Patent ID: 7770377
Filing Date: 2010-08-10
Classification: F02K,F05D

Abstract:
1. A bypass turbofan engine comprising: a first propulsion system comprising a first fan rotor, a core engine, a first low pressure turbine and a first fan shaft drivingly connecting the first turbine and the first fan rotor; a second propulsion system comprising a second fan rotor drivingly connected to a second low pressure turbine via a second fan shaft, wherein in use a fluid drivingly flows through the first turbine then the second turbine, and wherein the first and second shafts are not coaxial with one another; and a heat exchanger positioned between the first low pressure turbine and the second low pressure turbine, wherein said engine further comprising a compressor, a combustor and a valve, and wherein the heat exchanger is constructed and arranged to receive an airflow from the compressor such that the airflow may selectively be passed into the combustor by the valve.