Abstract: An exhaust system of a turbine typically includes an exhaust collector that turns the axial flow of exhaust, output by the turbine, radially outward, with the intent of diverting the flow up an exhaust stack. However, the width of the exhaust collector may be limited by packaging engineering, which can decrease the efficiency of the exhaust system. Accordingly, an exhaust collector is disclosed that utilizes non-cylindrical conical shapes in an exhaust diffuser to maximize volume and reduce velocity in the exhaust collector, to compensate for the decrease in efficiency caused by a reduced width of the exhaust collector.

Abstract: A tip shroud, comprising a plurality of tip shoes encircling a rotor assembly, in a turbine may deform due to thermal gradients experienced during operation of the turbine. Accordingly, a tip shoe is disclosed that utilizes an internal cooling cavity to supply coolant throughout the interior of the tip shoe, as well as to the slash faces of the tip shoe. In addition, features are described that increase the surface area exposed to the coolant, while remaining suitable for additive manufacturing.

Abstract: In a gas turbine engine, coolant (e.g., cooling air) is prone to leak out of the interface between the combustor case, the nozzle of the turbine, and the exhaust diffuser. Embodiments of an interface are disclosed that provide non-fretting sealing using an interference fit between radially facing surfaces of a combustor flange and diffuser flange. In addition, one or more contact sealing lands may be used between the combustor flange and diffuser flange and one or more seals may be provided between various components of the interface to provide additional sealing.

Abstract: Enclosures are used to attenuate noise produced by a high decibel producing device, such as a gas turbine engine or other rotating machinery. However, enclosures that achieve high Sound Transmission Class (STC) ratings are generally expensive and immobile, whereas inexpensive and mobile enclosures are generally incapable of achieving high STC ratings. Accordingly, a composite noise-attenuating panel system is disclosed that can achieve the high STC ratings associated with immobile, site-erected enclosures, using subpanels that are separated by an air gap and an internal filler (e.g., mineral wool), while maintaining the weight, form factor, and ease of use associated with lightweight, modular mobile enclosures.

Abstract: In a gas turbine engine, coolant (e.g., cooling air) is prone to leak out of the interface between the combustor case, the nozzle of the turbine, and the exhaust diffuser. Embodiments of an interface are disclosed that provide non-fretting sealing using an interference fit between radially facing surfaces of a combustor flange and diffuser flange. In addition, one or more contact sealing lands may be used between the combustor flange and diffuser flange and one or more seals may be provided between various components of the interface to provide additional sealing.

Abstract: A contamination sensor for a gas turbine engine is disclosed herein. The contamination sensor is made of a selected composition of material and includes a base alloy, an alloy for improving oxide formation, and at least one element from the transition metal group. The composition of the contamination sensor can be adjusted to react with specific contaminants at specific temperature ranges.

Abstract: In the compressor of a gas turbine engine, variable guide vanes are adjusted by virtue of connections to an actuation ring that can be rotated within a fixed range of degrees. The connections between the guide vanes and the actuation ring can undergo significant torsional stress. Accordingly, an actuation system is disclosed for reducing the torsional stress experienced by the actuation connections.

Abstract: In the turbine of a gas turbine engine, disk cavities exist between stator and rotor assemblies. These disk cavities enable hot gas from the hot gas flow path to ingress between the stator and rotor assemblies with detrimental effects to the durability of the turbine. Thus, a flow discourager is disclosed that can be mounted to the stator assembly. The flow discourager comprises a continuous external surface that defines a recirculation zone within the disk cavities to circulate the hot gas back out into the hot gas flow path.

Abstract: Industrial machines positioned along a gas transmission pipeline are controlled using setpoints. Operators of such pipelines would benefit from real-time data and recommendations to guide them in optimizing performance of the pipelines. Accordingly, a compression optimization system is disclosed that monitors and provides real-time data and notifications, recommends optimal control setpoints using a machine-learning or other artificial-intelligence model, which may self-learn to realistically represent the pipeline, and executes simulations for hypothetical scenarios. The compression optimization system enables efficient management of the gas transmission pipeline.

Abstract: Gas turbine engines generally comprise a first-stage nozzle guide vane. Temperatures in a trailing-edge area of the suction-side wall of such vanes can exceed material and coating limits. While an insert can be used to form passages for cooling air to flow along the inner surfaces of the vane walls, design constraints prevent the insert from extending beyond a certain point into the trailing edge of the vane. Accordingly, a fin is disclosed for insertion downstream of the insert. By eliminating sudden expansion beyond the downstream end of the insert and maintaining the speed of the cooling air across the trailing-edge area of the suction-side wall, the fin improves the cooling coefficient for the trailing-edge area, so as to prevent or reduce excessive temperatures in the trailing-edge area.

