Pratt-whitney Canada Corp

Andrew Ghattas

Sean McCarthy

Tatjana Pekovic

Michael Paul Smith

Benjamin Bregani

Charles Bolon-bruhn

Nicolas Renard

Peter Boyd

Sean Mccarthy

A method is provided for operating an aircraft system. During this method, a shaft of an aircraft powerplant is rotated. A torque signal is received indicative of a torque applied to the shaft while the shaft is rotating. A noise parameter is determined indicative of noise in the torque signal. A fault is identified in the torque signal when the noise parameter is equal to or greater than a threshold.

Identifying fault in torque signal / torque sensor for aircraft system

Health monitoring systems and associated methods for gas turbine engines are provided. A health monitoring method includes using a microphone to acquire operation data indicative of acoustic energy generated in a core gas path of the gas turbine engine. The operation data is compared to reference data indicative of an acoustic signature of fluid noise associated with a non-normal condition in the core gas path of the gas turbine engine. Based on the comparing of the operation data to the reference data, the non-normal condition is determined to exist within the core gas path of the gas turbine engine. A signal indicative of the existence of the non-normal condition within the core gas path of the gas turbine engine is output.

Acoustical health monitoring of gas turbine engines

Methods and systems for validating component integrity in an engine are described. First usage data associated with a period of operation of the engine is obtained at an engine controller. An indication of the first usage data is transmitted from the engine controller to a first presentation device. Second usage data associated with the period of operation of the engine is received at the engine controller from an input device. The first usage data is compared to the second usage data at the engine controller. Based on the comparing, an alert is issued to a second presentation device independent from the first presentation device.

System and method for validating component integrity in an engine

Herein provided is a fluid level sensor and associated systems and methods. The fluid level sensor comprises a floater movable along a floater path in response to changes in a fluid level and a sensing circuit disposed along the floater path. The floater path has a first end associated with a low fluid level and an opposite second end associated with a high fluid level. The sensing circuit comprises first and second electrically-coupled circuit branches with first and second sensing terminals arranged proximate to the first end of the floater path, a plurality of passive elements connected in series along the first circuit branch, and plurality of switching elements each connected in parallel between the second circuit branch and the first circuit branch at connection points along the first circuit branch between pairs of adjacent passive elements, the switching elements configured for being actuated by movement of the floater.

Fluid level sensor, fluid reserviour, and methods for sensing a fluid level

Methods and systems for monitoring component integrity during operation of an engine are provided. Usage data associated with a period of operation of the engine is obtained at an engine controller. The engine controller has assigned thereto a first trust level. A first indication of the usage data is transmitted from the engine controller to a first presentation device forming part of a first communication path, which has assigned thereto a second trust level lower than the first trust level. A second indication of the usage data is transmitted from the engine controller to a second presentation device forming part of a second communication path, which is independent from the first communication path and has assigned thereto the second trust level. The trust level of the first and second communication paths is elevated by having the usage data transmitted through the first and second independent communication paths.

System and method for monitoring component integrity during engine operation

A method and system are described for detecting a fault of a fluid level sensing device associated with an aircraft engine, the fluid level sensing device arranged to measure a variance in a fluid level. The method comprises triggering a timer, while the timer is running, receiving a measurement indicative of the fluid level from the fluid level sensing device, resetting the timer when at least one timer-reset condition has been met, and outputting a fault signal when the timer reaches a timer threshold.

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La Prairie, Canada

Andrew Ghattas