Pratt-Whitney Canada Corp

Pratt & Whitney Canada Corp.

Roja Tabar

Alireza Gharagozloo

Philippe Beauchesne-Martel

James Robert Jarvo

Jasraj Chahal

Ella Yakobov

Sean McCarthy

Pascal Lavoie

Sean Mccarthy

Allreza Gharagozloo

A system and method for controlling an aircraft engine is provided. The method includes a) producing first sensor data using a first sensor sensing a first parameter during operation of the aircraft engine on a flight mission; b) producing other sensor data using a plurality of second sensors sensing a plurality of other parameters, during operation of the aircraft engine; c) providing the first and other sensor data to a control unit during operation of the aircraft engine; d) storing the first and other sensor data during operation of the aircraft engine; e) using an artificial intelligence (AI) model that is trained using the stored first and other sensor data produced during operation of the aircraft engine, to produce one or more derived first parameter values; and f) selectively providing the one or more derived first parameter values to the control unit for use in controlling the aircraft engine.

Engine control system and method with artificial intelligence sensor training

Methods and systems for mitigating corrosion and/or erosion in an aircraft engine are provided. A method includes receiving usage data characterizing a medium accumulated inside the aircraft engine. Using a trained model, the usage data is related to an assigned aircraft engine condition from a plurality of aircraft engine conditions. The trained model is trained using machine learning and historical data relating characteristics of the medium to the plurality of aircraft engine conditions. When the assigned aircraft engine condition is indicative of a corrosion risk for the aircraft engine, a corrosion-mitigating action is initiated for the aircraft engine. When the assigned aircraft engine condition is indicative of an erosion risk for the aircraft engine, an erosion-mitigating action is initiated for the aircraft engine.

Method and system for mitigating corrosion and/or erosion in an aircraft engine

A method of mitigating corrosion and erosion in an aircraft engine, includes: receiving a concentration of contaminants contained within a sample of an environmental medium ingested by the aircraft engine; determining a frequency of corrosion and erosion mitigation actions based on the concentration of the contaminants; and instructing a performance of the corrosion and erosion mitigation actions at the frequency.

Method of mitigating corrosion and erosion in an aircraft engine

A method for monitoring a bleed valve of an aircraft engine includes obtaining operational data of the aircraft engine, the operational data indicative of operational performance of the aircraft engine. The method further includes utilizing one or more neural networks to determine a health status of a bleed valve of the aircraft engine based on the operational data, the bleed valve configured to bleed air from a compressor section of the aircraft engine, wherein the one or more neural networks have been trained with root cause data relating to a plurality of potential failure modes of the bleed valve.

Method and system for monitoring a bleed valve of a gas turbine engine

A method is provided involving a turbine engine. During this method, data is received indicative of twist of a shaft of the turbine engine. The data is monitored over time to identity one or more reversal events while the turbine engine is operating, where each of the reversal events corresponds to a reversal in a value sign of the data. Shaft shear is identified in the shaft based on occurrence of N number of the reversal events.

Turbine engine shaft shear detection

Herein provided are systems and methods for synchrophasing multi-engine aircraft. A phonic wheel is coupled to a first propeller of a first engine of the aircraft. A sensor is disposed and configured for producing a signal in response to passage of first and second position markers on the phonic wheel. A control system is communicatively coupled to the sensor for obtaining the signal, and configured for: determining an expected delay between two subsequent signal pulses of the signal; identifying from within the plurality of signal pulses a particular pulse associated with the second position marker; determining, based on a particular time at which the particular pulse associated with the second position marker was produced, that a rotational position of the first propeller corresponds to a reference position at the particular time; and performing at least one synchrophasing operation for the aircraft based on the rotational position of the first propeller.

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Longueuil, Canada

Roja Tabar