Pratt-whitney Canada Corp

Richard Robert Kudrna

Ian Farrell

Benjamin James Renaud

Sean Durand

Pierre Huppe

Danielle Methot

Carmine Lisio

Reza Pedrami

A fireproof assembly for an aircraft engine, comprises a fireproof housing having an internal volume and an opening. A fireproof internal shield is located within the fireproof housing. The internal shield divides the volume into a first sub-volume and a second sub-volume, the first sub-volume configured for receiving a component of the aircraft engine. A non-fireproof component seals the opening of the fireproof housing. Fireproof fasteners are used to support internal shield inside the housing.

Fireproof assembly

There is provided an aircraft engine printed circuit board assembly generally having a functional circuit contributing to the operation of an aircraft engine. The functional circuit has a first substrate portion, a first electronic component supported by the first substrate portion, and a first electrical conductor supported by the first substrate portion and leading to the first electronic component. The aircraft engine printed circuit board assembly generally has a monitoring circuit having a second substrate portion, a second electronic component supported by the second substrate portion, a second electrical conductor supported by the second substrate portion and leading to the second electronic component, the second electrical conductor having a shorter life expectancy than the first electrical conductor, and a detector monitoring an indicator of operativeness of the second electrical conductor, in which the first electrical conductor and the second electrical conductor are both exposed to the same environment.

Printed circuit board assembly for aircraft engine, and method monitoring same

A blade angle feedback assembly for an aircraft-bladed rotor is provided. The rotor is rotatable about a longitudinal axis and having an adjustable blade pitch angle. The assembly comprises a feedback device coupled to rotate with the rotor with adjustment of the blade pitch angle, the feedback device comprising a non-magnetically permeable body defining a root surface and a plurality of magnetically permeable position markers circumferentially disposed on the root surface, and at least one sensor mounted adjacent the feedback device and configured to detect a passage of the plurality of position markers as the feedback device rotates about the longitudinal axis.

Feedback device with differing magnetic permeability zones

A blade angle feedback assembly for an aircraft-bladed rotor is provided. The rotor is rotatable about a longitudinal axis and has an adjustable blade pitch angle. The assembly comprises a feedback device coupled to rotate with the rotor with adjustment of the blade pitch angle, the feedback device having a root surface, a plurality of position makers circumferentially disposed on the root surface, the plurality of position markers circumferentially spaced from one another and non-aligned with the longitudinal axis, and at least one sensor mounted adjacent the feedback device and configured to detect a passage of the plurality of position markers as the feedback device rotates about the longitudinal axis.

Feedback device with non-axially aligned position markers

Systems and methods for providing pitch position feedback for pitch-adjustable blades of an aircraft bladed rotor are disclosed. In one embodiment, the systems include a sensor comprising a magnet having a magnetic field, a pole piece coupled to a first pole of the magnet and directing the magnetic field toward the feature and a coil mounted in the magnetic field. The coil generates a sensor signal indicative of a variation in the magnetic field caused by movement of the feature in the magnetic field. The sensor also includes a magnetic shield mounted in the magnetic field. The magnetic shield defines a magnetic return path for some magnetic flux of the magnetic field exiting the pole piece toward an opposite second pole of the magnet.

Feedback system for pitch-adjustable blades of aircraft bladed rotor

A gasket providing electrical conductivity between components is disclosed. The gasket comprises a body having a fastener hole extending therethrough and an electrically conductive insert lining at least part of the fastener hole in the body. The insert has a first contact face disposed for electrically contacting a first component and a second contact face disposed for electrically contacting a second component. The first contact face is in electrical communication with the second contact face.

Gasket

A magnetic chip device such as a chip detector or chip collector, comprising a horseshoe magnet held within a housing and having two adjacent tips protruding from the housing, and having a plurality of portions extending sequentially from one of the tips to the other, the plurality of portions including two end portions, each one of the two end portions extending to a corresponding one of the tips, and a rare-earth magnet portion made of a rare earth magnet material and positioned between the two end portions in the sequence.

Magnetic chip detector/collector

Variable rate ignition method and system that take advantage of knowledge and analysis of environmental conditions and/or operational conditions. A variable ignition rate for igniting the engine permits an optimal use of the igniters and thereby prolongs their life as well as its associated maintenance schedule. Operating costs and durability are also enhanced. Furthermore, flexibility is enhanced since any changes to the method of determining the best spark rate can be made through update in the software of the engine controller instead of change in the hardware (e.g., the exciter).

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Greenfield Park, Canada

Richard Robert Kudrna