Paul G Acquaviva, Age 60104 Central St, Hampstead, NH 03841

6402471, Jun 11, 2002

Nov 3, 2000

09/706387

Daniel Edward Demers - Ipswich MA
Robert Francis Manning - Newburyport MA
Paul Joseph Acquaviva - Newburyport MA

General Electric Company - Schenectady NY

F01D 518

416 97R, 416 96 R, 416193 A, 415115

A turbine blade includes a platform having an internal cavity formed therein and an airfoil extending radially from the platform. An internal cooling circuit is formed in the airfoil for circulating a coolant therethrough, and at least one supply passage extends between the internal cooling circuit and the internal platform cavity for diverting coolant to the internal platform cavity. The coolant is expelled from holes located in the forward and aft edges of the platform for purging the forward and aft disk wheel spaces and impingement cooling adjacent nozzle bands.

6416284, Jul 9, 2002

Nov 3, 2000

09/706403

Daniel Edward Demers - Ipswich MA
Robert Francis Manning - Newburyport MA
Paul Joseph Acquaviva - Newburyport MA

General Electric Company - Schenectady NY

F01D 518

416 97R, 416 96 R, 416193 A, 415115

A turbine blade includes a platform and an airfoil extending radially from the platform. An internal cooling circuit is formed in the airfoil for circulating a coolant therethrough to cool the airfoil. At least one supply passage is provided to direct some of the coolant that has passed at least partially through the internal cooling circuit onto the platform for cooling the platform.

6183198, Feb 6, 2001

Nov 16, 1998

9/192229

Robert F. Manning - Newburyport MA
Paul J. Acquaviva - Wakefield MA
Daniel E. Demers - Ipswich MA

General Electric Company - Cincinnati OH

F01D 518

416 97R

A gas turbine engine airfoil includes first and second sidewalls joined together at opposite leading and trailing edges, and spaced apart from each other therebetween to define a leading edge channel extending longitudinally from a root to a tip of the airfoil. A plurality of film cooling holes extend through the leading edge and are disposed in flow communication with the leading edge channel. An isolation plenum extends along the first sidewall and adjacent the leading edge channel, and is separated therefrom by a partition having a plurality of inlet holes. A plurality of film cooling gill holes extend through the first sidewall, and are disposed in flow communication with the isolation plenum. Cooling air is channeled from the leading edge channel to the isolation plenum for feeding the gill holes with reduced pressure air.

6099252, Aug 8, 2000

Nov 16, 1998

9/192227

Robert F. Manning - Newburyport MA
Paul J. Acquaviva - Wakefield MA
Daniel E. Demers - Ipswich MA

General Electric Company - Cincinnati OH

F01D 508

416 97R

A gas turbine engine airfoil includes an axial serpentine cooling circuit therein. A plurality of the serpentine circuits are preferably stacked in a radial row along the airfoil trailing edge for cooling thereof.

6036441, Mar 14, 2000

Nov 16, 1998

9/192225

Robert F. Manning - Newburyport MA
Paul J. Acquaviva - Wakefield MA
Daniel E. Demers - Ipswich MA

General Electric Company - Cincinnati OH

F01D 518

416 97R

A gas turbine engine airfoil includes first and second sidewalls joined together at opposite leading and trailing edges, and extending longitudinally from a root to a tip. The sidewalls are spaced apart from each other to define in part first and second adjoining flow chambers extending longitudinally therein, and defined in additional part by corresponding first and second partitions disposed between the sidewalls. The second partition is common to both chambers, and both partitions include respective pluralities of first and second inlet holes sized to meter cooling air therethrough in series between the chambers.