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Air control mechanism within a power turbine section of a gas turbine engine. The power turbine section includes a rotor and at least one variable pitch propulsor blade. The propulsor blade is coupled to and extends radially outwardly of the rotor. A first annular fairing is rotatable with the propu

Air control mechanism within a power turbine section of a gas turbine engine. The power turbine section includes a rotor and at least one variable pitch propulsor blade. The propulsor blade is coupled to and extends radially outwardly of the rotor. A first annular fairing is rotatable with the propulsor blade and interposed between the propulsor blade and the rotor. A second fairing is located longitudinally adjacent to the first fairing. The first fairing and the second fairing are differentially rotatable. The air control mechanism includes a platform fixedly coupled to a radially inner end of the propulsor blade. The platform is generally positioned in a first opening and a first fairing. The platform and the first fairing define an outer space. In a first position corresponding with a first propulsor blade pitch, the platform is substantially conformal with the first fairing. In a second position corresponding with the second propulsor blade pitch, an edge portion of the platform is displaced radially outwardly from the first fairing. When the blades are in the second position and rotating about the engine axis, the displacement of the edge portion with respect to the first fairing allows air to flow from the outer space to the annular cavity.

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In a gas turbine engine having a rotor section coupled in driving relationship to forward and aft counterrotating propulsors each including a plurality of unducted propulsor blades extending radially outward of the engine and having hub portions adjacent the engine, a nacelle surrounding the engine

In a gas turbine engine having a rotor section coupled in driving relationship to forward and aft counterrotating propulsors each including a plurality of unducted propulsor blades extending radially outward of the engine and having hub portions adjacent the engine, a nacelle surrounding the engine and defining a first cavity within which the blade hub portions are located, a system for ventilating the blade hub portions comprising: means for defining a plurality of second annular cavities, each of said second cavities circumscribing a corresponding one of the blade hub portions of the forward propulsors, each of said second cavities having a plurality of air distribution holes extending through said defining means adjacent selected portions of the corresponding blade hub portion; means operatively associated with each of the forward propulsors for establishing an air scoop for directing air into said second cavities when the forward propulsor is at a predetermined pitch angle; air outlet means positioned between the forward and aft propulsors for exhausting air from said first cavity; and means operatively associated with the aft propulsor for establishing a plurality of air inlets when the aft propulsor is at the predetermined pitch angle, said air inlets being aft of said aft propulsor, air entering said air inlets being directed forwardly over the blade hub portions of said aft propulsors toward said air outlet means.