Patent ID: 9353684
Filing Date: 2016-05-31
CPC Classification: F02C,F02K,Y02T

Claim Text:
1. An airflow modulation system for use in aircraft propulsion, the airflow modulation system comprising: a turbine engine disposed at least partially within an engine bay defined by an engine bay wall, the turbine engine including: a first fan duct defined at an outer diameter by a center housing, the center housing having an upstream end; a second fan duct including a first portion defined by an annular duct wall formed concentrically about a first portion of the center housing, and a second portion formed concentrically about a second portion of the center housing, wherein the annular duct wall has an upstream end and a downstream end; an annular cooling duct formed concentrically about at least a portion of the second fan duct, wherein the cooling duct and the second fan duct are at least partially defined by a common wall portion formed concentrically about the second portion of the center housing, wherein the annular duct wall and the common wall portion are radially aligned with one another with respect to a longitudinal axis of the turbine engine, and wherein the upstream end of the annular duct wall surrounds the upstream end of the center housing; and an airflow modulator mounted on the downstream end of the annular duct wall and operably associated with the second fan duct and the cooling duct, the airflow modulator movable between a first position, wherein the airflow modulator directs airflow to the second fan duct, and at least a second position, wherein the airflow modulator directs airflow to both the second fan duct and the cooling duct.