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 integrated system for monitoring a deployed product on a movable platform, gathering data about the deployed product, and disseminating the, data about the deployed product is disclosed. The system includes a server located on the movable platform capable of communication with the server from a remote location. The server communicates with a source of data about the deployed communicates with a source of data about the deployed product. The system further includes a portal onto which data gathered by the server may be downloaded and with which one can upload information to the server. The server may be provided in the form of a card adapted to be mounted into a pre-existing electronic controller of the deployed product.

Abstract: The subject invention reveals a method for preparing a coated fabric which comprises (I) applying a vulcanizable elastomer composition to a layer of fabric, wherein the vulcanizable elastomer composition is made by: (1) mixing a cross-linkable functionalized polyethylene with at least one cross-linkable liquid elastomer to form a non-reactive extrudant, wherein the mixing occurs at a temperature in the range of 10° F.

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: 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: An example method of estimating a gas turbine engine surge margin and surge margin deterioration includes monitoring debris in at least a portion of an engine and establishing an estimated surge margin for the engine using information from the monitoring The method may use gas path parameters, such as pressures, temperatures, and speeds to establish the estimated surge margin. An example gas turbine engine surge margin 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 establishes an estimated surge margin and loss in surge margin of the engine based on information from the debris monitoring system.

Abstract: The subject invention reveals a method for preparing a coated fabric which comprises (I) applying a vulcanizable elastomer composition to a layer of fabric, wherein the vulcanizable elastomer composition is made by: (1) mixing a cross-linkable functionalized polyethylene with at least one cross-linkable liquid elastomer to form a non-reactive extrudant, wherein the mixing occurs at a temperature in the range of 10° F.

Abstract: The present invention relates to an apparatus (100) for the storing and dispensing of products. In particular, the present invention relates to an apparatus (100) for the storing and dispensing of inter-reactive compounds wherein the inter-reactive compounds are efficiently mixed on extrusion or expulsion.

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 apparatus for assessing health of a device comprising a data alignment module for receiving a plurality of sensory outputs and outputting a synchronized data stream, an analysis module for receiving the synchronized data stream and outputting at least one device health feature, and a high level diagnostic feature information fusion module for receiving the at least one device health feature and outputting a device health assessment.

Abstract: 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 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.

Abstract: 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 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.

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 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 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.

Abstract: A method for detecting integrity degradation of a turbine engine component includes the steps of detecting oxygen in a cavity of a turbine engine component; receiving a signal confirming the detection of oxygen; and detecting an integrity degradation of the turbine engine component by the detection of oxygen.

Abstract: A system and method for determining thermal growth of motor or engine parts to thereupon control the clearance of motor or engine fan blades is disclosed herein. In addition, a system and method for monitoring the health of a turbine engine, its components and sub-components is also described herein. The system(s) and method(s) described herein permit continuous monitoring during the life of the engine for radial clearances and blade and rotor vibration problems, which will assist in correcting and retaining performance for a longer on-wing time in operation. In addition, inconsistent engine-to-engine performance variations due to component tolerances, engine operation characteristics, and operation during extremes in ambient temperatures can be eliminated or significantly minimized when employing the system(s) and method(s) described herein.

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.

Abstract: The present invention is an improved shipping system that provides for third-party billing and shipment of a package from a first location to a second location where neither the first or second location is the location of the third-party. An embodiment is disclosed in which a pre-existing call-tag system is modified to permit third-party billing and anywhere to anywhere functionality.

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 pressure-flow reducer, and an aerosol focusing system incorporating such a pressure-flow reducer, for performing high-flow, atmosphere-pressure sampling while delivering a tightly focused particle beam in vacuum via an aerodynamic focusing lens stack. The pressure-flow reducer has an inlet nozzle for adjusting the sampling flow rate, a pressure-flow reduction region with a skimmer and pumping ports for reducing the pressure and flow to enable interfacing with low pressure, low flow aerosol focusing devices, and a relaxation chamber for slowing or stopping aerosol particles. In this manner, the pressure-flow reducer decouples pressure from flow, and enables aerosol sampling at atmospheric pressure and at rates greater than 1 liter per minute.