Abstract: A lubricant supply system for a squeeze film damper. The lubricant supply system includes a fluid passage configured to supply a lubricant to the squeeze film damper of a bearing assembly. The fluid passage includes a first flow path for lubricant into the lubricant supply system and into the squeeze film damper of the bearing assembly and a second flow path for lubricant into the squeeze film damper of the bearing assembly. The lubricant supply system includes a valve assembly configured to allow the fluid passage to move from the first flow path to the second flow path in response to an interruption of the first flow path.

Abstract: A fuel system including a fuel metering unit, a heat exchanger, a plurality of fuel nozzles, and a coke filtration system. The fuel metering unit is configured to meter a flow of a hydrocarbon fuel. The heat exchanger is fluidly connected to the fuel metering unit. The heat exchanger is configured to heat the hydrocarbon fuel to improve engine performance or efficiency. The plurality of fuel nozzles is fluidly connected to the heat exchanger downstream of the heat exchanger to receive the hydrocarbon fuel heated by the heat exchanger. The coke filtration system includes at least one filter to remove coke particles in the heated fuel. The coke filtration system is located upstream of the plurality of fuel nozzles and directly downstream of the heat exchanger.

Abstract: An annular combustor includes a combustion liner defining a combustion chamber, the combustion liner having an outer liner and an inner liner and a plurality of dimples in the combustion liner. The combustion liner is characterized by a performance factor greater than or equal to one and less than or equal to seven. An engine includes the annular combustor.

Abstract: An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment, the combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The aft end portion of the combustion liner defines a turbine nozzle. The combustion liner defines a cavity forward of the turbine nozzle. The cavity extends between the first side wall and the second side wall. An impingement cooling apparatus positioned within the cavity. The impingement cooling apparatus includes a flange. The impingement cooling apparatus further includes a plurality of impingement members configured to direct coolant to impinge upon the first side wall and the second side wall. Each impingement member extends from a respective inlet defined within the flange to a respective closed end. A plurality of impingement apertures are defined on each impingement member.

Abstract: Diffuser apparatus for turbine frames and outlet guide vanes are disclosed. An example diffuser is integrated into a turbine engine. The example diffuser includes a plurality of struts extending between an inner portion and an outer portion of the turbine engine; and a plurality of flowpath surfaces supported by the plurality of struts. The example plurality of flowpath surfaces extends circumferentially within the turbine engine at a plurality of radial spans to control diffusion of air flow within the turbine engine.

Abstract: Systems and methods of servicing engines including a method of servicing an engine, the method including navigating at least a portion of a robotic assembly to a location associated with the engine; applying, from the robotic assembly, a medium to one or more adjustable components of the engine while the engine is at an elevated temperature; waiting a duration of time; and with the robotic assembly, operating on the one or more adjustable components.

Abstract: A swirler assembly includes a swirler having primary swirler with a primary swirler venturi, a swirler ferrule plate connected to the primary swirler, and a fuel nozzle disposed in the swirler ferrule plate. The swirler ferrule plate has an aft wall, an annular conical wall, and an annular cavity wall that together form an annular cavity. The annular cavity includes a plurality of inlet orifices, and at least one outlet orifice. A flow of oxidizer through the plurality of inlet orifices into the annular cavity incurs a first pressure drop from a first pressure of a pressure plenum to a second pressure lower than the first pressure, and a flow of the oxidizer from the annular cavity through the at least one outlet orifice into the primary swirler venturi incurs a second pressure drop from the second pressure to a third pressure lower than the second pressure.

Abstract: An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment. The combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The integrated combustor nozzle further includes an impingement cooling apparatus positioned within the cavity. The impingement cooling apparatus includes a flange. The impingement cooling apparatus further includes a plurality of impingement members that each extend from a respective opening defined in the flange to a respective closed end. Each impingement member defines a plurality of impingement apertures that direct air to impinge upon one of the first side wall and the second side wall. The impingement cooling apparatus further includes stand-offs extending from each impingement member of the plurality of impingement members. The stand-offs space apart each impingement member of the plurality of impingement members from surrounding surfaces.

Abstract: A combustor includes a skeleton mesh structure having a plurality of structural elements configured to mesh together to form the skeleton mesh structure, each of the plurality of structural elements including a frame and, a plurality of louvers connected to the frame. The combustor also includes an inner liner mounted to the skeleton mesh structure to define a combustion chamber. The inner liner includes a plurality of inner planks mounted to the skeleton mesh structure, each of the plurality of inner planks being mounted to a corresponding one of the plurality of structural elements.

Abstract: A thermal management system of a gas turbine engine, the thermal management system including: a thermal transport bus configured to have a heat exchange fluid flowing therethrough and including a pump including a plurality of bearings; an auxiliary thermal bus in thermal communication with the plurality of bearings; and an auxiliary heat exchanger in thermal communication with the auxiliary thermal bus.

