Daniel J Demers

US Patent:

6402471, Jun 11, 2002

Filed:

Nov 3, 2000

Appl. No.:

09/706387

Inventors:

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

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 518

US Classification:

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

Abstract:

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.

US Patent:

6416284, Jul 9, 2002

Filed:

Nov 3, 2000

Appl. No.:

09/706403

Inventors:

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

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 518

US Classification:

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

Abstract:

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.

US Patent:

6890153, May 10, 2005

Filed:

Apr 29, 2003

Appl. No.:

10/425262

Inventors:

Daniel Edward Demers - Ipswich MA, US
Mohammad Esmaail Taslim - Needham MA, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D005/08

US Classification:

416 97R, 416 96 R, 415 1, 415115

Abstract:

A turbine airfoil includes pressure and suction sidewalls joined together at opposite leading and trailing edges, and at a forward bridge spaced behind the leading edge to define a flow channel. The bridge includes a row of impingement holes. The flow channel includes a row of fins behind the leading edge, a row of first turbulators behind the pressure sidewall, and row of second turbulators behind the suction sidewall. The fins and turbulators have different configurations for increasing internal surface area and heat transfer for back side cooling the leading edge by the cooling air.

US Patent:

20090293495, Dec 3, 2009

Filed:

May 29, 2008

Appl. No.:

12/129375

Inventors:

Victor Hugo Silva Correia - Milton Hills NH, US
Daniel Edward Demers - Ipswich MA, US
Robert Francis Manning - Newburyport MA, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F02C 7/18
F01D 9/02

US Classification:

60782, 415115

Abstract:

A turbine airfoil for a gas turbine engine includes: (a) spaced-apart pressure and suction sidewalls extending between a leading edge and a trailing edge; (b) a first cavity disposed between the pressure and suction sidewalls, the first cavity being adapted to be fed cooling air from a source within the engine, and connected to at least one film cooling hole which communicates with an exterior surface of the airfoil; (c) a second cavity disposed between the pressure and suction sidewalls, the second cavity being adapted to be fed cooling air from a source within the engine, and connected to at least one film cooling hole which communicates solely with the suction sidewall of the airfoil; and (d) a metering structure adapted to substantially restrict air flow into the second cavity.

US Patent:

61831980, Feb 6, 2001

Filed:

Nov 16, 1998

Appl. No.:

9/192229

Inventors:

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

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 518

US Classification:

416 97R

Abstract:

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.

US Patent:

62277987, May 8, 2001

Filed:

Nov 30, 1999

Appl. No.:

9/451279

Inventors:

Daniel E. Demers - Ipswich MA
Mark D. Gledhill - Hamilton MA
Aureen C. Currin - Reading MA
Gene C. F. Tsai - Lexington MA

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 514
F03B 1100

US Classification:

415115

Abstract:

A gas turbine engine nozzle segment includes at least two circumferentially adjacent vanes joined together along an interface between the vanes. Each of the vanes includes a hollow airfoil disposed between radially inner and outer band panels and a cooling air intake duct leading to a hollow interior of the airfoil for directing cooling air into the hollow interior. The intake duct has a duct wall protruding radially outward from the outer band panel and at least one impingement cooling hole disposed through the intake duct wall and circumferentially and radially inwardly angled. A flange portion extends circumferentially along the outer band panel and an opening in the flange portion is in fluid communication with the intake duct. The hollow airfoil, radially inner and outer band panels, intake duct wall, and flange portion are integrally formed and, preferably, integrally cast such that the vane is a single piece integrally cast vane.

US Patent:

60992522, Aug 8, 2000

Filed:

Nov 16, 1998

Appl. No.:

9/192227

Inventors:

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

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 508

US Classification:

416 97R

Abstract:

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.

US Patent:

60364416, Mar 14, 2000

Filed:

Nov 16, 1998

Appl. No.:

9/192225

Inventors:

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

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F01D 518

US Classification:

416 97R

Abstract:

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.

Address:

6 Lavin Ct, Sanford, ME 04073

VIN:

1FAFP34NX7W252302

Make:

FORD

Model:

FOCUS

Year:

2007