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: Hybrid subtractive-additive production of a superconducting multi-layer transition-edge sensor includes: forming a superconductor layer; forming a patterning photoresist on the superconductor layer; forming a sensor pattern in the patterning photoresist; subtractively forming, from the superconductor layer, the superconductor sensor layer; removing the patterning photoresist from the superconductor sensor layer; forming a template photoresist on the superconductor sensor layer; forming an inverse normal metal layer pattern in the template photoresist and exposing a bilayer portion of the superconductor sensor layer for addition of a normal metal layer; and additively forming the normal metal layer on the superconductor sensor layer such that the sensor pattern is interposed between the normal metal layer and the substrate.

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.

Abstract: A turbomachine includes a spool; and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along an axial direction and rotatable with one another. The turbomachine also includes a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member; a second support member, the second plurality of turbine rotor blades supported by the second support member; and a bearing assembly including a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and each being supported by the turbine center frame.

Abstract: A propellant container for a perforating gun includes a lower cap, one or more pieces of propellant positioned within the lower cap, wherein at least one of the one or more pieces of propellant defines one or more through-holes, and an upper cap matable with the lower cap to secure the one or more pieces of propellant within the lower cap. A filler material is present within interstitial spaces between the one or more pieces of propellant.

Abstract: A damper seal for a turbomachine includes an annular body having an inner circumferential surface and an outer circumferential surface separated by a thickness. As such, the inner circumferential surface may define a plurality of cavities arranged into a plurality of circumferential rows and at least one partition positioned between at least two of the plurality of cavities. In addition, the inner circumferential surface may further define at least one plenum arranged between two of the plurality of circumferential rows.

Abstract: A rotor support system for a gas turbine engine includes a rotatable drum rotor and a non-rotatable support casing. The rotor support system includes a bearing assembly configured for positioning between the rotatable drum rotor and the non-rotatable support casing. The bearing assembly includes, at least, a stationary support frame and a rotatable race. Further, the rotatable race is configured to engage the rotatable drum rotor at separate and discrete locations that are circumferentially spaced apart around the rotatable drum rotor.

Abstract: A controllable magneto-rheological device includes an annular cylinder formed by inner and outer walls connected at first and second opposing ends and forming an inner shaft configured to receive an operational component of an engine, generator or other device including one or more rotating structures. A magneto-rheological fluid is provided to fill a volume between the inner and outer walls of the annular cylinder. A plurality of electro-magnetic coils are positioned around the outer wall of the annular cylinder. One or more current controllers are coupled to the plurality of electro-magnetic coils for introducing a current through each of the electro-magnetic coils and corresponding magnetic flux through the magneto-rheological fluid. A level of current provided to each of the plurality of electro-magnetic coils directly affects the viscosity of the magneto-rheological fluid and thus the stiffness and damping levels of the controllable magneto-rheological device.

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.

Abstract: A turbomachine includes a spool and a turbine section including a turbine rear frame, a turbine, and a support member. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The support member extends between the first plurality of turbine rotor blades and the spool and couples the first plurality of turbine rotor blades to the spool. The turbomachine also includes a bearing assembly including a bearing, the bearing rotatably supporting the support member and supported by the turbine rear frame, the bearing spaced apart from the spool along the radial direction.

Abstract: Aspects of the subject disclosure may include, for example, associating a global-to-local network profile with a user profile of a first communications network and detecting a number of local networks managed separately from the first communications network. The local networks include local user profiles, wherein access to resources of a local network is based on credentials available by way of a local user profile associated with the user. A location of the user is determined and a proximity of the user to a first local network is determined based on the location of the user. Information is transferred between the global-to-local network profile and a local user profile based on the proximity of the user to the first local network, wherein the transferring of the information supports a registration status of the user with the first local network of the plurality of local networks. Other embodiments are disclosed.

Abstract: A turbomachine includes a spool and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a bearing assembly substantially completely supporting rotation of the turbine, the bearing assembly including a total of four bearings, each of the four bearings aligned with, or positioned aft of, the turbine center frame.

Abstract: A turbomachine includes a spool and a turbine section. The turbine section includes a turbine center frame and a turbine, with the turbine including a first plurality of turbine rotor blades and a second plurality of turbine rotor blades. The first plurality of turbine rotor blades and second plurality of turbine rotor blades are alternatingly spaced along the axial direction. The turbomachine also includes a gearbox aligned with, or positioned aft of, a midpoint of the turbine. The gearbox includes a first gear coupled to the first plurality of rotor blades, a second gear coupled to the second plurality of rotor blades, and a third gear coupled to the turbine center frame. The turbomachine also includes a support member, the first plurality of turbine rotor blades coupled to the spool through the support member, the support member extending aft of the gearbox.

Abstract: The present disclosure is directed to a method of turbine section thermal management for a gas turbine engine. The engine includes a first turbine bearing defining an outer air bearing disposed radially adjacent to a low speed turbine rotor hub of a low speed turbine rotor and an inner bearing disposed radially adjacent to a high pressure (HP) shaft coupled to a high speed turbine rotor, wherein a first manifold is in fluid communication from a pressure plenum of a combustion section to the first turbine bearing, and wherein a second manifold is in fluid communication from the first turbine bearing to a pressure regulating valve and an outer diameter secondary flowpath of the turbine section, and wherein a third manifold is in fluid communication from the pressure plenum of the combustion section to the pressure regulating valve.

Abstract: A turbomachine includes a turbine frame and a turbine, the turbine including a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a first support member assembly including a first support member supporting the first plurality of turbine rotor blades; a second support member assembly including a second support member supporting the second plurality of turbine rotor blades; a frame support member assembly including a frame support member coupled to and extending from the turbine frame; and a bearing assembly including a first bearing and a second bearing. The first bearing is positioned between the first support member and the second support member, and the second bearing is positioned between the frame support member and one of the first support member or the second support member.

Abstract: A method of creating and finishing perforations in a hydrocarbon well having a well wall that includes causing a high velocity jet of a material to shoot into the well wall, thereby creating a perforation in the well wall. The method further includes introducing a gas blast into the perforation, for a blast time duration, the gas blast creating an increasing pressure at the perforation until a maximum pressure is reached; and allowing the pressure of the gas blast to undergo a period of rapid decline to a level of less than 50% of the maximum pressure.

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 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: Aspects of the subject disclosure may include, for example, associating a global-to-local network profile with a user profile of a first communications network and detecting a number of local networks managed separately from the first communications network. The local networks include local user profiles, wherein access to resources of a local network is based on credentials available by way of a local user profile associated with the user. A location of the user is determined and a proximity of the user to a first local network is determined based on the location of the user. Information is transferred between the global-to-local network profile and a local user profile based on the proximity of the user to the first local network, wherein the transferring of the information supports a registration status of the user with the first local network of the plurality of local networks. Other embodiments are disclosed.

Abstract: A turbomachine includes a turbine section including a turbine center frame and a turbine, the turbine including a plurality of low-speed turbine rotor blades and a plurality of high-speed turbine rotor blades alternatingly spaced along the axial direction. The plurality of low-speed turbine rotor blades each extend between a radial inner end and a radial outer end. At least two of the plurality of low-speed turbine rotor blades are spaced from one another along the axial direction and coupled to one another at the radial outer ends. The turbomachine also includes a gearbox aligned with, or positioned forward of, a midpoint of the turbine. The gearbox includes a first gear coupled to the plurality of low-speed turbine rotor blades, a second gear coupled to the plurality of high-speed turbine rotor blades, and a third gear coupled to the turbine center frame.