Abstract: A control system for a turbine engine assembly includes a controller operable to control operation of the turbine engine assembly and to determine a trim configuration to balance a rotating engine structure associated with the turbine engine assembly. The controller is programmed to determine the trim configuration based on information indicative of an out of balance condition of the rotating engine structure and an assigning a quality score based on a determined veracity of the information.

Abstract: The present disclosure provides methods and systems for propeller balancing of an aircraft comprising a propeller. Acceleration data is obtained from an acceleration sensor coupled to the aircraft. The acceleration data is filtered using a filter to obtain propeller-specific vibration data, the filter defining a range of acceptable frequencies associated with a frequency of rotation of the propeller. The propeller-specific vibration data is compared to trend data associated with the propeller. When the propeller-specific vibration data differs from the trend data beyond a predetermined threshold, an alert indicative of a balancing need for the propeller is issued.

Abstract: The present disclosure provides methods and systems for propeller balancing of an aircraft comprising a propeller. Acceleration data is obtained from an acceleration sensor coupled to the aircraft. The acceleration data is filtered using a filter to obtain propeller-specific vibration data, the filter defining a range of acceptable frequencies associated with a frequency of rotation of the propeller. The propeller-specific vibration data is compared to trend data associated with the propeller. When the propeller-specific vibration data differs from the trend data beyond a predetermined threshold, an alert indicative of a balancing need for the propeller is issued.

Abstract: There is described herein a propeller balancing system and method that selects at least a portion of received propeller vibration data by comparing received aircraft data collected concurrently with the propeller vibration data with at least one customizable flight criterion, and identifying the portion of the vibration data acquired at a time when the aircraft data meets the at least one customizable flight criterion. The selected portion of the propeller vibration data is analyzed to assess a vibration level of the propeller and a balancing need is signaled when the vibration level reaches a threshold.

Abstract: Devices and methods useful for balancing high-pressure spools of gas turbine engines are disclosed. An exemplary device may comprise: an input shaft configured to be coupled to an output of an accessory gear box driven by a high-pressure spool of a gas turbine engine; a first trigger rotatably coupled to the input shaft at a first speed ratio; and a sensor configured to detect the trigger at each revolution of the trigger. The first speed ratio may permit a rotational speed of the first trigger to be substantially the same as a rotational speed of the high-pressure spool. Upon detection of the trigger, the sensor may generate one or more signals representative of each associated revolution of the high-pressure spool of the gas turbine engine.

Abstract: There is described herein a propeller balancing system and method that selects at least a portion of received propeller vibration data by comparing received aircraft data collected concurrently with the propeller vibration data with at least one customizable flight criterion, and identifying the portion of the vibration data acquired at a time when the aircraft data meets the at least one customizable flight criterion. The selected portion of the propeller vibration data is analyzed to assess a vibration level of the propeller and a balancing need is signaled when the vibration level reaches a threshold.

Abstract: There is described herein a propeller balancing system and method that determines a stable cruise condition of an aircraft during flight, and considers vibration data for propeller balancing collected while the aircraft is in the stable cruise condition. Parameters used to determine stable cruise condition may be unique for each flight and/or aircraft, and balancing solutions may be determined based on these unique parameters.

Abstract: Methods of assembling a rotor assembly of a gas turbine engine having a plurality of components. The method comprises, in one aspect, determining a static unbalance force of each component using the mass and the center of mass location, and determining an optimum assembly arrangement minimizing static unbalance forces. Optimal component stacking positions, among other things, may then be established.

Abstract: Methods of assembling a rotor assembly of a gas turbine engine having a plurality of components. The method comprises, in one aspect, determining a static unbalance force of each component using the mass and the center of mass location, and determining an optimum assembly arrangement minimizing static unbalance forces. Optimal component stacking positions, among other things, may then be established.

Abstract: Methods of assembling a rotor assembly of a gas turbine engine having a plurality of components. The method comprises, in one aspect, determining a static unbalance force of each component using the mass and the center of mass location, and determining an optimum assembly arrangement minimizing static unbalance forces. Optimal component stacking positions, among other things, may then be established.

Abstract: Lubricant compositions for use in automotive engine oils comprising a combination of a specific base stock or mixture of base stocks and a friction reducing additive to improve fuel economy and fuel economy longevity of the automotive engine oil. The friction reducing additive is a specific partial polyol ester and may also include a specific saturated primary amide.

Abstract: Methods of assembling a rotor assembly of a gas turbine engine having a plurality of components. The method comprises, in one aspect, determining a static unbalance force of each component using the mass and the center of mass location, and determining an optimum assembly arrangement minimizing static unbalance forces. Optimal component stacking positions, among other things, may then be established.

Abstract: A computing device embodiment includes a processor, memory coupled to the processor, and computer executable instructions executable by the processor. Computer executable instructions are provided to the memory and executable by the processor to access a first provider's communications computing device, having a user's information thereon, through a data lookup utility used by the first carrier. The computer executable instructions can also retrieve the user's information from the first provider's communications computing device and transfer the retrieved information to a second provider's communications computing device.

Abstract: An artificial neuron is formed from an input subcircuit, a capacitor free leaky integrator subcircuit, and an output switching subcircuit. The input subcircuit is configured to supply a pulsed input signal. The capacitor free leaky integrator subcircuit is configured to supply a parasitic capacitance and to utilize the parasitic capacitance to provide differing time constants for the rising and falling edges of an output signal produced in response to the pulsed input signal. The output switching subcircuit s configured to, upon receipt of a sufficient output signal from the capacitor free leaky integrator subcircuit, switch off the input subcircuit and to release a neuron firing signal.

Abstract: A mixture of aromatic hydrocarbons, comprising xylenes, is isomerized in the presence of ZSM-22 zeolite to produce a product stream wherein the proportion of para-xylene is substantially equal to the equilibrium ratio of the para-isomer. The process is conducted at about 500.degree. F. to about 1100.degree. F., at about 0 to about 3000 psig, optionally in the presence of hydrogen, and also optionally with the catalyst comprising about 0.005% to about 5.0% of a metal, e.g., platinum, palladium or cobalt, based on total catalyst weight.