Abstract: Belts having a cover layer and opposing continuous tooth section defining an outer surface, a cross-linked elastomeric body, and a tensile reinforcement section disposed between the cover layer and the cross-linked elastomeric body. The continuous tooth section includes a plurality of tooth structures, each having tooth flank, a land, and an easement area between the tooth flank and the land, and the easement area has a progressively decreasing radial thickness from the tooth flank to the land. In some aspects, the easement area has a low pressure-angle of contact with a sprocket, when engaging a sprocket. In some aspects, the belt is an endless belt, while in some other aspects, the belt is a spliced belt having a splice.

Abstract: A system for controlling a plurality of electromechanical effectors operably connected to an engine to control engine parameters. The system also includes a plurality of sensors operably connected to measure a state or parameter of each effector, a power supply configured to supply power to the plurality of effectors, and a controller operably connected to the plurality of sensors, the plurality of effectors, and the power supply. The controller executes a method for an adaptive model-based control for controlling each effector, The method includes receiving a request indicative of a desired state for each effector, receiving a weighting associated each request, obtaining information about a current state of each effector, and updating an adaptive model based control (MBC) based upon the information. The method also includes generating a control command for an effector based upon the adaptive MBC and commanding the effector based upon the control command.

Abstract: A system for controlling a plurality of electromechanical effectors operably connected to an engine to control engine parameters. The system also includes a plurality of sensors operably connected to measure a state or parameter of each effector, a power supply configured to supply power to the plurality of effectors, and a controller operably connected to the plurality of sensors, the plurality of effectors, and the power supply. The controller executes a method for an adaptive model-based control for controlling each effector, The method includes receiving a request indicative of a desired state for each effector, receiving a weighting associated each request, obtaining information about a current state of each effector, and updating an adaptive model based control (MBC) based upon the information. The method also includes generating a control command for an effector based upon the adaptive MBC and commanding the effector based upon the control command.

Abstract: A hybrid gas turbine engine comprises a turbine, a compressor, and a gear system that is driven by the turbine where the gear system includes a sun gear, a ring gear and a plurality of planet gears, where the ring gear has a ring gear radius of RRing gear and the sun gear has a sun gear radius of RSun gear such that the gear system provides a reduction ratio of RRing gear/RSun gear. A fan is driven by the ring gear, and a generator is driven by the ring gear and provides a generator output signal. A power circuit receives the generator output signal and provides a gain RRing gear/RSun gear to the generator output signal and provides a gain signal indicative thereof to an electrical load.

Abstract: A clearance control system for a gas turbine engine may comprise a rotor blade, an outer structure disposed radially outward from the rotor blade, and a heating element configured to cause the outer structure to be heated in response to electric current being supplied to the heating element, wherein 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.

Abstract: A system can comprise one or more processors; and one or more non-transitory computer-readable media storing computing instructions configured to run on the one or more processors and perform: receiving a request for a write operation of an input record in a data store associated with a sharded database and an alternate-key-global-index (AKGI) database; generating a new optimistic lock value, the new optimistic lock value being unique in the sharded database; when the data store does not include a data record associated with the input record, creating the dummy data record in the data store; locking the data record for the write operation by setting the DROpLock of the data record to the new optimistic lock value; and performing the write operation of the input record in the AKGI database and the sharded database.

Abstract: System and method for using automated 3D scans to diagnose the mechanical status of substantially intact vehicles. One or more processor controlled 3D scanners utilize optical and other methods to assess the exposed surfaces of various vehicle components. Computer vision and other computerized pattern recognition techniques then compare the 3D scanner output versus a reference computer database of these various vehicle components in various normal and malfunctioning states. Those components judged to be aberrant are flagged. These flagged components can be reported to the vehicle users, as well as various insurance or repair entities. In some embodiments, the 3D scans can be performed using time-of-flight cameras, and optionally infrared, stereoscopic, and even audio sensors attached to the processor controlled arm of a mobile robot. Much of the subsequent data analysis and management can be done using remote Internet servers.

Abstract: System and method for using automated 3D scans to diagnose the mechanical status of substantially intact vehicles. One or more processor controlled 3D scanners utilize optical and other methods to assess the exposed surfaces of various vehicle components. Computer vision and other computerized pattern recognition techniques then compare the 3D scanner output versus a reference computer database of these various vehicle components in various normal and malfunctioning states. Those components judged to be aberrant are flagged. These flagged components can be reported to the vehicle users, as well as various insurance or repair entities. In some embodiments, the 3D scans can be performed using time-of-flight cameras, and optionally infrared, stereoscopic, and even audio sensors attached to the processor controlled arm of a mobile robot. Much of the subsequent data analysis and management can be done using remote Internet servers.

Abstract: An aircraft jet engine system includes at least one gas turbine engine having a fan including a rotor and a plurality of fan blades. A sensor system in the fan section senses information about the operation of the blades and provides feedback on the condition of each blade to a control. The control is programmed to take in the sensed information and identify a safe operating range for the gas turbine engine based upon damage information developed from the sensed information with regard to each of the blades. An aircraft jet engine system incorporating a plurality of gas turbine engines wherein safe operating ranges are developed for each of the gas turbine engines is also disclosed as is a method of operating an aircraft jet engine system.

