pressure ratio in a range of 1.4-2.5, and a sum of operational fan tip speeds in a range of 1000 to 2500 feet per second.Type: ApplicationFiled: March 1, 2002Publication date: September 4, 2003Inventors: Jorge F. Seda, Lawrence W. Dunbar, Peter N. Szucs, John C. Brauer, James E. Johnson
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Patent number: 6550235Abstract: A turbofan engine includes a pulse detonation system to create a temperature rise and a pressure rise within the engine to generate thrust from the engine. The system includes a pulse detonation augmentor including a shock tube sub-system. The shock tube sub-system includes a plurality of shock tubes which mix air and fuel introduced to the pulse detonation augmentor and detonate the mixture. The detonation creates hot combustion gases which are directed from the engine to produce thrust for the engine. Alternatively, the system includes a pulse detonation augmentation system that replaces a core engine of a turbo-fan engine.Type: GrantFiled: February 12, 2002Date of Patent: April 22, 2003Assignee: General Electric CompanyInventors: James E. Johnson, Lawrence W. Dunbar, Lawrence Butler
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Publication number: 20030029160Abstract: A turbofan engine includes a pulse detonation system to create a temperature rise and a pressure rise within the engine to generate thrust from the engine. The system includes a pulse detonation augmentor including a shock tube sub-system. The shock tube sub-system includes a plurality of shock tubes which mix air and fuel introduced to the pulse detonation augmentor and detonate the mixture. The detonation creates hot combustion gases which are directed from the engine to produce thrust for the engine. Alternatively, the system includes a pulse detonation augmentation system that replaces a core engine of a turbo-fan engine.Type: ApplicationFiled: February 12, 2002Publication date: February 13, 2003Inventors: James E. Johnson, Lawrence W. Dunbar, Lawrence Butler
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Patent number: 6442930Abstract: A turbofan engine includes a pulse detonation system to create a temperature rise and a pressure rise within the engine to generate thrust from the engine. The system includes a pulse detonation augmentor including a shock tube sub-system. The shock tube sub-system includes a plurality of shock tubes which mix air and fuel introduced to the pulse detonation augmentor and detonate the mixture. The detonation creates hot combustion gases which are directed from the engine to produce thrust for the engine. Alternatively, the system includes a pulse detonation augmentation system that replaces a core engine of a turbo-fan engine.Type: GrantFiled: March 31, 2000Date of Patent: September 3, 2002Assignee: General Electric CompanyInventors: James E. Johnson, Lawrence W. Dunbar, Lawrence Butler
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Patent number: 5820345Abstract: A split fan for providing lift for an aircraft is described. In one embodiment, a main engine shaft extends to the split fan, and a portion of the split fan is located at an elevation above the main engine shaft and a portion of the split fan is located at an elevation below the main engine shaft. In the one embodiment, the split fan includes an outer casing configured to be mounted to a fuselage of the aircraft, a first stage rotor including a shaft, a gear secured to the shaft, and a plurality of rotor blades radially extending from the shaft. The split fan also includes a second stage rotor including a shaft, a gear secured to the shaft, and a plurality of blades radially extending from the shaft. A drive shaft having a first end and a second end is coupled at the drive shaft first end to the main engine shaft.Type: GrantFiled: December 20, 1996Date of Patent: October 13, 1998Assignee: General Electric CompanyInventors: Rollin G. Giffin, III, Lawrence W. Dunbar, Ronald F. Petsch
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Patent number: 5381655Abstract: A variable cycle jet engine is provided with a mixing duct assembly which mixes core engine exhaust gas with bypass air when the engine is operating in a turbofan mode and which blocks flow from the core engine and isolates the core engine from the bypass flow when the engine is operating as a ramjet.Type: GrantFiled: May 10, 1993Date of Patent: January 17, 1995Assignee: General Electric CompanyInventors: Robert J. Orlando, Lawrence W. Dunbar
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Patent number: 5261229Abstract: An array of chutes is permanently mounted within the flowpath of an exhaust nozzle of an aircraft jet engine for entraining and mixing ambient air with the exhaust gas so as to reduce the noise level of aircraft, particularly during take-off. In order to provide good engine performance during all modes of jet engine operation, a convergent-divergent flap assembly is arranged downstream from the chutes for controlling the nozzle throat and exit areas when the chutes are closed.Type: GrantFiled: August 3, 1992Date of Patent: November 16, 1993Assignee: General Electric CompanyInventors: Eric A. Ford, Jeremiah P. Wolf, Lawrence W. Dunbar