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GAS TURBINE DISK CAVITY INGESTION INHIBITOR

  • US 20020159880A1
  • Filed: 04/26/2001
  • Published: 10/31/2002
  • Est. Priority Date: 04/26/2001
  • Status: Active Grant
First Claim
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1. A supplemental air cooling system for use in gas turbine engines to inhibit ingestion of hot gas flow into certain circumferential locations of turbine disk cavities, said air cooling system comprising:

  • a plurality of ingestion inhibiting dynamic jet orifices located on an underside of turbine nozzle trailing edges;

    said orifices penetrating through turbine nozzle hot gas flow path discouraging structural elements;

    said orifices being optionally located on each side of each stator blade airfoil trailing edge, or directly underneath each stator blade airfoil trailing edge;

    the centerline of each said orifices directed to a point within the turbine disk cavity;

    said point being located about midway between the stationary turbine nozzle and the rotating turbine blade hot flow path gas discouraging structural elements;

    a flow of gas turbine engine cooling air traversing through the plurality of ingestion inhibiting dynamic jet orifices and flowing into the turbine disk cavity;

    whereby the flow of cooling air traversing through the plurality of ingestion inhibiting dynamic jet orifices and into the turbine disk cavity forces incoming hot flow gases to turn circumferentially and go back out into the path of hot gas flow before it can cause an adverse increase in internal component temperatures.

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