Active ground vortex suppression system for an aircraft engine

摘要

A movable convergent nozzle (24) in fluid communication with an actuator assembly (14) receives fluid from a fluid source through the actuator assembly. The fluid is injected into a desired area of a turbo-jet engine (12) through an engine inlet from the nozzle, so as to disrupt the flow structure of the ground vortex generated by the engine. Independent claims are also included for the following: (1) aircraft turbo-jet engine assembly; and (2) ground vortex wide area suppression method.