John A Hebert

US Patent:

7513116, Apr 7, 2009

Filed:

Nov 9, 2004

Appl. No.:

10/984951

Inventors:

John A. Hebert - Fennville MI, US
Douglas A. Diemer - Zeeland MI, US

Assignee:

Woodward FST, Inc. - Zeeland MI

International Classification:

F02C 1/00
F02G 3/00

US Classification:

60748, 60740

Abstract:

A fuel injector for a gas turbine engine includes a support member and a nozzle tip disposed on the support member with a deformable, removable metallic or non-metallic seal member disposed between facing sealing surfaces of the support member and a shroud member of the nozzle tip. The deformable seal member includes one or more fuel passages through which fuel in one or more fuel circuits flows with the seal member sealingly separating the first and second fuel circuits and preventing external fuel leakage from the nozzle tip. The nozzle tip can include an inner fuel swirler that includes one or more swirler slots wherein each slot is so angled in an axial direction toward the discharge orifice of the nozzle tip assembly that operation of the nozzle tip assembly is unaffected by changes in fuel viscosity.

US Patent:

20070193272, Aug 23, 2007

Filed:

Feb 21, 2006

Appl. No.:

11/358732

Inventors:

John Hebert - Fennville MI, US
James Sager - Holland MI, US

International Classification:

F02C 1/00
F02M 63/00
F02C 3/16
B05B 7/10

US Classification:

060740000, 060735000, 060737000, 239533200, 239399000, 239403000

Abstract:

A fuel injector for a gas turbine engine includes a support member having a fuel discharge nozzle proximal an end thereof, a first tubular heat shield disposed about a length of the support member to form a thermal insulating space therebetween, and a second tubular heat shield disposed about the first heat shield to form an annular air flow passage between the first heat shield and the second heat shield. The second heat shield has one or more upstream inlet openings for entry of pressurized air for flow through the air flow passage to a downstream discharge opening disposed about the fuel discharge nozzle to permit fuel to be discharged therefrom to a combustor of the gas turbine engine while pressurized air is discharged from the discharge opening. The Mach number of the air flowing through the air flow passage is controlled by the spacing between the first and second heat shields to improve cooling of the heat shields, fuel atomization and combustor fuel/air mixing.