Patent ID: 7882695
Filing Date: 2011-02-08
Classification: F02C,F02K,F05D

Abstract:
1. A turbine engine comprising: a fan having a plurality of radially extending fan blades, wherein at least one of the plurality of fan blades defines a compressor chamber extending radially therein, wherein rotation of the at least one fan blade provides centrifugal compression of core airflow; a turbine blade operatively coupled to the fan for rotatably driving the fan; a combustor for generating a high-energy gas stream to the turbine blade after the turbine engine is started, the centrifugally compressed core airflow being supplied to the combustor; and a fluid outlet supplying high-pressure fluid onto the turbine blade to cause rotation of the turbine blade to start the turbine engine before the combustor generates a high-energy gas stream, wherein the high-pressure fluid from the fluid outlet is distinct from the core airflow.