Cooling Air System for an Exhaust Nozzle of a Gas Turbine Engine.
Abstract
The patent application relates to 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 curtain liner (flap and seal liners) up toward the center line of the nozzle.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 27, 1976
- Accession Number
- ADD003331
Entities
People
- Richard E. Warburton
Organizations
- United States Department of the Air Force