Fuel spray nozzle comprising axially projecting air guiding element for a combustion chamber of a gas turbine engine

A combustion chamber assembly group, comprising

• a burner seal (4) that comprises a bearing section (41) that extends along a nozzle longitudinal axis (DM) and has a passage opening, and
• a nozzle for a non-staged combustion chamber (3) of an engine (T) that is positioned inside a passage hole of a bearing section (41) for providing a fuel-air mixture at a nozzle exit opening of the nozzle (2), wherein the nozzle (2) has a nozzle main body (20) that comprises the nozzle exit opening and that extends along the nozzle longitudinal axis (DM), and the nozzle main body (20) further comprises at least the following:
• at least one first, inner air guiding channel (26) that extends along the nozzle longitudinal axis (DM) for conveying air to the nozzle exit opening,
• at least one fuel guiding channel (25) for conveying fuel to the nozzle exit opening, which is located radially further outside with respect to the nozzle longitudinal axis (DM) as compared to the first air guiding channel (26), and
• at least one further air guiding channel (27b) that is located radially outside with respect to the nozzle longitudinal axis (DM) with regard to the fuel guiding channel (25), wherein an air guiding element (271b) for guiding air flowing from the at least one further air guiding channel (27b) is provided at an end of this at least one further air guiding channel (27b) located in the area of the nozzle exit opening
• wherein
• on end of the fuel guiding channel (25) at the nozzle exit opening is bordered by a flow-off edge (250) that is located radially outside and the air guiding element (271b) projects into the axial direction (x) with respect to the nozzle longitudinal axis (DM) in such a manner with regard to this flow-off edge (250) that
• a reference angle (α) that is present between the nozzle longitudinal axis (DM) and a straight boundary line (6) extending through a point at the flow-off edge (250) and tangentially to the axially projecting air guiding element (271b), and/or
• a reference angle (α) that is present between the nozzle longitudinal axis (DM) and a straight boundary line (6) extending through a point at the flow-off edge (250) and a point (2712b) of the air guiding element (271b) that projects maximally beyond the flow-off edge (250) in the axial direction (x)
• is less than or equal to 50°;
• wherein the burner seal (4) has a radially widening flow guiding element (40) in the area of the nozzle exit opening of the nozzle (2) and an inner shell surface of the radially widening flow guiding element (40) extends at the end of the burner seal (4) at an angle to the nozzle longitudinal axis (DM) that substantially corresponds to the reference angle (α) or that is identical to the reference angle (α).