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Auxiliary power unit with excess air recovery

  • US 10,696,417 B2
  • Filed: 06/25/2015
  • Issued: 06/30/2020
  • Est. Priority Date: 06/25/2015
  • Status: Active Grant
First Claim
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1. An auxiliary power unit for an aircraft, comprising:

  • an internal combustion engine core having a shaft;

    a compressor having an outlet in fluid communication with an inlet of the engine core;

    a turbine section in fluid communication with an outlet of the engine core, wherein the turbine section includes a first stage turbine having an inlet in fluid communication with the outlet of the engine core, and a second stage turbine having an inlet in fluid communication with an outlet of the first stage turbine, the first stage turbine having at least one rotor on a turbine shaft of the turbine section, the second stage turbine having at least one rotor on the turbine shaft, the turbine shaft in driving engagement with the shaft of the engine core to compound power with the engine core;

    a bleed conduit having a first end in fluid communication with the outlet of the compressor and a second end configured for connection with a pneumatic system of the aircraft;

    an excess air duct having a first end in fluid communication with the outlet of the compressor and a second end in fluid communication with the turbine section, the excess air duct defining a flow path between the outlet of the compressor and the turbine section separate from the engine core, wherein the second end of the excess air duct is in fluid communication with the second stage turbine of the turbine section downstream of the first stage turbine such that the flow path bypasses the first stage turbine; and

    a diverter valve selectively opening and closing a fluid communication through the excess air duct between the first and second ends thereof.

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