Patent ID: 9701415
Date: 2017-07-11
CPC Classifications: B64D,F01D,F02C,F02K,F04D,F05D

Claim:
1. A nacelle assembly for a high-bypass gas turbine engine comprising: a core nacelle defined about an engine centerline axis; a fan nacelle mounted at least partially around said core nacelle to define a fan bypass flow path for a fan bypass airflow; and a fan variable area nozzle that defines a trailing edge of the fan nacelle and is axially movable relative said fan nacelle between an open position and a closed position to open an auxiliary port and to vary a fan nozzle exit area such that bypass airflow flows concurrently through both the auxiliary port and the fan nozzle exit area to adjust a pressure ratio of the fan bypass airflow during engine operation, wherein the fan variable area nozzle includes a chord length and a radial outer wall surface that is at a radial distance from the engine centerline axis and a ratio of the radial distance to the chord length is greater than 0.7.