Abstract: A method of repairing a component removes a prior coating from an underlying metal substrate. Small cooling air holes extend through the substrate and the coating that is to be removed. A new coating layer is placed on the metal substrate, and over the existing cooling air holes. The location of the cooling air holes is identified by inspecting the coated component for the location of indicators of the coating passing over the cooling air holes. The identified location of the indicators is used to control a cutting tool to remove any new coating from the cooling air holes. The basic method may also benefit new manufacture.

Abstract: A method of repairing a component removes a prior coating from an underlying metal substrate. Small cooling air holes extend through the substrate and the coating that is to be removed. A new coating layer is placed on the metal substrate, and over the existing cooling air holes. The location of the cooling air holes is identified by inspecting the coated component for the location of indicators of the coating passing over the cooling air holes. The identified location of the indicators is used to control a cutting tool to remove any new coating from the cooling air holes. The basic method may also benefit new manufacture.

Abstract: An augmentor for a gas turbine engine includes an augmentor spray bar with a spray bar outlet, and an augmentor spray bar tip. The spray bar tip includes a tip body, a tip bushing and a tip support strut. The tip body includes a first flow passage extending therethrough between a tip inlet and a tip outlet, wherein the tip inlet is connected to the spray bar outlet. The tip bushing includes a bushing bore. The tip body extends through the bushing bore defining a second flow passage between the tip body and the tip bushing. The tip support strut connects the tip body to the tip bushing across the second flow passage.

Abstract: A gas turbine engine combustor has inboard and outboard walls. A forward bulkhead extends between the walls and cooperates therewith to define a combustor interior volume. Bluff body fuel injectors are along the bulkhead.

Abstract: In accordance with one aspect of the disclosure, a swirler is disclosed. The swirler may include an outer shroud and inner shroud. The inner shroud may be positioned radially inside the outer shroud. At least one of the outer shroud and inner shroud may have a major diameter greater than that of a minor diameter such that the shrouds define an ovate shape. The swirler may further include a plurality of vanes which may be positioned between the inner and outer shrouds.

Abstract: In accordance with one aspect of the disclosure, a swirler is disclosed. The swirler may include an outer shroud and inner shroud. The inner shroud may be positioned radially inside the outer shroud. At least one of the outer shroud and inner shroud may have a major diameter which is larger than a minor diameter such that the shrouds define an oblong shape. The swirler may further include a plurality of vanes which may be positioned between the inner and outer shrouds.

Abstract: The oscillating tube (10) includes a first end (12), an opposed second end (16), and a fluid conduit (18) defined by the tube extending between the opposed ends (12, 16). A segmented damping coating (20) covers in intimate contact a covered or coated portion (22) of the tube (10) so that the coated portion (22) of the tube includes at least about ten percent of an axial length of the tube and an uncoated portion (34, 36) that is not covered by the segmented damping coating (22) includes greater than about ten percent of an axial length of the tube (10). The segmented damping coating (20) may include polymers, polytetrafluoroethylene, single composition polymers, ceramic fibers, polymer fibers, reinforced polymer fibers including a polytetrafluoroethylene, ceramics, including monolithic and matrix ceramics, thermoplastics, carbon/graphic materials, silicon materials, metal rings or clamps, and combinations thereof.

Abstract: The oscillating tube (10) includes a first end (12), an opposed second end (16), and a fluid conduit (18) defined by the tube extending between the opposed ends (12, 16). A segmented damping coating (20) covers in intimate contact a covered or coated portion (22) of the tube (10) so that the coated portion (22) of the tube includes at least about ten percent of an axial length of the tube and an uncoated portion (34, 36) that is not covered by the segmented damping coating (22) includes greater than about ten percent of an axial length of the tube (10). The segmented damping coating (20) may include polymers, polytetrafluoroethylene, single composition polymers, ceramic fibers, polymer fibers, reinforced polymer fibers including a polytetrafluoroethylene, ceramics, including monolithic and matrix ceramics, thermoplastics, carbon/graphic materials, silicon materials, metal rings or clamps, and combinations thereof.

Abstract: An example damper includes a damping member configured to damp a duct wall at an interface between a duct band and the duct wall

Abstract: A combustor for a gas turbine engine includes an forward fuel injection system in communication with a combustion chamber and a downstream fuel injection system that communicates with the combustion chamber downstream of the forward fuel injection system.

