Pratt-whitney Canada Corp

Michael J Dowhan

Joseph Horace Brand

Kevin Allan Dooley

Lev Alexander Prociw

Andreas Eleftheriou

Cameron Todd Walters

John Greer

Nashed Youssef

Richard Harvey

Haruhisa Chijiiwa

William Savage

Andrew Robertson Waterston

A heat exchange device comprising a fluid flow passage having a plurality of successive segments in fluid flow communication with one another, the segments being adapted to maintain a developing flow therein and thereby improve heat transfer.

Heat exchange device and method

An aero-engine nose cone anti-icing system () using a rotating heat pipe () is provided to replace the current method of blowing hot compressor bleed air over the nose cone surface. Heat is transferred from a hot source () within the engine () to the nose cone () through a rotating heat pipe () along the central shaft (). A condenser () and evaporator () are provided which are adapted to the heat transfer requirements and space constraints in the engine ().

Anti-icing apparatus and method for aero-engine nose cone

A method of providing an outside rotor electric machine having a reduced radial air gap variation across an axial length of the air gap, the machine including a rotor having a cylindrical elongated portion supporting magnets and a flange extending at least partially radially from a rotating shaft, the method comprising increasing a radial deflection of the elongated portion in proximity of the flange by connecting the elongated portion to the flange through a radial spring having a stiffness lower than that of the elongated portion.

Outside rotor electric machine with reduced air gap variation

An aircraft propulsion system comprises a power plant driving a number of outboard propulsion units to propel a fixed wing aircraft.

Aircraft propulsion system

The invention provides a method and apparatus for controlling a machine in which the magnetic flux emanating from a rotor is selectively diverted to a second path in the stator which bypasses the winding or windings so as to magnetically de-couple the winding or windings from the rotor.

Method and apparatus for controlling an electric machine

A method of manufacturing a composite wall with an open cell metal foam core layer bonded to an inner cladding layer and an outer cladding layer. The method involves: creating a core substrate of open cell gas permeable foam in a chosen shape; impregnating the open cell foam substrate with metal vapour and depositing a porous layer of metal on exposed internal and external surfaces of the substrate thereby forming the open cell metal foam core through metal vapour deposition; and forming the inner and outer cladding layers upon the metal foam core through spray application of metal or ceramic.

Foam wall combustor construction

Method of manufacturing a composite wall

A method of manufacturing a seamless self-supporting metal part using nickel vapor deposition, where the part has a selected minimum thickness, a first aerodynamically contoured surface and a second substantially parallel surface. The method replaces labor intensive welding of individually manufactured sheet metal segments for complex aerodynamic shapes, and produces a part with higher accuracy, less cost, controlled strength and hardness properties. Nickel vapor deposition is commonly used for plating electronic components, and for producing a metallic lining for plastic injection moulds. The seamless sheet metal part is cast by: fabricating a mould with at least one mould surface being a negative of the first surface of the part; enclosing the mould in a nickel vapor deposition chamber; depositing nickel on the mould surface by nickel vapor deposition until a blank of nickel is deposited having at least the minimum thickness and an external deposition surface; and separating the blank from the mould.

Method of manufacturing seamless self-supporting aerodynamically contoured sheet metal aircraft engine parts using nickel vapor deposition

A fan blade retention device includes a collar (13) inserted into a circumferential groove (14) cut into the hub (6) of a turbofan engine. The outward facing groove (14) is positioned aft of the fan blade fixing channel (15). When the fan blade root (11) is completely received within the blade fixing channel (15), the blade root (11) contacts the collar (13) and is prevented from traveling further aft. If the collar 13 is segmented, an annular rear cover plate (19) holds the segmented collar (13) radially within the groove (14).

Growing community of inventors

Milton, Canada

Michael J Dowhan