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US 7,581,398 B2Granted
Purged flameholder fuel shield
AssigneeGeneral Electric Company
InventorsJeffrey Carl Mayer, Brian Benscoter Roberts
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AssigneeGeneral Electric Company
InventorsJeffrey Carl Mayer, Brian Benscoter Roberts
Estimating the term…
A fuel shield is configured for use in the afterburner of a turbofan aircraft engine. The shield includes wings obliquely joined together at a nose to conform with the leading edge region of a flameholder vane. A hood is joined to the wings and extends obliquely therefrom to conform with a supporting outer shell of the flameholder.
An afterburner for a turbofan engine comprising:
For a turbofan engine having an afterburner with a row of flameholder vanes mounted to radially outer and inner annular shells, and each vane including first and second sidewalls jointed together at opposite leading and trailing edges, a fuel shield comprising:
For a turbofan engine having an afterburner with a row of flameholder vanes mounted between radially outer and inner shells, and each vane including first and second sidewalls extending between leading and trailing edges, a fuel shield comprising:
Dependencies are inferred from the claim text.
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From the US filing history. Foreign family members aren’t listed.
By means of pivoted flaps: of three series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure, the…
With supplementary heating of the working fluid; Control thereof: by after-burners
Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants: incorporating fuel injection means
Aeronautics or air transport: efficient propulsion technologies, e.g. for aircraft
About 1 year of term left · ends 28 Oct 2027 (estimated)
The present invention relates generally to gas turbine engines, and, more specifically, to augmented turbofan engines.
The typical turbofan gas turbine aircraft engine includes in serial flow communication a fan, compressor, combustor, high pressure turbine (HPT), and low pressure turbine (LPT). Inlet air is pressurized through the fan and compressor and mixed with fuel in the combustor for generating hot combustion gases.
The HPT extracts energy from the combustion gases to power the compressor through a corresponding drive shaft extending therebetween. The LPT extracts additional energy from the combustion gases to power the fan through another drive shaft extending therebetween.
The invention, in accordance with preferred and exemplary embodiments, together with further objects and advantages thereof, is more particularly described in the following detailed description taken in conjunction with the accompanying drawings in which:
FIG. 1 is an axial sectional schematic view of exemplary turbofan aircraft gas turbine engine having an afterburner.
FIG. 2 is an enlarged axial sectional view of a portion of the annular flameholder assembly in the afterburner illustrated in FIG. 1.
Illustrated schematically in FIG. 1 is an aircraft turbofan gas turbine engine 10 configured for powering an aircraft in flight. The engine includes in serial flow communication a row of variable inlet guide vanes (IGVs) 12, multistage fan 14, multistage axial compressor 16, combustor 18, single stage high pressure turbine (HPT) 20, single stage low pressure turbine (LPT) 22, and a rear frame 24 all coaxially disposed along the longitudinal or axial centerline axis 26.
During operation, air 28 enters the engine through the IGVs 12 and is pressurized in turn through the fan 14 and compressor 16. Fuel is injected into the pressurized air in the combustor 18 and ignited for generating hot combustion gases 30.
Energy is extracted from the gases in the HPT 20 for powering the compressor 16 through a drive shaft extending therebetween. Additional energy is extracted from the gases in the LPT 22 for powering the fan 14 through another drive shaft extending therebetween.