Fuel nozzle for a gas turbine engine

Details Fuel nozzle for a gas turbine engine Fuel nozzle for a gas turbine engine

F - Mech Eng,Light,Heat,Weapons

23

D

60/113

F23D 11/24 (2006.01) F23D 17/00 (2006.01)

Patent

CA 1176477

13DV-7453 FUEL NOZZLE FOR A GAS TURBINE ENGINE ABSTRACT OF THE DISCLOSURE In one form, a fuel nozzle includes a primary flowpath and a secondary flowpath, each of which includes a pair of axially opposing input and output ends disposed along a common central longitudinal axis. The secondary path is circumferentially disposed around the primary path. A nozzle discharge portion is circumferentially disposed around the primary and secondary output ends for receiving inter- acting output flows from the first and second paths and developing a nozzle output therefrom. The nozzle discharge portion includes a conical portion having an input end of smaller diameter which increases along the longitudinal axis to an output end of relatively larger diameter. In a preferred embodiment, the conical portion defines an included solid angle of 60 degrees with respect to the central longitudinal axis. Other embodiments are disclosed.

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