Honeywell International Inc.

United Technologies Corporation

Raytheon Technologies Corporation

Telectro-mek, Inc.

Robert H Luppold

Boris Karpman

Ian Michael Dinsmore

Tom Brotherton

Thomas Niemczycki

David Sembiante

Paul Grabill

Zaffir A Chaudhry

Timothy J Crowley

Allan J Volponi

Gregory S Hagen

Sheridon Everette Haye

Sorin Bengea

Tyler J Selstad

Yan Chen

Danbing Seto

Lichu Zhao

Jeffrey A Goodrich

Jeffery A Goodrich

A method for fault diagnosis of a bearing includes detecting, using an oil debris monitor (ODM) sensor, ODM data corresponding to an amount of debris flowing downstream from the bearing. The method also includes detecting, using a vibration sensor, vibration data corresponding to vibration of the bearing during use. The method also includes determining, by a controller, a vibration stage flag corresponding to a severity of damage of the bearing based on the vibration data. The method also includes determining, by the controller, a severity level of the damage of the bearing based on a combination of the vibration stage flag and the ODM data. The method also includes outputting, by an output device, the severity level.

Integrated vibe/ODM fusion and trending analysis for prognostic health management of engine bearing

Systems and methods for controlling a fluid-based system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states, the dynamic states input to an open loop model based on the model operating mode, where the open loop model generates current state derivatives, solver state errors, and synthesized parameters as a function of the dynamic states and a model input vector. A constraint on the state derivatives and solver state errors is based a series of utilities that are based on mathematical abstractions of physical laws that govern behavior of the component. The model processor may include an estimate state module for determining an estimated state of the model based on at least one of a prior state, the current state derivatives, the solver state errors, and the synthesized parameters.

Compact aero-thermo model based control system

A fuel system for a gas turbine engine includes, among other things, a plurality of components defining a plurality of localized nodes at distinct locations relative to a fuel flow path, each of the plurality of localized nodes characterized by a distinct set of failure parameters. One or more fuel sensors are configured to measure at least one fuel condition relating to flow through the fuel flow path. A fuel observation assembly is coupled to one or more engine sensors configured to measure at least one engine condition. The fuel observation assembly comprises an estimation module operable to calculate an expected condition of each of the plurality of localized nodes based upon the set of failure parameters, an observation module operable to calculate an observed condition of each of the plurality of localized nodes, the observed condition based on present values of the at least one fuel condition and the at least one engine condition, and a comparison module operable to determine an abnormality corresponding to a first one of the plurality of localized nodes based upon a comparison of the expected condition and the observed condition for each of the plurality of localized nodes.

Leak detection, isolation and accommodation assembly for gas turbine engines

Systems and methods for controlling a fluid based engineering system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode, the model generates current state derivatives and synthesized parameters as a function of the dynamic states and the model input, wherein a constraint on the current state derivatives is based a series of modules, each member of the series of modules arranged in at least a primary stream group and a secondary stream group corresponding to a component of the system. The model processor may further include an estimate state module for determining an estimated state of the model.

A method for health monitoring for an aircraft includes the steps of obtaining vibration data for the aircraft, obtaining navigation data for the aircraft, and determining a measure of health of the aircraft using the vibration data and the navigation data.

Methods and systems for health monitoring for aircraft

A system to monitor aircraft equipment, having a chassis, defining an interior compartment, an arrangement configured to accept input data of at least one aircraft parameter, the arrangement configured to be placed within an aircraft, crash survivable cockpit voice and flight data recorder, and a power supply arrangement connected to arrangement configured to accept input data and the recorder.

Vehicle monitoring system

A method and apparatus for improving fuel efficiency in an aircraft having a digital avionics system and at least first and second engines. The avionics system includes first and second full-authority digital engine control (FADEC) systems and corresponding first and second engines. At least one processor is provided that is programmed with a differential specific fuel consumption (DSFC) algorithm and first and second engine optimization algorithms. The DSFC algorithm adjusts the throttle of the first and second engines to substantially equalize the differential specific fuel consumption of the engines and thereby improve the fuel efficiency of the aircraft. The first and second engine optimization algorithms adjust at least one operating parameter of the first and second engines respectively to improve the fuel efficiency of the first and second engines.

Apparatus and method for reducing aircraft fuel consumption

Growing community of inventors

West Newton, PA, United States of America

Robert H Luppold