Accession Number : ADD007278

Title :   Cooling Apparatus for an Exhaust Nozzle of a Gas Turbine Engine.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON DC

Personal Author(s) : Warburton,Robert E

Report Date : 20 May 1980

Pagination or Media Count : 8

Abstract : A cooling control system for a convergent-divergent gas turbine exhaust nozzle which permits automatic ducting of cooling air during the augmented mode of engine operation. The convergent flaps of the nozzle have longitudinal ducts embedded therein with a pair of openings near the aft extreme of each of the convergent flaps and openings located in the forward half of the convergent flaps. The convergent seals overlap the convergent flaps and are slideably mounted for positioning over the aft openings on the flaps. A positive pressure is generated under the convergent flap liner and seal liner when the convergent seal is opened to allow cooling air to be ducted through the flap. The positive pressure forces the convergent flap and seal liners up toward the center line of the nozzle. (Author)

Descriptors :   *Patents, *Convergent divergent nozzles, *Air cooled, *Turbofan engines, Inventions, Flaps(Control surfaces), Seals(Stoppers), Exhaust nozzles

Subject Categories : Air Condition, Heating, Lighting & Ventilating
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE