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 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 method of repairing an annular sheet metal combustor liner of a gas turbine engine includes cutting circumferentially around combustor liner bands bounding an effusion patch extending circumferentially around the liner, the effusion patch having effusion cooling holes and being bounded on either side by at least one effusionless band free from effusion cooling holes, to thereby remove a portion of the combustor liner having the effusion patch. A replacement liner portion including an effusion patch is provided and welded to the liner assembly, the weld extending circumferentially around the cut band to provide a welded effusionless band. The welded effusionless bands is cooled during engine use using one of film cooling of an inner surface of the welded effusionless band and impingement cooling of an outer surface of the welded effusionless band.

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 floating collar is metal injected molded with an excess portion intended to be separated, such as by shearing, from the reminder of the molded floating collar to leave a chamfer thereon and/or remove injection marks.

Abstract: A floating collar is metal injected moulded with an excess portion intended to be separated, such as by shearing, from the reminder of the moulded floating collar to leave a chamfer thereon and/or remove injection marks.

Abstract: A method of repairing an annular sheet metal combustor liner of a gas turbine engine includes cutting circumferentially around combustor liner bands bounding an effusion patch extending circumferentially around the liner, the effusion patch having effusion cooling holes and being bounded on either side by at least one effusionless band free from effusion cooling holes, to thereby remove a portion of the combustor liner having the effusion patch. A replacement liner portion including an effusion patch is provided and welded to the liner assembly, the weld extending circumferentially around the cut band to provide a welded effusionless band. The welded effusionless bands is cooled during engine use using one of film cooling of an inner surface of the welded effusionless band and impingement cooling of an outer surface of the welded effusionless band.

Abstract: A method of providing a floating collar for a gas turbine engine combustor is provided, and comprises providing an annular sheet metal blank and bending the blank to provide the floating collar with an axial extending annular collar portion, an annular flange portion extending radially from the collar portion and a smooth transition portion between the collar and flange portions. The arrangement offers reduced cost, and simplicity, and therefore facilitates manufacturing.

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 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 gas turbine engine combustor having a dome heat shield includes a cooling scheme having a plurality of impingement cooling holes extending through the combustor and a plurality of adjacent ejector holes for directing cooling air past the heat shield lips of the dome heat shields. The impingement and ejector holes are preferably staggered to reduce interaction therebetween.

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 combustor heat shield has a body defining a fuel nozzle hole. The back face of the body is mounted adjacent and spaced-apart from a combustor dome. A ridge extends around the nozzle opening to a height adapted to substantially contact the combustor dome. The ridge thereby defines a cooling compartment between the body and the combustor dome. A plurality of slots is provided through the ridge. The slots are closed by the combustor dome to provide cooling holes when the heat shield is mounted on the combustor. The cooling holes direct pressurized cooling air from the compartment to adjacent regions of the back face of the heat shield body.

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: 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 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 floating collar is metal injected moulded with an excess portion intended to be separated, such as by shearing, from the reminder of the moulded floating collar to leave a chamfer thereon and/or remove injection marks.

Abstract: A floating collar is metal injected moulded with an excess portion intended to be separated, such as by shearing, from the reminder of the moulded floating collar to leave a chamfer thereon and/or remove injection marks.

Abstract: A floating collar is metal injected moulded with an excess portion intended to be separated, such as by shearing, from the reminder of the moulded floating collar to leave a chamfer thereon and/or remove injection marks.

Abstract: A floating collar is metal injected moulded with an excess portion intended to be separated, such as by shearing, from the reminder of the moulded floating collar to leave a chamfer thereon and/or remove injection marks.