Pratt-whitney Canada Corp

Michael Paul Smith

Piotr Szczesnowicz

Antwan Shenouda

Patrick Manoukian

Andrew Ghattas

Hytham Mokhtar

Kulbir Singh Madhok

Kasra Hamzehi

Charles Bolon-bruhn

Dennis Deorajh

Daniel Arnone

Alexander Campbell

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

Methods and systems for operating an aircraft engine. A health parameter for the engine received from a first instrument is monitored by a health evaluation device communicatively coupled to a communication link between an engine controller and a second instrument which generates an operation parameter signal indicative of an engine operating condition. The health parameter is compared, by the health evaluation device, to a predetermined threshold. When the health parameter is below the threshold, the health evaluation device causes the operation parameter signal to be transmitted from the second instrument to the controller. When the health parameter reaches the threshold, the health evaluation device prevents the operation parameter signal from being transmitted from the second instrument to the controller, and transmits to the controller a fault signal to elicit a health response therefrom, the fault signal containing at least two mutually-exclusive fault codes associated with the operating condition.

Methods and systems for operating an aircraft engine

A chip detection system for an engine fluid system includes an emitter located in a first position proximate to a fluid passage of the engine fluid system, the emitter including a radioactive source that generates ionizing radiation particles and transmits the ionizing radiation particles through a liquid within the fluid passage. A detector includes a detecting element located in a second position relative to the fluid passage with the liquid disposed between the emitter and the detector. The detecting element generates an electric current in response to the ionizing radiation particles contacting the detector. A controller is in communication with the detector to receive the electric current generated by the detecting element. The controller is operable to detect chips in the liquid when the electric current generated by the detecting element is greater than a threshold value of the electric current.

Chip detection system for an engine fluid system

An electric apparatus is provided that includes a fiber optic system and an electric conductor. The fiber optic system includes an inner cladding, an outer cladding and a fiber optic core between the inner cladding and the outer cladding. The electric conductor extends longitudinally along a centerline within the fiber optic system. The centerline may be a centerline of any one or more or all of the fiber optic system, the inner cladding, the outer cladding, the fiber optic core and/or the electric conductor.

Detecting damage to electric conductor using electromagnetic radiation

There is described a multi-channel, multi-range transducer for measuring a parameter, the transducer comprising N channels and M sensing elements, the M sensing elements centered on distinct calibration points of distinct measuring ranges, the M sensing elements distributed across the N channels of the transducer, wherein sensing elements having adjacent measuring ranges are provided in different ones of the N channels.

Multi-channel multi-range transducer

Electromagnetic chip detectors and associated methods of detecting a metallic chip in engine fluid of an engine are provided. The method comprises supplying an electric current to a circuit extending between a first node and a second node to magnetize both a first electrically conductive terminal and a second electrically conductive terminal spaced apart from each other to define a chip-receiving gap therebetween, and detecting a change in resistance across the first node and the second node. The change in resistance is indicative of a capture of the chip by the electromagnetic chip detector. The chip electrically connects the first electrically conductive terminal to the second electrically conductive terminal. The first electrically conductive terminal is electrically connected to the first node. The second electrically conductive terminal is electrically connected to the second node.

Electromagnetic chip detector

There is provided a blade angle feedback assembly for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. The assembly comprises a feedback device coupled to rotate with the rotor, the feedback device having a root surface having a first edge, first position markers extending from the root surface and oriented substantially parallel to the axis, the first position markers circumferentially spaced from one another, at least one second position marker extending from the root surface and positioned between two adjacent first position markers at an angle thereto, the at least one second position marker having an end positioned adjacent to the first edge and non-flush therewith, and at least one sensor mounted adjacent the feedback device and configured to detect a passage of the first position markers and the at least one second position marker as the feedback device rotates about the axis.

Blade angle position feedback system with profiled marker terminations

A method of operating a gas turbine engine having a bleed air system with a switching valve, operable to switch between multiple air sources depending on an operating mode of the gas turbine engine (e.g. a motive powered mode or a standby mode), is described. The method includes operating the switching valve to provide pressurized air from a selected one or more of the multiple air sources to a cavity of the gas turbine engine having seals, and testing the switching valve to determine if the switching valve is functioning normally or abnormally. The switching valve is functioning normally when operable to switch between the multiple air sources and is functioning abnormally when switching between the multiple air sources is not possible. If the switching valve is determined to be functioning abnormally, the gas turbine engine is controlled to prevent a change of the operating mode.

Growing community of inventors

Mississauga, Canada

Michael Paul Smith