Patent ID: 6971241

Claim:
A gas turbine engine, comprising: a compressor having an inlet and a compressed air outlet; a turbine having at least an inlet; a combustor system including: a housing having at least a first air inlet in fluid communication with the compressed air outlet, a second air inlet adapted to receive compressed air from a second compressed air source, and an inlet plenum in fluid communication with the first and second air inlets, a combustor mounted at least partially within the housing, the combustor having one or more air inlets in fluid communication with the housing inlet plenum, and an outlet in fluid communication with the turbine inlet, a bypass conduit having an inlet, an outlet, and a flow passage therebetween, the bypass conduit inlet in fluid communication with the housing inlet plenum, and the bypass conduit outlet in fluid communication with the combustor outlet, and a valve mounted on the bypass conduit and moveable between (i) an open position, whereby fluid flow through the bypass conduit is allowed, and (ii) a closed position, whereby fluid flow through the bypass conduit is prevented.