Abstract: The build-up of carbon deposition on the front face of a combustor heat shield is discouraged by jetting air out from the front face of the heat shield with sufficient momentum to push approaching fuel droplets or rich fuel-air mixture way from the heat shield.

Abstract: A heat shield unit for a gas turbine engine combustor comprises a panel body secured to a combustor liner. A first surface of the body is oriented toward a combustion zone of a combustor. A second surface is oriented toward the liner. The body is separated into upstream and downstream portions. Pin fins project from the second surface of the body. The pin fins are arranged in arrays of at least two different densities of volume of pin fins per unit volume. One density, lower than the second density, is in the upstream portion and another in the downstream portion of the body. Connectors connect the body to the liner with a line between the upstream and downstream portions of the body aligned with fluid-coolant injection apertures in the liner. A gas turbine engine combustor and a method for cooling a heat shield unit in a combustor liner of a gas turbine engine are also provided.

Abstract: A heat shield unit for a gas turbine engine combustor comprises a panel body secured to a combustor liner. A first surface of the body is oriented toward a combustion zone of a combustor. A second surface is oriented toward the liner. The body is separated into upstream and downstream portions. Pin fins project from the second surface of the body. The pin fins are arranged in arrays of at least two different densities of volume of pin fins per unit volume. One density, lower than the second density, is in the upstream portion and another in the downstream portion of the body. Connectors connect the body to the liner with a line between the upstream and downstream portions of the body aligned with fluid-coolant injection apertures in the liner. A gas turbine engine combustor and a method for cooling a heat shield unit in a combustor liner of a gas turbine engine are also provided.

Abstract: A method for making or repairing a laser drilled hole in a component of gas turbine engines, to meet requirements of air flow through the hole, includes deformation of an excess material melted during the laser drilling process and remaining around an opening end of the hole, thereby causing a marginal reduction in an effective diameter of the hole.

Abstract: A combustor for a gas turbine engine includes an annular combustor shell having an inner liner and an outer liner respectively with inner and outer flanges at least partly overlapping to form a dome end portion of the shell, at least the outer flange including intersecting upstream and downstream wall portions defining a corner therebetween, the upstream wall portion having a plurality of cooling apertures defined therethrough immediately upstream of the corner, and the cooling apertures being oriented to direct a cooling air flow from outside the combustor shell therethrough and adjacent an inner surface of the downstream wall portion.

Abstract: A combustor for a gas turbine engine is provided, the combustor having an outer shell with an outer surface exposed to cooling air and an inner surface, and at least one floatwall panel attached to the inner surface of the outer shell and having a trailing edge. At least one dilution hole is in the floatwall panel near the trailing edge and in communication with the outer surface of the outer shell, and at least one local air impingement hole is in the outer shell downstream of each at least one dilution hole, that directs the cooling air towards the trailing edge of the floatwall panel.

Abstract: A combustor for a gas turbine engine is provided, the combustor having an outer shell with an outer surface exposed to cooling air and an inner surface, and at least one floatwall panel attached to the inner surface of the outer shell and having a trailing edge. At least one dilution hole is in the floatwall panel near the trailing edge and in communication with the outer surface of the outer shell, and at least one local air impingement hole is in the outer shell downstream of each at least one dilution hole, that directs the cooling air towards the trailing edge of the floatwall panel.

Abstract: A combustor for a gas turbine engine includes an annular combustor shell having an inner liner and an outer liner respectively with inner and outer flanges at least partly overlapping to form a dome end portion of the shell, at least the outer flange including intersecting upstream and downstream wall portions defining a corner therebetween, the upstream wall portion having a plurality of cooling apertures defined therethrough immediately upstream of the corner, and the cooling apertures being oriented to direct a cooling air flow from outside the combustor shell therethrough and adjacent an inner surface of the downstream wall portion.

Abstract: A combustor for a gas turbine engine includes a sheet metal combustor wall having a plurality of cooling apertures therein immediately upstream of a corner between two intersecting combustor wall portions.

Abstract: A combustor for a gas turbine engine includes a sheet metal combustor wall having a plurality of cooling apertures therein immediately upstream of a corner between two intersecting combustor wall portions.

Abstract: The individual outputs of a large laser diode array are combined using an optical transformer of diffractive optics. To allow for the tolerances in the laser array and combining optics required for mass production, the system further includes corrector optics. The corrector optics includes individual lens elements which are fabricated to provide specific correction of faults in the individual lasers and associated combining optics resulting from manufacturing tolerances. The preferred corrector lenses include diffractive lenses fabricated by laser milling.