Abstract: Aspects of the disclosure are directed to a method for forming a cooling circuit in at least one of a combustor panel or liner wall of an aircraft engine. The method includes producing a substrate with the cooling circuit formed in the substrate, where the cooling circuit is located in proximity to an aperture associated with the at least one of a panel or liner wall.

Abstract: A gas turbine engine has a pair of components having a high-pressure chamber on one side, and a low pressure chamber on an opposed side. A three-sided seal has one side in sealing contact with each of said components. A third side is associated with a third component. At least one non-metallic wear surface is positioned between one of the three sides of the seal and its respective component.

Abstract: A unitary one-piece hub has first and second rings and a midsection arranged between the first and second rings. The midsection includes a plurality of windows configured to receive a plurality of cross members. The windows include a lip configured to surround the cross members. A gas turbine engine and a method of providing a hub for a gas turbine engine are also disclosed.

Abstract: A liner of a combustor wall assembly generally defines a combustion chamber and includes a film cooling circuit having a channel communicating through a hot face of a substrate of the liner. An aperture of the circuit is defined by the substrate, extends through the cold face and is in fluid communication with the channel. The hot face of the substrate is covered with a coating that extends over and thus defines in-part the channel. A film cooling hole extends through the coating and is in fluid communication with the channel. A method of manufacturing the circuit includes casting the substrate with the aperture and hole; then placing an insert into the channel prior to application of the coating over the substrate and insert. The insert is then removed and the film cooling hole is formed through the coating.

Abstract: A single-walled combustor includes a multi-layered wall having a first face defining a cooling plenum and an opposite second face. A thermal barrier coating of the wall may be secured to the second face and defines at least in-part a combustion chamber. A plurality of cooling circuits each extend through the base layer and the thermal barrier coating for flowing cooling air from the plenum and into the combustion chamber. Each circuit includes a first surface recessed from the second face and spaced from the thermal barrier coating with a channel defined in-part by the first surface and covered by the thermal barrier coating. A hole in the thermal barrier coating is in fluid communication between the channel and the combustion chamber. A method of manufacturing the circuit includes fabricating the base layer with the aperture and hole; then placing an insert into the channel prior to application of the coating over the base layer and insert.

Abstract: A combustor of a gas turbine engine includes an additively manufactured liner panel with a heat transfer augmentation feature.

Abstract: A method of coating a component having a multiple of cooling holes including removing at least a portion of a prior coating from a component; mapping a location of each of the multiple of cooling holes to generate a map of cooling holes; applying a coat to the component; adjusting the map of cooling holes to account for said coat to generate a adjusted map of cooling holes; and re-drilling the multiple of cooling holes in response to the adjusted map of cooling holes.

Abstract: An ignition system for a combustor of a gas turbine engine is disclosed. The ignition system may include an igniter operatively associated with the combustor, and an electrode operatively associated with the combustor and spaced from the igniter, wherein an electrical potential is created between the igniter and the electrode to produce an electric arc therebetween.

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: Gas turbine engine systems and methods involving enhanced fuel dispersion are provided. In this regard, a representative method for operating a gas turbine engine includes: providing a gas path through the engine; introducing a spray of fuel along the gas path downstream of a turbine of the engine; and impinging the spray of fuel with a relatively higher velocity flow of air such that atomization of the fuel is increased.

Abstract: Gas turbine engine systems and methods involving enhanced fuel dispersion are provided. In this regard, a representative method for operating a gas turbine engine includes: providing a gas path through the engine; introducing a spray of fuel along the gas path downstream of a turbine of the engine; and impinging the spray of fuel with a relatively higher velocity flow of air such that atomization of the fuel is increased.

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: 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 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: 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: 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.