Abstract: A fuel delivery system having a base, a fuel inlet configured to receive fuel from a secondary fuel supply, a fuel outlet configured to deliver fuel to a machine, a filter assembly and a coalescer configured to filter the fuel, a fuel controller configured to regulate pressure of the fuel that will be delivered to a machine, a boost pump assembly and a main pump assembly configured to pressurize the fuel.

Abstract: During operation of a gas turbine engine, the turbine blades are subjected to extremely high temperatures. While internal cooling passages may be provided within the turbine blades to cool the airfoils, the platforms of the turbine blades also experience high temperatures. In an embodiment, cooling holes are provided in each platform to cool distressed locations in the platform and improve the durability of each turbine blade.

Abstract: During operation of a gas turbine engine, the turbine blades are subjected to extremely high temperatures. While internal cooling passages may be provided within the turbine blades to cool the airfoils, the platforms of the turbine blades also experience high temperatures. In an embodiment, cooling holes are provided in each platform to cool distressed locations in the platform and improve the durability of each turbine blade.

Abstract: A turbomachinery power generation station can be too large and heavy for transportation. Thus, embodiments are disclosed for separating a full power generation station into road-ready turbine and generator trailers, as well as realigning and recoupling the trailers for operation of the power generation station at a desired destination.

Abstract: A human-machine interface (HMI), HMI system, turbomachinery package, and method of modifying a partition of an HMI are disclosed. The HMI comprises a first partition storing a first operating system exclusively supporting a primary application; and a second partition storing a second operating system exclusively supporting an imaging application. The HMI system comprises the HMI; an external computing device; a serial cable; and, optionally, a network cable. The turbomachinery package comprises a housing; a gas turbine; a plurality of sensors; a plurality of actuators; and an HMI. The imaging application may be an image deploy function, an image back-up function, and/or an image restore function, any of which can be executed without the use of removable media.

Abstract: A magnetic bearing assembly for a rotary machine may lose power and fail to support the rotating assembly resulting in damage to magnetic bearing assembly and/or other components. An auxiliary bearing assembly may be used to support the rotating assembly during such a failure. The auxiliary bearing assembly is located radially inwards of the magnetic bearing assembly and may reduce resonance and/or whirl of the rotating assembly during failure of the magnetic bearing assembly.

Abstract: A compact heat exchanger is disclosed for re-circulating bleed air from a combustor into an inlet and/or exhaust of a gas turbine engine. In an embodiment, the heat exchanger may comprise a plurality of airfoils with internal passages that receive bleed air. The bleed air may be forced through outlets in one or a plurality of concentric passages from the internal passage of each airfoil to an internal cavity of each airfoil, and out of micro-holes within a trailing surface of the airfoil. This enables bleed air to be mixed with gas flowing through the airfoils, in close proximity to the compressor or turbine of the gas turbine engine, while providing acoustic noise suppression and low thermal mixing stratification.

Abstract: Gas turbine engines generally comprise a first-stage nozzle guide vane. Temperatures in a trailing-edge area of the suction-side wall of such vanes can exceed material and coating limits. While an insert can be used to form passages for cooling air to flow along the inner surfaces of the vane walls, design constraints prevent the insert from extending beyond a certain point into the trailing edge of the vane. Accordingly, a fin is disclosed for insertion downstream of the insert. By eliminating sudden expansion beyond the downstream end of the insert and maintaining the speed of the cooling air across the trailing-edge area of the suction-side wall, the fin improves the cooling coefficient for the trailing-edge area, so as to prevent or reduce excessive temperatures in the trailing-edge area.

Abstract: A fuel injector is disclosed for reducing flashback. In an embodiment, the fuel injector may comprise an injector head with purge holes on a radial wall along a radial axis between an assembly axis of the fuel injector and a plurality of vanes arranged circumferentially around the assembly axis. In addition, the plurality of vanes may comprise fuel outlets connecting interior fuel passages to spaces between the vanes. The introduction of these purge holes near the bases of the vanes and the configuration and positioning of the fuel outlets in the vanes and elsewhere in the fuel injector may alter the stoichiometry (e.g., fuel-air ratio) within the premix passage of the fuel injector to reduce flashback. A plurality of such fuel injectors may be used in the combustor of a gas turbine engine.

Abstract: A stator assembly, at a compressor mid-plane in a gas turbine engine, to be mounted around a rotor disc, enables access to the rotor disc (e.g., for trim balancing), without requiring disassembly of the stator assembly and/or a compressor case in which the stator assembly is housed, via a removable stator vane. The stator assembly may comprise vane apertures, aligned along a radial axis, that hold the removable stator vane when inserted into the stator assembly, and provide a radial pathway to the rotor disc, when the removable stator vane is removed from the stator assembly. In addition, a case access assembly may seal the removable stator vane in place within a compressor case when engaged, and provide access to the removable stator vane and radial pathway through the compressor case when disengaged. This enables trim balancing of a mid-plane compressor rotor assembly through the stator assembly and compressor case.