Thomas E Demarche

6652235, Nov 25, 2003

May 31, 2002

10/160527

Sean Robert Keith - Fairfield OH
Thomas Edward DeMarche - Boxford MA
John Robert Staker - Cincinnati OH
Judd Dodge Tressler - Mason OH

General Electric Company - Schenectady NY

F01D 518

416 92, 416 97 R

A method for fabricating a rotor blade for a gas turbine engine facilitates reducing operating temperatures of a tip portion of the rotor blade. The method comprises forming an airfoil including a first sidewall and a second sidewall connected at a leading edge and a trailing edge to define a cavity therein, wherein the first and second sidewalls extend radially between a rotor blade root and a rotor blade tip plate, and forming a first tip wall extending from the rotor blade tip plate along the first sidewall, such that at least a portion of the first tip wall is at least partially recessed with respect to the rotor blade first sidewall to define a tip shelf that extends from the airfoil trailing edge towards the airfoil leading edge. A second tip wall is formed to extend from the rotor blade tip plate along the second sidewall.

6746209, Jun 8, 2004

May 31, 2002

10/160548

Thomas Edward DeMarche - Boxford MA
Robert Francis Manning - Newburyport MA

General Electric Company - Schenectady NY

F01D 906

416 97R

A method for fabricating a nozzle for a gas turbine engine facilitates extending a useful life of the nozzles. The nozzle includes an airfoil. The method includes forming the airfoil to include a suction side and a pressure side connected at a leading edge and a trailing edge such that a cooling cavity and a cooling circuit are defined within the airfoil, wherein the suction side and the pressure side extend radially between a tip and a root. The method also includes forming a plurality of cooling slots within the airfoil that extend from the cooling circuit towards the airfoil trailing edge, and forming a control vane within the cooling circuit to facilitate maintaining a substantially constant cooling effectiveness within the cooling circuit.

6749396, Jun 15, 2004

Jun 17, 2002

10/173009

Vincent Anthony Barry - Rowley MA
Thomas Edward Demarche - Boxford MA

General Electric Company - Schenectady NY

F01D 518

415115, 416 97 R

A flowpath wall is provided for bounding hot combustion gases in a gas turbine engine. The wall includes opposite outer and inner surfaces and a plurality of cooling holes extending therebetween. A thermal barrier coating is bonded to the outer surface and covers blind the holes thereat.

6779597, Aug 24, 2004

Jan 16, 2002

10/053534

Thomas Edward DeMarche - Boxford MA
Robert Francis Manning - Newburyport MA

General Electric Company - Schenectady NY

F28F 312

165169, 165908, 415115

A multiple impingement cooled structure is provided having two or more stages of impingement cooling wherein the stages are arranged so as to have substantially constant cooling effectiveness.

7246999, Jul 24, 2007

Oct 6, 2004

10/959615

Robert Francis Manning - Newburyport MA, US
Thomas Edward Demarche - Boxford MA, US
David Allen Flodman - Rowley MA, US

General Electric Company - Schenectady NY

B63H 1/14

416 97R, 415115, 415116

A turbine airfoil includes an internal cooling circuit between opposite pressure and suction sidewalls. The pressure sidewall includes a row of outlet slots for the circuit separated by converging partitions. Each slot includes an inlet, throat, and diverging outlet. Each of the partitions includes a step in a converging sidewall thereof for increasing divergence of the slots to diffuse coolant discharged therethrough.

54723167, Dec 5, 1995

Sep 19, 1994

8/308227

Mohammad E. Taslim - Needham MA
Samuel D. Spring - Stratham NH
Thomas E. Demarche - Boxford MA

General Electric Company - Cincinnati OH

F01D 518

416 97R

An improved cooling passage configuration for a gas turbine engine airfoil is disclosed for enhancing convective cooling over that afforded by conventional wall turbulator ribs. An internal cooling passage bounded by pressure and suction side walls and at least one partition has raised turbulator ribs disposed on at least one side wall and the partition. A side wall turbulator rib extends over at least a portion of the side wall and abuts the partition. A turbulator rib disposed on the partition extends from a point spaced from the wall rib to the opposed side wall. The gap formed between the partition rib and wall rib accelerates a coolant flow passing therethrough, locally enhancing convective heat transfer. Partition ribs may be aligned with or offset from the wall ribs in the spanwise direction and may be normal to the primary direction of cooling flow or angled thereto. Convective heat transfer is particularly enhanced in flow passages having cavity height blockage due to wall ribs greater than about 10%.

45741123, Mar 4, 1986

Dec 23, 1983

6/564989

Richard D. Breault - Coventry CT
Richard D. Sawyer - Canton CT
Thomas E. DeMarche - New Haven CT

United Technologies Corporation - Hartford CT

H01M 824

429 26

A cooling system 24 for an electrochemical cell stack 12 is disclosed. Various construction details which avoid plugging of the cooling system during long term operation with a cooling fluid having dissolved species and suspended particles, such as water, are discussed. The cooling system includes spaced apart cooler assemblies 30. Conduits 32 for supplying cooling fluid to the cooler assemblies include sets of cooling tubes 74 in serial flow communication.

53972171, Mar 14, 1995

Nov 24, 1992

7/980832

Thomas E. DeMarche - Boxford MA
Mario E. Abreu - San Diego CA

General Electric Company - Cincinnati OH

F01D 518
F01D 902

416 97R

A pulse-cooled gas turbine engine assembly includes a hollow airfoil and a fluidic oscillator joined thereto. The fluidic oscillator discharges pressurized cooling air inside the airfoil at a predetermined pulsation frequency for cooling the airfoil.