Abstract: Methods are provided of forming a plurality of fan-shaped effusion holes on a combustor having a surface, each hole having an outlet on the combustor surface. The method may include rotating the combustor relative to a laser beam, and positioning the combustor to a first position where the laser beam is at a first predetermined angle relative to the combustor surface. The laser beam is pulsed at the combustor surface to form a first plurality of trepan cuts. The first predetermined angle is adjusted to a second position where the laser beam is at a second predetermined angle relative to the combustor surface. The laser beam is pulsed at each trepan cut of the first plurality of trepan cuts, to thereby form a cut for at least a portion of the fan shape of each effusion hole outlet, wherein each cut overlaps a trepan cut of the first plurality of trepan cuts.

Abstract: Methods are provided of forming a plurality of fan-shaped effusion holes on a combustor having a surface, each hole having an outlet on the combustor surface. The method may include rotating the combustor relative to a laser beam, and positioning the combustor to a first position where the laser beam is at a first predetermined angle relative to the combustor surface. The laser beam is pulsed at the combustor surface to form a first plurality of trepan cuts. The first predetermined angle is adjusted to a second position where the laser beam is at a second predetermined angle relative to the combustor surface. The laser beam is pulsed at each trepan cut of the first plurality of trepan cuts, to thereby form a cut for at least a portion of the fan shape of each effusion hole outlet, wherein each cut overlaps a trepan cut of the first plurality of trepan cuts.

Abstract: A premix chamber for a combustor of a gas turbine engine comprises a cylindrical chamber having a premix chamber wall, the cylindrical chamber having a chamber inlet end longitudinally separated from a chamber outlet end along a central axis, a chamber inlet plate in communication with the premix chamber wall at the chamber inlet end, the chamber inlet plate having a fuel nozzle inlet hole disposed through the chamber inlet plate, the chamber inlet plate further comprising a plurality of swirler passages disposed through the chamber inlet plate, and the chamber outlet end being open. A method of producing turbine gas is also disclosed.

Abstract: A method for controlling combustor liner carbon formation on repaired combustors includes making modular effusion panel subassemblies remote from the combustor liner; removing a non-effusion or damaged panel from the combustor liner; and replacing the non-effusion or damaged panel with the modular effusion panel.

Abstract: An apparatus and method for controlling combustor liner carbon formation is provided. The apparatus includes a dome subassembly that is removeably affixed to a modular outer panel subassembly and a modular inner panel subassembly. Each panel subassembly includes panels that are removeably affixed to one another.