General Electric Company

Chester J Lamando, Jr

John W Vdoviak

Wayne R Oliver

Thomas J Shimmel

A turbojet engine includes a compressor and turbine, with a combustor disposed therebetween for generating exhaust gas. An afterburner includes an annular casing and liner spaced radially inwardly therefrom to define a cooling duct therebetween. A recoup duct is disposed in flow communication with the compressor for receiving a portion of compressed air therefrom as recoup air. A plenum is disposed at an upstream end of the afterburner casing, and includes an inlet disposed in flow communication with the recoup duct for receiving the recoup air, and an outlet disposed in flow communication with the afterburner cooling duct for discharging the recoup air therein.

Recoup turbojet engine

A flameholder is disclosed for use in an afterburner of an aircraft gas turbine engine. The flameholder comprises at least one annular ring and a plurality of open ended slots around the forward end of the ring with the open end of each slot open through the forward edge of the ring for accepting a plurality of fuel spraybars. One particular embodiment provides two or more sub-pluralities of slots having two or more differing axial lengths to accommodate different axially spaced sub-pluralities of spraybars such as primary and pilot spraybars. A fastening means is provided for attaching the annular ring to the outer engine casing and is accessible through the exhaust nozzle of the engine. One embodiment provides a fastening means with an anti-rotation means on a connecting link into which a bolt head may be slipped and held from rotating during torquing of a nut. Another feature of the present invention is the use of a bolt having a thread diameter smaller than the bolt shank diameter which is particularly useful when the threads are seized due to high temperature exposure. Overtorqing the nut will fail the bolt at the threads facilitating removal of the flameholder.

Removable afterburner flameholder

A new and improved gas turbine engine augmentor including a liner having a film-coolable first portion joined to a convection-coolable second portion is disclosed. A cooling gas, such as fan bypass air, is channeled to the liner for film cooling the first portion and providing a residual cooling film to the second portion. The second portion is also convection coolable by air passing over an outer surface thereof. In a particular embodiment of the invention, the augmentor liner also includes a screech portion disposed at an upstream end of the first portion and downstream of a flameholder. The screech portion includes a substantially imperforate outer wall and an inner wall spaced therefrom which define a manifold therebetween. The inner wall includes a plurality of apertures in flow communication with the combustion zone. The manifold and apertures are effective for suppressing screech while substantially preventing the leakage of cooling air therethrough.

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Nahant, MA, United States of America

Chester J Lamando, Jr