Abstract: A power system of an aircraft includes a hybrid energy storage system with at least two energy storage subsystems each having a different power-energy density, power draw characteristics and/or dissimilar configuration. A primary power unit includes an aircraft engine coupled to an electric motor and a first generator. A secondary power unit is coupled to a second generator. A bidirectional power converter is coupled to the hybrid energy storage system and one or more controllers of the electric motor, the first generator, and the second generator. A power management controller is configured to interface with the hybrid energy storage system and the one or more controllers of the electric motor, the first generator, and the second generator and perform a model predictive control to dynamically adjust one or more electric power flows through the bidirectional power converter based on an engine propulsion power demand of the aircraft engine.

Abstract: A turbine engine includes integrated electric machines in the compressor section and the turbine section to supplement power produced from fuel with electric power. The example compressor section includes a compressor electric motor that is coupled to a compressor generator. The example turbine section includes a turbine electric motor that is coupled to the geared architecture to supplement power driving the fan section. A turbine generator provides electric power to the turbine electric motor.

Abstract: A gas turbine engine includes a generator that is configured to be driven by a turbine section, an electric motor that is configured to receive at least a portion of electric power from the generator, a gearbox that is mechanically coupled to both the electric motor and the generator, and a control system that has an operational amplifier that is configured to synchronize operation of the electric motor and the generator. The operational amplifier electrically couples the electric motor to the generator and is configured to define an electrical gain that matches a mechanical gain that is defined by the gearbox.

Abstract: A turbine engine includes integrated electric machines in the compressor section and the turbine section to supplement power produced from fuel with electric power. The example compressor section includes a compressor electric motor that is coupled to a compressor generator. The example turbine section includes a turbine electric motor that is coupled to the geared architecture to supplement power driving the fan section. A turbine generator provides electric power to the turbine electric motor.

Abstract: A turbine engine includes integrated electric machines in the compressor section and the turbine section to supplement power produced from fuel with electric power. The compressor section includes a compressor electric motor that is electrically coupled to a compressor generator. The example turbine section includes a turbine electric motor that is coupled to a geared architecture to supplement power driving the fan section. A turbine generator driven by a portion of the turbine section provides electric power to the turbine electric motor.

Abstract: A clearance control system for a gas turbine engine may include a rotor blade, an outer structure disposed radially outward from the rotor blade, a heating element, a hybrid electric power source, and a controller. The heating element is configured to cause the outer structure to be heated in response to electric current being supplied to the heating element. A gap between the rotor blade and the outer structure is at least one of increased, decreased, and maintained in response to the outer structure being heated. The hybrid electric power source is configured to supply the electric current to the heating element. The controller is configured to regulate the electric current being supplied to the heating element.

Abstract: A hybrid energy storage and control system for a clearance control system for a gas turbine engine may comprise a hybrid electric power source, a first converter, a second converter configured to receive electric power from the hybrid electric power source via the first converter and configured to send the electric power to a heating element for controlling a blade tip clearance between a rotor blade and an outer structure of the gas turbine engine, and a controller in electronic communication with the second converter. The hybrid electric power source may comprise a battery, a supercapacitor, and/or an ultracapacitor.

Abstract: A propulsion system for an aircraft includes at least one gas turbine engine, an electric auxiliary fan driving motor configured to selectively receive electric power input from one or more electric power sources, and at least one auxiliary propulsion fan configured to selectively receive a motive force from either or both of the at least one gas turbine engine and the electric auxiliary fan driving motor. The propulsion system also includes a controller configured to establish a plurality of takeoff thrust settings of the at least one gas turbine engine and the electric auxiliary fan driving motor such that a minimum total aircraft thrust required for takeoff of the aircraft is produced.

Abstract: Particles are removed from electronic components, such as components of data storage devices by use of an electrochemical process. An electronic component is immersed in an electrochemical bath, and a voltage is applied across the +ve electrode and ?ve electrode in an amount sufficient to remove charged particles present on a surface of the electronic component.

Abstract: Described are methods for processing microelectronic device substrates by a lapping step, e.g., a final lapping step, wherein the step includes the use of an elastomeric pressure-sensitive adhesive to secure the microelectronic device substrate to a carrier that holds the substrate to a surface of the carrier during the lapping step, and wherein the pressure-sensitive adhesive can be a non-polysilicone based adhesive having mechanical properties that include a tan delta that is below about 0.2.

