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Turbofan arrangement

  • US 7,770,377 B2
  • Filed: 04/03/2006
  • Issued: 08/10/2010
  • Est. Priority Date: 04/10/2003
  • Status: Expired due to Fees
First Claim
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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.

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