Patent ID: 7162874
Filing Date: 2007-01-16
Classification: F02C,F05D,F23N,F23R

Abstract:
1. A gas turbine engine comprising an air compressor, a premixer for mixing fuel with a first portion of compressed air to provide a fuel/air mixture the premixer having a fixed area exit, a combustor for receiving and combusting the mixture to provide combustion gases, the compressor also providing a second portion of the compressed air to an exit of the combustor as dilution air, a compressed air valve for controlling the first compressed air portion, a fuel valve for controlling fuel flow to the premixer, and a turbine operatively connected to the combustor for expanding the combustion gases and the dilution air to drive the compressor and provide net power, the engine further comprising: (1) an engine controller responsive to engine power output and engine power demand for controlling the fuel valve and the air valve, (2) means for diverting part of the second portion of compressed air to bypass at least the turbine, and