Patent ID: 8322127

Claim:
A nozzle assembly for a turbine engine, comprising: a convergent portion for converging fluid flow from a turbine engine core; a divergent portion for diverging fluid flow from the turbine engine core, said divergent portion in fluid flow communication with said convergent portion; and a first conduit for communication with a bypass fluid flow, said first conduit having a first thrust vectoring port and disposed proximate said divergent portion, wherein said first conduit has a first wall spaced from a second wall, said first wall defining an exterior portion of said divergent portion and said second wall defining an interior portion of said divergent portion, said interior portion for guiding fluid flow from the turbine engine core; a second conduit for communication with the bypass fluid flow, said second conduit having a second thrust vectoring port; a third wall spaced between said first conduit and said second conduit, said third wall extending transversely to one of said first wall and said second wall; a third conduit for communication with the bypass fluid flow, said third conduit located between said first conduit and said second conduit; and a device for reducing pressure loss, said device disposed across said third conduit, wherein said device for reducing pressure loss comprises a screen extending transversely to a direction of flow through said second conduit.