×

Aircraft cabin air conditioning system with improved fresh air supply

  • US 5,299,763 A
  • Filed: 12/23/1991
  • Issued: 04/05/1994
  • Est. Priority Date: 12/23/1991
  • Status: Expired due to Fees
First Claim
Patent Images

1. In an aircraft having a cabin and a pressurized bleed air flow, a cabin air conditioning system, comprising:

  • a turbine having a rotatable turbine wheel mounted within a turbine housing with a full circle turbine scroll for admission of airflow into driving relation with said turbine wheel defining a pair of housing inlets which are generally diametrically opposed to each other, and further including a turbine scroll valve mounted within said turbine scroll at a position generally opposite said one inlet and upstream from said other inlet, said turbine scroll valve being closed during said first mode whereby the bleed and supplemental air flows each flow into and fill a generally semi-annular half of the turbine scroll, said turbine scroll valve being open during said second mode whereby the bleed air flow fills substantially the entire full circle turbine scroll;

    a compressor mounted for rotation with said turbine to draw in and compress a supplemental air flow;

    means for supplying the bleed air flow to one of said turbine housing inlets for rotatably driving said turbine wheel and said compressor;

    means for supplying the bleed air flow to one of said turbine housing inlets for rotatably driving said turbine wheel and said compressor;

    means for supplying the supplemental air flow to the other of said turbine housing inlets to supplementally drive said turbine wheel during a first mode of operation, and for mixing the supplemental airflow with the bleed air flow at a downstream side of said turbine during a second mode of operation wherein said supplemental air flow supply means comprises a flow conduit for normally supplying the supplemental air flow from said compressor to said other turbine housing inlet, a bypass conduit connected between said flow conduit and the discharge side of said turbine, and a bypass valve for preventing passage of the supplemental air flow through said bypass conduit during said first mode, and for permitting supplemental air flow passage through said bypass conduit during said second mode; and

    means for supplying the bleed and supplemental air flow from the downstream side of said turbine to the aircraft cabin.

View all claims
  • 3 Assignments
Timeline View
Assignment View
    ×
    ×