Patent ID: 9714608
Date: 2017-07-25
CPC Classifications: F02C,F02K

Claim:
1. A gas turbine engine system, comprising: a 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, wherein the turbine system is configured to discharge a first stream flow in the form of an engine core flow; and wherein the fan system is configured to discharge a second stream flow in the form of a bypass flow and to discharge a third stream flow in the form of another bypass flow; and an exhaust nozzle system in fluid communication with the fan system and the turbine system, including: a first nozzle configured to discharge the first stream flow and the second stream flow; an ejector configured to entrain ambient free stream air into the third stream flow, the ejector including a plurality of ejector doors extending from forward ends to aft ends located aft of the forward ends, the ejector doors pivotably mounted for rotation about points closer to the aft ends of the ejector doors than the forward ends of the ejector doors; and a lobed mixer configured to mix the first stream flow and the second stream flow.