Abstract: The systems and methods disclosed herein include an assessment system and process for assessing an industrial machine and its various sections, sub-sections, and parts. In embodiments, the assessment system includes an assessment device that includes an assessment overviewer and a part assessor. The assessment overviewer provides an assessor with a selectable industrial machine schematic that illustrates the assessment status of each section of the industrial machine, such as by changing the appearance of each section based its assessment status. The part assessor provides a part assessment interface with engineering instructions and a part grading user interface that provides for a comparison of digital images to complete the part grading.

Abstract: A fuel injector for a combustor of a gas turbine engine is disclosed herein. In embodiments, the fuel injector includes an injector head adjoining a stem. The injector head includes a main premix passage, a main air inlet, vanes, and a main premix resonator. The main premix passage extends through the injector head and the main air inlet directs compressed air into the main premix passage. The vanes are located within the main premix passage for swirling the compressed air. The main premix resonator is located adjacent to and downstream of the vanes.

Abstract: A ventilation panel for an enclosure of an industrial machine is disclosed herein. In embodiments, the ventilation panel includes a panel silencer and a fire damper assembly. The panel silencer includes a number of panels joined together to form an internal cavity and a front panel opening that provides access into the internal cavity. The fire damper assembly partially inserts into the panel silencer. The fire damper assembly includes a plurality of isolation louvers and an actuation assembly. The plurality of isolation louvers are rotatably affixed within the fire damper assembly. The actuation assembly rotates the plurality of isolation louvers into a closed position when activated.

Abstract: A fuel distribution manifold for a gas turbine engine is disclosed herein. The fuel distribution manifold includes a manifold body, a stage divider, and a plurality of manifold outlet ports. The stage divider subdivides an internal volume of the manifold body into a primary stage volume and a secondary stage volume. A majority of the plurality of manifold outlet ports extends from the manifold body between the primary inlet port and the stage divider, each being fluidly connected to the primary stage volume. A remainder of the plurality of manifold outlet ports extends from the manifold body between the secondary inlet port and the stage divider, each being fluidly connected to the secondary stage volume.

Abstract: A system for automated design of a machine having multiple driven bodies is disclosed. The system may have a multi-body database with at least one of a parts section and a launch code section. The system may also have one or more processors configured to cause a listing of components selectable for inclusion within a machine to be shown on a display device, and to receive a selection of an input component and the multiple driven bodies from the listing via an input device. The processors may also be configured to retrieve data regarding the selected input component and the multiple driven bodies from the at least one of the parts section and the launch code section, and to generate a design for at least one new support component in the machine based on the input component, the multiple driven bodies, and the data.

Abstract: A fuel injector for a gas turbine engine may include a center body disposed about a longitudinal axis, and a premix barrel positioned radially outwardly from the center body to define an annular passageway between the center body and the premix barrel. The annular passageway may extend from an upstream end that is configured to be fluidly coupled to a compressor to a downstream end that is configured to be fluidly coupled to a combustor. The premix barrel may include a first portion at the upstream end and a second portion at the downstream end. The first portion may include a stainless steel material, and the second portion may include a nickel based superalloy material. The second portion may be coupled to the first portion by a laser clad coupling.

Abstract: A fuel injector for a combustion engine includes an injector head including a nozzle, a premixer, and a distributor structured to distribute a plurality of different fuels to different sets of fueling orifices in the premixer. A pilot assembly of the fuel injector is coupled to the premixer and includes a first fueling passage for a first fuel and a second fueling passage for a second fuel. Multiple sets of fueling orifices are positioned within the fuel injector, the fueling orifice sets being selectively connectable to a plurality of different fuel supplies, and both located and sized so as to accommodate a wide range of flow rates to enable a combustion engine coupled with the fuel injector to operate on fuels having a range of Wobbe indices and compositions.

Abstract: A flanged component for a gas turbine engine is disclosed herein. The flanged component includes a flange body with a flange mating surface and a plurality of threaded features. Each threaded feature includes a threaded portion and a relief portion. The threaded portion has threads and extends into the flange body from the flange mating surface. The relief portion extends into the flange body from the flange mating surface located outward from the threaded portion forming a rim portion therebetween. The rim portion includes an upper rim surface having an annular shape. The relief portion includes an inner surface extending from the rim and tapering outward from the upper rim surface.

Abstract: A system and method for detecting the rotation breakaway of a spacer from a compressor rotor disk are disclosed herein. The method includes detecting a disk sensed feature and a spacer sensed feature on the compressor rotor disk and the spacer respectively. The method also includes comparing the timing between the two to a predetermined threshold to determine whether the relative position of the spacer to the compressor rotor disk exceeds a predetermined amount. The predetermined amount may be selected to determine whether an imbalance, rubbing, or binding can occur in the gas turbine engine or to determine whether anti-rotation features have been broken.

