Abstract: A propulsion system for an aircraft including a core engine connected to a forward frame and a turbine frame assembly, and an aft frame assembly is connected by a turbine casing to the core engine aft of the turbine frame assembly. A core cowl surrounds the core engine, wherein the core cowl is connected to the forward frame. A plurality of cowl mount links selectively loads the core cowl to the aft frame assembly and the turbine frame assembly, wherein the plurality of cowl mount links is each loaded by deflection of the core engine.

Abstract: Highly dispersed, highly filled, low viscosity liquid compositions and uses thereof. A composition can include a carrier fluid, a plurality of nano- and micro-sized particles, and multiple dispersants. A carrier fluid can comprise nonpolar organic liquids. A plurality of particles can comprise inorganic particles. A portion of dispersants can exhibit different association affinities for nano-versus micro-sized particles. A composition can be free of water, other solvents, or diluents. A composition can comprise 30 weight % or greater of particles. A composition can exhibit a consistent viscosity of about 1000 centipoise or lower at about 25° C. A curable composition can comprise curable carrier fluids, such as, for example, monomers and/or oligomers. A composition can be utilized in chemical processing, microfluidics, colloidal fluids, 3D printing, coatings, and other types of additive manufacturing. An object can be made, for example, by vat polymerization 3D printing of one or more curable composition(s).

Abstract: The present technology provides methods for varying physical properties in 3D printed products from a single resin composition, a single printing process, and a single curing process. An image stack used during the 3D printing process controls the position and intensity of light administered by a light source. The image stacks control an intensity of light to be used on different regions of the resin pool at different points in time to induce higher levels of polymerization in certain regions and lower levels of polymerization in other regions. Regions exposed to higher intensities of light will achieve a higher percent cure compared to regions exposed to lower intensities of light. The higher percent cure in a given region in a product will result in different physical properties after a post-print curing process when compared to a given region in the product with a lower percent cure.

Abstract: The invention relates to a power supply system comprising a modular combination of a hydrogen generation unit, a hydrogen usage unit and a control or regulation unit for controlling or regulating the operation of the hydrogen generation unit and the hydrogen usage unit.

Abstract: A turbomachine is provided. In one aspect, the turbomachine includes a rotating component and an electric machine that includes a stator assembly and a rotor assembly rotatable with the rotating component relative to the stator assembly. Further, the turbomachine includes an actuator coupled with the rotor assembly, the stator assembly, or both for moving the rotor assembly, the stator assembly, or both relative to one another. In addition, the turbomachine includes a controller configured to receive data indicating an operating state of the rotating component and cause the actuator to adjust a position of at least one of the stator assembly and the rotor assembly based at least in part on the operating state of the rotating component.

Abstract: A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.

Abstract: A rotor damping device for a turbomachine is provided. The rotor damping device includes a first fluid damper; and a second damper in communication with the first fluid damper, the second damper comprising a wire mesh, wherein the first fluid damper is transitionable between a working condition and an interruption condition, and wherein, during the interruption condition, the wire mesh of the second damper dampens vibration of the turbomachine.

Abstract: A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.

Abstract: A damping device that includes features for damping bending vibration of a shaft rotating about its axis of rotation and methods for damping bending vibration utilizing the damping device are provided. In one exemplary aspect, the damping device includes a damping disc operatively coupled with a shaft, e.g., of a turbine engine or shaft system. The damping disc is at least partially received within a chamber defined by a housing. The chamber of the housing is configured to receive a damping fluid. When the shaft is rotated about its axis of rotation, the damping disc is movable within the chamber to move the damping fluid such that the damping fluid absorbs bending vibration emitted by the shaft. The damping fluid moved by the damping disc dampens bending vibration emitted by the shaft.

Abstract: A rotor damping device for a turbomachine is provided. The rotor damping device includes a first fluid damper; and a second damper in communication with the first fluid damper, the second damper comprising a wire mesh, wherein the first fluid damper is transitionable between a working condition and an interruption condition, and wherein, during the interruption condition, the wire mesh of the second damper dampens vibration of the turbomachine.

Abstract: The present invention relates to systems for use for radio frequency ablation. The systems can include one or more of an ablation tool, power source for use with the ablation tool and a backstop for use in conjunction with the ablation tool during surgical procedures. Preferred ablation tools comprise a series of three or more blade-shaped electrodes disposed in a linear, curved, curvilinear or circular array. The backstops are useful for reducing direct physical and thermal heat transfer injuries to the patient or surgeon during procedures using radiofrequency (RF) ablation devices.

Abstract: A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.

Abstract: A turbomachine is provided. In one aspect, the turbomachine includes a rotating component and an electric machine that includes a stator assembly and a rotor assembly rotatable with the rotating component relative to the stator assembly. Further, the turbomachine includes an actuator coupled with the rotor assembly, the stator assembly, or both for moving the rotor assembly, the stator assembly, or both relative to one another. In addition, the turbomachine includes a controller configured to receive data indicating an operating state of the rotating component and cause the actuator to adjust a position of at least one of the stator assembly and the rotor assembly based at least in part on the operating state of the rotating component.

Abstract: A gas turbine engine is provided including a turbine section including a turbine having a plurality of first speed turbine rotor blades; a compressor section including a compressor having a plurality of first speed compressor rotor blades and a plurality of second speed compressor rotor blades; a gearbox; and a first spool rotatable by the plurality of first speed turbine rotor blades, the first spool coupled to the plurality of first speed compressor rotor blades for driving the plurality of first speed compressor rotor blades in a first direction and to the plurality of second speed compressor rotor blades across the gearbox for driving the plurality of second speed compressor rotor blades in a second direction, opposite the first direction.

Abstract: The present invention relates to systems for use for radio frequency ablation. The systems can include one or more of an ablation tool, power source for use with the ablation tool and a backstop for use in conjunction with the ablation tool during surgical procedures. Preferred ablation tools comprise a series of three or more blade-shaped electrodes disposed in a linear, curved, curvilinear or circular array. The backstops are useful for reducing direct physical and thermal heat transfer injuries to the patient or surgeon during procedures using radiofrequency (RF) ablation devices.

Abstract: A power transmission system includes a shaft, a stator disposed within the shaft and substantially concentric with the shaft; and at least one supporting element positioned between the stator and the shaft and configured to support the shaft on the stator to reduce a vibration of the shaft and allow the shaft to rotate relative to the stator. A gas turbine engine including the power transmission system is also described.

Abstract: A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.

Abstract: A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.

Abstract: A casing for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The casing includes an attachment feature at a radially outermost portion of the casing. The attachment feature is configured to be coupled to a static frame of the gas turbine engine. The casing further includes a plurality of support arms extend from the attachment feature to a radially innermost portion of the casing. At least one support arm of the plurality of support arms defines an internal cavity. Further, the radially innermost portion of the casing is configured to be coupled to an outer race of the bearing. The casing additionally includes a reinforcing member housed at least partially within the internal cavity of at least one support arm. Moreover, the reinforcing member includes a shape memory alloy material.