United Technologies Corporation

Rtx Corporation

Raytheon Technologies Corporation

William Donat

Ravi Rajamani

Amy Rose Grace

Angelo Martucci

Kevin Patrick McCormick

Eric Nelson Hettler

Rajendra K Agrawal

Alexander I Khibnik

Thomas A Bush

Sampath K Yerramalla

Haralambos Cordatos

Coy Bruce Wood

Kevin D Gibbons

Alek Gavrilovski

Steven Butler

Kevin Gibbons

Christopher Mazella

Kevin P Mccormick

Eric N Hettler

Amy R Grace

Kevin Mccormick

Eric Hettler

Amy Grace

Sampath K Yeramalla

A foreign object debris (FOD) detection system for a gas turbine engine comprises a light detection and ranging (LiDAR) sensor assembly. The LiDAR sensor assembly is configured to scan a pre-determined volume within an inlet of the gas turbine engine. The inlet may be defined by a nacelle of the gas turbine engine. The LiDAR sensor assembly may comprise a single transceiver, a transmitter and a receiver, a plurality of transmitters and a receiver, or a plurality of receivers and a transmitter.

LiDAR based FOD detection for gas-turbine engines

A fuel actuation system may comprise a servo valve (SV) including a torque motor and at least one screen, a metering valve (MV) fluidly connected to the SV, and an electronic engine control (EEC) operatively connected to the SV. The EEC may be configured and disposed to determine a travel time of the MV, a travel distance of the MV, a pressure of a fuel, and/or a temperature of the fuel, generate at least one of a travel time history, a travel distance history, a fuel temperature history, and a fuel pressure history, and determine a level of degradation of the fuel actuation system based on the at least one of the travel time history, the travel distance history, the fuel temperature history, or the fuel pressure history.

Fuel metering valve actuator initiated built in test

A system and method for the calculation of a fuel lacquer index using environmental monitoring is disclosed. The system and method may comprise: capturing a fuel temperature data; determining a fuel quality rating; calculating a volumetric fuel flow; calculating a fuel filter differential pressure; and calculating a fuel lacquer index. The fuel lacquer index may be calculated as a percentage value based upon the fuel temperature data, the fuel quality rating, the volumetric fuel flow, and the fuel filter differential pressure.

System and method for the calculation of a fuel lacquer index

Systems and methods for monitoring fuel actuation system health are described herein. A method for monitoring fuel actuation system health may comprise: moving a metering valve from a first position to a second position; detecting a first travel distance of the metering valve; storing the first travel distance of the metering valve to memory to generate a first travel distance history; and determining a level of degradation of the fuel actuation system based on at least the first travel distance history.

An example aircraft debris monitoring sensor assembly includes an aircraft conduit defining a hollow core passage extending axially from an inlet opening to an outlet opening. A sensor arrangement detects debris carried by a fluid within the hollow core passage.

Aircraft debris monitoring sensor assembly

An example method of partitioning turbomachine faults includes using a modeling computer to model a system, to establish a modeled gas path parameter, and to establish a modeled subsystem parameter. The method then determines a gas path condition representing a difference between an actual gas path parameter and the modeled gas path parameter. The method also determines a subsystem condition representing a difference between an actual subsystem parameter and the modeled subsystem parameter. The method diagnoses a sensor failure based on the gas path condition and the subsystem condition.

Partitioning of turbomachine faults

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.

IDMS signal processing to distinguish inlet particulates

A method for modeling the performance of a gas turbine engine is provided. The method includes the steps of: 1) providing a processor; 2) inputting flight condition parameter data and engine output parameter data into a gas turbine engine model operating on the processor, which model includes a physics-based engine model that uses the flight condition parameter data to produce estimated engine output parameter data, and determines residuals from the engine output parameter data and the estimated engine output parameter data; 3) partitioning the flight condition parameter data and residuals into training data and testing data; 4) performing a correlation reduction on the training data, which analysis produces correlation adjusted training data; 5) performing an orientation reduction on the correlation adjusted training data, which reduction produces orientation adjusted training data; 6) reviewing the orientation adjusted training data relative to at least one predetermined criteria, and iteratively repeating the steps of performing a correlation reduction and an orientation reduction using the orientation adjusted training data if the criteria is not satisfied, and if the criteria is satisfied outputting the orientation adjusted training data; 7) producing estimated corrections to the orientation adjusted training data using one or more neural networks; 8) evaluating the neural adjusted data using the partitioned testing data; and 9) modeling the performance of the gas turbine using the estimated corrections to the orientation adjusted training data.

Method and system for modeling the performance of a gas turbine engine

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Manchester, CT, United States of America

William Donat