JAMES MATTHEW JOHNSON
Pilots at Drew Dr, Hamilton, OH

6442930, Sep 3, 2002

Mar 31, 2000

09/540566

James E. Johnson - Hamilton OH
Lawrence W. Dunbar - Cincinnati OH
Lawrence Butler - Cincinnati OH

General Electric Company - Schenectady NY

F02K 308

602261, 60247, 60261

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.

4064692, Dec 27, 1977

Jun 2, 1975

5/583056

James Edward Johnson - Hamilton OH
Tom Foster - Cincinnati OH
Roy Duncan Allan - Cincinnati OH

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC

F02K 306, F02K 112

60261

A design technique, method, and apparatus for varying the bypass ratio and modulating the flow of a gas turbine engine of the bypass type in order to achieve improved mixed mission performance. The disclosed preferred embodiments each include a gas flow control system for management of core and bypass stream pressure comprising diverter valve means downstream of the core engine to selectively mix or separate the core and bypass exhaust streams. The flow control system may also include variable geometry means for maintaining the engine inlet airflow at a matched design level at all flight velocities. Each preferred embodiment thus may be converted from a high specific thrust mixed flow cycle at supersonic velocities to a lower specific thrust separated flow turbofan system at subsonic velocities with a high degree of flow variability in each mode of operation, wherein the engine inlet airflow may be maintained at a matched design level at all engine velocities. To further improve flow flexibility and assist in maintaining the engine inlet airflow matched to a design level throughout a variable velocity range, the flow control system may include a split fan in conjunction with two concentric bypass ducts. The disclosed variable cycle engine techniques, methods, and apparatus result in significantly reduced inlet and after-body drag levels and result in significantly improved installed fuel consumption for mixed mission aircraft.

5809772, Sep 22, 1998

Mar 29, 1996

8/625498

Rollin G. Giffin - Cincinnati OH
James E. Johnson - Hamilton OH
David W. Crall - Loveland OH
John W. Salvage - Jamesville NY
Peter N. Szucs - West Chester OH

General Electric Company - Cincinnati OH

F02K 302, F02K 307

602261

A multiple bypass turbofan engine including a core engine assembly has a fan bypass duct radially outward of the core engine assembly and has first and second inlets disposed between forward and aft fans driven by a low pressure turbine and a core engine turbine respectively. An inlet duct having an annular duct wall is disposed radially inward of the bypass duct and connects the second inlet to the bypass duct and has disposed within a supercharger means for compressing air which is drivingly connected to the core turbine. One embodiment of the aft fan may have radially inner and outer rows of aft fan vane airfoils separated by a non-rotatable portion of the annular duct wall such that the outer row of aft fan vane airfoils are disposed in the inlet duct and at least one of the aft fan vane airfoils is and, preferably, all of which are, independently variable. Radially inner and outer rows of aft fan rotor blade airfoils separated by a rotatable portion of the annular duct wall such that the outer row of aft fan rotor blade airfoils are disposed in the inlet duct adjacent to and longitudinally aft of radially inner and outer rows of aft fan vane airfoils, respectively. The radially outer rows of aft fan vane and rotor blade airfoils provide the supercharger means.

5402638, Apr 4, 1995

Oct 4, 1993

8/131515

James E. Johnson - Hamilton OH

General Electric Company - Cincinnati OH

F02K 3075

60204

A FLADE aircraft gas turbine engine having a FLADE duct circumscribing a preferably variable cycle inner gas turbine engine. A FLADE fan is disposed in the FLADE duct radially outward of and drivenly connected to a first fan disposed in a first fan duct of the engine. The inlet of the first fan duct is sized to receive essentially the full mass airflow of the engine at full power conditions with the FLADE duct inlet essentially closed off. The engine is further designed and operable to fully open the inlet of the flade duct at predetermined part power flight conditions to avoid spillage drag and essentially close it at full power conditions such as take off. Another embodiment relates to a supersonic engine which operates the FLADE fan fully open at supersonic cruise flight conditions and has a FLADE duct inlet which is sized essentially sufficiently large enough to receive essentially only the engine inlet boundary layer flow and pass it though the FLADE duct and not through the inner engine where it would decrease the inner engine efficiency.