Abstract: A combustor assembly includes a convergent segment followed by a divergent segment to advantageously improve combustion. The combustor assembly includes a first segment beginning at a forward end that transitions to a second segment past a transition segment in a direction along a combustor axis toward an aft end. The reduction in cross-sectional area within the first segment provides desirable fuel and air mixing properties. The convergent first segment in combination with the divergent second segment decreases residence time of fuel-air mixture within the combustor chamber that decreases production of undesirable emissions from the combustor assembly.

Abstract: A method of repairing a component removes a prior coating from an underlying metal substrate. Small cooling air holes extend through the substrate and the coating that is to be removed. A new coating layer is placed on the metal substrate, and over the existing cooling air holes. The location of the cooling air holes is identified by inspecting the coated component for the location of indicators of the coating passing over the cooling air holes. The identified location of the indicators is used to control a cutting tool to remove any new coating from the cooling air holes. The basic method may also benefit new manufacture.

Abstract: A seal for use between a first duct and a second duct and, the ducts having relative motion therebetween, includes a first plurality of fingers for attachment to the first duct to be disposed about one of the first duct and the second duct, a seal land attaching to about an other of the first duct and the second duct, and a seal attaching to the seal land and in contact with the plurality of fingers wherein one of the plurality of fingers and the seal is metallic and an other of the seal land or the plurality of fingers is non-metallic.

Abstract: An augmentor for a gas turbine engine includes an augmentor spray bar with a spray bar outlet, and an augmentor spray bar tip. The spray bar tip includes a tip body, a tip bushing and a tip support strut. The tip body includes a first flow passage extending therethrough between a tip inlet and a tip outlet, wherein the tip inlet is connected to the spray bar outlet. The tip bushing includes a bushing bore. The tip body extends through the bushing bore defining a second flow passage between the tip body and the tip bushing. The tip support strut connects the tip body to the tip bushing across the second flow passage.

Abstract: A section panel assembly for a bulkhead of a gas turbine combustor includes a section panel defining a rear or cold side and defining a front or hot side. The panel has a circumferential inner edge, a circumferential outer edge and radially extending first and second side edges each extending from the inner edge to the outer edge such that the inner and outer edges subtend a predetermined arc. The panel defines at least one opening extending from the rear side to the front side for receiving cooling air. The rear side includes a central lip extending about a periphery of the opening, and a circumferential rail spaced radially outwardly of and extending about the opening for defining a cavity region including the opening on the rear side of the section panel.

Abstract: An article has a metallic substrate having a first emissivity. A thermal barrier coating atop the substrate may have an emissivity that is a substantial fraction of the first emissivity.

Abstract: A combustor assembly includes a convergent segment followed by a divergent segment to advantageously improve combustion. The combustor assembly includes a first segment beginning at a forward end that transitions to a second segment past a transition segment in a direction along a combustor axis toward an aft end. The reduction in cross-sectional area within the first segment provides desirable fuel and air mixing properties. The convergent first segment in combination with the divergent second segment decreases residence time of fuel-air mixture within the combustor chamber that decreases production of undesirable emissions from the combustor assembly.

Abstract: A combustor for a turbine engine includes an outer liner having a row of circumferentially distributed outer combustion air holes and an inner liner circumscribed by the outer liner and having a row of circumferentially distributed inner combustion air holes. The inner and outer liners each include at least a major air hole having a first hole size, an intermediate air hole having a second hole size, and a minor air hole having a third hole size. The first, second, and third hole sizes are all different from each other.

Abstract: A combustor assembly includes a convergent segment followed by a divergent segment to advantageously improve combustion. The combustor assembly includes a first segment beginning at a forward end that transitions to a second segment past a transition segment in a direction along a combustor axis toward an aft end. The reduction in cross-sectional area within the first segment provides desirable fuel and air mixing properties. The convergent first segment in combination with the divergent second segment decreases residence time of fuel-air mixture within the combustor chamber that decreases production of undesirable emissions from the combustor assembly.

Abstract: A gas turbine engine has a combustor module including an annular combustor having a liner assembly that defines an annular combustion chamber having a length, L. The liner assembly includes a radially inner liner, a radially outer liner that circumscribes the inner liner, and a bulkhead, having a height, H1, which extends between the respective forward ends of the inner liner and the outer liner. The combustor has an exit height, H3, at the respective aft ends of the inner liner and the outer liner interior. The annular combustor has a ratio H1/H3 having a value less than or equal to 1.7. The annular combustor may also have a ration L/H3 having a value less than or equal to 6.0.