Daniel R Demers

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:

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.

US Patent:

20140348636, Nov 27, 2014

Filed:

Dec 21, 2012

Appl. No.:

14/368962

Inventors:

- Schenectady NY, US
Marshall Scott Allen - Amesbury MA, US
Daniel Edward Demers - Ipswich MA, US
Robert Francis Manning - Newburyport MA, US

International Classification:

F01D 5/18
F01D 9/02

US Classification:

415115, 415175, 416 96 R

Abstract:

An airfoil cooling circuit includes an impingement cooling circuit and a serpentine cooling circuit. An airfoil for use in a gas turbine engine having a cooling circuit which includes an impingement cooling circuit and a serpentine cooling circuit