초록 ▼

Combustion apparatus for reducing objectionable exhaust emissions from gas turbine engines comprises a hollow conical member with an air inlet and fuel injector at its narrower end, the wider end being open into a combustion chamber, the wall of the conical member having a number of orifices for the

Combustion apparatus for reducing objectionable exhaust emissions from gas turbine engines comprises a hollow conical member with an air inlet and fuel injector at its narrower end, the wider end being open into a combustion chamber, the wall of the conical member having a number of orifices for the throughflow of air, the orifices being directed tangentially into the interior of the conical member to impart a swirl to the mixture of fuel and air from the air inlet and fuel injector within the conical member.

대표청구항 ▼

Combustion apparatus for a gas turbine engine comprising: an annular flame tube having an upstream end and a downstream end and a primary zone adjacent the upstream end thereof; a plurality of circumferentially spaced hollow frusto-conical members secured to the upstream end of said flame tube and i

Combustion apparatus for a gas turbine engine comprising: an annular flame tube having an upstream end and a downstream end and a primary zone adjacent the upstream end thereof; a plurality of circumferentially spaced hollow frusto-conical members secured to the upstream end of said flame tube and in communication with the interior thereof, each said frusto-conical member being open at each end, each said frusto-conical member having a plurality of orifices formed in the wall thereof for passage of air therethrough tangentially into said frusto-conical member to impart a swirl within the same; and an air inlet and fuel injection means positioned adjacent the narrower end of each of said frusto-conical members, said air inlet and fuel injecting means comprising a sleeve and a central fuel duct terminating in at least one nozzle, said sleeve and said fuel duct extending into the interior of said frusto-conical member, and a plurality of air swirling vanes positioned between said fuel duct and said sleeve, said air swirling vanes being arranged to impart a swirl to air from said air inlet and fuel from said nozzle in an opposite direction to the swirl of air caused by air entering through said orifices in said frusto-conical member to promote a mixing of fuel and air and a degree of swirl to the fuel and air mixture entering the primary zone of said flame tube while discouraging fuel from adhering to an interior surface of the wall of said frusto-conical member by a delay of the spread of fuel from the core of fuel and air issuing from the air inlet and fuel injecting means, thereby maintaining a relatively rich fuel and air mixture in the core and stability in burning in the primary zone of said flame tube over a complete power range of the gas turbine engine. *** BRS DOCUMENT BOUNDARY ***