Daniel A Demers

US Patent:

6991430, Jan 31, 2006

Filed:

Apr 7, 2003

Appl. No.:

10/408293

Inventors:

Philip Francis Stec - Medford MA, US
Daniel Edward Demers - Ipswich MA, US
Richard Ludwig Schmidt - Marblehead MA, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 5/18

US Classification:

416 97R, 415115, 4151731, 416 92, 416228

Abstract:

A turbine blade squealer tip has a continuous squealer tip wall extending radially outwardly from and continuously around a tip cap. A recessed tip wall portion of the tip wall is recessed inboard from a pressure side of an airfoil outer wall of an airfoil of the blade forming a tip shelf therebetween. A plurality of film cooling shelf holes are disposed through the tip shelf to an internal cooling circuit of the blade and are spaced away from a junction between the recessed tip wall portion and the tip shelf. The exemplary embodiment of the airfoil includes shelf hole centerlines of the holes passing through pierce points in the shelf. At least a majority of the shelf hole centerlines are angled in outboard directions away from and outboard of the squealer tip wall. A majority of centerlines are angled away from vertical lines passing through the pierce points at first component angles in a range between 2 degrees and 16 degrees.

US Patent:

7377742, May 27, 2008

Filed:

Oct 14, 2005

Appl. No.:

11/250660

Inventors:

Jason David Shapiro - Methuen MA, US
Daniel Demers - Ipswich MA, US
Robert Patrick Tameo - Peabody MA, US
Tyler F. Hooper - Amesbury MA, US
Robert Alexander Nicoll - Beverly MA, US
Douglas Patrick Probasco - Peabody MA, US

Assignee:

General Electric Company - Schenectady NY

International Classification:

F01D 25/26

US Classification:

415108, 415115, 4151821

Abstract:

A method for assembling a gas turbine engine includes coupling a rotor assembly including a plurality of rotor blades about a rotatable main shaft of the gas turbine engine. The main shaft is aligned in an axial direction of the gas turbine engine. A shroud assembly is coupled to the gas turbine engine. The shroud assembly includes a plurality of shroud segments circumferentially coupled about the rotor assembly such that a shroud spacing gap is formed in the axial direction between adjacent shroud segments. A cooling fluid source is coupled to each shroud segment such that cooling fluid is channeled through each shroud segment into a corresponding shroud spacing gap to facilitate positive purge flow through the shroud spacing gap.

US Patent:

55557210, Sep 17, 1996

Filed:

Sep 28, 1994

Appl. No.:

8/313951

Inventors:

John J. Bourneuf - Jamaica Plain MA
Dean T. Lenahan - Cinncinnati OH
Daniel E. Demers - Ipswich MA
Larry W. Plemmons - Fairfield OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02C 712

US Classification:

60 3975

Abstract:

A turbine cooling supply circuit for a gas turbine engine is disclosed in which the flow of coolant through the engine is directed to minimize temperature rise prior to discharge into the turbine. Bleed air from an impeller stage of a compressor is channeled along a backwall thereof into a cavity disposed radially inwardly of a combustor casing. The cavity is divided by a lightweight tubular member having a circumferentially uniform contour into a non-flow zone proximate the casing and a flow zone proximate a rotor. Maintenance of a high tangential flow component in the bleed flow in the flow zone facilitates discharge of the flow through apertures in a rotor into a bore portion thereof, minimizing work input and temperature rise of the coolant. Further, the coolant is isolated from the hot casing wall and nonuniform structures disposed thereon, thereby reducing heat flux and temperature rise associated with aerodynamic drag caused by increased surface area, nonuniform interruptions in the stationary surface or any combination thereof. Features are incorporated in the tubular member to provide margin against buckling.

US Patent:

42970776, Oct 27, 1981

Filed:

Jul 9, 1979

Appl. No.:

6/055833

Inventors:

George A. Durgin - Schenectady MA
Daniel E. Demers - Melrose MA

Assignee:

Westinghouse Electric Corp. - Pittsburgh PA

International Classification:

F01D 508

US Classification:

416 97R

Abstract:

A hollow gas turbine vane is shown enclosing, in spaced relation, a vane insert for receiving cooling air. The insert has a plurality of apertures for selectively directing jets of the cooling air against the internal walls of the vane. A portion of the air is discharged from within the vane chamber through a slit in the trailing edge which contains cooling pins extending transversely thereacross to maintain the slit dimensionally stable and also induce turbulence in the exhausting cooling air to improve its cooling effectiveness. Certain apertures in the insert adjacent the trailing edge are selectively directed to cause jets of the cooling air to impinge at the base of certain of the pins in the inlet area of the slit to promote turbulence in the air entering the slit and adjacent the internal face, thereby maximizing heat transfer from the slit walls to the air.

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