Patent ID: 9303875
Filing Date: 2016-04-05
CPC Classification: F02C,F23R

Claim Text:
1. An annular gas-turbine combustion chamber comprising: a radially outer and a radially inner combustion chamber wall relative to a central engine axis, a combustion chamber head, a combustion chamber outlet nozzle, wherein the combustion chamber head includes a plurality of fuel nozzles distributed over a circumference of the combustion chamber head, each including at least one air duct and at least one fuel duct for supplying air and fuel, the fuel exiting in an outlet surface of each of the fuel nozzles, each of the fuel nozzles including a burner axis which is perpendicular to the outlet surface, a center point of a line extending between widest points of the at least one air duct in a generally circumferential direction establishing a position of the burner axis, intersections of the burner axis with the outlet surfaces defining a circular burner centerline around the engine axis, wherein, each of the fuel nozzles includes a cross-sectional area radially outside the burner centerline of the air and fuel ducts and a cross-sectional area radially inside the burner centerline of the air and fuel ducts, with the cross-sectional area radially outside the burner centerline being identical to the cross-sectional area radially inside the burner centerline.