Abstract: The present invention relates to a thermally compliant liner for a gas turbine engine. The liner includes an outer wall, an inner wall spaced radially inwardly from the outer wall leaving a duct therebetween. A plurality of stiffeners are disposed in the duct. The stiffeners include a flexible medial portion which accommodates differential rates of thermal growth between the outer and inner walls. The stiffeners also include radially extending portions which in conjunction with the medial portion, minimize buckling of the liner due to pressure differentials.

Abstract: A serviceable liner is provided comprising an outer wall, an inner wall, a plurality of standoffs disposed between the walls, and a plurality of attachment assemblies for attaching the walls to one another. The outer wall includes a plurality of first apertures. The inner wall includes a plurality of sections, each section having at least one second aperture. Each attachment assembly includes a fastener and an insert. An insert is received within each first aperture and a fastener is received within each insert.

Abstract: A liner for a gas turbine engine is provided which includes an outer wall, an inner wall, a plurality of standoffs, a plurality of attachment assemblies, and a plurality of tapered ribs. The inner wall sections each have a first edge and a second edge. The standoffs are attached to the inner wall sections, and separate the inner and outer walls. The attachment assemblies fix at least one standoff, per inner wall section, to the outer wall section. Each tapered rib has a pair of surfaces tapering from a greater end to a lesser end. The tapered ribs are attached to the outer wall, with the lesser end is in contact with the outer wall and the tapered surfaces disposed between, and in contact with, adjacent inner wall sections.

Abstract: An afterburner 20 for a gas turbine engine 10 has a fuel spray ring 24a for injecting fuel into the afterburner, a flameholder gutter 34a for stabilizing combustion of a fuel-air mixture flowing through the afterburner, and an ignitor 35 for initiating combustion and includes an enclosure 50 attached to the gutter. The enclosure has radially inner and outer walls 52, 54 and circumferentially spaced apart webs 60, 62 extending between the walls to define a radially and circumferentially bounded chamber 64. Each web has a forward opening 72 and an aft opening 74 so that a portion of the spray ring and a portion of the gutter are embraced by the enclosure. The enclosure is ideally circumferentially aligned with the ignitor and regulates the fuel-air ratio within and in the vicinity of the chamber to ensure reliable lighting of the afterburner and flawless advancement to full afterburning operation.

Abstract: An augmentor for a gas turbine engine with a nozzle is provided having an outer casing, a liner, a stiffening ring, a plurality of fingerseals, and apparatus for fastening the stiffening ring and the fingerseals to the liner. The liner includes a plurality of first cooling apertures. The stiffening ring includes a plurality of second cooling apertures. The finger seals are positioned between the liner and the stiffening ring. Each fingerseal includes a plurality of cooling slots having a lengthwise axis. The cooling slots, first apertures, and second apertures are relatively positioned such that cooling air passing through the second cooling holes must thereafter travel within one of the cooling slots in a direction substantially along the lengthwise axis of the slot, before entering the first apertures.