Pratt-whitney Canada Corp

Michael Conciatori

Hai Tao Wu

Tommy Woo

Michael Woinowsky-Krieger

Daniel Alecu

Sylvain Lamarre

Nicolas Des Roches-Dionne

Simon Lopez

A flange assembly includes a primary flange and a secondary flange positioned adjacent the primary flange. The primary flange includes a primary flange body defining a primary bolt aperture. The secondary flange includes a secondary flange body defining a secondary bolt aperture. The flange assembly further includes a bolt. The bolt includes a bolt body extending between a head end and a distal end along a bolt axis. The bolt body includes an annular surface disposed about the bolt axis. The bolt body further includes an annular groove formed in the annular surface and disposed about the bolt axis. The bolt body is positioned within the primary bolt aperture and the secondary bolt aperture. The flange assembly further includes a clip attached to the bolt body within the annular groove. The clip is positioned between the between the primary flange and the secondary flange.

Flange assembly for fastener retention and method for assembling same

The coupling can have a female member configured to rotate around an axis, defining an axial recess, and having a plurality of connections circumferentially arranged along a radially inner face; a male member extending inside the axial recess concentrically to the female member and having a plurality of connections circumferentially arranged along a radially outer face; and a plurality of circumferentially arranged links, each link having an inner end engaged with a corresponding one of the male member connections, and an outer end engaged with a corresponding female member connection, the links being slanted off the radial orientation, with the inner end being circumferentially offset from the outer end, the links subjected to compression when transmitting torque between the female member and male member.

Coupling and associated method of transferring torque

Systems and methods for limiting power of a gas turbine engine for an aircraft are described herein. A blade angle of a propeller blade of the engine and a commanded power for the engine are obtained. A thrust transition direction is determined. The commanded power is compared to a selected threshold based on the blade angle and the thrust transition direction. Power to the engine is limited when the commanded power exceeds the selected threshold.

Method and system for limiting power of an engine

Herein provided are methods and systems for detecting failure of a sensor in a control system for a gas turbine engine. A signal is received from the sensor. A high-pass filter is applied to the signal to produce a high-frequency component signal. A rate of occurrence of signal spikes in the high-frequency component signal is determined. The high-frequency component signal is compared to a component signal threshold which is based on at least one known healthy component signal and at least one faulty component signal. The presence of intermittent open circuits caused by the sensor is detected based on the comparing and on the rate of occurrence of signal spikes.

Pre-emptive fault detection through advanced signal analysis

Herein provided are methods and systems for detecting failure of a sensor in a control system for a gas turbine engine. A filtered signal is received from the sensor. A high-pass filter is applied to the filtered signal to produce a high-frequency component signal. A rate of occurrence of signal spikes in the high-frequency component signal is determined. The high-frequency component signal is compared to a component signal threshold based on at least one known healthy component signal and at least one faulty component signal, wherein the faulty component signal is based on a known faulty signal caused by intermittent open circuits. The presence of intermittent open circuits caused by the sensor is detected based on the comparing and on the rate of occurrence of signal spikes.

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Saint-Leonard, Canada

Michael Conciatori