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Passive control of hot air injection for swirling rotational type anti-icing system

  • US 6,354,538 B1
  • Filed: 10/25/1999
  • Issued: 03/12/2002
  • Est. Priority Date: 10/25/1999
  • Status: Expired due to Fees
First Claim
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1. An anti-icing system for a nose cowl for an annular inlet of an aircraft jet engine propulsion system for an aircraft which comprises:

  • a substantially closed annular single skin nose cowl having an exterior surface and an interior surface and positioned at the leading edge of an inlet of an aircraft jet engine propulsion system and arranged for grazing flow of ambient air over the exterior surface when the aircraft is in flight, the annular nose cowl containing a quantity of air;

    a source of high pressure hot gas;

    at least one conduit means coupled to the source of high pressure hot gas and having an outlet end extending into said nose cowl;

    at least one outlet nozzle provided on the outlet end of said conduit means, said outlet nozzle being provided with circumferentially arranged means extending aft from said outlet nozzle and extending into the flow of hot gas issuing from said nozzle to create longitudinal vortices and transverse stirring in the hot gas flow, said outlet nozzle being oriented to eject said hot gas at high velocity in a direction substantially tangential to a centerline of said annular nose cowl, wherein said circumferentially arranged means extending from the outlet end of the conduit means includes a plurality of circumferentially arranged tabs that are canted inwardly into the flow of hot gas issuing from the nozzle, and whereby the turbulent high velocity hot gas flow issuing from said nozzle entrains the air within said annular nose cowl so that the total volume of air and hot gases swirling around the interior of said annular nose cowl in a rotational direction has a substantially uniform temperature intermediate between that of said air and said hot gas flow and by direct contact with the interior surface of the single skin nose cowl substantially uniformly heats the single skin nose cowl to a temperature that is sufficiently high to preclude the formation of ice on the exterior surface of the nose cowl by the grazing flow of ambient air when the aircraft is in flight while also precluding the creation of an area of elevated temperature in said nose cowl at a location downstream of said outlet nozzle.

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