Patent ID: 8844266
Filing Date: 2014-09-30
Classification: F01D,F02C,F05D

Abstract:
1. A power plant for a UAV comprising: a first gas turbine engine having a first compressor rotatably connected to a first turbine and a first combustor to produce a first hot gas flow that is passed through the first turbine; a second gas turbine engine having a second compressor rotatably connected to a second turbine and a second combustor to produce a second hot gas flow that is passed through the second turbine; a first flow control valve having an inlet connected to an outlet of the first turbine to receive a turbine exhaust flow from the first turbine; the first flow control valve having an outlet selectively connected to a mixer or a second flow control valve; the second compressor having a bleed off passage connected to the mixer to supply bleed off air from the second compressor; the mixer having an outlet connected to the second combustor; the second compressor having an outlet connected to a third combustor that burns a fuel to produce a third hot gas flow; an outlet of the third combustor is connected to the second flow control valve; a power turbine having an inlet connected to the second flow control valve; and, the power turbine driving a rotor shaft to produce useful work.