GAS TURBINE ENGINE EJECTOR

摘要

An ejector (200) comprises a primary nozzle (201) having an annular wall (234) forming part of an outer boundary of an exhaust portion of a primary flow path of a gas turbine engine (10). The annular wall (234) has a downstream end (37) defining a plurality of circumferentially distributed lobes (236). The ejector (200) further comprises a secondary nozzle (203) having an annular wall (234) disposed about the primary nozzle (201), the primary nozzle (201) and the secondary nozzle (203) defining a secondary flow passage (207) therebetween for channeling a secondary flow. The secondary nozzle (203) defines a mixing zone (209) downstream of an exit of the primary nozzle (201). A flow guide ring (205) is mounted to the primary nozzle lobes (236). The ring (205) has an aerodynamic surface extending from a leading edge (205a) to a trailing edge (205b) respectively disposed upstream and downstream of the exit of the primary nozzle (201). The aerodynamic surface of the ring (205) is oriented to guide the high velocity primary flow into the mixing zone (209).