Abstract: A component for a gas turbine engine. The component includes a body. The body has an exterior surface abutting a flowpath for the flow of a hot combustion gas through the gas turbine engine. Further, the body defines a cooling passageway within the body to supply cool air to the component. The component includes a leading face and a trailing face defining a trench therebetween on the exterior surface. The body defines a plurality of cooling holes extending between the cooling passageway and a plurality of outlets defined in the trench such that the trench is fluidly coupled to the cooling passageway. Additionally, the leading face and trailing face are each tangent to at least one of the plurality of outlets. The trench directs the cool air along a contour of the component.

Abstract: Nozzle segment assemblies for gas turbine engines include an outer band, inner band, and at least one airfoil body between the outer band and inner band. The airfoil body includes an outer end extending through the outer band and having an outer end reinforced wall portion engaging with the outer band and an inner end extending through the inner band and having an inner end reinforced wall portion engaging with the inner band. A thickness of the outer end and inner end reinforced wall portions are each greater than a thickness of a central wall portion of the airfoil body to reduce stresses in the airfoil body. The outer band, the inner band, and the airfoil bodies are ceramic matrix composite (CMC) materials. Direct mounting of the airfoil bodies to the inner and outer hangers of the nozzle further reduce stress.

Abstract: An airfoil assembly and a method of manufacturing the same are provided, the airfoil assembly defining a span axis, a root end, and a tip end. The airfoil assembly includes a reinforcement structure comprising a first helical support structure wrapped around the span axis between the root end and the tip end and a second helical support structure wrapped around the span axis between the root end and the tip end; a polymeric matrix material positioned at least partially around the reinforcement structure; and an outer skin positioned around the reinforcement structure and the polymeric matrix material.

Abstract: Methods and systems for synthesizing contrast images from a quantitative acquisition are disclosed. An exemplary method includes performing a quantification scan, using a trained deep neural network to synthesize a contrast image from the quantification scan, and outputting the contrast image synthesized by the trained deep neural network. In another exemplary method, an operator can identify a target contrast type for the synthesized contrast image. A trained discriminator and classifier module determines whether the synthesized contrast image is of realistic image quality and whether the synthesized contrast image matches the target contrast type.

Abstract: A gas turbine engine includes a casing, a rotor assembly rotatably mounted within the casing, the rotor assembly comprising a forward rotor portion defining a forward rotor cavity and an aft rotor portion defining an aft rotor cavity, the aft rotor cavity being fluidly isolated from the forward rotor cavity, and a cooling system. The cooling system includes a forward cooling fluid supply, a forward supply line providing fluid communication between the forward cooling fluid supply and the forward rotor cavity, an aft cooling fluid supply, an aft supply line providing fluid communication between the aft cooling fluid supply and the aft rotor cavity, and a flow control system fluidly coupled to the forward supply line and the aft supply line for regulating a flow of forward cooling fluid and a flow of aft cooling fluid.

Abstract: Additive manufacturing assemblies, printing assemblies, and methods for utilizing same are provided. A method includes providing a linear traversing stage (212) movable in a direction transverse to a rail (104) extending along a working axis of the additive manufacturing apparatus, and coupling a printing assembly (150) to the linear traversing stage (212) such that the printing assembly is movable along the linear traversing stage in a direction transverse to the working axis. In embodiments, the printing assembly includes a housing (201) including a printing head (154). At least one adjustment member (232) may be extended or retracted through a yaw bar (224) to rotate the housing. In embodiments, a printing head receptacle (502) may be provided for coupling the printing assembly to the rail. In embodiments, the yaw bar (224) may be provided between the housing and the printing head receptacle (502) for rotating the printing assembly relative to the printing head receptacle.

Abstract: A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gears, and a ring gear. The gear assembly is connected to an input shaft and an output shaft. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and is driven by the input shaft. A component of the gear assembly drives the output shaft. The gear assembly further comprises an output shaft reversal mechanism configured to reverse the rotational direction of the output shaft.

Abstract: A hazardous gas monitoring system is provided. The hazardous gas monitoring system includes a panel including multiple sensing lines. Each sensing line is configured to receive and monitor an air sample. Each sensing line includes a water separator to remove condensed moisture, a coalescing filter disposed downstream of the water separator, and a flow and gas monitoring system disposed downstream of the coalescing filter. The hazardous gas monitoring system may be used to monitor the presence of hazardous gases within an enclosure, such as an enclosure for a turbomachine.

Abstract: A method of operating a fuel management unit for a fuel system. The method including: receiving data indicative of a state of an exhaust assembly using a sensor of the fuel system, the state of the exhaust assembly including a temperature of a working gas flow within the exhaust assembly; determining an amount of a hydrogen fuel in a liquid phase to provide to a hydrogen delivery assembly in response to receiving data indicative of the state of the exhaust assembly; and directing one or more components to provide the determined amount of the hydrogen fuel to the hydrogen delivery assembly.

Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.

