Patent ID: 7854112

Claim:
A turbine engine assembly comprising: a fan including a plurality of fan blades, wherein at least one of the plurality of fan blades defines a centrifugal compressor chamber therein for compressing core airflow therein and guiding the compressed core airflow toward the combustor; a combustor burning fuel to generate a high-energy gas stream; a turbine downstream from the combustor, the turbine rotatably drivable by the high-energy gas stream; a transition duct downstream from the turbine and the fan, the transition duct having a first side and a second side opposite the first side; and a plurality of variable vanes spaced across the transition duct between the sides for vectoring airflow from the fan and the combustor, wherein each of the plurality of variable vanes is pivoted at an angle, and the angles progressively increase across the transition duct between the first side and the second side.