United Technologies Corporation

United States of America As Represented by the Secretary of the Air Force

Kurt J Hanloser

James H Shadowen

John A Harris, Iii

William J Egan, Jr

Raymond J Bruchez

George W Beal

James R Grant, Jr

James T Gill, Jr

A gas turbine augmentor fuel manifold is provided which includes a hollow body, a plurality of fuel valves and a cleansing port disposed in the hollow body, and apparatus for selectively admitting fuel into the hollow body. The hollow body has a forward surface and an aft surface. When the apparatus for selectively admitting fuel into the hollow body is in an off position, core gas flowing past the hollow body enters the cleansing port and purges the interior of the hollow body of residual fuel and fuel residue, thereby cleaning the hollow body.

Self-cleaning augmentor fuel manifold

An afterburner on a turbofan engine includes a flameholder means having an annular flameholder gutter positioned downstream of a first exhaust means of a core engine while said flameholder means also includes a plurality of radial gutter sections extending radially outward towards an outer wall of said afterburner and downstream of a second annular exhaust means of a bypass duct around said core engine; a plurality of said radial gutter sections having a manifold extending along the forward portion thereof, each manifold having an inlet at its inward end located downstream of said first exhaust means with said manifold directing a hot exhaust flow from said inlet to openings on each side of its associated radial gutter section in a portion downstream of said second annular exhaust means.

Afterburner flameholder construction

A partial swirl augmentor for a turbofan engine having an annular duct for directing hot gases into the augmentor combustion chamber. Located within the combustion chamber is a piloted vee-gutter flameholder system which has a circumferential pilot located at the outer edge of the swirlng hot turbine exhaust gas stream. As a result thereof, the partial swirl augmentor can attain state-of-the art engine after burning thrust levels with an increased altitude blow-out limit.

Partial swirl augmentor for a turbofan engine

A thrust augmentor for a turbofan, gas turbine engine is disclosed. Techniques for mixing and burning dissimilar density gases in a thrust augmentor are developed. In accordance with one specific teaching the flame front in a swirl augmentor is stabilized by a continuously operative pilot burner. The pilot burner is positioned in the radially outward portion of the augmentor.

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North Palm Beach, FL, United States of America

Kurt J Hanloser