Abstract: A combustor dome heat shield and a louver are separately metal injection molded and then fused together to form a one-piece combustor heat shield.

Abstract: A combustor assembly includes a hot skin of a combustion chamber wall having an inner face exposed to the combustion chamber and an opposite outer face, a receiving skin having a securing portion affixed to the hot skin outer face in an air-tight manner and a receiving flange, extending from the securing portion, that is offset from the hot skin outer face to form a female recess, a cold skin having a cold wall portion spaced from the hot skin and forming a cooling cavity therebetween, a securing portion extending from a first end of the cold wall portion affixed to the hot skin outer face in an air-tight manner and a male flange extending from a second end of the cold wall portion opposite the first end, the male flange snugly received in the female recess and forming a sliding engagement therebetween.

Abstract: A heat shield for a gas turbine engine combustor includes an apparatus for providing a spiral flow to improve at least the cooling of the heat shield.

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 is provided having one or more apertures adapted to asymmetrically introduce air adjacent the fuel nozzles to reduce smoke resulting from unburned hydrocarbons in a gas turbine engine combustion system by impeding escape of unburned hydrocarbons.

Abstract: A combustor dome heat shield and a louver are separately metal injection molded and then fused together to form a one-piece combustor heat shield.

Abstract: A crack-resistant floating collar mounting arrangement is provided comprising a collar mounted between spaced-apart mounting flanges, the flange being fixed to a dome from an outer surface unexposed to the hot combustor temperatures.

Abstract: A gas turbine engine combustor liner having a plurality of holes defined therein for directing air into the combustion chamber. The plurality of holes provide improved cooling efficiency in regions of the combustor dome corresponding to predetermined hotspots.

Abstract: A combustor dome heat shield and a louver are separately metal injection molded and then fused together to form a one-piece combustor heat shield.

Abstract: A reverse flow combustor for a gas turbine engine having an outer combustor liner and an inner combustor liner defining an annular combustion chamber, and a compound-angle frustoconical portion in the outer liner having a first and second conical slopes towards an engine centerline.

Abstract: A gas turbine engine combustor which is cooled by a hybrid cooling apparatus and method. Heat shields cooled by impingement cooling air are present at an upstream section of the combustor liners and exhausted impingement cooling air is substantially discharged outside of the primary zone of the combustor chamber. The single-skinned downstream section of the combustor liners is cooled by effusion cooling.

Abstract: Impingement hole patterns are provided in a combustor dome panel to provide efficient cooling of a combustor dome heat shield. The impingement holes are substantially aligned or located above partial height protuberances provided on the back face of the heat shield.

Abstract: A gas turbine engine combustor liner having a plurality of holes defined therein for directing air into the combustion chamber. The plurality of holes provide a greater cooling air flow in regions intermediate each diffuser pipe than in other areas of the combustor liner.

Abstract: A combustor heat shield has a body with heat exchange promoting protuberances extending from a back face thereof. The density of protuberances is less in hot spot regions than in other heat shield regions which require less cooling.

Abstract: A welded part comprises a first detail and a second detail at least partially overlapping the first detail in an overlapping zone. A pair of side-by-side weld seams is provided in the overlapping zone to form a part suited for used in a gas turbine engine with the first and second details.

Abstract: A gas turbine engine combustor liner with at least one of the inner and outer liners that is effusion cooled and has a row of groups of circumferentially spaced apart dilution holes defined therethrough. Each group is located within a respective zone of the combustor liner defined by an overlap of adjacent conical sections corresponding to the sprays of adjacent fuel nozzles.

Abstract: A gas turbine combustor is provided with a dome heat shield having a fuel nozzle opening, the opening receiving a floating collar assembly for permitting relative movement between nozzle and heat shield. The floating collar is provided with a louver to provide film cooling to the face of the combustor heat shield and, thus, improve cooling thereof.

Abstract: A combustor having a combustor wall with a plurality of angled effusion holes defined therethrough. The tangential component of the hole direction of the effusion holes corresponds to a same rotational direction about the central axis of the combustor. The effusion holes directional arrangement is angled from a radial plane and the combustor liner surfaces in order to promote swirl at the combustor exit.

Abstract: A gas turbine engine reverse-flow sheet metal combustor for an aero gas turbine engine has a louverless single-piece liner design which includes a plurality of effusion patches, containing multiple rows of effusion cooling holes, bounded by cooled effusionless bands to aid in repairability of the combustor. The cooling of the bands improves the durability of the combustor and provides a method of repair for the combustor.

Abstract: A combustor heat shield comprises a heat shield member defining at least one opening for receiving a fuel nozzle. A louver is received in the opening. The louver has a flow diverting portion extending radially outwardly from the opening for directing air along the hot side of the heat shield member.