Patent ID: 6679048
Filing Date: 2004-01-20
Classification: F02K

Abstract:
An apparatus for altering the direction of an exhaust stream produced by an aircraft engine, comprising:an upstream end portion, a downstream end portion, and a throat area between the upstream end portion and the downstream end portion; at least one pair of opposing side wall portions at the downstream end portion; an exit area in the downstream end portion at an end opposite the end adjoining the throat area, wherein the exhaust stream exits the apparatus at the exit area; at least one injector positioned on one of the side wall portions adjacent the exit area, the at least one injector being oriented to inject a secondary fluid flow into the exhaust stream in a direction opposing the direction of flow of the exhaust stream; and the aspect ratio at the exit area is approximately 4.5 and the ratio of the total area of the at least one injector to throat area is approximately 0.015.