Abstract: A power system of an aircraft includes a hybrid energy storage system with at least two energy storage subsystems each having a different power-energy density. The power system also includes one or more electric motors operably coupled to the hybrid energy storage system and to an aircraft engine. The power system further includes a means for controlling one or more electric power flows of the hybrid energy storage system to/from the one or more electric motors based on a modeled electric power demand associated with an engine load of one or more spools of the aircraft engine.

Abstract: A propulsion system for an aircraft includes at least one gas turbine engine, an electric auxiliary fan driving motor configured to selectively receive electric power input from one or more electric power sources, and at least one auxiliary propulsion fan configured to selectively receive a motive force from either or both of the at least one gas turbine engine and the electric auxiliary fan driving motor. The propulsion system also includes a controller configured to establish a plurality of takeoff thrust settings of the at least one gas turbine engine and the electric auxiliary fan driving motor such that a minimum total aircraft thrust required for takeoff of the aircraft is produced.

Abstract: A hybrid energy storage and control system for a clearance control system for a gas turbine engine may comprise a hybrid electric power source, a first converter, a second converter configured to receive electric power from the hybrid electric power source via the first converter and configured to send the electric power to a heating element for controlling a blade tip clearance between a rotor blade and an outer structure of the gas turbine engine, and a controller in electronic communication with the second converter. The hybrid electric power source may comprise a battery, a supercapacitor, and/or an ultracapacitor.

Abstract: Described are methods for processing microelectronic device substrates by a lapping step, e.g., a final lapping step, wherein the step includes the use of an elastomeric pressure-sensitive adhesive to secure the microelectronic device substrate to a carrier that holds the substrate to a surface of the carrier during the lapping step, and wherein the pressure-sensitive adhesive can be a non-polysilicone based adhesive having mechanical properties that include a tan delta that is below about 0.2.

Abstract: A gas turbine engine for an aircraft comprising an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising a plurality of fan blades; a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, and a front mount and a rear mount, the front and rear mounts being configured to connect the gas turbine engine to the aircraft, wherein the front mount is coupled to a casing of the engine core and the front mount is located at substantially the same axial position as a centre of gravity (CG) of the gas turbine engine or forward of the centre of gravity of the gas turbine engine.

Abstract: Particles are removed from electronic components, such as components of data storage devices by use of an electrochemical process. An electronic component is immersed in an electrochemical bath, and a voltage is applied across the +ve electrode and ?ve electrode in an amount sufficient to remove charged particles present on a surface of the electronic component.

Abstract: Disclosed herein are embodiments of a method of making a lubricant composition for lapping a ceramic material. The method includes mixing a base lubricant component and a powdered wax composition component to form the lubricant composition. The powdered wax composition component includes a powdered wax dispersion or a powdered wax emulsion. The amount of powdered wax composition component mixed with the base lubricant component is from 0.01 to 10 percent by weight of the lubricant composition. Also disclosed herein are embodiments of related lubricant compositions and/or methods of using the lubricant to lap a ceramic substrate (e.g., one or more bars of sliders).

Abstract: Disclosed herein are embodiments of a method of making a lubricant composition for lapping a ceramic material. The method includes mixing a base lubricant component and a powdered wax composition component to form the lubricant composition. The powdered wax composition component includes a powdered wax dispersion or a powdered wax emulsion. The amount of powdered wax composition component mixed with the base lubricant component is from 0.01 to 10 percent by weight of the lubricant composition. Also disclosed herein are embodiments of related lubricant compositions and/or methods of using the lubricant to lap a ceramic substrate (e.g., one or more bars of sliders).

Abstract: Systems and methods include determining whether a CRPS value has been breached in a number of requests for access by an IP address, and dropping the requests for access when the CRPS value has been breached and a UTF value is below a minimum UTF value. The request number matching a RC value when the CRPS value has not been breached is determined. A Turing test is implemented when a) the request number matches the RC value, b) the request number does not match the RC value but the UTF value is below the minimum UTF value, or c) the CRPS value has been breached but the UTF value is not below the minimum UTF value. An investigator computing device implements a rate limit control to the cloud services based on the CRPS value, the RC value, and the UTF value.

Abstract: The authentication method for stateless address allocation in IPv6 networks provides a P2P trust-verification approach for identifying a rogue node. Alternatively, the authentication method provides an information hiding scheme to avoid being plagued by rogue nodes. In both cases, the authentication method is embodied in a computer software product having machine readable code.