Abstract: A device and method for reducing swirl in a gas compressors is provided. The device can include a tubular or annular seal body having an abradable interior surface for use in forming a seal. The tubular body can further have a plurality of swirl teeth arranged on a high pressure side of the seal body. The swirl teeth are disposed so as to form swirl slots between the adjacent swirl teeth. The swirl teeth can have a brake chord and a brake pitch describing the length and separation of each adjacent swirl tooth. The ratio of the brake pitch to the brake chord can be optimized in order to maximize creation of free vortices between the swirl teeth as the compressor rotates to for swirl reduction.

Abstract: A method for operating a gas turbine engine is disclosed. The method includes detecting an off-load transient of the gas turbine engine. The method includes reducing a total flow of fuel to a combustor section of the gas turbine engine to a first reduced flow in response to detecting the off-load transient. The method includes adjusting a position of an inlet guide vane in response to detecting the off-load transient until either an on-load transient is detected or until an amount of time elapsed since detection of the off-load transient exceeds a maximum override time.

Abstract: A power connector for an electric motor is disclosed. The power connector includes a flange, a conductor rod, and an insulation sleeve. The conductor rod includes a first portion extending in a first direction from the flange and a second portion extending from the flange in a second direction, opposite the first direction. The second portion includes a lead wire connection end distal to the flange. The insulation sleeve covers the second portion from the flange to the lead wire connection end. The insulation sleeve includes a sleeve outer surface, and a sealing rib extending outward from the sleeve outer surface.

Abstract: A preswirler for a gas turbine engine diaphragm assembly is disclosed herein. In embodiments, the preswirler includes an outer ring and an inner ring. The outer ring includes an outer ring face, a first contact protrusion, and a second contact protrusion. The first and second contact protrusions are spaced apart and extend from an outer body portion at the outer ring face. The inner ring is located inward from the outer ring. The inner ring includes an inner ring face and a third contact protrusion. The third contact protrusion extends in from an inner body portion and at the inner ring face.

Abstract: A fuel injector for a combustor of a gas turbine engine is disclosed herein. In embodiments, the fuel injector includes an injector head, a stem, a fuel passage, a fitting, a fuel inlet, and a resonator. The stem extends from the injector head. The fuel passage extends within the towards the injector head. The fitting is joined to the stem distal to the injector head. The fuel inlet fluidly connects the fitting to the fuel passage. The resonator includes a resonator body enclosing a resonator cavity and a resonator neck passage that fluidly connects the resonator cavity to the fuel passage adjacent to the fuel inlet.

Abstract: A sump tank for use with a gas turbine engine in offshore conditions is disclosed. In embodiments, the sump tank includes two circuitous lubricant flow paths. Each flow path includes an end compartment, a side compartment, and a tube that feed to a central compartment. The baffles used to form the central compartment are angled so as to cause the lubricant entering from the tubes to swirl, which may increase the residence time of the lubricant and may help ensure that any entrained air is released from the lubricant prior to entering the suction line.

Abstract: A testing fixture for testing a component of an industrial machine is disclosed herein. The testing fixture includes a fixture block and a component interfacing fixture that fastens to the fixture block. The fixture block includes a block tapered bore that forms a block tapered bore wall. The block tapered bore wall includes a block tapered surface with a frustoconical shape. The component interfacing fixture includes a receiving slot for the component and a stem. The stem includes a tapered portion that has a stem tapered surface with a frustoconical shape that mates with the block tapered surface.

Abstract: A system and method for controlling bending modes of a rotor assembly is disclosed. The rotor assembly can be supported by one or more bearings in an integrated machine. The method can include accelerating the rotor assembly to a first rotational speed via a first torsional force applied to the drive shaft and then removing the first torsional force. The method can also include obtaining first measurements of the rotational speed and frequency of one or more bending modes of the rotor assembly during a first rotary machine coast down period from the first rotational speed. The process can be repeated to determine a relationship between rotational speed, bending mode frequency, and gain. The one or more bearings can then be controlled based on the measurements and the relationship. The system can have one or more processors or controllers to implement the method.

Abstract: A building structure for operating turbomachinery equipment is disclosed. The building structure includes a first pre-fabricated structure, a second pre-fabricated structure, and a connector attaching the first pre-fabricated substructure to the second pre-fabricated substructure. Each pre-fabricated substructure includes a rigid frame formed from a plurality of linear members. The plurality of linear members forms a first rectangular structure, a second rectangular structure, and connects the first rectangular structure to the second rectangular structure. Each pre-fabricated substructure also includes a noise attenuating sealing panel attached to one or more of the first rectangular structure and the second rectangular structure. The connector includes a spacer plate inserted between first and second pre-fabricated substructures and a fastener. The spacer plate includes an elongated opening extending through the spacer plate.

Abstract: A method forming a metallic structure having two or more portions is provided. The method can include providing a first layer of metal-forming material and then applying energy of a first power level to a first area of the first layer of metal-forming material to form a first portion of the metallic structure having a first density. Energy of a second power level can then be applied to a second area of the first layer of metal-forming material to form a second portion of the metallic structure having a second density. A second layer of the metal-forming material can be applied on top of the first portion and the second portion. The energy of the first power level can be applied to a first area of the second layer of metal-forming material and the energy of the second power level can be applied to a second area of the second layer to form the metallic structure.