Abstract: A gas turbine engine having a rotor blade stage with a plurality of circumferentially spaced rotors, a nozzle stage adjacent the rotor blade stage and including an outer nozzle end, at least one stop, and a shroud. The shroud having a forward end positioned radially outward from the circumferentially spaced rotor blades, and an aft end axially aft of the forward end. The at least one stop confronting at least a portion of the outer nozzle end.

Abstract: Embodiments of the present disclosure are directed to a gas flow delivery apparatus and systems of an additive manufacturing system. The gas delivery apparatus comprises a first conduit having an elbow and an outer diameter DA and at least one second conduit fluidly coupled to the first conduit at a mixing region. The mixing region is positioned downstream of the elbow of the first conduit, and the mixing region is at least a distance Z from a center line of the at least one second conduit to the elbow. A diffuser is fluidly coupled to the first conduit downstream of the mixing region, the diffuser comprising an outlet having a perforated plate.

Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine. A compressor section and a turbine section are arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An electrical machine is coupled to the rotary member and is located at least partially inward of the core airflow path in a radial direction. An enclosure at least partially encloses the electrical machine. The enclosure at least partially defines a first cooling airflow path within the enclosure that at least partially defines a first cooling airflow buffer cavity at least partially around the electrical machine.

Abstract: An additive manufacturing machine includes an energy beam system situated in a fixed position relative to a reference plane coinciding with an expected location of a build plane, an energy beam system with an irradiation device configured to generate an energy beam and to direct the energy beam upon the build plane, and a position measurement system configured to determine a position of the build plane. A position measurement assembly includes one or more position sensors, and one or more mounting brackets configured to attach the one or more position sensors to an energy beam system of an additive manufacturing machine. The position measurement assembly is configured to determine a position of a build plane with the energy beam system situated in a fixed position relative to a reference plane coinciding with an expected location of the build plane.

Abstract: An unducted thrust producing system, includes a rotating element, a stationary element. An inlet may be located forward or aft of the rotating element and the stationary element. An exhaust may be located forward, aft, or between the rotating element and the stationary element.

Abstract: Additive manufacturing apparatus, along with methods of forming an object therewith, are provided. The additive manufacturing apparatus may include at least one build unit; a build platform (such as a rotating build platform); and a pair of collectors positioned on the apparatus such that a first collector contacts an outer surface of an object as it is formed on the build platform and a second collector contacts an inner surface of the object as it is formed on the build platform.

Abstract: An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane formed of a first material, and an edge guard disposed about an edge of the fan blade. The edge guard may include a matrix composite that has a toughness that is greater than a toughness of the first material. The airfoil may include a fan blade or an outlet guide vane. The first material of the airfoil may include a metal alloy and/or a matrix composite. A method of manufacturing an airfoil for a fan section of a turbine engine may include manufacturing an edge guard, attaching the edge guard to the airfoil.

Abstract: A heat exchanger for a hydrogen fuel delivery system includes a tube bank including an inner-tube where a first portion of the inner-tube extends through an inlet region of the tube bank, a second portion of the inner-tube extends through a mid-region of the tube bank, and a third portion of the inner-tube extends through an outlet region of the tube bank. A thermal buffer at least partially surrounds the inner-tube. A first portion of the thermal buffer extends along the first portion of the inner-tube, a second portion of the thermal buffer extends along the second portion of the inner-tube, and a third portion of the thermal buffer extends along the third portion of the inner-tube. A plurality of fins is disposed along the inner-tube and extends radially outwardly from an outer surface of the thermal buffer.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed for a structure of an engine component, including a first plurality of unit cells offset from a neutral plane in a first direction, a second plurality of unit cells offset from the neutral plane in a second direction, a plurality of nodes joining ones of the first plurality of unit cells and ones of the second plurality of unit cells, wherein the first plurality of unit cells and the second plurality of unit cells are arranged in pairs such that ones of the first plurality of unit cells are laterally adjacent to and interconnected with ones of the second plurality of unit cells, and wherein the structure is a stiffened structure.

Abstract: A seal assembly for a component of a turbomachine and method of assembly thereof is provided. The seal assembly includes at least one mating face positioned adjacent to the component and a seal coupled to the mating face. The seal includes an outer shell defining an interior space; an inner matrix filling the interior space comprising a plurality of unit cells comprising one or more metamaterials, wherein at least a portion of the plurality of unit cells are identical, and wherein the plurality of unit cells are repeated throughout the inner matrix; and one or more support struts extending throughout the inner matrix. The method of building the seal assembly may include selecting a first material for the outer shell and selecting the one or more metamaterials for the inner matrix based on the first material.