5694768, Dec 9, 1997

Feb 23, 1990

7/484083

James Edward Johnson - Hamilton OH
Elmore Verne Sprunger - Cincinnati OH
John Robert Simmons - Cincinnati OH

General Electric Company - Cincinnati OH

F02K 302, F02K 3075

602263

An improved variable cycle turbofan-ramjet engine is disclosed. The engine includes a split fan assembly, a bypass channel surrounding a core engine and a mode selector valve for selectively bypassing air around an aft fan and the core engine. In a first, single bypass mode of operation, the mode selector valve allows air to flow through both a forward fan and the aft fan, and a portion of which bypasses the core engine. In a second, double bypass mode of operation, the mode selector valve allows air from the forward fan to bypass the aft fan and a portion of the air from the forward fan to bypass the core engine. In a third, ramjet mode of operation, the mode selector vane bypasses air around the aft fan and the core engine and the core engine is shut down for ramjet operation. In the preferred embodiment, the forward fan is allowed to windmill and powers a fuel pump connected thereto for providing fuel to a ram burner of the engine for ramjet operation.

4080785, Mar 28, 1978

May 3, 1976

5/682307

Bernard L. Koff - Cincinnati OH
Raymond E. Budinger - Montgomery OH
James E. Johnson - Hamilton OH

General Electric Company - Cincinnati OH

F02K 116, F02K 306

60226R

A turbofan engine is provided with a core engine, a first fan and a second fan. First and second fan ducts are provided for bypassing a portion of the air flow leaving the fans around the core engine. One of these fan ducts has its inlet disposed downstream of the second fan, while the second duct has its inlet disposed between the first and second fan. Means are provided for varying the proportion of the flow of air among the fan ducts and core engine. Integrated, or separate coaxial nozzles are provided for receiving the flows from the individual fan ducts and core engine and exhausting these flows into the atmosphere.

7475545, Jan 13, 2009

Apr 29, 2005

11/118698

James Edward Johnson - Hamilton OH, US

General Electric Company - Schenectady NY

F02K 3/10

60761, 60262

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.

7395657, Jul 8, 2008

Oct 20, 2003

10/689289

James Edward Johnson - Hamilton OH, US

General Electric Company - Schenectady NY

F02K 3/00, F02K 3/072

602261, 602263, 60268, 244 53 B

An aircraft propulsion system includes a gas turbine engine having a fan section, at least one row of FLADE fan blades disposed radially outwardly of and drivingly connected to the fan section, the row of FLADE fan blades radially extending across a FLADE duct circumscribing the fan section, an engine inlet including a fan inlet to the fan section and an annular FLADE inlet to the FLADE duct. A fixed geometry inlet duct is in direct flow communication with the engine inlet. The fan section may include only a single direction of rotation fan or alternatively axially spaced apart first and second counter-rotatable fans in which the FLADE fan blades are drivingly connected to one of the first and second counter-rotatable fans. The row of FLADE fan blades may be disposed between rows of variable first and second FLADE vanes.

7877980, Feb 1, 2011

Dec 28, 2006

11/617371

James Edward Johnson - Fairfield OH, US

General Electric Company - Schenectady NY

F02K 3/02

602261

A gas turbine engine includes a turbomachinery core operable to generate a flow of pressurized combustion gases at a variable flow rate, while maintaining a substantially constant core pressure ratio; a rotating fan disposed upstream of the core, the fan adapted to extract energy from the core and generate a first flow of air which is compressed at a first pressure ratio; and at least a first bypass duct surrounding the core downstream of the fan adapted to selectively receive at least a first selected portion of the first flow which is compressed at a second pressure ratio lower than the first pressure ratio, and to bypass the first selected portion around the core, thereby varying a bypass ratio of the engine. The fan is adapted to maintain a flow rate of the first flow substantially constant, independent of the bypass ratio.

7216475, May 15, 2007

Nov 21, 2003

10/719884

James Edward Johnson - Hamilton OH, US

General Electric Company - Schenectady NY

F02K 3/02, F02K 1/38

602261, 60262

An aft FLADE gas turbine engine includes a fan section drivenly connected to a low pressure turbine section, a core engine located between the fan section and the low pressure turbine section, a fan bypass duct circumscribing the core engine and in fluid communication with the fan section, and a mixer downstream of the low pressure turbine section and in fluid communication with the fan bypass duct, and an aft FLADE turbine downstream of the mixer. At least one row of aft FLADE fan blades disposed radially outwardly of and connected to the aft FLADE turbine and radially extending across a FLADE duct circumscribing the fan bypass duct. The aft FLADE turbine may be a free turbine or connected to and rotatable with the low pressure turbine section. A power extraction apparatus may be disposed within the engine and drivenly connected to the aft FLADE turbine.