James William Bartos

US Patent:

6584778, Jul 1, 2003

Filed:

May 11, 2000

Appl. No.:

09/567240

Inventors:

James Alan Griffiths - West Chester OH
Mitchell Donald Smith - Morrow OH
James William Bartos - Wilmington OH

Assignee:

General Electric Co. - Schenectady NY

International Classification:

F02C 712

US Classification:

60782, 60730, 60736, 60806, 602261

Abstract:

A cooling air cooling system is selectively operable to reduce fuel gum deposits within the cooling system during gas turbine engine operations. The cooling system includes a recirculating loop that includes at least three heat exchangers in fluid communication with the recirculating loop. A first heat exchanger cools cooling air supplied to the gas turbine engine. A second heat exchanger cools fluid exiting the first of the heat exchangers with fan discharge air prior to the fluid entering the third heat exchanger. A third heat exchanger uses combustor main fuel flow to cool the fluid circulating in the recirculating loop.

US Patent:

62610546, Jul 17, 2001

Filed:

Jan 25, 1999

Appl. No.:

9/235914

Inventors:

Ronald Scott Bunker - Niskayuna NY
James William Bartos - Wilmington OH
Nicholas Damlis - Cincinnati OH
Mark Eugene Noe - Hamilton OH
Steven Douglas Ward - Cincinnati OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 518

US Classification:

415115

Abstract:

An apparatus and method including a closed-circuit coolable airfoil assembly for use and exposure in a hot fluid flow of a machine portion. The assembly includes a first flange configured to be connected with a casing of the machine portion. A second flange is configured to be connected with the casing. An airfoil is connected with and between the first flange and the second flange, the airfoil including a peripheral portion surrounding a medial portion. At least one channel is disposed in the peripheral portion, the channel extending between the first flange and the second flange and being in flow communication with each. A closed flow path is formed from the casing and through the first flange, the second flange and the channel in which a coolant fluid can pass to cool the airfoil assembly.

US Patent:

41991516, Apr 22, 1980

Filed:

Aug 14, 1978

Appl. No.:

5/933257

Inventors:

James W. Bartos - Wilmington OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F16J 1528

US Classification:

277 1

Abstract:

An annular E-seal is installed in a retainer ring in such a way as to have limited degrees of freedom in the radial and axial directions while being retained in a groove of the retainer ring during component assembly and disassembly. The relative diameters of the retainer ring and the seal leg are such that installation or removal of the seal can only be accomplished by a deliberate tipping of the seal leg in such a way as to reduce its effective projected radial height. Thus, once installed, the seal is connected to and remains with one of the elements defining the gap to be sealed.

US Patent:

58679804, Feb 9, 1999

Filed:

Dec 17, 1996

Appl. No.:

8/767932

Inventors:

James W. Bartos - Wilmington OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02K 302
F02K 310

US Classification:

602263

Abstract:

A multiple bypass turbofan engine includes a core Brayton Cycle gas generator with a fuel rich burning combustor and is provided with a variable supercharged bypass duct around the gas generator with a supercharging means in the supercharged bypass duct powered by a turbine not mechanically connected to the gas generator. The engine further includes a low pressure turbine driven forward fan upstream and forward of an aft fan and drivingly connected to a low pressure turbine by a low pressure shaft, the low pressure turbine being aft of and in serial flow communication with the core gas generator. A fan bypass duct is disposed radially outward of the core engine assembly and has first and second inlets disposed between the forward and aft fans. 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. A supercharger means for compressing air is drivingly connected to the low pressure turbine and is disposed in the inlet duct.