Abstract: A hoist for lifting at least a portion of a gas engine assembly includes a support member including an upper portion, a lower portion, and a connecting portion extending therebetween. The hoist also includes an elongate member coupled to the lower portion of the support member and extending substantially orthogonally to the lower portion, and at least one bracket slidably engaged with the elongate member and axially translatable along a length of the elongate member. In addition, the hoist includes a plurality of linkage members coupled to the at least one bracket, where each linkage member of the plurality of linkage members is configured to attach to at least a portion of the gas engine assembly.

Abstract: Hybrid electric propulsion systems includes a combustion engine and an electric motor. The hybrid electric propulsion systems may include or utilize a non-transitory computer-readable medium comprising computer-executable instructions, which when executed by a processor associated with the hybrid electric propulsion system, cause the processor to perform a method that includes determining an occurrence of a thrust asymmetry in the hybrid electric propulsion system, and controlling the electric motor to decrease an efficiency of the electric motor for a transient time period sufficient to reduce a torque output of the combustion engine to match an electrical load on the combustion engine.

Abstract: A composite component for a gas turbine engine includes a body including a composite material. Furthermore, the composite component includes a connection feature integrally woven to the body. Additionally, the connection portion includes a composite material. Moreover, the composite material of the body and the composite material of the connection feature include alternating layers of fiber tows integrally woven together.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to implement an integrated stator-fan frame assembly. An integrated fan exit stator-fan frame strut assembly for a gas turbine engine includes a fan exit stator portion having an airfoil including a leading edge and a trailing edge, and a fan frame strut portion including a leading edge and a trailing edge, the leading edge of the fan frame strut portion aerodynamically integrated with the trailing edge of the fan exit stator portion.

Abstract: A method of servicing equipment, the method comprising: recording information associated with servicing of the equipment in view of a workscope at a first location; sending the recorded information to a node; receiving service input from a third party located at a second location different from the first location, the third party having prepared the service input in response to the recorded information on the node; and performing the service using the received service input.

Abstract: An additive manufacturing apparatus is disclosed. The apparatus includes a build surface, at least a portion of which is transparent. The apparatus includes a first material depositor operable to deposit a curable resin to form a deposited resin layer on the build surface. A first sensing device is configured to measure the thickness of the deposited resin layer; and wherein the at least one sensing device is configured to generate a signal indicative of the thickness of the deposited resin layer. The first sensing device can be connected to a computer such that the additive manufacturing apparatus is configured to control the thickness of the deposited resin layer. The thickness of the deposited resin layer can be controlled such that it varies from side to side. The thickness can also be controlled such that it varies with time.

Abstract: An additive manufacturing apparatus includes a feed module and a take-up module that are configured to operably couple with a foil. A stage is configured to hold one or more cured layers of a resin that form a component. A radiant energy device is positioned opposite to the at least one stage. The radiant energy device is operable to generate and project radiant energy in a predetermined pattern. An actuator is configured to change a relative position of the at least one stage and the foil. An accumulator is positioned between the feed module and the take-up module. The accumulator is configured to retain an intermediate portion of the foil to allow a first portion of the foil upstream of the accumulator to move at a first speed and a second portion of the foil downstream of the accumulator to move at a second speed during a defined time period.

Abstract: A motorized apparatus for use in maintaining a pipe having a sidewall defining an interior cavity is provided. The motorized apparatus includes a body assembly extending along a longitudinal axis, at least one maintenance device coupled to the body assembly, and a plurality of leg assemblies coupled circumferentially around the body assembly. The motorized apparatus also includes a plurality of drive mechanisms coupled to the plurality of leg assemblies. The plurality of drive mechanisms are configured to interact with the sidewall. The plurality of drive mechanisms include at least two wheels. The plurality of drive mechanisms are arranged to move the body assembly in a first direction parallel to the longitudinal axis, move the body assembly in a second direction perpendicular to the longitudinal axis, and rotate the body assembly around the longitudinal axis.

Abstract: A combustor includes an inner liner and an outer liner defining a combustion chamber. The inner liner includes an inner mesh structure, and a plurality of inner planks mounted to the inner mesh structure. The outer liner includes an outer mesh structure, and a plurality of outer planks mounted to the outer mesh structure. Each of the plurality of inner planks and outer planks includes an inner wall, an outer wall, and lateral walls defining a cavity to allow circulation of airflow within the cavity to cool down the inner wall.

Abstract: A method for providing grid-forming control of an inverter-based resource includes receiving, via a controller, a power reference signal. The method also includes determining a dynamic power change limit. Further, the method includes determining, via the controller, an upper power boundary and a lower power boundary for grid-induced power deviations from a desired power operating point based on the power reference signal. Moreover, the method includes determining, via the controller, limits for an inertial power regulator reference based, at least in part, on the upper and lower power boundaries and the dynamic power change limit. In addition, the method includes applying, via the controller, the limits to the inertial power regulator reference in an inertial power regulator of the inverter-based resource.