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: An airfoil for a turbomachine such as a gas turbine engine includes a pressure side and a suction side, a flow-distributing forward wall and an inner cooling wall. A switchbacked passage extends through the airfoil, and the flow-distributing forward wall has a plurality of jetting orifices formed therein and connecting the switchbacked passage to a forward cavity. The jetting orifices are oriented to produce wall jets of cooling fluid directed in an upstream direction toward a back side of the leading edge. A second passage extends between the forward cavity and outlets of the airfoil, so as to convey cooling fluid in a downstream direction toward the outlets.

Abstract: A control system for preventing electrical power supply disruptions in an electrical power system includes an electronic control unit structured to receive a power signal indicative of reactive power in an electrical generator that is produced in response to a change in an electrical load of an electrical power bus. The electronic control unit is further structured to determine voltage commands based on the power signal and vary output voltage of the electrical generator non-linearly such that occurrence of a reactive power shutdown condition is inhibited.

Abstract: An airfoil for a turbomachine such as a gas turbine engine includes a switchbacked passage for conveying cooling fluid, and flow-distribution passages in a forward wall so as to direct cooling fluid from the internal passage for back side impingement upon a leading edge of the airfoil. An inner cooling wall forms a passage for discharging the spent cooling air from a trailing edge of the airfoil after impingement, and cools one of a pressure side and a suction side of the airfoil by way of conduction. The switchbacked passage may have a serpentine form.

Abstract: A turbine blade for a gas turbine engine may include an outer, peripheral wall extending along a suction side and a pressure side of the blade from a leading edge to a trailing edge of the blade and from a root end to a tip end of the blade, a substantially vertical bifurcating internal wall extending between the leading edge and the trailing edge of the blade in between the suction side and the pressure side of the blade, a plurality of pressure side cooling fluid passages defined between the peripheral wall on the pressure side of the blade and the bifurcating internal wall and extending at least part way from the root end to the tip end of the blade, and a plurality of suction side cooling fluid passages defined between the peripheral wall on the suction side of the blade and the bifurcating internal wall and extending at least part way from the tip end to the root end of the blade.

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 turbine blade for a gas turbine engine may include at least two wrapped, serpentine-shaped internal cooling paths. A first one of the serpentine-shaped internal cooling paths may include a first passage that extends radially along a leading edge of the turbine blade from adjacent a root end of the turbine blade to adjacent a tip end of the turbine blade. The first passage may be configured to provide fresh cooling fluid to the leading edge. A second passage downstream of the first passage may be configured to discharge spent cooling fluid from the first passage of the first one of the serpentine-shaped internal cooling paths across a plurality of flow disrupters positioned along an upper span of a trailing edge of the turbine blade before exiting from the trailing edge of the turbine blade. A second one of the serpentine-shaped internal cooling paths may be configured to supply fresh cooling fluid to a lower span of the trailing edge of the turbine blade.

Abstract: A tool is provided for stabilizing a position of a shaft disposed within a casing and rotatably supported by a pair of bearings that are spaced-apart from one another and located within the casing. The tool includes an arcuately-shaped shoe that is located between the pair of bearings and releasably connected to the casing. The shoe has a concave surface defining a radius corresponding to a radius of the shaft. The shoe is resiliently biased away from the casing for facilitating the concave surface of the shoe to radially abut with a portion of an outer circumference of the shaft.

Abstract: A control system for a gas turbine engine is disclosed. In embodiments, control system includes a controller and a high speed recorder. The controller obtains sensor values from sensors connected to the gas turbine engine and publishes a map of trigger events. The high speed recorder reads the sensor values from the controller. The high speed recorder checks a map header for a change to the map header on a predetermined map reading interval, sets a flag when the map header has changed, and reads the map during the next loop of the map reading interval. The control system maintains timestamps assigned for the sensor values and to the trigger events on the same temporal axis.

Abstract: A modular building structure for a turbomachinery equipment includes a first prefabricated structure, a second prefabricated structure, and a plurality of guides to align and couple the first prefabricated structure to the second prefabricated structure. The first prefabricated structure includes a first rigid frame formed from first linear members, and defines first pin receiving holes. The second prefabricated structure includes a second rigid frame formed from second linear members, and defines second pin receiving holes. Each guide includes a plate having an opening extending through the plate, and an elongated member extending through the opening of the plate. The elongated member includes a first end portion extending inside a corresponding first pin receiving hole and a second end portion extending inside a corresponding second pin receiving hole for coupling the first prefabricated structure with the second prefabricated structure.

