Abstract: Proppant compositions and methods for using same are disclosed herein. In particular, a proppant composition for use in hydraulic fracturing is disclosed herein. The proppant composition can contain a plurality of particulates and at least one particulate of the plurality of particulates containing a chemical treatment agent. The at least one particulate having a long term permeability measured in accordance with ISO 13503-5 at 7,500 psi of at least about 10 D. The at least one chemical treatment agent can separate from the at least one particulate when located inside a fracture of a subterranean formation after a period of time.

Abstract: A system includes a propeller assembly comprising a propeller, a drive shaft coupled to the propeller assembly, wherein the drive shaft when in operation generates rotation of the propeller, a reduction gearbox coupled to the drive shaft, wherein the reduction gearbox when in operation alters a rotation speed between a power turbine shaft and the drive shaft, and an electric motor disposed between the propeller assembly and the reduction gearbox, wherein the electric motor is coupled to the drive shaft, wherein the electric motor when in operation imparts torque to at least partially rotate the drive shaft.

Abstract: A system includes a first electric motor that when in operation imparts rotation to a fan stage of an engine. The system also includes a combustion section of the engine comprising a combustor that when in operation generates combustion gas through ignition of fuel and compressed air. The system further includes a turbine of the engine coupled to a shaft of the engine, wherein the turbine when in operation receives the combustion gas from the combustion section and imparts rotation to the shaft using the combustion gas.

Abstract: A system includes a marine vessel internal combustion engine. The system also includes a propeller that when in operation rotates. The system further includes an electric motor disposed between the marine vessel internal combustion engine and the propeller, wherein the electric motor when in a selected operating mode imparts rotation to the propeller.

Abstract: A device includes a first rotor segment and a second rotor segment, wherein the first rotor segment and the second rotor segment are configured to be directly coupled together about a shaft to form at least a portion of a unitary rotor. The device also includes a first stator segment and a second stator segment, wherein the first stator segment and the second stator segment are configured to be directly coupled together to form at least a portion of a unitary stator.

Abstract: An electric propulsion system for an aircraft includes a nacelle and an electric machine. The electric machine includes a stator positioned in the nacelle, and a rotor and fan assembly positioned in a primary flow path through the nacelle. The rotor and fan assembly includes a cylindrical fan shroud, a plurality of rotor magnets positioned on an outer surface of the fan shroud, and a fan hub mounted on a central support shaft via one or more bearings. A plurality of fan blades extend between an inner surface of the fan shroud and an outer surface of the fan hub. The rotor magnets may be loaded in compression in a radial direction when the rotor and fan assembly is at rest. The fan blades may be pre-stressed in a radial direction when the rotor and fan assembly is at rest.

Abstract: A system includes a first electric motor that when in operation imparts rotation to a fan stage of an engine. The system also includes a combustion section of the engine comprising a combustor that when in operation generates combustion gas through ignition of fuel and compressed air. The system further includes a turbine of the engine coupled to a shaft of the engine, wherein the turbine when in operation receives the combustion gas from the combustion section and imparts rotation to the shaft using the combustion gas.

Abstract: A device includes a first rotor segment and a second rotor segment, wherein the first rotor segment and the second rotor segment are configured to be directly coupled together about a shaft to form at least a portion of a unitary rotor. The device also includes a first stator segment and a second stator segment, wherein the first stator segment and the second stator segment are configured to be directly coupled together to form at least a portion of a unitary stator.

Abstract: A device includes a first rotor segment and a second rotor segment, wherein the first rotor segment and the second rotor segment are configured to be directly coupled together about a shaft to form at least a portion of a unitary rotor. The device also includes a first stator segment and a second stator segment, wherein the first stator segment and the second stator segment are configured to be directly coupled together to form at least a portion of a unitary stator.

