Patent ID: 8938943
Filing Date: 2015-01-27
Classification: F02K,F05D

Abstract:
1. A gas turbine engine, comprising: a fan system operative to generate a bypass flow; a bypass duct in fluid communication with the fan system and operative to transmit the bypass flow from the fan system; a compressor system in fluid communication with the fan system; a combustion system in fluid communication with the compressor system; a turbine system in fluid communication with the combustion system and operative to discharge an engine core flow; an engine nozzle in fluid communication with the fan system and the turbine system, wherein the engine nozzle is operative to receive the bypass flow and the core flow and to discharge both as an engine exhaust flow; and a variable area bypass mixer configured to vary a ratio of the bypass flow to the core flow directed into the engine nozzle to form the engine exhaust flow, wherein the variable area bypass mixer includes an axially translatable sled structured to form a bypass exit flow area for the bypass flow as it merges with the engine core flow, the bypass exit flow area defined between a downstream end of the axially translatable sled and a sidewall; and wherein the variable area bypass mixer is configured to axially translate the sled between a first position yielding a maximum bypass exit flow area of the bypass duct that directly provides bypass flow to the core flow and is exposed to the engine nozzle and a second position yielding a minimum bypass exit flow area of the bypass duct that directly provides bypass flow to the core flow and is exposed to the engine nozzle, the first position being upstream of the second position, wherein the turbine system includes a discharge portion having an inner core flowpath wall; and wherein the sled forms at least a portion of an outer core flowpath wall.