Abstract: A cutting assembly for cutting a workpiece includes a frame, a fixture, and a saw. The fixture is coupled to the frame, and is configured to receive the workpiece. The saw has a cutter to cut the workpiece. The saw is pivotally coupled to the frame. The cutting assembly further includes a locking assembly for locking the workpiece within the fixture. The locking assembly includes a lock structure pivotally coupled to the fixture. The lock structure is configured to lock the workpiece within the fixture. The locking assembly further includes a telescopic structure coupled to the saw and the lock structure. The telescopic structure is configured to move the lock structure in response to a pivotal movement of the saw. The telescopic structure facilitates a locking, by the lock structure, of the workpiece within the fixture.

Abstract: A lifting tool for gripping an object, is provided. The lifting tool includes a body and a locking arrangement. The body defines a gripping cavity for receiving the object. The locking arrangement lock the object within the gripping cavity. The locking arrangement includes a shaft having an eccentric structure and a pin. The shaft and the eccentric structure are configured to rotate about a longitudinal axis. The pin is configured to engage with the eccentric structure and lock the object within the gripping cavity. The pin is biased in a first position, where a portion of the pin extends into the gripping cavity and locks the object within the gripping cavity.

Abstract: A lifting tool for gripping an object, is provided. The lifting tool includes a body and a locking arrangement. The body defines a gripping cavity for receiving the object. The locking arrangement lock the object within the gripping cavity. The locking arrangement includes a shaft having an eccentric structure and a pin. The shaft and the eccentric structure are configured to rotate about a longitudinal axis. The pin is configured to engage with the eccentric structure and lock the object within the gripping cavity. The pin is biased in a first position, where a portion of the pin extends into the gripping cavity and locks the object within the gripping cavity.

Abstract: A gas turbine engine system includes a gas turbine engine and a control system including sensors for monitoring operating properties of the engine, a signaling device that outputs a discrete switching signal indicative of an engine load change, such as connecting or disconnecting an electrical load in an electrical power system powered by the gas turbine engine, and an electronic control unit. The control unit calculates an engine load estimate based upon the switching signal, the operating properties, and statistical information in a recursive statistical estimator.

Abstract: A noise attenuation baffle assembly for a duct, is provided. The baffle assembly includes a number of baffles arranged in a spaced apart relation to one another. Each baffle includes a first side and a second side. The baffle assembly further includes a first bracket coupled to the first side of each baffle of the number of baffles. The baffle assembly further includes a second bracket coupled to the second side of each baffle of the number of baffles. The first and the second bracket are configured to be coupled to the duct.

Abstract: A fuel injector for a gas turbine engine is disclosed. The fuel injector includes a flange assembly with a distribution block, three main gas tubes, and an injector head. The distribution block evenly distributes a main gas fuel to the three main gas tubes. The injector head includes an injector body with a primary gas gallery including an annular shape. The three main gas tubes are connected in a parallel configuration between the distribution block and the primary gas gallery. The three main gas tubes are all in flow communication with the primary gas gallery and provide the main gas fuel from the same main gas fuel source.

Abstract: A center body assembly for a fuel injector is disclosed. The center body assembly defines a primary liquid passage, a liquid gallery, swirl slots, and a prefilm passage. The primary liquid passage supplies liquid fuel to the liquid gallery. The liquid gallery includes a gallery discharge end and a gallery inlet end that aligns with the primary liquid passage. The liquid gallery tapers down from the gallery inlet end to the gallery discharge end. The swirl slots extend from the liquid gallery to the prefilm passage in a helical pattern. The prefilm passage includes an annular shape that turns inward towards an assembly axis of the center body assembly.

Abstract: A method of monitoring a turbomachinery is disclosed herein. The method includes measuring the pressure drop across the intake filter. The method further includes determining clog rate parameters for a clog rate of a filter area of the intake filter based on the measured pressure drop across the intake filter. The method yet further includes predicting the pressure drop across the intake filter for the intake filter life cycle based on the determined clog rate parameters and providing a recommended time to service the intake filter to an operator of the turbomachinery system based on the predicted intake filter life cycle.

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: 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.