Abstract: The present invention provides a linear friction welded blisk of a gas turbine engine and method of fabricating the blisk. The blisk includes a blisk hub having a curved periphery and having a central axis formed therethrough. At least one blade joining stub including a planar weld joint surface to which at least one airfoil blade may be welded by linear friction welding is formed about the periphery of the blisk hub. The planar weld joint surface is formed in a plane parallel to the central axis of the blisk hub thereby providing for linear friction welding of the airfoil blade to the planar weld joint surface in a tangential, chordal, or axial direction. The planar weld joint surface reduces the complexity of the linear friction welding machines and tooling, and further provides for an increase in blade count and leading edge accessibility.

Abstract: An apparatus is provided for a gas turbine engine. The gas turbine engine comprises a high pressure compressor, a single-stage high pressure turbine, a multi-stage low pressure turbine, and a reverse flow combustor unit. The reverse flow combustor comprises a combustor liner assembly, a combustor dome, and a plurality of straight-shafted fuel injectors. The combustor liner assembly includes an inner liner and an outer liner. The inner liner surrounds the single-stage high pressure turbine, and the outer liner is disposed radially outwardly of, and at least partially surrounding, the inner liner. The combustor dome assembly is coupled between the inner liner and the outer liner to define a combustion chamber therebetween. The plurality of straight-shafted fuel injectors are coupled to the combustor dome, with each fuel injector having at least an inlet, an outlet, and a linear fuel passageway extending therebetween.