Pratt-Whitney Canada Corp

Guy Riverin

Jason Tremblay

Matthew Chiasson

Carmine Lisio

Yusuf Razi Syed

Bruce Calvert

Faran Hafeez

Dave Sellors

Jean-François Bisson

Romain Chevalier

Golnaz Shaverdi

A control system for a turbine engine assembly includes a controller operable to control operation of the turbine engine assembly and to determine a trim configuration to balance a rotating engine structure associated with the turbine engine assembly. The controller is programmed to determine the trim configuration based on information indicative of an out of balance condition of the rotating engine structure and an assigning a quality score based on a determined veracity of the information.

System and method of performing fan trim balancing

Magnetic chip detectors and associated for detecting metallic chips in engine fluid of an engine are provided. A magnetic chip detector includes first and second magnetic chip capture zones. The first magnetic chip capture zone includes a first electrically conductive terminal spaced apart from a second electrically conductive terminal to define a first chip-receiving gap therebetween. The second magnetic chip capture zone includes a third electrically conductive terminal and either the second electrically conductive terminal or a fourth electrically conductive terminal to define a second chip-receiving gap therebetween. The magnetic chip detector includes an electric circuit including both the first chip-receiving gap and the second chip-receiving gap. The electric circuit provides an output indicative of a chip detection by one or both of the first magnetic chip capture zone and the second magnetic capture zone.

Multi-zone magnetic chip detector

A turbofan engine has a fan drivingly engaged by a shaft for rotation about a rotation axis and having: fan blades circumferentially distributed about the rotation axis and drivingly engaged by the shaft; an ice-accruing feature located on a surface of the fan exposed to an air flow flowing between the fan blades, the ice-accruing feature having a shape providing a non-axisymmetric ice accumulation on the fan to create a rotational imbalance; a balancing feature secured to the fan or to the shaft to counteract the ice-accruing feature such that the fan is rotationally balanced when the fan is free of ice, the balancing feature being located such as to be outside the air flow; an aircraft controller; and a sensor operatively connected to the fan and operable to send a signal to the aircraft controller, the signal indicative of the rotational imbalance caused by the ice-accruing feature.

Fan icing detection system

Method and system for controlling engine speed in a multi-engine aircraft, comprising monitoring a request for a first engine and a second engine to generate a given thrust and determining a corresponding engine speed for the first engine and the second engine in accordance with the given thrust. When the corresponding engine speed is outside of a selected speed range, a first engine speed and a second engine speed are allowed to track the corresponding engine speed. When the corresponding engine speed is within the selected speed range, a transition of the first engine speed and the second engine speed through the selected speed range is staggered by allowing one of the first engine speed and the second engine speed to transition through the selected speed range while holding the other of the first engine speed and the second engine speed outside of the selected speed range.

System and method for controlling engine speed in multi-engine aircraft

At least a selected one of a first and second engine are connected to a drive train for driving an aircraft accessory. A gearbox is connected to a primer mover propulsor and an actuator operatively associated with the selected engine is moveable between a position in which the selected engine drivingly engages the gearbox for driving the propulsor and a position in which the selected engine disengages from the gearbox. A position signal, a status signal, and a request signal respectively indicative of a present position of the actuator, a governing state and present speed of each engine, and a request for movement of the actuator from the present position to the other position are received. If the selected engine's speed differs from a predetermined threshold, a control signal is output for causing the engine's speed to be adjusted towards the threshold. A control signal indicating that movement of the actuator is permitted is then output.

System and method for operating a multi-engine aircraft in an auxiliary power unit mode

A system and a method useful for determining and controlling flow in an engine load compressorhaving an inletand an outlet. Meansare provided for measuring static pressure at one or more locations within the load compressor inlet. Meansare also provided for measuring static pressure at one or more locations within the load compressor outlet. The system further comprises meansfor measuring temperature at at least one location within the compressor, and one or more processorsadapted for calculating ratios relating compressor outlet and inlet pressures, optionally normalizing the calculated pressure ratios according to any one or more of reference temperatures, inlet guide vane positions, and compressor speeds, and for determining, using the optionally normalized pressure ratios, desired load compressor output flow rates Q.

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Montreal, Canada

Guy Riverin