AUREEN C CURRIN
Engineering in Reading, MA
License number
Massachusetts 45178
Issued Date
Jan 13, 2003
Expiration Date
Jun 30, 2018
Type
Mechanical Engineer
Address
Address
Reading, MA 01867
Professional information
Methods And Apparatus For Fabricating Gas Turbine Engine Combustors
US Patent:
7325403, Feb 5, 2008
Filed:
Mar 26, 2007
Appl. No.:
11/728387
Inventors:
Aureen Cyr Currin - Reading MA, US
Kamil Bazyli Kaczorowski - Warszawa, PL
John Carl Jacobson - Melrose MA, US
Joseph Douglas Monty - Boxford MA, US
Kamil Bazyli Kaczorowski - Warszawa, PL
John Carl Jacobson - Melrose MA, US
Joseph Douglas Monty - Boxford MA, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F23R 3/14
US Classification:
60772, 2989002
Abstract:
A method for fabricating a dome assembly for a gas turbine engine combustor includes forming an annular dome plate including a plurality of substantially circular eyelets circumferentially spaced thereon, coupling a seal plate to the dome plate at each eyelet such that an opening defined in each seal plate is aligned substantially concentrically with respect to a respective eyelet, coupling a baffle to each seal plate such that an opening defined in each baffle is aligned substantially concentrically with respect to a respective eyelet, and coupling a swirler assembly having an integrally formed swirler and flare cone to each seal plate such that the flare cone extends at least partially through the baffle opening, and such that cooling air may be directed towards the flare cone through openings formed in the assembly.
Methods And Apparatus For Fabricating Gas Turbine Engine Combustors
US Patent:
7246494, Jul 24, 2007
Filed:
Sep 29, 2004
Appl. No.:
10/953318
Inventors:
Aureen Cyr Currin - Reading MA, US
Kamil Bazyli Kaczorowski - Warsaw, PL
John Carl Jacobson - Melrose MA, US
Joseph Douglas Monty - Boxford MA, US
Kamil Bazyli Kaczorowski - Warsaw, PL
John Carl Jacobson - Melrose MA, US
Joseph Douglas Monty - Boxford MA, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F23R 3/14
US Classification:
60748, 60752
Abstract:
A method for fabricating a dome assembly for a gas turbine engine combustor includes forming an annular dome plate including a plurality of substantially circular eyelets circumferentially spaced thereon, coupling a seal plate to the dome plate at each eyelet such that an opening defined in each seal plate is aligned substantially concentrically with respect to a respective eyelet, coupling a baffle to each seal plate such that an opening defined in each baffle is aligned substantially concentrically with respect to a respective eyelet, and coupling a swirler assembly having an integrally formed swirler and flare cone to each seal plate such that the flare cone extends at least partially through the baffle opening, and such that cooling air may be directed towards the flare cone through openings formed in the assembly.
Turbine Nozzle Segment Band Cooling
US Patent:
6227798, 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
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.