Abstract: A method for operating a debris monitoring system comprises continuously sensing the passage of particulates through a gas turbine engine to produce a time-domain sensor signal. The time-domain sensor signal is Fourier transformed to produce a frequency domain sensor signal. The frequency domain sensor signal is partitioned into bins corresponding to particulate composition categories. At least one feature is identified within each bin, and is used to determine the amount of particulate flow in each particulate composition category.

Abstract: An aircraft jet engine system includes at least one gas turbine engine having a fan including a rotor and a plurality of fan blades. A sensor system in the fan section senses information about the operation of the blades and provides feedback on the condition of each blade to a control. The control is programmed to take in the sensed information and identify a safe operating range for the gas turbine engine based upon damage information developed from the sensed information with regard to each of the blades. An aircraft jet engine system incorporating a plurality of gas turbine engines wherein safe operating ranges are developed for each of the gas turbine engines is also disclosed as is a method of operating an aircraft jet engine system.

Abstract: A gas turbine engine system includes an air inlet, an inlet particle separator located at the air inlet and having a blower selectively driven by a variable output motor, and a controller for dynamically controlling the variable output motor that selectively drives the blower of the inlet particle separator.

Abstract: A method for operating a debris monitoring system comprises continuously sensing the passage of particulates through a gas turbine engine to produce a time-domain sensor signal. The time-domain sensor signal is Fourier transformed to produce a frequency domain sensor signal. The frequency domain sensor signal is partitioned into bins corresponding to particulate composition categories. At least one feature is identified within each bin, and is used to determine the amount of particulate flow in each particulate composition category.

Abstract: An example method of controlling gas turbine engine debris monitoring sensors includes detecting debris carried by air moving through an engine using at least first and second debris sensors, and processing signals from both the first and second debris sensors using a common signal conditioning unit. Another example method of monitoring gas turbine engine debris includes configuring at least one first debris sensor to detect debris carried by airflow moving through a first portion of an engine and configuring at least one second debris sensor to detect debris carried by airflow moving though a second portion of the engine. The method alternates between using the first debris sensor to detect debris and using the second debris sensor to detect debris.

Abstract: An example method of estimating gas turbine engine performance deterioration includes monitoring debris in at least a portion of an engine and estimating performance deterioration of at least one component of the engine using information from the monitoring. The method may use gas path parameters, such as pressures, temperatures, and speeds to establish the estimated performance deterioration. An example gas turbine engine performance assessment system includes a debris monitoring system configured to monitor debris moving through a portion of an engine and a controller programmed to estimate performance deterioration of at least one component of the engine based on information from the debris monitoring system.

Abstract: A fabric or cord is treated with an elastomeric compound comprises 20-80 parts per hundred cross-linkable materials of liquid elastomer. The liquid elastomer has a complex dynamic viscosity less than 5 McP (5,000 N*s/m2) at a temperature between 20° C. and the maximum flow temperature TF, and the elastomeric compound the elastomeric material, prior to cure, has a complex dynamic viscosity of less than 5 McP (5,000 N*s/m2) for at least 2 minutes at a maximum flow temperature TF. The coated fabric and cord materials are useful as facing fabrics for power transmission products.

Abstract: An example method of assessing a component of a gas turbine engine includes monitoring debris in at least a portion of an engine and establishing an estimated thermal energy level for a component of the engine based on the monitoring. The method may use gas path parameters to establish the estimated thermal energy level. An example gas turbine engine component assessment system includes a debris monitoring system configured to monitor debris moving through a portion of an engine and a controller programmed to execute an engine deterioration model that assesses a thermal energy level of at least one component of the engine based on information from the debris monitoring system.

Abstract: A computerized method and system for designing an aerodynamic focusing lens stack, using input from a designer related to, for example, particle size range to be considered, characteristics of the gas to be flowed through the system, the upstream temperature and pressure at the top of a first focusing lens, the flow rate through the aerodynamic focusing lens stack equivalent at atmosphere pressure; and a Stokes number range. Based on the design parameters, the method and system determines the total number of focusing lenses and their respective orifice diameters required to focus the particle size range to be considered, by first calculating for the orifice diameter of the first focusing lens in the Stokes formula, and then using that value to determine, in iterative fashion, intermediate flow values which are themselves used to determine the orifice diameters of each succeeding focusing lens in the stack design, with the results being output to a designer.

Abstract: A gas turbine engine system includes an air inlet, an inlet particle separator located at the air inlet and having a blower selectively driven by a variable output motor, and a controller for dynamically controlling the variable output motor that selectively drives the blower of the inlet particle separator.

Abstract: A variable vane control system for use with a gas turbine engine includes a plurality of vanes, an actuation assembly, a mechanical linkage assembly, and a sensor. Each of the plurality of vanes has an airfoil portion disposed in a gas flowpath of the gas turbine engine, and a position of each of the vanes is adjustable with respect to an angle of attack of the airfoil portion of each vane. The actuation assembly is configured for generating actuation force to position the plurality of vanes. The mechanical linkage assembly operably connects the actuation assembly to at least one of the plurality of vanes. The sensor is configured to sense at least one of the position of the airfoil portions of the plurality of vanes and the mechanical linkage assembly, and to generate a position output signal.