Combustion apparatus for gas turbine engines

Claim 2

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.

Claim 3

Combustion apparatus as claimed in claim 1 in which said sleeve and said fuel duct extend into the interior of said frusto-conical member to an extent approximately one-half the diameter of said sleeve.

Claim 4

Combustion apparatus as claimed in claim 1 in which said fuel duct includes a plurality of radially directed nozzles positioned immediately downstream of said air swirling vanes for directing fuel across the swirl of air from said air swirling vanes.

Claim 5

Combustion apparatus as claimed in claim 1 including a seal between said sleeve and said frusto-conical member, said seal permitting relative movement between said sleeve and said frusto-conical member.

Claim 6

Combustion apparatus as claimed in claim 1 in which said orifices are elongated slots.

Claim 7

Combustion apparatus as claimed in claim 1 in which said orifices are a plurality of holes having an angular pitch between 18° and 30°.

Claim 8

Combustion apparatus for a gas turbine engine comprising: an annular flame tube having an upstream end, a downstream end and a primary zone adjacent the upstream end; a plurality of first burner means in communication with the upstream end of said flame tube for supplying a fuel and air mixture into the primary zone of said flame tube, each of said first burner means including an air inlet and fuel injector means, each having a capability of stable burning over a complete power range of the gas turbine engine; and a plurality of second burner means in communication with said annular flame tube for supplying a fuel and air mixture to the primary zone of the flame tube with a reduced residence time within said primary zone to reduce formation of oxides of nitrogen and thereby emissions from the gas turbine engine, each of said second burner means including a hollow frusto-conical member, said frusto-conical member being open at each end thereof and having the larger end attached to said flame tube and in communication with the interior thereof and an air inlet and fuel injecting means adjacent the narrower end of said frusto-conical member, said air inlet and fuel injecting means including a sleeve carried in the smaller end of said frusto-conical member and a central fuel duct terminating in at least one fuel nozzle, and a plurality of air swirling vanes located between said sleeve and said fuel duct for imparting a swirl to the air and the fuel issuing from the at least one fuel nozzle, and said frusto-conical member having at least two sets of orifices formed in the wall thereof, one set of orifices inducing a swirl in the same direction as the swirl imparted by said air swirling vanes and the other set of orifices inducing a swirl in the opposite direction to produce a highly turbulent flow within the frusto-conical member to adequately mix the fuel and air therein and reduce the net angular momentum of the mixture flow from each of said second burner means into the primary zone of said flame tube.

Claim 9

Combustion apparatus for a gas turbine engine comprising: an annular flame tube having an upstream end, a downstream end and a primary zone adjacent the upstream end; a plurality of first burner means in communication with the upstream end of said flame tube for supplying a fuel and air mixture into the primary zone of said flame tube, each of said first burner means including an air inlet and fuel injector means, each having a capability of stable burning over a complete power range of the gas turbine engine; and a plurality of second burner means in communication with said annular flame tube for supplying a fuel and air mixture to the primary zone of the flame tube with a reduced residence time within said primary zone to reduce formation of oxides of nitrogen and thereby emissions from the gas turbine engine, each of said second burner means including a hollow frusto-conical member, said frusto-conical member being open at each end thereof and having the larger end attached to said flame tube and in communication with the interior thereof and an air inlet and fuel injecting means adjacent the narrower end of said frusto-conical member, said air inlet and fuel injecting means including a sleeve carried in the smaller end of said frusto-conical member and a central fuel duct terminating in at least one fuel nozzle, and a plurality of air swirling vanes located between said sleeve and said fuel duct for imparting a swirl to the air and the fuel issuing from the at least one fuel nozzle, and said frusto-conical member having at least two sets of orifices formed in the wall thereof, one set of orifices inducing a swirl in the same direction as the swirl imparted by said air swirling vanes and the other set of orifices inducing a swirl in the opposite direction to produce a highly turbulent flow within the frusto-conical member to adequately mix the fuel and air therein and reduce the net angular momentum of the mixture flow from each of said second burner means into the primary zone of said flame tube.

Claim 10

Combustion apparatus as claimed in claim 7 in which each of said air inlet and fuel injector means in each of said first burner means further includes a hollow frusto-conical member for each of said air inlet and fuel injector means, said last mentioned frusto-conical member being open at each end thereof and having the larger end attached to said flame tube and in communication with the interior thereof and the air inlet and fuel injection means positioned adjacent the narrower end thereof, said last mentioned frusto-conical member having a plurality of orifices formed in the wall thereof for the passage of air therethrough tangentially into said frusto-conical member to impart a swirl within the same, said air inlet and fuel injector means for said first burner 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 the frusto-conical member of said first burner means, 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 the orifices in said frusto-conical member of said first burner means to promote a mixing of fuel and air and a degree of swirl to the fuel and air mixture entering the primary zone of the flame tube from said first burner means while discouraging fuel from adhering to an interior surface of the wall of said frusto-conical member of said first burner means by a delay of the spread of fuel from the core of fuel and air issuing from the air inlet and fuel injection 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 in the core entering the primary zone.

Claim 11

Combustion apparatus as claimed in claim 8 in which said sleeve and said fuel duct of said first burner means extend into the interior of the frusto-conical member of said first burner means to an extent of approximately one-half the diameter of said sleeve.

Claim 12

Combustion apparatus as claimed in claim 7 in which said fuel duct in said frusto-conical member of said first burner means terminates in a plurality of radially directed nozzles positioned immediately downstream of said air swirling means for directing fuel across air flow swirled therefrom.

Claim 13

Combustion apparatus as claimed in claim 7 including a seal provided between said sleeve and said frusto-conical member of each of said first burner means for allowing relative movement therebetween.

Claim 14

Combustion apparatus as claimed in claim 7 in which said orifices in said frusto-conical member of said first burner means are elongated slots.

Claim 15

Combustion apparatus as claimed in claim 7 in which said orifices in said frusto-conical member of said first burner means are a plurality of holes having an angular pitch of between 18° and 30°.