Abstract: An electric propulsion system for an aircraft includes a nacelle and an electric machine. The electric machine includes a stator positioned in the nacelle, and a rotor and fan assembly positioned in a primary flow path through the nacelle. The rotor and fan assembly includes a cylindrical fan shroud, a plurality of rotor magnets positioned on an outer surface of the fan shroud, and a fan hub mounted on a central support shaft via one or more bearings. A plurality of fan blades extend between an inner surface of the fan shroud and an outer surface of the fan hub. The rotor magnets may be loaded in compression in a radial direction when the rotor and fan assembly is at rest. The fan blades may be pre-stressed in a radial direction when the rotor and fan assembly is at rest.

Abstract: A device includes a first rotor segment and a second rotor segment, wherein the first rotor segment and the second rotor segment are configured to be directly coupled together about a shaft to form at least a portion of a unitary rotor. The device also includes a first stator segment and a second stator segment, wherein the first stator segment and the second stator segment are configured to be directly coupled together to form at least a portion of a unitary stator.

Abstract: A system, includes a movable platform slidingly coupled to one or more supports and configured to be selectively moved towards a drill floor and away from the drill floor. The system also includes a roughneck disposed on the movable platform and configured to make up or break out a threaded joint between a first tubular segment and a second tubular segment. The system additionally includes a support member disposed on the movable platform and configured to support one of the first tubular segment or the second tubular segment as the movable platform is selectively moved towards a drill floor or away from the drill floor.

Abstract: An electric propulsion system for an aircraft includes a nacelle and an electric machine. The electric machine includes a stator positioned in the nacelle, and a rotor and fan assembly positioned in a primary flow path through the nacelle. The rotor and fan assembly includes a cylindrical fan shroud, a plurality of rotor magnets positioned on an outer surface of the fan shroud, and a fan hub mounted on a central support shaft via one or more bearings. A plurality of fan blades extend between an inner surface of the fan shroud and an outer surface of the fan hub. The rotor magnets may be loaded in compression in a radial direction when the rotor and fan assembly is at rest. The fan blades may be pre-stressed in a radial direction when the rotor and fan assembly is at rest.

Abstract: An electric propulsion system for an aircraft includes a nacelle and an electric machine. The electric machine includes a stator positioned in the nacelle, and a rotor and fan assembly positioned in a primary flow path through the nacelle. The rotor and fan assembly includes a cylindrical fan shroud, a plurality of rotor magnets positioned on an outer surface of the fan shroud, and a fan hub mounted on a central support shaft via one or more bearings. A plurality of fan blades extend between an inner surface of the fan shroud and an outer surface of the fan hub. The rotor magnets may be loaded in compression in a radial direction when the rotor and fan assembly is at rest. The fan blades may be pre-stressed in a radial direction when the rotor and fan assembly is at rest.

Abstract: Techniques and systems to provide automatic positioning of a tripping apparatus. A system may include a sensor configured to detect a physical characteristic of a tubular string moving past the sensor and generate a signal indicative of the physical characteristic. The system may also include a processing device configured to process the signal indicative of the physical characteristic, determine whether the processed signal is indicative of a deviation of the tubular string, and generate output data utilized to automatically position a tripping apparatus at a location of the deviation on the tubular string.

Abstract: A system, including one or more supports disposed on a drill floor.

Abstract: A system, includes a movable platform slidingly coupled to one or more supports and configured to be selectively moved towards a drill floor and away from the drill floor. The system also includes a roughneck disposed on the movable platform and configured to make up or break out a threaded joint between a first tubular segment and a second tubular segment. The system additionally includes a support member disposed on the movable platform and configured to support one of the first tubular segment or the second tubular segment as the movable platform is selectively moved towards a drill floor or away from the drill floor.

Abstract: A device includes at least one float. The at least one float is configured to provide a buoyancy force away from a seabed when placed in water. The device also includes an enclosure configured to house the at least one float. The enclosure comprises at least one connection configured to couple the enclosure to a self-elevating unit used in offshore oil operations or offshore gas operations.

Abstract: A system, including one or more supports disposed on a drill floor.