Abstract: A turbofan engine augmenter includes an exhaust casing and a combustion liner therein which define therebetween a cooling duct for receiving bypass air. A diffusion liner adjoins the combustion liner and defines with the casing an outer inlet for receiving the bypass air, and a radially inner inlet for receiving core gases. A ring flameholder includes an aft facing radial wall adjoining the diffusion liner, and an integral axial wall adjoining the combustion liner. A plurality of circumferentially spaced apart radial flameholders extend inwardly from the casing and through the diffusion liner forward of the ring flameholder, and each includes a first fuel spraybar for injecting fuel into the core gases. A mixer defined by a plurality of injector chutes extends radially inwardly through the diffusion liner, with the chutes being spaced between respective pairs of the radial flameholders.

Abstract: A cooled ignition flameholder assembly includes a first heat shield having first and second spaced apart chambers. A fuel spraybar is disposed inside the first chamber, and a hollow baffle is disposed inside the second chamber. A second heat shield is joined to the first heat shield for closing the second chamber with the baffle therein. The baffle includes an inlet for receiving cooling air which is discharged through a plurality of outlet holes for impingement cooling the first and second heat shields. An ignition bulb is disposed adjacent to the second chamber and receives an igniter tip and a fuel injector tip for initiating combustion.

Abstract: A plurality of circumferentially displaced hollow members are positioned between an outer bypass duct and the center body of the core engine. Each of the hollow members is open at the radially outward end thereof for receiving relatively cool gas from the bypass duct. Each hollow member is formed with an opening in the side thereof extending substantially the full length of the hollow member near the trailing edge thereof for discharging bypass gas from the bypass duct in a direction facilitating thorough mixing of the bypass gas and core gases. A pivoted vane is provided in this opening of each of the hollow members and these vanes are controlled to vary the airflow through the aforementioned openings. Radially extending spraybars or fuel rods are provided within each hollow member adjacent opposite sides thereof so as to be cooled by the bypass air flowing through the hollow member.

Abstract: An augmented mixed flow gas turbine engine is provided with a variable area bypass injector system which varies the area through which the bypass stream is injected into the core stream and which also selectively obtrudes cooling airflow to the augmentor liner. The ability to vary the area through which the bypass stream is injected into the core stream permits the mixed flow gas turbine engine of this invention to operate efficiently over a wide range of bypass ratios and further permits the total pressure of the bypass stream to be maintained at a level which will keep the engine inlet airflow matched to an optimum design level throughout a wide range of engine thrust settings. The ability to selectively obtrude cooling flow to the augmentor liner allows the augmentor cooling flow to be optimized for development of engine thrust during the augmented and non-augmented modes of operation and thereby further improve the operating range and efficiency of the engine of this invention.